Systems and methods for scalable combustors

Abstract

In one example, a gas turbine system, includes a pressurized fluid delivery system configured to deliver into a combustor system, which includes a pressurized fuel fluid, a pressurized oxidant fluid; and a pressurized diluent fluid comprising a diluent. The gas turbine system also includes an oxidant fluid discharge system configured to control a first flow of the pressurized oxidant fluid incoming from the pressurized fuel delivery system into the combustor system, and a pressurized diluent injection system configured to control a second flow of the pressurized diluent fluid incoming from the pressurized fuel delivery system into an upstream diluted fuel rich combustion stage included in the combustor system, and into a. downstream diluted oxidant combustion stage included in the combustor system, wherein the pressurized diluent fluid comprises a. superheated fluid. The gas turbine system additionally includes a control system.

Description

SYSTEMS AND METHODS FOR SCALABLE COMBUSTORS CLAIM OF PRIORITY This application claims the priority benefit of U.S. provisional patent application serial number 63 / 574,116 filed on April 3, 2024 and entitled “SYSTEMS AND METHODS FOR SCALABLE COMBUSTION,” which is hereby incorporated by reference in its entirety. FEDERALLY SPONSORED RESEARCH AND DEVELOPMENT

[0001] This invention was made with U.S. Department of Energy High Performance For Manufacturing (HPC4Mfg) grants with the Argonne National Laboratory, ANL No. A18179 and A21020, and with the Lawrence Livermore National Laboratory, LLNL No. TC02306 and TC02380. JOINT RESEARCH AGREEMENT

[0002] This invention was made with government support under a Cooperative Research and Development Agreement (CRADA) No. TC02380 between the Department of Energy (DOE), Lawrence Livermore National Security LLC, University of Chicago Argonne LLC, and VAST Power Systems, LLC. The government may have certain rights in the invention. TECHNICAL FIELD

[0003] The present disclosure relates to combustor or reactor systems, and more specifically, to scalable combustor systems. BACKGROUND OF THE INVENTION

[0004] In certain combustion and power generation systems, such as conventional, green, renewable, and / or sustainable energy systems, combustors are used to combust or otherwise react fuels useful in generating thermal energy. For example, a combustor can deliver and mix a fuel fluid comprising a fuel, an oxidizer fluid comprising an oxidizer, and a diluent fluid comprising a diluent, to combust a fluid mixture comprising fuel, oxidant, and a diluent, resulting in a working fluid having useful thermal energy. The working fluid can then be used, for example, to produce heat and / or power via direct and / or indirect energy transfers, such as rotating a gas turbine system, heating, or cooling. It would be beneficial to improve on such combustor systems, processes, and controls.BRIEF DESCRIPTION OF DRAWINGS

[0005] Fig. 1A is an elevation view of a transversely elongated vertical Cuboidal “Scalable Combustor” with fluid manifolds feeding opposed combustor walls, according to some examples.

[0006] Fig. 1B is a schematic detail of an upstream flame authority in the Cuboidal Scalable Combustor, according to some examples.

[0007] Fig. 1C is an elevation view of a combusting chamber and Blend-Trim region in the Cuboidal Scalable Combustor, according to some examples.

[0008] Fig. 1D is an elevation view of upstream diluted oxidant, and downstream diluted oxidant fluid manifolds feeding a first side of an adjacent combusting chamber and Blend-Trim region of the Cuboidal Scalable Combustor, according to some examples.

[0009] Fig. 1E is a detail section of an insulated combusting chamber wall with diluted fuel delivery orifices in the Cuboidal Scalable Combustor, according to some examples.

[0010] Fig. 1F is a detail section of an insulated combusting chamber wall with diluted oxidant delivery orifices in the Cuboidal Scalable Combustor, according to some examples.

[0011] Fig. 1G is a detail section of an insulated wall in a downstream Blend- Trim region with diluted oxidant and diluent delivery orifices in the Cuboidal Scalable Combustor, according to some examples.

[0012] Fig. 1H is an elevation view of upstream diluted fuel and downstream diluted oxidant fluid manifolds in the vertical Cuboidal Scalable Combustor feeding a second side of the adjacent combusting chamber and Blend-Trim region, according to some examples.

[0013] Fig.1I is a plan view of the vertical Cuboidal Scalable Combustor through plane A-A’, according to some examples.

[0014] Fig. 2A is a schematic of a scalable combustor with a blower and diluent delivery, according to some examples.

[0015] Fig.2B is a perspective view of a horizontal Cuboidal Scalable Combustor with diluent spray and common ignition authority, according to some examples.

[0016] Fig. 2C is a detailed section view of an insulated combusting chamber wall with fluid delivery orifices, according to some examples.

[0017] Fig. 2D is a perspective view of a vertically oriented Cuboidal Scalable Combustor section with downstream diluent delivery, according to some examples.

[0018] Fig. 2E is a perspective view of a vertically oriented Cuboidal Scalable Segmented Combustor section with multiple rich combusting delivery, and intermediate diluent delivery, according to some examples.

[0019] Fig. 3A An axial transverse schematic view of a Scalable Gas Turbine Combustor, according to some examples.

[0020] Fig. 3B A perspective upstream view of a cylindrical Scalable Gas Turbine Combustor with a common pilot, according to some examples.

[0021] Fig. 3C Detail of an insulated wall with fluid delivery orifices in a Scalable Gas Turbine Combustor, according to some examples.

[0022] Fig. 3D A Radial Circumferential Outer Cross Section of the Scalable Gas Turbine Combustor, according to some examples.

[0023] Fig. 3E A Circumferential Axial Unrolled Perspective of Symmetric Adjacent Gas Turbine Combusting Shell Sections, according to some examples.

[0024] Fig. 3F Graph of Axial Combustor Temperature, Ammonia Fuel, and NOx, according to some examples.

[0025] Fig 3G A Circumferential Axial Unrolled Perspective of a Symmetric Gas Turbine Feeder Manifold Section, according to some examples.

[0026] Fig. 3H A Circumferential Axial Unrolled Perspective of Adjacent Asymmetric Gas Turbine Combusting Shell Sections with common adjacent oxidant and Fuel Manifolds, according to some examples.

[0027] Fig. 3I A Circumferential Axial Unrolled Perspective of an Outer Asymmetric Combusting Blend-Trim Feeder, according to some examples.

[0028] Fig. 3J An axial-circumferential detail view of axially and circumferentially offset fuel and oxidant orifices from outer feeders into a combusting chamber, according to some examples.

[0029] Fig. 3K An axial-circumferential detail view of axially and circumferentially offset fuel and oxidant orifices from inner feeders into a combusting chamber axially and / or radially offset from opposed feeder orifices, according to some examples.

[0030] Fig. 3L An axial-circumferential detail view of axially and circumferentially offset diluent and / or oxidant orifices from outer feeder(s) into a downstream combustor Blend-Trim region, according to some examples.

[0031] Fig. 3M An axial-circumferential detail view of axially and circumferentially offset diluent and / or oxidant orifices from inner feeder(s) into a combustor Blend-Trim region axially and / or radially offset from radially opposed feeder orifices, according to some examples.

[0032] Fig. 3N A radial-axial elevation view of a CounterclockWise wall outer side of a radially outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.

[0033] Fig. 3O A radial-axial elevation view inwardly adjacent to a CounterClockWise outer wall of an outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.

[0034] Fig. 3P A radial-axial elevation view inwardly adjacent to a clockwise outer wall of an outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.

[0035] Fig. 3Q A radial-axial elevation view of a clockwise wall outer side of a radially outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.

[0036] Fig. 3R An axial-circumferential detail view of Fuel and offset oxidant delivery orifice spacing in fuel and oxidant feeders radially adjacent to a Scalable Combusting Region, according to some examples.

[0037] Fig. 3S An axial-circumferential detail view of fuel and aligned oxidant orifices in feeders adjacent a combusting region, according to some examples.

[0038] Fig. 3T A radial-circumferential detail view of fuel and oxidant orifice orientations into a combusting chamber from adjacent feeders, according to some examples.

[0039] Fig. 3U A radial-axial elevation detail view of fuel and oxidant channels and orifices in outer and inner feeders adjacent a radially outward combusting region, according to some examples.

[0040] Fig. 3V A radial-circumferential detail view of an oxidant orifice in a combusting chamber wall, according to some examples.

[0041] Fig. 3W A radial-circumferential detail view of an angled oxidant orifice in a combusting chamber wall, according to some examples.

[0042] Fig. 3X A radial-circumferential detail view of an oxidant feeder closed end, according to some examples.

[0043] Fig. 3Y A radial-circumferential detail view of a fuel feeder closed end, according to some examples.

[0044] Fig. 4A is an axial radial schematic view of a Gas Turbine System with a Scalable Combustor, according to some examples, according to some examples.

[0045] Fig. 4B is a perspective view of the upstream section of an Annular Scalable Gas Turbine Combustor with a feeder comprising multiple ignition authorities, according to some examples, according to some examples.

[0046] Fig. 4C is a detailed perspective view of an insulated wall with fluid delivery orifices in a Scalable Gas Turbine Combustor, according to some examples, according to some examples.

[0047] Fig. 4D is a Radial Circumferential Outer Cross Section of the Scalable Gas Turbine Combustor, according to some examples, according to some examples.

[0048] Fig.4E is a Radial Axial Unrolled Perspective of Symmetric Adjacent Gas Turbine Combusting Shell Sections, according to some examples.

[0049] Fig. 4F is a Graph of Axial Combustor Temperature, Ammonia Fuel, and NOx, according to some examples.

[0050] Fig. 4G is a Radial Axial view of a Symmetric Gas Turbine Feeder Manifold Section, according to some examples.

[0051] Fig. 4H is a Radial Axial view of Adjacent Asymmetric Gas Turbine Combusting Shell Sections with common adjacent oxidant and Fuel Manifolds, according to some examples.

[0052] Fig.4I is a Radial Axial view of an Outer Asymmetric Combusting Blend- Trim Feeder, according to some examples.

[0053] Fig.4J is a Radial Axial detail view of axially and circumferentially offset fuel and oxidant orifices from outer feeders into a combusting chamber, according to some examples.

[0054] Fig. 4K is a Radial Axial detail view of axially and circumferentially offset fuel and oxidant orifices from inner feeders into a combusting chamber axially and / or radially offset from opposed feeder orifices, according to some examples.

[0055] Fig.4L is a Radial Axial detail view of axially and circumferentially offset diluent and / or oxidant orifices from outer feeder(s) into a downstream combustor Blend-Trim region, according to some examples.

[0056] Fig. 4M is a Radial Axial detail view of axially and circumferentially offset diluent and / or oxidant orifices from inner feeder(s) into a combustor Blend- Trim region axially and / or radially offset from radially opposed feeder orifices, according to some examples.

[0057] Fig. 4N is a Radial Axial elevation view of a CounterClockWise wall outer side of a radially outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.

[0058] Fig. 4O is a Radial Axial elevation view inwardly adjacent to a CounterClockWise outer wall of an outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.

[0059] Fig. 4P is a Radial Axial elevation view inwardly adjacent to a clockwise outer wall of an outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.

[0060] Fig. 4Q is a Radial Axial elevation view of a clockwise wall outer side of a radially outer combusting region of a Gas Turbine Scalable Combustor, according to some examples.

[0061] Fig. 4R is a Radial Axial detail view of Fuel and offset Oxidant delivery orifice spacing in fuel and oxidant feeders radially adjacent to a Scalable Combusting Region, according to some examples.

[0062] Fig. 4S is a Radial Axial detail view of fuel and aligned oxidant orifices in feeders adjacent a combusting region.

[0063] Fig. 4T is a Radial Circumferential detail view of fuel and oxidant orifice orientations into a combusting chamber from adjacent feeders, according to some examples.

[0064] Fig. 4U is a Radial Circumferential elevation detail view of fuel and oxidant channels and orifices in outer and inner feeders adjacent a radially outward combusting region, according to some examples.

[0065] Fig. 4V is a Radial Circumferential detail view of an oxidant orifice in a combusting chamber wall, according to some examples.

[0066] Fig. 4W is a Radial Circumferential detail view of an angled oxidant orifice in a combusting chamber wall, according to some examples.

[0067] Fig. 4X is a Radial Axial detail view of an oxidant feeder closed end, according to some examples.

[0068] Fig. 4Y is a Radial Axial detail view of a fuel feeder closed end, according to some examples, according to some examples.

[0069] Fig. 4Z is a Radial Axial view of an Outer Asymmetric Combusting Blend-Trim Feeder having a heating / cracking section, according to some examples.

[0070] Fig. 5A is a Circumferential-Radial Cross-section of Combusting Chamber With Radial Combusting Regions, according to some examples.

[0071] Fig. 5B is a Circumferential-Radial Cross-section of Combusting Chamber With Combusting Regions at a Skew Angle to the Radial Axis, according to some examples.

[0072] Fig. 5C is a Close-Up Perspective View of The Combusting Regions at a Skew Angle to the Radial Axis, according to some examples.

[0073] Fig.5D is a Graph of hot gas temperature T35 versus combustor radius R, from temperature T35i at an inner radius Ri, to temperature T35o at an outer radius Ro, at the downstream end of the fuel delivery region at the axial location CZ35, according to some examples.

[0074] Fig. 5E is a Graph of hot gas temperature T4 versus combustor radius R, from temperature T4i at inner radius Ri to temperature T4o at outer radius Ro, at the combustor outlet CZ4, according to some examples.

[0075] Fig. 5F is a Graph of hot Wall Temperature TW versus combustor axial length Z, from a wall temperature TW35 at the downstream end of the fuel delivery region CZ35, to a wall temperature TW4 the combustor outlet at CZ4, according to some examples.

[0076] Fig.5G is a Graph of hot gas mean Velocity V4M versus combustor radius R at the combustor outlet CZ4, from inner velocity V4i at inner radius R4i to outer velocity V4o at outer radius Ro, according to some examples.

[0077] Fig. 5H is a Graph of hot gas temperature T versus combustor Temperature Ti at combustor inner radius Ri, and Outer Temperature To at outer ) to a second clockwise , according to some examples.

[0078] Fig. 5I is a Graph of hot gas temperature T versus combustor Temperature Ti at combustor inner radius Ri, and Outer Temperature To at outer, according to some examples.

[0079] Fig. 5J is a Graph of hot gas velocity V versus combustor circumferential angle Theta, for Inner Velocities Vi at combustor inner radius Ri, and Outer Velocities Vo, at outer radius Ro, with a cooled counterclockwise first combustion , according to some examples.

[0080] Fig. 5K is a Scalable Omega Combustor Equilibrating Region Radial- Axial Cross-Section Elevation View, according to some examples.

[0081] Fig. 5L is a Premixed Scalable Combustor Premixing of Fuel, Oxidant and Diluent, Radial-Axial Plan View, according to some examples.

[0082] Fig. 5M is a Plan View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle Combusting Region, according to some examples.

[0083] Fig. 5N is a Perspective View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle Combusting Region, according to some examples.

[0084] Fig. 5O is a Schematic Plan View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle Combusting Region, according to some examples.

[0085] Fig.5P illustrates Fuel / Oxidant Orifices in Ignition Authority Upper Inner Wall Plan View, according to some examples.

[0086] Fig.5Q is a Ignition Authority Mid-Section Plan View, according to some examples.

[0087] Fig. 5R illustrates Fuel / Oxidant Orifices in Ignition Authority Lower Inner Wall Plan View, according to some examples.

[0088] Fig. 5S is a Schematic Plan View of an Ignition Authority Inner Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle Combusting Region, according to some examples.

[0089] Fig.5T is a Close-up schematic of Igniter in Wall of the Pilot Combusting Region, according to some examples.

[0090] Fig.5U is a Radial-Axial Cross Section of Combustor Wall Fluid Cooling Capable of Ammonia Cracking, according to some examples.

[0091] Fig. 5V is a Radial Inner to Outer Temperature Profile (T vs R) of Equilibrating Zone Flow Temperature Upstream at CZ39 and Downstream at CZ4, according to some examples.

[0092] Fig. 6A is a Power Versus Temperature Graph of Brayton Cycle and VAST Cycles, according to some examples.

[0093] Fig. 6B is a Schematic of Control System Configuration of Controller Subsystems, according to some examples.

[0094] Fig. 6C is a Schematic Graph of Control System with Control Sections, according to some examples.

[0095] Fig.6D is a Schematic Graph of Control System with Sensors, according to some examples.

[0096] Fig. 6E is a Schematic Graph of Low Pilot and Combustor Temperatures, Expander-Generator Speeds, and Power Generation versus Time Showing Flexible Operations, according to some examples.

[0097] Fig. 6F is a Schematic Graph of High Pilot and Emergency Combustor Temperatures, Expander-Generator Speeds, and Power Generation versus Time Showing Flexible Operations, according to some examples.

[0098] Fig. 6G is a Combined Schematic Graph of Flexible & Emergency Low and High Pilot and Combustor Temperatures, Expander-Generator Speeds, and Power Generation versus Time, according to some examples.

[0099] Fig. 7A is a block diagram of a Scalable Power Generating System, according to some examples.

[0100] Fig. 7B is block diagram of a Scalable Power Major Control System, according to some examples.

[0101] Fig.7C is a block diagram of Scalable Power Control System Controllers, including sub controllers, according to some examples.

[0102] Fig. 7D is a block diagram of a Scalable Power Control System and certain Sensor placement, according to some examples.

[0103] Fig. 7E is a sectional view of a Pressurized Oxidant Fluid Extraction System for Recovery Expansion, according to some examples.

[0104] Fig. 7F is a sectional view of a Pressurized Diluent Delivery System for Stall and Acoustic Management, according to some examples.

[0105] Fig.7G is a side view of a Liquid Gas Coaxial Injector, according to some examples.

[0106] Fig. 7H is a side view of a Fuel, Liquid, Gaseous Diluent Fluid Multi- fluid Injector, according to some examples.

[0107] Fig. 7I is a sectional view of a Liquid and Gaseous Fluid Delivery with Co-Axial Orifices System, according to some examples.

[0108] Fig. 7J is a sectional view of a Dynamic Oxidant Delivery Control via Distributed Orifices System, according to some examples.

[0109] Fig. 7K is a Surge Choke Margin Diagram, according to some examples.

[0110] Fig.7L is a Power versus relative Air / Fuel Lambda and Pressure Diagram, according to some examples.

[0111] Fig. 7M is a Schematic VAST versus Brayton Design and Emergency Powers Diagram, according to some examples.

[0112] Fig. 7N depicts a Dual Expander and Generator Stacked Gas Turbine Power System, according to some examples.

[0113] Fig. 7O illustrates a Stacked Dual Expander and a Generator with Supports, according to some examples.

[0114] Fig. 7P illustrates a Three Combustor, Expander and Generator Gas Turbine System, according to some examples. DETAILED DESCRIPTION

[0115] A conventional combustor’s delivery of fluids is impacted by the ability of combustor systems and processes used to spatially and / or temporally control the delivery of fuel (or reactant), oxidant (or co-reactant), and diluent fluids. Combustion and emissions (or reaction and byproducts) are often impacted by the distribution and rates of conventional fluid delivery and mixing. These are typically limited by physical, thermal, and temporal apparatus, fluid design, delivery, cooling systems, control processes, and material thermal and strength constraints.

[0116] Micro- to large Brayton gas turbines nominally use about 420% to 280% excess air to cool combustion to tolerable Turbine Inlet Temperatures (herein “TIT”) over a range of about 1,000°C (1,832°F) to 1,500°C (2,732°F). Such large excess air flows increase the size and cost of compressors which are typically the most expensive component in Simple Cycle gas turbines. Compressing and re-expanding such large excess air fractions cause systemlosses in Brayton turbines. Large gas flows cause uncertainties in measuring TIT.

[0117] Combustor systems (or reactor systems) deliver fluids through relatively few passageways or orifices. Increasing fluid mixing typically incurs substantial pressure drops with associated power losses to achieve turbulence of injected fluids. E.g., gas turbine combustors may have fluid flow pressure drops of 2.5% to 5% of combustor inlet pressures, thus increasing compressor size and cost, while reducing system power and efficiency.

[0118] Reducing gas turbine emissions to certain levels (e.g., regulatory-imposed levels) in hot lean air diluted flames increases complexity and cost. Brayton gas turbine emissions such as nitrogen oxides (NO, N2O, and NO2, referred to herein collectively as “NOx”) and carbon monoxide (referred to herein as "CO”) are typically substantially higher than international and other jurisdictionally legislated limits. Certain large gas turbines may be limited to operating above 50% of design power to constrain NOx generation, and to enable NOx emission catalytic cleanup to below legislatively prescribed levels.

[0119] Commercial combustion ranges over nine orders of magnitude from <1 Watt to >1,000 MW turbine systems. However, combustor systems generally do not scale well. Combustion systems are more difficult to design over widely different temperatures, pressures, power levels, and over rapid ramp-up rates, with frequent shutdowns.

[0120] Conventional or non-scaling combustors typically mix volumes of disparate fluids at pressures ranging from atmospheric to over 4.5 MPa (44 atmospheres). High performance gas turbines have TIT limited by material strength and cooling capabilities. E.g., often below 1,500°C (2,732°F). Higher combustion temperatures typically increase NOx emissions. Conventional large Simple Cycle (Brayton) gas turbine generate emissions typically an order of magnitude higher than stringent legislated emissions. e.g., above typical ~2.4 parts per million by volume diluted to 15% Oxygen (referred to herein as “ppmvd” and O2) NOx legislated limits, for example in the state of California in the United States.

[0121] Combusting methane (referred to herein as “CH4”) or natural gas at higher temperatures typically increases CO and Unburned Hydrocarbon (referred to herein as “UHC”) emissions. NOx emissions generally increasingexponentially with temperature. Some gas turbines are being designed with the TIT approaching 1,700°C (3,092°F) which will likely amplify NOx emissions and increase CO emissions. Reducing NOx and CO emissions typically involves catalytic reduction systems that increase system complexity and may cost from 4% to 7% of installed capital cost. Reducing chemicals such as ammonia (referred to herein as “NH3”), plus pumping, maintenance, and catalyst replacement commonly add cleanup operating costs over life of power production systems.

[0122] Very “lean” oxidant mixtures with high excess oxidant (e.g., air) concentrations have been used to reduce NOx emissions. However, such lean operation may cause difficulties in maintaining combustion stability bordering on flameout. Combustion stability may constrain the lower turndown ratio and minimum power of gas turbines. Operational variations in commercial natural gas delivery (e.g., differing in chemical makeups and / or heating values) have reportedly even caused flameouts with shutdown of large gas turbines.

[0123] Conventional turbine combustion noise typically results in certain acoustic enclosures to meet legislated workspace or urban noise limits. Conventional concentrated fuel delivery can generate intense combustion dynamics in combustion systems, especially with low pressure gaseous fuel delivery. Highly diluted diffusion flames operating near combustion stability limits can cause and amplify self-excited thermoacoustic instabilities. Such factors make “noise” more difficult to control. Strong combustion acoustic resonance has been known to increase scheduled and / or unscheduled maintenance activity for combustor liners, fatigue combustor sides, and mechanically distort combustor “cans”.

[0124] Certain gas turbines may use a “Rich Quench Lean” combustion methodology, with an initial fuel-rich combustion zone, a middle quenching zone, and a final lean-burn zone. Conventional inlet water injection, “fogging”, or “humid” combustion has had limited success in reducing gas turbine NOx emissions. Injecting water mixed with liquid kerosene has caused quenching for mixtures with water / kerosene mass ratio (Omega) greater than 0.4 to 1.1 depending on equivalence ratio.

[0125] Certain water and stream delivery efforts have worsened combustion performance, increasing CO and UHC emissions. For example, water injectionmay use ultrapure water to reduce hot section deposits and corrosion, but may increase maintenance. It reportedly increases system complexity, and fuel consumption. Such conventional water purification costs alone may be high.

[0126] Injecting diluent in from outer walls of a cylindrical “can” combustor can cause poor mixing and circulation, limiting reductions in NOx. Higher steam fractions increase ignition delay and reduce laminar flame speed. Quenching combustion can constrain water and steam delivery in typical Brayton gas turbines. Premixed fuel and oxidant delivery raises the possibility of combustion “flashback.” Likewise, higher flame speed of hydrogen (referred to herein as “H2”) may amplify the flashback.

[0127] Efforts to transition to renewable fuels raise challenges of cost-effective power generation, delivery, storage, and use. Rising use of renewable (“sustainable” or “green”) fuels, such as hydrogen, ammonia (referred to herein as “NH3”), methanol (referred to herein as “CH3OH”), and ethanol (referred to herein as “CH5OH”), may raise combustor design, control, and durability issues. For example, hydrogen use can increase intra-combustion temperatures, extend flammability limits, and increase emissions, such as of CO and NOx.

[0128] Ammonia (NH3) is generally available for agriculture and is a leading candidate for renewable fuels. However, conventional ammonia combustion commonly generates higher NOx than legislated emission levels. Ammonia low flame speed may further impact combustion operating regimes. Cracking ammonia back to hydrogen and nitrogen typically requires more equipment, heat, catalysts, and operating effort.

[0129] Increasing non-dispatchable renewable power use is rapidly increasing the frequency of backup power use to sustain grid power frequency, and for minimizing or preventing grid blackouts. Frequent large thermal cycling with high temperatures can lead to lessening the life of insulating tiles in cylindrical “can” combustors and additionally fatigue combustor sides.

[0130] Increasing ambient temperatures typically reduce conventional gas turbine power. This causes reductions in backup power capacity when it is most needed for cooling in hot climates. E.g., Brayton cycle “peaker” gas turbines may lose ~13% in peak power and a further ~2.5% in efficiency for a 25 kelvin (Celsius deg) increase in ambient temperature from rated power at 15 deg C up to 40 deg C (59 deg F to 104 deg F) hot ambient conditions.

[0131] Higher combustion temperature at peak power typically rapidly increases blade creep that reduces a gas turbine’s useful life. E.g., just increasing temperature as power increases from 70% to 100% in conventional Brayton “peaker” gas turbines may cause about a 300-fold reduction in life, due to rapidly increasing creep with higher temperature. A ten kelvin increase or decrease in TIT may halve or double the life of some gas turbines. Yet such high temperatures are difficult to accurately measure or control in conventional gas turbines.

[0132] Cycling power in conventional Brayton cycle turbines further causes thermal creep, with higher cyclic strain fatigue. High TIT temperature sensors may be adversely affected, leading to more frequent maintenance. Combustor failure results in unwanted maintenance of power systems. Discrete fuel injectors and combustor liner cooling can cause combustor hot streaks that vary TIT and temperature distribution. Conventional combustion, its variations, and higher TIT make it more difficult to accurately sense TIT temperatures.

[0133] Legislation requiring higher renewable energy is increasing the retirement of dispatchable coal fired power systems. Higher renewable energy use is increasing the use of standby power and backup gas turbines, with more frequent starts and faster power ramps. Higher renewable energy use is further forcing combined cycle turbines to operate at lower annual capacity factors with more frequent power cycling. Such trends are degrading grid resilience and reliability.

[0134] California’s “100 Percent Clean Energy Act of 2018” mandated a Renewable Power Standard (RPS) with targeting 60% of electricity from eligible renewable energy sources and zero-carbon resources by 2030, and 100% by 2045. Such legislated increases in renewable power are reducing the average annual usage of combined cycle base load power. Reduced usage with more frequent cycling is making combined cycle turbines more maintenance prone, and reducing availability, despite their higher efficiency. Increased cycling is similarly degrading peaker gas turbines and increasing backup costs.

[0135] Legislated increases in renewable power are projected to increase California Independent System Operator (CAISO)’s “Duck Curve” of rapid backup power demand ramp. This ramp from an afternoon peak solar to an evening peak demand is projected to reach ~7,400 MW / hr (~26,000 MWrise / 3.5 hours) on weekdays by 2030. Solar and wind supplied about 36% California Independent System Operator (CAISO’s) power in 2019.

[0136] Non-dispatchable solar plus wind power have already exceeded 97% of CAISO’s demand. Declining reliable dispatchable generation needed left CAISO with a 1,700 MW shortfall in its 2022 planned capacity. CAISO was forced to implement rolling (“rotating”) blackouts during heat waves in August 2020 and September 2022.

[0137] Besides rapid 15-minute dispatches, CAISO has now added faster 5- minute dispatches. CAISO has even introduced 1 minute interval emergency dispatches to stabilize grid voltage and control grid frequency. Ramp up rates for major combined cycle and industrial gas turbines were up to 8 hours to avoid turbine fatigue. Now, ramp rates may be reduced from 30-minute startups to about 10 minutes for combined cycles, 5 minutes for industrial turbines, and even 2 minutes for aeroderivative turbines.

[0138] CAISO’s increasingly frequent dispatches may be causing higher thermal cyclic fatigue that can lead to shortening the life of gas turbines and turbine blades. This requires more frequent inspections, and refurbishments, with a markedly shorter useful life. Consequently, higher non-dispatchable solar and wind use have increased California’s retail power costs to about twice that in other US western states.

[0139] The 2021 winter storm Uri triggered blackouts in the Electric Reliability Council of Texas’ (ERCOT) grid. Renewables could not compensate for power generation and natural gas supply failures. In 2023, ERCOT warned: “On the hottest days of summer, there is no longer enough on-demand dispatchable power generation to meet demand…”

[0140] The North American Electric Reliability Corp. (NERC), in its 2023 Summer Reliability Assessment, warns that 2 / 3rds of North America risks energy shortfalls with rolling blackouts, during periods of extreme demand at peak summer temperatures with low winds. i.e., in the seven power regions of SPP and MISO (US West), ERCOT (Texas), SERC Central (particularly North & South Carolina), and NPCC (New England and Ontario).

[0141] Current trends of increasing non-dispatchable renewable power while reducing adequate rapid backup power generation or storage capacity is increasing the likelihood of blackouts. The US Energy Information Agency(EIA) (2020) projected 46.5 GW loss in Reliable Electricity Capacity from 2022-2030 (with 72.3 GW reductions and only 25.8 GW of additions).

[0142] The US Environmental Protection Agency’s (EPA) 2023 “Greenhouse Gas Standards and Guidelines for Fossil Fuel-Fired Power Plants Proposed Rule” seeks to reduce or sequester 90% of CO2 emissions by 2030 from coal and natural gas power plants that now supply 20% and 40% of US electricity. That could further reduce US Reliable Electricity Capacity.

[0143] Extended periods of low solar and wind can lead to increased use of non- renewable power and / or energy storage to ensure grid reliability. E.g., During Germany’s dark cold winter doldrums (“Dunkleflaute”) it experienced a shortage of 18 days of average load (27 TWh) equivalent of wind and solar availability in 1996-1997. Germany’s maximum wind plus solar power generation often drop below 3% of total demand in such doldrum periods.

[0144] These trends may increase operating, maintenance, and refurbishment requirements, reduce availability, shorten system life, increase NOx and CO emissions, in both simple Brayton cycle gas turbines, and of combined cycle (base load) gas turbines. These trends may increase the need for cleaner reliable power with rapid response rates, particularly for intermediate usage above peaking power and below conventional base load. Scalable Combustor Design and Operation

[0145] Accordingly, several technical features in this disclosure lead to reactors that deliver and more cleanly burn reactant, oxidant, and, in some examples, add diluent fluids. The techniques described herein include combustors that combust fuel with an oxidant (e.g., air or oxygen), and that may add a diluent such as water, carbon dioxide, nitrogen or excess oxygen, in any phase and / or combination, in ways that are more scalable across broader ranges of commercial combustor pressures, temperatures, and / or power levels, therein improving power system capabilities and economics.

[0146] The techniques described further scalably design combustors for wider operating ranges in gas turbine systems, with fuel, oxidant, and diluent types, combinations, and loads, therein enabling more reliable grid operation and backup with major intermittent non-dispatchable renewable power penetration.

[0147] The techniques enable widely scaling combustor designs with power; e.g., providing a greater than a 10:1, or a 25:1 or wider range in power percombusting shell from their mean, and using multiple shells, therein increasing design capability and economics. Diffusing Region

[0148] Diffusing region techniques include varying delivery of liquid and / or gaseous diluent through multiple orifices into the upstream fluid delivery region, therein improving fluid delivery rates, liquid evaporation, and / or combustion. Pilot Ignition

[0149] Techniques include providing a diluted fuel rich pilot to more cleanly provide ignition of downstream fluid delivery, therein initiating reliable combustion while reducing the generation of NOx emissions. Combusting Region Manifolds and Feeders

[0150] Techniques further include providing an oxidant rich manifold, and a fuel rich manifold transversely adjacent to one or more combusting chambers, therein improving scalability, mixing, combustion, and economics.

[0151] Techniques include providing a diluent manifold or duct adjacent to an oxidant or fuel manifold, mixing gaseous and / or liquid diluent with oxidant and / or fuel, and delivering mixed fluid through orifices, therein facilitating fluid mixing and delivery.

[0152] Techniques include providing a diluted oxidant rich manifold between perpendicularly or transversely adjacent combusting chambers, therein reducing the number of oxidant manifolds, and improving manufacturability and economics.

[0153] Techniques include providing a diluted fuel rich manifold between perpendicularly or transversely adjacent combusting chambers, therein reducing the number of fuel manifolds, and improving manufacturability and economics. Combusting Chamber

[0154] Techniques include providing the upstream combusting chamber in a transversely elongated distribution having a transverse width to perpendicular (or radial) depth ratio normal to the flow axis greater than 1.15, and with fuel, oxidant, and diluent fluid delivery through the elongated walls, therein improving fluid mixing into and / or in the combusting chamber.

[0155] Techniques include adjusting the angle orifices transverse to the fluid flow relative to the combusting chamber wall surface normal, therein improving combusting fluid mixing.

[0156] Techniques include adjusting the number of transversely distributed fuel and oxidant fluid delivery orifices through opposing shallowly displaced sides of the combustor, as a function of axial distance upstream to downstream, therein improving combusting fluid mixing and combustion reliability.

[0157] Techniques include transversely offsetting oxidant rich fluid orifices relative to fuel rich fluid orifices, therein improving fluid mixing.

[0158] Techniques include changing or reducing upstream diluent / oxidant and / or diluent / fuel ratios, relative to hot pilot fluid delivery and / or to downstream combustor orifices, therein improving upstream combustibility and extending combustion delivery limits. Combustion Quenching, Stability, and Flashback

[0159] Techniques include delivering fuel rich fluid through adjacent transverse fuel feeders, and oxidant rich fluid through separate adjacent transverse oxidant feeders, through respective orifices into the combusting chamber, therein improving combusting fluid mixing, and reducing quenching or flashback risks.

[0160] Techniques provide configuring combustor upstream transverse width versus axial length profiles, of one or more combusting chambers, within combustion stability, manufacturability, and aerodynamic flow efficiency objectives, therein improving reliability and competitiveness. Blend Trim Region

[0161] Techniques include controlling remaining diluent delivery and mixing in the blend trim region, to axially control cumulative diluent to fuel mass ratios Omega, therein configuring axial combusting and equilibrating temperature profiles and reducing emissions to below prescribed regulatory levels.

[0162] Techniques include controlling remaining oxidant delivery and mixing in the blend trim region, to axially and / or transversely control cumulative relative oxidant to fuel mass stoichiometric ratios Lambda, therein configuring axial and / or transverse combusting and equilibrating oxidant profiles and reducing emissions to below prescribed regulatory levels.Scalable Pilot Combustor

[0163] Techniques further provide controlling upstream pilot combusting region temperature equal to or greater than downstream combusting chamber diluted fuel oxidant mixture standby ignition temperature, therein improving pilot reliability;

[0164] Techniques may provide multiple upstream pilot chambers feeding respective scalable combusting chambers or regions, therein improving combustion scalability, range, ramp rate, and / or reliability. Combustor Outlet Temperature Control and Scaling

[0165] Techniques may further improve control of Combustor Outlet Temperature (COT), or Turbine inlet Temperature (TIT), reduce outlet temperature variation, and / or reduce outlet temperature uncertainty.

[0166] Techniques may include configuring fluid delivery to control diluent to fuel mass ratio Omega with the relative oxidant to fuel ratio Lambda across a plurality of orifices, therein scaling combustor designs across wide temperature ranges, e.g., between about 700°C to 2,500°C for commercial combustors and / or gas turbines.

[0167] Techniques may control fuel, oxidant, and / or diluent fluid delivery rate per combustor volume, (MW / m3-atm) and provide predominantly axial laminar flow within the combustor, therein improving transverse combustor outlet or turbine inlet temperature (TIT) control, expander durability, and economics. Scalable Control of NOx and CO Emissions

[0168] Techniques provide for designing combustor fuel, and / or oxidant spatial fluid delivery rates to substantially reduce NOx and CO emissions relative to conventional combustors. In some configurations these may deliver NOx and CO emissions below legislated emission limits; e.g., NOx and / or CO below 75 ppmvd.

[0169] Techniques further include reducing NOx and / or CO emissions while controlling combustor outlet temperature within a range from 500°C to 2,500°C, by using thermal diluent spatial fluid delivery rates, therein increasing applications, thermal efficiency, and / or economics; e.g., by controlling the H2O, CO2, N2, O2 and / or other diluent to fuel mass delivery ratio Omega, for an Omega greater than about 1.15, (or the corresponding enthalpy delivery ratio) and with lower catalyst and reductant usage than with Brayton turbines.

[0170] Further techniques and advantages of the will become apparent from consideration of the drawings and ensuing description. SUMMARY OF THE DISCLOSURE

[0171] The techniques described herein include scalable ultraclean combustion (or chemical reaction) and equilibration equipment, configurations, and processes. These may progressively deliver and combust mixtures of fuel, oxidant, and thermal diluent along the axial flow direction. These techniques may deliver fluids via one or more fuel, oxidant, and diluent fluid manifolds, through numerous fuel, oxidant, and / or diluent orifices into one or more upstream combusting chambers, and downstream Blend-Trim regions.

[0172] Such techniques described herein may comprise one or more upstream transversely elongated combusting chambers with shallowly separated combusting chamber walls relative to the axial flow direction, (referred to herein as “transversely elongated”). Combusting techniques may configure enclosed transverse cross-sectional combusting areas that generally increase along the axial flow direction. Such techniques may configure fluid compositions in combusting regions preferably provide upstream fuel rich conditions, while maintaining combusting temperatures above quench limits.

[0173] These techniques may distribute numerous fuel fluid (or reactive fluid) orifices and oxidant fluid (such as air, or co-reactant fluid such as oxygen) orifices across the transversely elongated shallowly separated combusting chamber sides. Fuel and / or oxidant fluids may be fed into the fuel and oxidant fluid orifices from respective fuel and / or oxidant manifolds.

[0174] Further techniques may configure downstream Blend-Trim regions with similar transversely elongated walls with shallow spacing, configured transversely and normal to the axial fluid flow axis. Blend-Trim techniques may similarly configure oxidant and / or diluent delivery through numerous orifices in transversely elongated shallowly spaced walls about the combusting flow. These techniques may further combustion, control combustor axial and outlet temperature(s), and control emissions (or minor products).

[0175] Techniques may further mix diluent fluid with fuel fluid, oxidant fluid, and / or Blend-Trim oxidant fluids to deliver them into the combusting chamber, and / or Blend-Trim region, through respective fuel, oxidant, and / or Blend-Trimorifices. Similar techniques may use upstream flame authorities comprising fuel, oxidant, and diluent with rich primary combustion and downstream oxidant and diluent trim, wherein similarly constraining combustion temperatures to provide reliable combustion while constraining emissions.

[0176] Such techniques may vary the composition of fuel, oxidant, and / or diluent delivered into upstream versus downstream combusting and / or Blend-Trim regions. Such combusting and Blend-Trim regions may be replicated to scale the combustor(or reactor) to provide the combusting power (or reacting rate) desired while achieving improved mixing and low emissions (or byproducts).

[0177] The techniques disclosed herein may improve on conventional power generation methods by extracting excess compressed oxidant fluid with net recovery of gas compression power. Such excess compressed oxidant may be utilized in a second combustor to generate power through a second expander. It may utilize controlled compressed air or oxidant discharge (“bleed”). Such reductions in, recovery of, and / or utilization of excess air or oxidant may enable injecting more cool, heated, or superheated diluent (such as water and / or CO2) to increase diluent enthalpy delivery into one or more gas turbines. Such steps may extract, discharge, expand, recover, and / or further utilize from 2% to 95% of the compressed excess oxidant (or air). Such steps may enable greater fuel delivery into one or more combustors therein generating about 10% to 100%, 5% to 200%, or 2% to >300%, greater power than Brayton cycle gas turbines with the same compressor, depending on pressure, compressed fluid extraction, expansion, and / or delivery to one or more additional combustors and expanders, and / or to larger combustors and expanders. The techniques described herein include methods of enhancing systems to improve power output by the introduction of high enthalpy dilutant (e.g. superheated water and / or superheated steam) while controlling system parameters such as “bleed” to avoid unwanted conditions such as compressor surge and / or compressor choke. (i.e., sudden and potentially damaging reversal of flow). Superheated water is water in a liquid state with a temperature greater than 100 deg C. By way of example the superheated water may have a temperature greater than 110, 125, 150, 175, 200, 500 or 750 deg. C. More particularly, the superheated water may be heated to and delivered at a pressure above the combustor pressure with corresponding higher temperature, such as from 150 deg C to 500 deg C orcombinations thereof or in between. A high enthalpy condition one where the energy level of the diluent is at or above that of a superheated condition. The injection of high enthalpy dilutants provide an unexpected benefit with regards to increased power production when coupled with the opening and modulation of bleed systems, particularly under near design rated load operations (e.g. peak loading). The techniques described herein may deliver cooled, chilled, unheated, heated, or superheated liquid water, and / or steam, and / or superheated steam into one or more of the gas turbine compressor, one or more combustors, and / or one or more expanders. Such delivered cooled and / or heated fluid temperature may variously range from 10°C to 1,500°C, 5°C to 1,600°C, or from 1°C to 1,800°C etc.

[0178] The techniques disclosed herein may include delivering one or more of humidified or “wet” fuel, oxidant, and / or diluent into the upstream portion of the combustor to achieve controlled diluted combustion. It may provide downstream delivery of oxidant and / or diluent into the combustor downstream fuel “lean” (oxidant “rich) (blend-trim) region after upstream fuel rich (oxidant “lean”) diluted combustion. This may improve combustion, reduce emissions, increase efficiency, and / or increase net power output.

[0179] The techniques disclosed herein may dynamically (such as actively modulating system control elements) manage operating conditions within compressor surge and / or stall operating margins relative to expander choke limits. It may deliver fluids and shift net combustion stoichiometry to enhance one or more of power, efficiency, emissions, and / or fuel flexibility.

[0180] Such techniques may efficiently combust a broad range of conventional and / or sustainable fuels. E.g., these may comprise one or more of natural gas, methane, syngas, diesel fuels, JP5, JP8, methanol, ethanol, hydrogen, ammonia, and / or similar conventional or renewable fuels, or mixtures thereof.

[0181] Such techniques may combine reducing excess oxidant delivery with scalable combustion technology. These may enable high net power, ultra-clean emissions, high efficiency, and fuel-flexible operation. These may control combustibility boundaries and reduce emissions, while improving power and profitability.

[0182] Referring now Fig. 1A and Fig. 1B, combusting fluid temperature in an upstream combusting chamber 740 and / or a downstream Blend-Trim region 850 may be controlled by controlling one or more of the ratios of diluent fluid F7 to fuel fluid F1, diluent fluid F7 to oxidant fluid F4, and / or diluent fluid F7 to Blend-Trim oxidant fluid F4, in diluted fuel fluid delivery F2, upstream diluted oxidant fluid delivery F5, and / or downstream Blend-Trim diluted oxidant fluid delivery F15, and diluent fluid F7, and / or liquid diluent fluid F14 delivered into the Blend-Trim region. The transverse cross-sectional area (X-Y axes) of the combusting chamber 740 may be progressively increased along the axial fluid flow direction (Z axis) to progressively increase the combusting chamber volume, and to accommodate gas expansion from increasing temperature. This may beneficially reduce axial fluid acceleration and fluid pressure drop across the combustor.

[0183] An upstream diluted ignition authority or pilot 720 may be configured to provide a diluted pilot flame F22 to reliably ignite downstream fuel fluid F2 and diluted oxidant fluid F5. This may include controlling a pilot combusting temperature and pilot combusting emissions resulting in pilot fluid F22. A downstream diffuser 429 may be used to reduce an axial combusting fluid pressure drop while providing additional combusting (or reacting) residence time to reduce unburned fuel and combusting (or reacting) emissions such as carbon monoxide and oxides of nitrogen.

[0184] Referring to Fig. 2A through Fig. 2E, combusting fluid oxidant concentration (or oxidant to fuel ratio) in the combusting region 740 may be varied between an upstream combusting region 742 and a downstream combusting region 744. The order and magnitude of residual oxidant fluid and / or of residual diluent fluid may be varied in the Blend-Trim region 850. E.g., they may be varied between an upstream oxidant rich combusting (Blend- Trim) region 852, and a downstream oxidant rich combusting (Blend-Trim) region 854.DETAILED DESCRIPTION Scalable Combustor Design and Operation

[0185] Certain embodiments of a scalable reactor or scalable combustor 700 are depicted in Fig. 1A, as further detailed in Fig. 1B through Fig. 1I. These embodiments exhibit one or more transversely elongated shallow combusting chambers 740 in a combustion section 730, disposed between combusting chamber near and far side feeder walls and 737 spaced shallowly apart (along the Y axis), and bounded transversely (along an X axis) to a longitudinal axial flow direction (along a Z axis) by combusting chamber near end walls 734 and far end walls 735 perpendicular to the longitudinal axial flow direction (along the Z axis) from an upstream inlet region 134 to a downstream outlet 136.

[0186] Further embodiments of a scalable reactor or scalable combustor 706 with a combusting section 730 are shown in Fig. 2A as further detailed in Fig. 2B through Fig. 2E. A blower 406 (BLW) may be used to compress an intake air or oxidant mass flow WX2, comprising optional liquid diluent F7, to a pressurized oxidant mass flow WX3 and deliver it to the inlet of a diffuser 420 at axial location CZ31. Such configurations may include an upstream diluent delivery section 710 comprising diluent delivery spray system 24, an ignition section 720 comprising an ignition authority or pilot 100, the combusting region 740, the Blend – Trim region 850 for further oxidant and diluent delivery, and an equilibration zone 750. These may deliver a hot fluid flow W4 exiting the combustor 706 after the end of the equilibrating zone 750 at CZ 394. Transversely Elongated Perforated Combustor Side Walls

[0187] Certain embodiments of a cuboidal configuration of the scalable reactor or combustor 700 are depicted in Fig.1A, as further detailed in Fig.1B through Fig.1I. In one embodiment, the cuboidal scalable reactor or combustor 700 may be formed by creating one or more transversely elongated shallow reacting regions or combusting chambers 740 in an upstream combustion section 730 of the scalable reactor or combustor. The embodiment of Fig. 1A, including detail in Fig. 1B, displays the scalable combustor 700 oriented with an upstream inlet region 134, near an upstream combustor end wall 241, with an upstream pilot chamber 720. Said scalable combustor 700 has a downstream combustor outlet 136 at the downstream combustor end (or top in the Z direction).

[0188] In this embodiment, the scalable combustor 700 is configured with a flow direction from an upstream pilot fluid F22 flow at the upstream inlet 134, to an energetic fluid F20 exiting the combustor outlet 136, along a generally upward vertical direction (similar to the vertical Z axis). In other embodiments, the flow axis of the scalable combustor 700 may be oriented horizontally, or downwards, or at some intermediate angle.

[0189] Per Fig. 1A, in this embodiment, the upstream combustion section 730 may comprise one or more elongated shallow reacting or combusting chambers 740 generally elongated in a transverse direction (X axis). In this embodiment, this is depicted as generally perpendicular to the primary axial flow direction (along the Z direction). Correspondingly, such one or more combusting chambers 740 may be generally shallowly displaced in a normal direction (Y axis) perpendicular to the transverse elongation direction, (typically normal to both the axial flow in the Z axis and to the transverse X direction).

[0190] Correspondingly, Figs. 2B, Fig. 2D, and Fig. 2E detail such scalable reactor configurations 706, depicted here in a similar cuboidal configuration. Fig. 2B, Fig. 2D, and Fig. 2E similarly show the combusting section 730 with the combusting chamber 740 bounded by transversely elongated (“far” side) oxidant feeder perforated wall 737, and an opposing combusting chamber transversely elongated (“near” side) fuel feeder perforated wall 736.

[0191] Similarly, per Fig. 2D and Fig. 2E, the combusting chamber 740 may further be configured into an upstream combusting chamber 742, and a downstream combusting chamber 744. Upstream combusting chamber 742 may be bounded by upstream perforated fuel feeder 805 with orifices 81 and upstream perforated oxidant feeders 815 with orifices 82. Downstream combusting chamber 744 may be bounded by downstream perforated fuel feeder 806 with orifices 81 through fuel feeder walls 736, and downstream perforated oxidant feeders 816 with orifices 82 through oxidant feeder walls 737. Combusting Chamber Transverse End Walls

[0192] Further per Fig. 1A, such transversely elongated shallow combusting chambers 740 may generally be configured between correspondingly sized combusting chamber side fuel feeder walls 736 and oxidant feeder walls 737 similarly transversely elongated along the X direction. The combusting chamber740 between such elongated combusting side fuel feeder walls 736 and oxidant feeder 737 may be transversely bounded along the transverse X direction by combusting chamber bounding end walls. These transverse end bounds typically include a combusting chamber near end wall 734 (in the negative X direction), and a combusting chamber far end wall 735 (in the positive X direction).

[0193] Further per perspective views Fig.2D, and Fig.2E, transversely elongated shallow combusting chambers 740 with combusting chamber side feeder perforated walls 736 and 737, may be transversely bounded by combusting chamber bounding end walls such as end walls 734, similar to that shown in Fig. 1A, Fig. 1C, and elevation view Fig. 1D. Shallowly Separated Combusting Chamber Side Walls

[0194] Per Fig. 1A, the elongated far side feeder wall 737 and near side feeder wall 736 may be spaced shallowly apart with a shallow spacing depth 748 in the Y direction perpendicular (normal) to both the axial flow and the transverse X direction. Such shallow spacing depth 748 may separate near side feeder walls 736 and far side feeder walls 737 relatively closer, in the perpendicular Y direction, than the transverse elongated width 746 separating the near end wall 734 from the far end wall 735 and bounding the elongated combusting chamber 740 along the transverse X direction. Such shallow separation spacing 748 or perpendicular (normal) combusting chamber depth, between elongated side feeder walls 736 and 737 bounding the combusting chamber 740, may be provided by a corresponding shallow separation depth of the near side bounding walls 734 and far side bounding walls 735 separating elongated nearside feeder walls 736 and elongated far side feeder wall 737 along the Y axis perpendicular to the Z flow axis. Combusting Section Manifolds and Ducts Opposed Fuel and Oxidant Ducts

[0195] With reference to Fuel Fluid Delivery Elevation View Fig.1D, Fuel Fluid Wall Section View Fig. 1E, Oxidant Fluid Wall Section view Fig. 1F, and Oxidant Manifold Elevation View Fig.1H, in one embodiment, a separated fuel- oxidant scalable combustor may be formed having at least one first fluid or fuel manifold 770 configured to deliver first fuel fluid F1, comprising fuel fluid (and / or reactant fluid), to one or more perforated fuel feeders 750 (or first fluidreactant perforated delivery ducts) such as shown in Fig. 1D and Fig. 1I. As shown in Fig. 1A, 1C, 1H and Fig. 1I, this embodiment may comprise at least one second fluid or oxidant manifold 780 configured to deliver second oxidant fluid F4 comprising oxidant fluid (or second co-reactant) through oxidant manifolds 780 to one or more perforated second fluid or oxidant delivery ducts or oxidant feeders 760 having a plurality of oxidant orifices 82 to deliver second oxidant fluid F4 into the combusting chamber 740.

[0196] Referring further to Fuel Fluid Delivery Elevation View Fig. 1D and Fig. 1E, in some configurations, the first fuel fluid F1 may be mixed with third diluent fluid F7 to form and deliver a diluted fuel fluid F2 for delivery into fuel manifold 770, and thence into perforated fuel feeders 750 (or perforated reactant delivery duct). The second oxidant fluid F4 comprising oxidant fluid and / or co- reactant fluid may be diluted with diluent fluid F7 to form diluted oxidant (and / or co-reacting) fluid F5 for delivery into oxidant manifold 760.

[0197] As depicted in combustor perspective view Fig 1A, Fuel Fluid Delivery Elevation View Fig. 1D, Oxidant Fluid Delivery Elevation View Fig. 1H and Combustor Plan View Fig. 1I, diluted first fluid or fuel fluid F2 may similarly be delivered from fuel manifold 770 into perforated fuel feeders 750 adjacent to the combusting chamber(s) 740. Similarly, diluted second fluid, diluted oxidant (or co-reactant) fluid F5 may be delivered from oxidant manifold(s) 780 into oxidant fluid feeder (perforated duct(s)) 760 adjacent to combusting chamber(s) 740.

[0198] As depicted in Combustor Plan View Fig. 1I, a central combusting / feeder region 739 may comprise one or more fuel feeders 750 having perforated near side fuel feeder wall(s) 736, and one or more oxidant feeders 760 (perforated second fluid ducts) having perforated far side oxidant feeder wall(s) 737. These fuel feeders 750 and oxidant feeders 760, may form proximate combusting chambers (or zone(s)) 740 between opposing fuel feeders 750 and oxidant feeders 760, and bounded by perforated fuel feeder walls 736 and oxidant feeder walls 737, and combusting chamber end walls 734 and 735.

[0199] Referring to Fig. 1E, Fig. 1F, Fig. 1G, and Fig. 1I, fuel fluid orifices 81, oxidant fluid orifices 82, and Blend-Trim oxidant ports or orifices 83 in the respective near side fuel feeder walls 736, and far side oxidant feeder walls 737, Blend-Trim oxidant near side feeder walls 856 and Blend-Trim oxidant far sidefeeder walls 857 may be configured to provide respective distributions of one or more of fluid port diameters and port spacings along the streamwise flow direction. These may be configured to provide desired streamwise distributions of fuel fluid and oxidant fluid delivery to achieve desired streamwise composition distributions in the energetic fluids within a plurality of streamwise reaction zones.

[0200] Similarly, as depicted in Combustor Perspective View Fig. 2D, fuel fluid orifices 81, and oxidant fluid orifices 82 may be configured in fuel feeder walls 736, and oxidant feeder walls 737. These deliver fuel fluid F2 through diluted fuel feeder 804, and oxidant fluid F5 through diluted oxidant feeder 814 into the combusting chamber or region 740.

[0201] As depicted in Segmented Combustor Perspective View Fig. 2E upstream and downstream fuel and oxidant fluid delivery feeders may be configured to feed fuel and oxidant fluids with different diluent compositions into upstream combusting regions 742 and downstream combusting regions 744. E.g., fuel fluid F1 may be delivered through perforated fluid delivery feeder 805 via fuel orifices 81 into upstream combusting chamber(s) 742. Similarly diluted fuel fluid F2 may be delivered through downstream fuel fluid delivery feeder 806 via fuel orifices 81 into downstream combusting chamber(s) 744.

[0202] Correspondingly, oxidant fluid F4 may be delivered through upstream perforated oxidant fluid delivery feeder 815 via oxidant orifices 82 into the upstream combusting chamber 742. Similarly diluted oxidant fluid F5 may be delivered through downstream oxidant fluid delivery feeder 816 via oxidant orifices 82 into a downstream combusting chamber 744.

[0203] Further in Fig. 2E, in similar configurations, upstream and downstream fuel fluids F1 and F2 may comprise differing diluent compositions. E.g., the diluent to fuel ratio Omega1 and Omega2 of fuel fluids F1 and F2 may be configured differently in the upstream perforated fuel feeder 805 versus the downstream perforated fuel feeder 806. This enables controlling the temperature differently upstream combustion region 742 verses downstream combusting region 744 degrees of diluent to fluid composition.

[0204] Similarly upstream and downstream oxidant fluids F4 and F5 may comprise differing degrees of diluent to oxidant composition. These fluids may be configured to control the relative oxidant to fuel ratio to stoichiometricoxidant to fuel ratio Lambda of F4 in the upstream oxidant feeder 815 into the upstream combusting region 742 differently from the relative oxidant to fuel ratio Lambda of diluted oxidant fluid F5 in the downstream oxidant feeder 816 into the downstream combusting region 744. This enables controlling combusting region richness (relative oxidant to fuel ratio) and thus the fuel combusting or oxidizing rate in the upstream combusting region 742 differently from that the downstream combusting region 744.

[0205] The separated fuel-oxidant combustor may be configured in generally transversely elongated shallow combusting chambers 740, (such as rectangular- like configurations) between opposed perforated duct sides (or liners) and in an axial direction along the fluid flow.

[0206] With further reference to Fig. 1A, Fig. 1C, Fig. 1D, and Fig. 1H, the scalable combustor 700 may be configured with a downstream transversely expanding (or hand “fan”) shape combusting chamber 740, between transversely bounding end walls 734 and 735 (in the X direction), (between shallowly separated side feeder walls 736 and 737) that generally increases transversely (in the X direction) to the fluid flow, along the streamwise flow direction (along the Z axis) and with progressively increasing fluid flow.

[0207] This scalable combustor may be configured such that the cross-sectional area of the combusting (or reacting) zones increases with increasing axial distance along the flow direction. The opposed fuel fluid and oxidant fluid delivery through perforated fuel and oxidant feeders may comprise individually mixed proportions of diluent as desired to achieve a desired axial temperature distribution. The effectiveness of the Thermal Barrier Coating (TBC) may be adjusted (or the TBC removed) to configure the heat transfer rate from the reaction zone to the fluid within one or both adjacent ducts. Downstream Blend-Trim Region

[0208] Per Fig. 1A, and Fig. 1C, a Blend-Trim section 426 comprising a Blend- Trim region 850 may be configured downstream of the combustion section 730 comprising the combusting chamber 740. This Blend-Trim region 860 may deliver one or both of further oxidant fluid F4 and / or further diluent fluid F7. These oxidant fluids F4 and diluent fluids F7 may be mixed such as by delivering diluted second reactant fluid or diluted oxidant fluid F5 into the Blend-Trim region 860.

[0209] Per Fig. 1D and Fig. 1H, the Blend-Trim region may axially begin at an adjacent upstream Blend-Trim manifold bounding wall 248 separating fluid delivery into the upstream combusting chamber (or region) 740 from diluted oxidant fluid delivery into the downstream Blend-Trim region 850. The Blend- Trim region 850 may extend to a downstream Blend-Trim Manifold and Blend- Trim feeder bounding wall 249.

[0210] The Blend-Trim region of Fig. 1A further depicts a portion of the transversely elongated downstream Blend-Trim region near side wall 856 and Blend-Trim region far side wall 857 between transversely bounding near end wall 734 and transversely bounding far end wall 735, (or between counterclockwise walls 250 and clockwise walls 251) such as shown in Fig.1D and Fig. 1H. The downstream Blend-Trim region side wall 856 and side wall 857 may further extend between axial boundaries of Blend-Trim region upstream wall 248 and Blend-Trim region downstream wall 249.

[0211] Referring to Fig. 1A, Fig. 1G, and Fig. 1I, Blend-Trim oxidant ports or orifices 83 in the Blend-Trim oxidant near side feeder walls 856 and equivalent Blend-Trim oxidant farr side feeder walls 857 may be configured to provide respective distributions of one or more of fluid port diameters and port spacings along the streamwise flow direction. These may be configured to provide desired streamwise distributions of oxidant fluid delivery and / or optional diluent fluid delivery to achieve desired streamwise composition distributions in the energetic fluids within a plurality of streamwise reaction zones. Bounding Distance Between Transverse End Walls

[0212] In the upstream combustion section 730, as shown in Fig. 1A, Fig. 1C, Fig. 1D, and Fig. 1H, the combusting chamber 740 has a transverse width 746 along the transverse X direction, between transverse near end walls 734 and transverse far end walls 735 bounding the combusting chamber 740. Such combusting chamber transverse width 746 may generally increase along the Z axial flow direction in the combustion section 730 from an upstream combustor inlet (or pilot outlet) 134, near an upstream combustor end wall 241, and progressively increasing with downstream distance along the Z flow direction.

[0213] In the downstream Blend-Trim region 426, as shown in Fig. 1A, Fig. 1C, Fig.1D, and Fig.1H, the Blend-Trim flow region 850 has a transverse bounding separation or combusting transverse width 746 between near bounding end wall734 and far bounding end wall 735. Such transverse bounding width 746 may further increase in the transverse X direction within the Blend-Trim fluid delivery region 426 between the upstream Blend-Trim region manifold boundary 248 and a corresponding downstream Blend-Trim region boundary 249, and downstream of the combusting chamber 740. In other configurations, the transverse bounding width 746 may be fairly uniform in the Blend-Trim region 426.

[0214] As further shown in Fig. 1C, and Fig. 1I, in some configurations of the combustion section 730, the transverse end walls 734 and 735 may be configured with an upstream convex wall section 731, providing a non-linearly increasing bounding separation width 746 between those transverse bounding walls. Similarly, per Fig.2D and Fig.2E, the upstream transverse end walls 734 (and 735 not shown), may be configured with upstream curved convex end wall sections 731 with radial to axial slopes increasing with downstream axial distance.

[0215] As further shown in Fig. 1C, the convex end wall section 731 bounding combustion section 730, may be followed downstream by an end wall section 732 with a maximum slope (or low curvature) of transverse increase with axial distance. Similarly, per Fig. 2D, and Fig. 2E, the combustion section 740 may be bounded axially midway by an end wall section 732 having a maximum slope of transverse increase with axial distance, or similar section with low radial to axial curvature.

[0216] Such a maximum slope end wall section 732 in one or both bounding end walls 735 and / or 734 may be configured to provide a low curvature (or fairly linear) increase in the transverse bounding separation between those bounding end walls. Such maximum slope (low curvature or fairly linear) sections may be utilized to accommodate overhang slope limitations in 3D printing manufacturing of such bounding end walls. E.g., such as when 3D printing may be used to form the bounding end walls 735 and / or 735 with the combusting Z axis in the vertical gravitational direction.

[0217] Similarly, per Fig. 2D and Fig. 2E, the bounding end walls 734 (and similarly bounding end walls 735) of the combusting section 740 may similarly have maximum radial to axial slopes 732 with fairly linear radial to axial slopes (or low curvature).

[0218] Further to Fig. 1C, in some configurations of the combustion section 730, the transverse bounding end walls 734 and 735 may further be configured with a downstream concave wall section 733 downstream of the fairly linear bounding end wall section 732. This downstream generally concave transversely bounding end wall section 733, providing a non-linear section with the bounding separation width 746 between those transverse bounding walls further increasing along the axial Z flow direction.

[0219] Such concave nonlinear bounding end wall sections 733 in one or both bounding end walls 735 and / or 734 may be configured to provide a declining rate of increase along the axial Z flow direction. This declining rate of increase in bounding separation with 746 between bounding end walls 735 and 734 may beneficially improve the expansion fluid dynamics in one or both of the combusting chamber 740 and the Blend-Trim transition region 850.

[0220] Similarly, per Fig. 2D and Fig. 2E, the bounding end walls 734 (and similar end walls 735) of the combusting section 740 may similarly be configured with downstream concave radial to axial sloped wall sections 733 downstream of the transition bounding end wall section 732 with maximum slope. Radial to axial slopes of bounding sections 733 may decline towards zero curvature bounding the downstream Blend-Trim section 852 and thence to connect with downstream equilibrating section 750. This beneficially reduces transition turbulence and combustor pressure drop from the upstream combustor inlet at CZ31 to the combustor outlet CZ394 per Fig. 2A.

[0221] As depicted in Fig. 2B, the diluent delivery section 710 near the inlet 134 may comprise delivering oxidant fluid F4 through an upstream oxidant manifold 242 and out through a plurality of perforated oxidant feeders 11 distributed across the upstream region. Similarly, a distributed fuel delivery system may inject diluent F7 through a downstream fuel manifold 244 and out through distributed perforated oxidant feeders 14 into incoming oxidant fluid F4. Pilot Light or Ignition Authority

[0222] As schematically depicted in the upstream closeup Fig. 1B, the combusting chamber 740 may have an upstream pilot light, ignition source or flame authority 720, such as near the combustor upstream end wall 241. Ignition source 720 may form a diluted hot pilot flow F22 at the pilot outlet flowing into the adjacent combusting chamber 740.

[0223] Per schematic Fig. 2A, the combusting chamber 740 may have an upstream Flame Holder or Ignition Authority 100 comprising a Pilot P with an inlet axially at CZ33 and an outlet axially at CZ34. Perspective Fig. 2B depicts diluted pilot fuel F10 being delivered to ignition authority or flame holder 100 downstream of the diluted oxidant delivery section 720. Combusting diluted pilot fuel may be delivered via hot gas delivery flame tubes 116 to one or more combusting chambers in Combustion Section 730 where the chambers may have Combustion Chamber Radially Outer Side Walls 736. Fluid Delivery Orifices

[0224] Per Fig. 1A, as detailed in combustor wall sections Fig. 1E, Fig. 1F, and Fig. 1G, at least one of the scalable combusting region’s transversely elongated near side feeder wall (or “fan” wall) 736 and elongated far side feeder wall 737, bounding the adjacent combusting chamber 740, may comprise a plurality of fuel fluid orifices 81, or oxidant fluid orifices 82. Such orifices may be configured about the one or more perforated combustor side (or liner) far side oxidant feeder walls 737 and near side fuel feeder walls 736 adjacent to at least one combusting chamber 740.

[0225] Per Fig.1A (and Fig.1B) such transversely elongated combustor near side fuel feeder walls 736 and far side oxidant feeder walls 737may be generally shallowly opposed to each other about reacting or combusting chambers 740.

[0226] As further detailed in Fig. 1E, and Fig.1F, one or more diluted fuel fluids F2 (or fuel fluid F1 not shown) and / or diluted oxidant fluids F5 (or oxidant fluid F4 not shown) may be delivered through a plurality of perforated wall orifices 81 and 82 (in the Y, or negative Y direction) configured in the combusting region side fuel feeder (or liner) walls 736, and oxidant feeder (or liner) walls 737 adjacent to and into transversely flow combusting fluid F12 flowing axially (Z direction) along the combusting chamber 740. For example, Oxidant Wall Section Detail Fig. 1F depicts a Diluted Oxidant Delivery Combusting Wall Section 745 having multiple oxidant fluid orifices 82 configured to deliver diluted co-reactant or oxidant fluid F5 (or oxidant fluid F4 not shown), and may be configured about fluid duct feeder wall 737 section of the combusting chamber 740 of Fig. 1A. The near side oxidant fluid duct feeder wall 737 may have an optional thermal barrier coating (TBC) or insulating coating 738protecting the fluid duct wall 132 from hot reacting or combusting fluid F12 flowing axially (Z direction) along the combusting chamber 740.

[0227] Fig. 1E depicts a Diluted Fuel Delivery Wall Section 743 enlarged from the combusting chamber wall of Fig. 1A. Fig. 1E depicts a portion of the transversely elongated upstream combusting chamber near side fuel feeder wall 736 between axial (Z axis) boundaries of the upstream end wall 241 and the downstream wall 248. Combusting chamber wall section detail Fig. 1E, is further located between transverse near bounding wall 734 and far bounding wall 735 (along X axis), such as further detailed in Fig. 1C, Fig. 1D, and Fig. 1H.

[0228] Fig.1E details how some configurations may configure multiple fuel fluid orifices 81, to deliver diluted first reacting fluid or fuel fluid F2 (or fuel fluid F1 not shown) through a perforated duct wall section 132 in the combusting near side fuel feeder wall 737 into the adjacent combusting chamber 740 per Fig.1A and Fig.1C. Per detail Fig.1E, fluid duct feeder wall section 736 may optionally have a thermal barrier coating (TBC) or insulating coating 738 adjacent to the hot combusting fluid F12 flowing axially through the combusting chamber 740.

[0229] Similarly, Blend-Trim Wall Section Detail Fig. 1G depicts detail of an enlarged wall section 747 of the Blend-Trim Region 850 in the Blend-Trim section 426 downstream of the combusting chamber 740. This Blend-Trim region wall section 747 of Fig. 1G may comprise one or more Blend-Trim orifices 83. These Blend-Trim orifices 83 may be configured to deliver Blend- Trim diluted oxidant fluid F5 (and / or optionally diluent fluid F7 not shown) into an axially flowing Rich Reacting or Combusting Fluid F12 coming from the upstream combusting chamber into the Blend-Trim region 860 shown in Fig. 1A.

[0230] Per Blend-Trim Wall Section Detail Fig. 1G, such blend-trim orifices 83 may distributed across the Blend-Trim region wall section 856 to deliver Blend- Trim fluid F7 from Blend-Trim feeder 860 into the Blend-Trim region 850 within the downstream Blend-Trim section 426, as depicted in Fig. 1A. Such delivery of oxidant F5 in Blend-Trim diluted oxidant fluid F5 may increase the oxidant concentration of transversely flowing fuel rich combusting fluid F12 from the upstream combusting chamber 740. Adding diluted oxidant fluid F5(or oxidant fluid F7 not shown) then forms an oxidant rich Blend-Trim fuel lean reacting fluid F13 flowing downstream in the Blend-Trim region 850.

[0231] Per Blend-Trim Wall Section Detail Fig. 1G, fluid duct wall section 856 may have an optional thermal barrier coating (TBC) or insulating coating 738 protecting the Blend-Trim wall section 856 from the adjacent hot fuel rich (oxidant lean) energetic fluid F12 flowing downstream into the Blend-Trim region 850. Delivering further oxidant fluid F4 in diluted fluid F5 increases oxidant in the Blend-Trim region, furthers combustion of the fuel rich energetic fluid F12, and forms an oxidant rich energetic fluid F13 within the Blend-Trim region 850.

[0232] Similarly, detailed Fig.2C details a Diluted Fluid Delivery Wall Section, comprising fluid orifices 80 extending through fluid duct / combusting chamber walls 132, and adjacent thermal insulating coating 150 on combusting chamber wall, to deliver fuel, oxidant, and / or diluent fluids such as further depicted in Fig. 2D, and Fig. 2E.

[0233] Per Fig. 2B, In some configurations, Pilot Fuel Fluid F3 delivery may be controlled by Fuel Control Valve 232 and delivered through Pilot Fuel Fluid Tube or Passage 101 to Flame Holder 100. Similarly, Pilot Oxidant Fluid F6 may be controlled by Pilot Oxidant Valve 232 and delivered through Pilot Oxidant Fluid Tube or Passage 102 to Flame Holder 100. Correspondingly, Pilot Diluent Fluid F8 may be controlled by Pilot Oxidant Valve 232 and delivered through peripheral Diluent Fluid Tube or Passage 103 to Flame Holder 100.

[0234] Further to Fig. 2B, one or more of the Pilot Fuel Fluid Tube 101, Pilot Oxidant Fluid Tube 102, and / or Pilot Diluent Fluid Tube 103 may be used as electrical conductors to connect excitation or Ignition Voltage Source(s) 308 to the Ignition Authority 720, along with Ground 302. Such Pilot Fluid Tubes 101, 102, and / or 103 may be positioned along the Transverse End Walls 734 (and / or 735) and / or Pilot Hot Fluid Feeder Passages 116. Orifice Sizing

[0235] Referring to Fig. 1A, Fig. 1E, and Fig. 1I, the perpendicular (normal) separation distance 748 (along the Y axis) between opposing transversely elongated combustor near side (or liner) fuel feeder walls 736, and combustor far side oxidant feeder wall 737 may be configured together with the size of the fuel fluid orifices 81 and the respective fuel fluid pressure to generallyprovide a combusting fuel fluid jet (or “fuel jet”) mean penetration distance F71 of the diluted fuel fluid F2 delivered through the combusting chamber side or feeder wall orifices 81 into the inter side wall combusting chamber 740.

[0236] Referring to Fig. 1A, Fig. 1F, and Fig. 1I, the perpendicular (normal) separation distance between combustor side walls 746 (along the Y axis) between one or more opposing transversely elongated combustor near side (or liner) feeder walls 736, and combustor far side feeder walls 737, may be configured together with one or both of the size of the oxidant fluid orifices 82 and the respective fluid delivery pressure to generally provide combusting oxidant fluid jet (or “oxidant jet”) mean penetration distance F72 of the diluted oxidant fluid F5 delivered through the combusting chamber side wall orifices 82 into the inter side wall combusting chamber 740.

[0237] Referring to Fig. 1A, Fig. 1G, and Fig. 1I, the perpendicular (normal) Blend Trim perpendicular (normal) separation distance 748 (along the Y axis) between opposing transversely elongated combustor near side (or liner) feeder walls 736, and combustor far side feeder walls 737, may be configured together with one or both of the size of the Blend-Trim diluted oxidant fluid orifices 83, and the respective fluid delivery pressure of Blend-Trim diluted oxidant fluid F15, to generally provide a Blend-Trim Diluted oXidant fluid (or “oxidant jet”) mean penetration distance F73 of the Blend-Trim diluted oxidant fluid F15 delivered through the combusting chamber side wall orifices 83 into the inter side wall Blend-Trim region 850. As depicted in Fig. 1G, in some configurations diluent fluid F7 comprising liquid and / or gaseous diluent, may similarly be delivered through orifices 78 into reacting fluid F12 to form diluted combusting (or reacting) fluid F13.

[0238] For example, such side wall separation distance, orifice diameter (or area), and fluid pressure may generally be configured to deliver fuel fluid jets of diluted fuel fluid F2, oxidant fluid jets of diluted oxidant fluid F5, and / or Blend-Trim diluted oxidant fluid fluid jets F15, with about 0.1 to 10 times the equivalent fluid penetration distance under similar conditions without an opposing impinging wall. Such design of the jet penetration distance F72 and / or F71 may use configurations of one or more of the combustor side wall spacing 748, fuel orifice size 81, oxidant orifice size 82, Blend-Trim diluted oxidant fluid orifice size 83, and / or controlling the delivery pressure of fuelfluid F2, oxidant fluid F5 and / or Blend-Trim oxidant fluid F14. This fluid penetration distance F71, oxidant fluid penetration distance F72 and / or Blend- trim diluted oxidant fluid penetration distance F73 may be configured for about 20% to 200% of the shallow combusting wall separation 748. The fuel, oxidant, and trim oxidant fluid penetration distances F71, F72 and / or F73, may further be configured to between 40% to 100% of the shallow combusting wall separation distance 748. Combusting Chamber Transverse End Walls

[0239] Per Fig. 1A, Fig. 1C, Fig. 1D, Fig. 1H, and Fig. 1I, the combusting chamber outer (far) side (liner) feeder wall 737 and the shallowly displaced inner (near) side feeder wall 736 adjacent to combusting chambers 740 may be joined or abutted together along their elongated transverse ends along the X axis perpendicular to the axial fluid flow Z axis. This joining may be achieved by forming near end walls 734 and / or far end walls 735 of a fluid delivery duct between adjacent combusting side feeder (or liner) walls 736 and 737.

[0240] These combusting chamber transverse near end walls 734 and transverse far end walls 735 may be generally convex (outwardly) curved facing downstream. These form one or more reacting or combusting zones between adjacent shallowly opposed near combusting chamber side feeder wall(s) 736 and far side feeder wall(s) 737. The upstream combusting chamber 740 may generally increase in cross sectional area perpendicular to the axial combusting flow direction with increasing axial distance downstream towards the reactor or combustor outlet 136. This increasing combustor cross section may beneficially accommodate an increasing temperature and an increasing volume of the hot combustion gas formed. This increasing area with increasing combusting gas mass may beneficially reduce the fluid flow pressure drop across the scalable combustor 700 from the combustor inlet 134 to the combustor outlet 136.

[0241] The transversely elongated and opposed combusting section’s near side feeder wall 736 may comprise a generally increasing number of fuel fluid orifices 81 to deliver fluid comprising fuel fluid F1 into the reacting or combusting chamber 740 between the opposed combusting chamber near side wall 736 and combusting chamber far side wall 737. The transversely elongated combusting chamber far side feeder wall 737 may comprise a generally increasing number of oxidant fluid orifices 82 to deliver fluid comprisingoxidant fluid F4 into the reacting or combusting chamber between the opposed combustor side walls.

[0242] The corresponding configuration of shallowly displaced transversely elongated perforated combustor near and far side feeder walls 736 and 737, with transverse combustor end walls 734 and 735, may form an upstream to downstream expanding combusting chamber 740 having a generally downstream scalable expanding (hand “fan”) shape. Thermal Resistance & Insulation

[0243] The combustor chamber near and far side feeder walls 736 and 737, and combustor chamber transversely bounding near end wall 734 and far end wall 735 may be formed from a high temperature material sufficient to withstand elevated combustion gas temperatures in the reacting or combusting chamber 740.

[0244] One or more of these combusting chamber near side feeder walls 736, and / or combusting chamber far side feeder walls 737, may be covered by a thermal barrier coating (TBC) or insulating layer 738. Such TBC insulating layers 738 may be used to protect the structural material of combustor near and far side feeder walls 736 and 737 from the hot adjacent reacting fluid or energetic fluid and any corresponding radiation. Such TBC insulating layers 738 may comprise chemical protecting materials such as to protect combustor side feeder walls 736 and 737 from elevated steam and / or oxygen with their corrosive or oxidizing characteristics.

[0245] At least one reactive fluid or fuel fluid F1 may typically be delivered through the fuel fluid duct 770 and through the perforated near side (or liner) feeder walls 736 into the reacting or combusting chamber (or zone) 740.

[0246] In some configurations, the reactive fluid or fuel fluid F1 may be a premixed fuel fluid comprising a fuel and one or both of oxidant and diluent therein forming a diluted reactive fluid or fuel fluid F2 (not shown). For example, Fuel fluid F2 may comprise a mixture of natural gas, air, and a diluent comprising one or more of water vapor, steam formed from heated water, and / or a water mist. The diluted reactive fluid or diluted fuel F2 may similarly comprise chemical reactants with one or more other diluents such as carbon dioxide (CO2) and / or nitrogen (N2).

[0247] The combustor far side (or “liner”) oxidant feeder wall 737, and combustor near side fuel feeder wall 736 may be configured between outermost enclosure walls of the combustor (not shown), similar to unperforated versions of oxidant side feeder wall 737 and fuel side feeder wall 736.

[0248] The embodiment depicted in Fig.1A and Fig.1I enables using a moderate differential pressure between the fluid supply duct on one side of the combustor side (or liner) wall and the fluid in the reacting or combusting zone between the opposed combustor oxidant side feeder wall(s) 737 and combustor fuel side feeder wall(s) 736 (each optionally coated with insulating coatings 738). The fluid jets may then penetrate a portion of the way into the fluid between the combustor walls.

[0249] Per Fig. 1A, Fig. 1I and as further detailed in Fig. 1E, Fig. 1F, and Fig. 1G, numerous fuel fluid ports 81 and oxidant fluid ports 82 supplied with pressurized fluid to form fluid jets may be configured to provide substantial penetration of 33% to 67% into the shallow combusting chamber depth under a substantial combustion power level. The fuel and oxidant fluid jet orifices 81 and 82 and corresponding fluid delivery pressures may similarly be configured to provide major penetration of 40% to 100% of the distance across the shallow combusting chamber while achieving major portion of combustion power. This generally provides good mixing of the injected fluid(s) F2 and F5 with the transverse distribution of axially flowing combusting (or reacting) fluid F12 in the transversely extended shallow combusting chamber 740 between the combustor fuel side feeder wall 736 and oxidant side feeder walls 737.

[0250] In some configurations, the scalable configurations may be operated as a chemical reactor. In such configurations, numerous jets may form an effective mixing system to mix reacting fluid with co-reacting fluid to form a product fluid or energetic fluid. Such configurations may facilitate bringing injected reactive and co-reactive fluid rapidly up to a desired reacting temperature and to begin reacting.

[0251] Per Fig.1E and Fig.1G, in further configurations, thermal diluent may be delivered with one or both of the reacting fluid and / or co-reacting fluid to form first diluted reacting fluid F2 and second diluted co-reacting fluid F5 for delivery through ports 81 and / or ports 82 respectively. For example, a premixed humid fuel F2 and air-mist oxidant fluid F5 may be injected into axially flowingreacting or combusting fluid F22 or into hot or energetic fluid. Similarly, diluent fluid F7 may be delivered separately through diluent orifices 78 into reacting fluid F12.

[0252] When using the scalable (“Fan”) combustor 700, multiple fuel orifices 81 and oxidant orifices 82 may be configured to provide an axial distribution of net orifice area sufficient to deliver the flow rate of reactive or fuel fluid F1 and co- reactive or oxidant fluid F4 with the desired axial flow rate distribution. For example, this may include an increasing number of orifices of similar size about the reaction zone transverse to the combustor flow axis. Downstream Transition or Diffuser Region

[0253] With reference to Fig. 1A, a downstream end transition or end diffuser 428 may be provided downstream of the combustion section 730, and the blend- trim equilibration region 426 where present. This may provide further fluid residence time which may beneficially increase the degree of reaction or combustion. Such an end diffuser 428 may reduce the pressure drop of delivering the energetic fluid F20 out from the downstream combustor outlet 136 of the scalable combustor 700. Ignition System or Flame Authority

[0254] With reference to Fig. 1B, in some embodiments, an ignition system or flame authority 720 may be provided near the upstream end wall 241 of the combusting chamber 740. This flame authority 720 may deliver hot igniting fluid F22 into an upstream reacting zone or pilot region or chamber 720 between one or more of the perforated opposed pilot chamber side walls 722. Pilot Igniter

[0255] With further reference to Fig.1B, an igniter 124 may be provided near the upstream end of the flame authority 720. The igniter 124 may comprise one or more of a spark igniter, a pilot light, a hot gas jet, a plasma jet, a laser beam, a light pipe, a glow plug, a heated surface, a microwave heater, or other igniters such as may be used to ignite combustion or initiate chemical reactions.

[0256] Combustion may also be initiated by providing a starter fuel or reactant fluid flow F3 and second reactant or oxidant fluid flow F6, which together may comprise two or more hypergolic fluids that ignite on mutual contact.Pilot Diluent Delivery

[0257] With reference to Figure 1B, in some embodiments, further diluent F8 may be delivered through a pilot thermal diluent delivery system 373. In some configurations, an outlet of the Pilot diluent delivery system 373 may be positioned downstream of a pilot reactant or fuel delivery system 372 outlet delivering pilot reactive fluid or fuel fluid F3 to an upstream Combustor Inlet (or pilot outlet) 134 to the combusting chamber 740. Pilot diluent delivery system 373 may be located downstream of a co-reactant or oxidant pilot fluid F6 delivery through an Oxidant Pilot Delivery port 371. Such configurations may reduce the likely hood of quenching the pilot reaction or flame.

[0258] Further to Fig. 1B, the energetic pilot fluid F22 formed by the pilot reaction may be cooled by using one or both of more pilot diluent fluid, and / or cooler pilot diluent fluid F8 through pilot fluid delivery port 373. For example, this enables conducting an upstream primary reaction at a hotter temperature and / or with less oxidant fluid F6 present. e.g., with fuel rich, (and oxygen or air lean) fluid mixture of Pilot Fuel / First Fluid F3 and Pilot oXidant / Second Fluid F6.

[0259] Such diluent delivery cooling the pilot may beneficially lower byproduct combustion emissions such as NOx. It may further enable operating the reaction or combustion at hotter temperatures. This may beneficially more rapidly consume the primary reactants and optionally shorten the residence time required to achieve desired emissions of unburnt reactants or fuel. E.g., such as residual unburned hydrocarbons, alcohols, or ammonia.

[0260] For example, one or more perforated direct contactor perforated wall sections such as depicted in Fig. 1E, Fig. 1G, and / or Fig. 1F, may be used to deliver one or more diluent fluids comprising one or more of cold water, hot water, superheated water, saturated steam, superheated steam, air, carbon dioxide, nitrogen, an inert gas, or one or more reacted fluids. These may use one or more of the processes variously described in VAST Patent Applications appended or incorporated by reference. i.e., the VAST.001 (Direct Contactor), VAST.002 (Trifluid), VAST.003 (Cycle), and / or the Campbell (VAST.014) patent.

[0261] Referring to Fig. 1I, Fig. 1E, Fig. 1G, (and correspondingly to Fig. 1F) orifices 81 and / or 82 in such perforated wall sections may be further configuredto orient the diluent jets at an angle transverse to the fuel-rich combusting fluid flow such as F12 in the upstream combusting chamber 740 generally flowing axially along the Z axial direction. Similarly, orifices 83 may be oriented at an angle transverse to the Blend-Trim fuel rich (oxidant lean) fluid flow F12, and / or fuel lean (oxidant rich) fluid flow such as F13, that generally flows axially along the Z axial direction.

[0262] Correspondingly, one or more fluid delivery ducts may be formed between the combustor side walls (or liners) to deliver one or more such fluids through the orifices in those side walls. This can help improve one or more of mixing, increase the residence time within the fluid, and increase the time for liquid diluent evaporation as needed. Temperature Control by Diluent

[0263] With reference to Fig.1D, and Fig.1H relative to Fig.1A, the downstream diluent delivery may be configured to provide a diluent flow distribution vapor and / or steam may also be delivered through the direct contactor. Plan View Combusting chamber

[0264] Fig. 1I depicts a transverse X-Y cross-section through the combusting chamber (or region) 740 perpendicular to the axial flow in the Z axial direction. This cross-sectional view is in the A-A’ plane noted in the elevation views Fig. 1C, Fig. 1D, and Fig. 1H. This depicts combusting chambers 740 between diluted fuel feeders 750 and diluted (rich) oXidant feeders 760.

[0265] The combusting chamber 740 is bounded along the shallow depth in the Y perpendicular direction by combusting chamber near side feeder wall 736 and combusting chamber far side feeder wall 737. Combusting chamber 740 is further bounded by combusting chamber transverse oXidant-Diluent end wall 734 along the elongated transverse width in the positive X transverse direction. Combusting chamber 740 is further bounded by combusting chamber transverse Fuel-Diluent end wall 735 in the negative X direction.

[0266] The combusting chamber near side feeder walls 736 and far side feeder walls 737 may be protected by a thermal barrier coating or insulation layer 738. The combusting chamber end walls 735 and 734 may similarly be protected by a combusting end wall thermal barrier coating or (TBC) insulation layer 738 in the positive and negative X axial sides.

[0267] The combusting chamber near (or inner) side feeder wall 736 is shown with a plurality of fuel orifices 81 as detailed in Fig. 1E. The combusting chamber far (or outer) side feeder wall 737 is shown with a plurality of oxidant orifices 82 as detailed in Fig.1F. One or more of fuel orifices 81, and / or oXidant orifices 82 may be slant oriented at a transverse angle to the transverse X direction. Diluted Fuel / Reactant Fluid Delivery

[0268] Reactant and / or Fuel fluid F1 may be delivered into fuel feeders 750, as depicted in the elevation view Fig. 1D, in perspective view Fig. 1A, and in the plan view Fig. 1I. As shown in perspective view Fig. 1E and plan view Fig. 1I, fuel fluid orifices 81 may be angled transversely to the axial fluid flow F12 through combusting chamber side feeder wall 736 and thermal barrier coating (TBC) 738. Diluted Oxidant / Co-reactant Fluid Delivery

[0269] Co-reactant and / or Oxidant fluid F4 may be delivered into oXidant manifold 760, as depicted in elevation view Fig. 1H, in perspective view Fig. 1A, and in plan view Fig. 1I. As further shown in perspective view Fig. 1E and plan view Fig. 1I, oxidant fluid orifices 82 may be angled transversely to the axial fluid flow F12 through combusting chamber far side oxidant feeder wall 737 and thermal barrier coating (TBC) 738.

[0270] The fuel fluid orifices 81 and oxidant fluid orifices 82 may be circumferentially oriented about the axial flow axis in the same clockwise (CW) orientation as shown in Fig. 1I. Similarly, they may be equivalently oriented counterclockwise (CCW) about the fluid flow axis (about the normal to the plane of Fig. 1I). In further embodiments (not shown), the fuel fluid orifices 81 may be oriented clockwise (CW) and opposed to the opposite counterclockwise (CCW) orientation of oxidant fluid orifices 82 about the fluid flow axis (normal to the plane of Fig. 1I). Equivalently the fuel fluid orifices 81 may be oriented counterclockwise (CCW) to oppose the clockwise (CW) orientation of the oxidant fluid orifices 82 about the fluid flow axis. Blend Trim Region Downstream Oxidant and Diluent Delivery

[0271] With reference to Fig. 1D, Fig. 1F, and Fig. 1H, in context of Fig. 1A, in some embodiments, further diluent and oxidant containing fluid F5 may bedelivered into the energetic fluid into Blend-Trim region 850 downstream of the combusting chamber 740. This oxidant fluid F5 may be delivered through diluted oxidant fluid duct 860 and / or diluted oxidant fluid duct 870 into the downstream Blend-Trim region 860. As depicted in Fig. 1F, diluted oxidant fluid ducts 860 and / or 870 may have perforated walls comprising multiple orifices 83, to deliver diluted oxidant fluid F5. These may be similar to upstream fuel feeders 750 and oxidant feeders 760 in the upstream combustion section 730 adjacent to the upstream combustor side (or liner) walls. E.g., with suitable thermal barrier coating 738 to protect the walls as needed.

[0272] With further reference to Fig. 1F, Fig. 1D, Fig. 1G, and Fig. 1H, downstream diluted oxidant duct 860 and / or diluted oxidant duct 870 may have a thermal barrier coating (TBC) 738 protecting the Blend-Trim duct wall 856 from high reaction or combustion temperatures. A fluid duct with feeder walls 856 may be used, similar to the perforated direct contactor combustor side feeder walls 736, and / or 737.

[0273] Similarly, per Fig. 1F and Fig. 1I, the diluted oxidant fluid delivery orifices 83 may be configured at a Clockwise (CW) and / or CounterClockWise (CCW) angle to the reacting or combusting flow fluid flow axis, similar to the fuel fluid orifices 81 and / or oxidant fluid orifices 82, therein improving fluid mixing of injected diluted oxidant fluid F5 with incoming reacting fluid F12 and Blend-Trim fluid F13. The number and size of diluted oxidant orifices 83 and relative delivery pressure of diluted oxidant fluid F5 may be configured to achieve effective jet penetration into the energetic fluid F12.

[0274] Delivery of Blend-Trim diluted oxidant fluid F5 may be accomplished with a modest differential pressure compared to conventional combustors. Such downstream oxidant fluid may assist in reducing the oxygen concentration during most of the combustion and thus reducing the NOx emissions. Yet the downstream oxidant delivery may provide sufficient excess oxidant to enable efficient conversion of fuel, unburned hydrocarbons and carbon monoxide to carbon dioxide.

[0275] Regarding Fig. 2A, Fig. 2D and Fig. 2E, the downstream Blend-Trim combustor region 850 may be differentiated into an upstream Blend-Trim region 852 and downstream Blend-Trim region 854. Fig.2D depicts delivery of diluted oxidant F5 through diluted oxidant delivery perforated feeders 856 intoupstream Blend-Trim region 852. Correspondingly, diluent fluid F7 may be delivered via downstream perforated Thermal Diluent Tube 106 through Diluent Orifices 78 into downstream Blend-Trim region 854.

[0276] Correspondingly, Fig. 2E depicts delivery of diluent fluid F44 through perforated Thermal Diluent Tubes 106 via diluent orifices 78 into the upstream Blend-Trim region 852. Perforated Thermal Diluent Tubes 106 may similarly deliver diluent fluid F44 through diluent orifices 78 into downstream Blend- Trim Region Duct 858. The upstream Blend-Trim Region Duct 858 may deliver Diluent Fluid F44 into downstream Blend-Trim Region Duct 858. Such Diluent Fluid F44 together with Blend-Trim Oxidant Fluid F42 may thence be delivered via orifices 83 into downstream Blend-Trim Region 854.

[0277] Fig. 2E, similarly depicts delivery of diluent fluid F46 through perforated Thermal Diluent Ducts or Tubes 107 via diluent orifices 78 into the upstream Blend-Trim region 852. Perforated Thermal Diluent Tubes 107 may similarly deliver Diluent Fluid F46 through orifices 78 into downstream Blend-Trim Region Duct 857. The upstream Blend-Trim Region Duct 857 may deliver Diluent Fluid F46 into downstream Blend-Trim Region Duct 857. Diluent Fluid F46 together with Blend-Trim Oxidant Fluid F45 may thence be delivered through downstream Blend-Trim Region Duct 859, and thence via diluted oxidant orifices 83 into downstream Blend-Trim region 854.

[0278] In further configurations, the methods of fluid delivery into the Blend- Trim region depicted in Fig. 2D and Fig. 2E may be combined and adapted. E.g., by transversely alternating delivery of Diluent Fluids and / or Diluted Oxidant fluids F5 and F7, and Diluent and / or Diluted Oxidant fluids F42 and F44, and F45 and F46 upstream and downstream by transversely alternating upstream versus downstream configurations of Blend-Trim delivery ducts 856 and 858, and between Blend-Trim delivery ducts 857 and 859. Such methods enable configuring the axial concentrations of trim oxidant delivery relative to the upstream fuel delivery (Lambda). Similarly they may be used to configure the average axial concentrations of Balance-Trim residual diluent to the upstream fuel delivery (Omega).

[0279] This scalable combustor is designed to achieve ultra-clean combustion for gas turbines, combined heat and power systems, industrial heating, cooling, andother applications requiring clean controlled combustion and / or chemical reaction.

[0280] In some configurations, multiple fluid jets may be configured with shallower spacing between walls to improve relative jet penetration. The rate of diluted oxidant and fuel delivery to upstream combusting flow may be configured to increase operating range and operational robustness.

[0281] Rapidly Changing Gas Turbine Power Market

[0282] Power demand is increasing from rising population, economic growth, and growing electric vehicle fleets. Rapidly growing solar and wind power requires correspondingly greater rapid backup power. Rapidly growing Artificial Intelligence (AI) use is increasing data center power usage, which requires ultra- high reliability.

[0283] Consequently, the US Energy Information Agency’s (herein EIA) Annual Energy Outlook (AEO 2022) long term power evaluation forecasts ~331 GW more US gas turbine power by 2050. EIA projects 175 GW Simple Cycle “Peaker” turbines and 156 GW Combined Cycle turbines. This is creating a $195 billion ($7.5 billion / year) US market for intermediate or backup power up through 2050. The International Energy Agency (herein IEA, 2020) finds the US with 500 GW gas fired power plants, has ~28% of global gas fired power plants, comprising ~1,785 GW.

[0284] Demand for reliable power is growing even faster in China, India, Southeast Asia, and Africa than in the US and EU. IEA (2023) reports gas turbines generate 21.8% of global power. The EIA (AEO 2022) projects global electrical power capacity to grow ~55%-108% by 2050. (i.e., much faster than power generation growth at 30% to 76%.)

[0285] The EIA expects natural gas turbines to supply 15% to 20% of total global power. This indicates global power gas turbines will likely grow by 982 GW to 1,938 GW by 2050. This indicates a likely $1,100 billion to $2,150 billion global gas turbine growth market. This suggests potential global market share of $550 billion to $1,070 billion market for applicant’s ultra clean gas turbine power innovations as described herein.

[0286] With finite supplies of natural gas, oil and coal, there is a strategic need to develop alternate sustainable power using renewable fuels. There are also concerns over climate change and greenhouse gases. These are driving effortsto develop and use sustainable fuels, such as hydrogen (herein H2), ammonia (herein NH3), methanol (herein CH3OH), and ethanol (herein CH3CH2OH).

[0287] Ensuring Grid Reliability with Dispatchable Backup Power

[0288] Grid collapse from failure of a mid-sized power plant lost 78.64 GW of power in 2003, caused the US northeast blackout affecting 7.37 million people, and cost $4 to $10 billion in damages (Borenstein et al. 2023). California’s CAISO power grid already has a ~24 GW “duck curve” demand power rise from no demand (excess mid-day solar and wind) to the evening peak demand after sunset under calm conditions.

[0289] Ensuring reliable power with increasing solar and wind power requires greater installed dispatchable backup power (or expensive storage) than the maximum demand, to ensure grid reliability at night with low wind. This is especially stringent considering power transmission limits during peak winter or summer loads. Existing grids cannot now support interstate or national Real Zero renewable energy goals without CO2 emissions (herein “Real-Zero”, or “Net-Zero” without CO2 credits) power distribution demands. Such pressures form a strategic power system fragility.

[0290] For reliable power, grids must strategically maintain excess local dispatchable backup power sized at ~120% of peak power. This must allow for night use, cloudy periods, and low wind, while also accommodating plant maintenance and failures. Almost all current gas turbines rely on natural gas. Underground natural gas storage provides current energy buffers. Yet extreme winter conditions in Texas with equipment failures have challenged its reliability.

[0291] Achieving future Real Zero Renewable energy (without offsets) requires reliable cost-effective backup with Long Duration Energy Storage (LDES>4 hours). A 100% Real Zero renewable power grid must further cover long term climate variations. It must provide 300% of the worst 2 week’s shortages, spread over a 4-month period, per Ruhnau and Qvist (2022), and Fekete et al. (2023).

[0292] Commonly touted batteries are too expensive. Biofuels have relatively little constrained production and backup capacity. Liquid NH3 storage offers compact, long-term, cost-effective backup energy, leveraging existing transportation and storage infrastructure. However, the challenging NH3Paradox, of high NOx emissions and potential ammonia slip, must be met reliably, economically, and quickly.

[0293] Ammonia Power Growth and Opportunities

[0294] At 202 million tons / yr (183 M t / yr) ammonia (NH3) is the 2nd most manufactured chemical after sulfuric acid (H2SO4). Ammonia’s energy density (22.5 MJ / kg) is similar to methanol’s (22 MJ / kg). Widespread fertilizer production, agricultural infrastructure, and inexpensive liquid fuel transport favor sustainable NH3 fuel over hydrogen. Transport dominates costs in energy importing countries.

[0295] Strategically, NH3 will likely replace depleting hydrocarbon fuels, and become the primary sustainable fuel especially in energy importing regions and countries. NH3 is 29 times cheaper to store than H2. MacFarlane et al. (2020) provide “A Roadmap to the Ammonia Economy”. Nazemi et al. (2021) review Georgia Tech’s micro-NH3 production system (MAPS). Hydrofuel acquired Kontak and licensed Georgia Tech’s MAPS technology. These promise production of sustainable NH3 cheaper than natural gas.

[0296] Industry is building green NH3 production plants. Martin (2023) reports that Brazil’s Unigel Chemicals plans to quadruple output to 240,000 tonne / year NH3 by 2025. Saudi Arabia’s NEOM complex will make 1.2 million tonne / year of green NH3 by the end of 2026. China’s Jilin province targets producing 2 million tonne / year NH3 by 2030. Global ammonia production is forecast to grow 250% (from 200 Mt / y to 700 Mt / y) by 2050 (GPCA 2023).

[0297] The International Energy Agency (2023) updated its Ammonia Technology Roadmap and projects NH3 to supply 44% of global shipping fuel by 2050 versus 19% each for biofuels and hydrogen. Laursen et al. (2023) extensively detail advantages and challenges of using NH3 as a shipping fuel, for EMSA. Wood McKenzie (2022) projects ~50 Mt / year global NH3 use in gas / coal fired power generation by 2050, rising to 100 Mt / yr in its high-end scenario. Adeli et al. (2023) review potentials for synthesizing and using green H2 and NH3 for fuel, and energy storage.

[0298] With few natural energy resources, Japan is strategically seeking sustainable fuel imports. Japan plans to import 3 Mt / y NH3 by 2030, increasing to 30 Mt / year by 2050. At the G20 meeting in India in 2023, Japan committed to issue 20 trillion Yen (~USD 136 billion) in the Green Transformation (GX) EconomyTransition Bonds, backed by future financial assets. This will encourage public / private investment of >150 trillion yen (~ USD 1 trillion) in the GX economy. G20(2023).

[0299] Large Gas Turbine Companies

[0300] IHI and General Electric’s joint study found transport costs to Japan for imported hydrogen are reportedly 50% more expensive than ammonia (Patel 2024). IHI and GE are developing NH3 combustion technology. Japan funded IHI co-firing to 70% NH3 in a 2 MW gas turbine (Patel 2024). US Amogy (2023) and Mitsubishi Heavy Industries (MHI) are exploring the use of Amogy’s NH3 cracking technology. Mitsubishi is developing a 100% NH3 fired 40 MW H-25 gas turbine. Cesaro et al. (2024) model a Combined Cycle Gas Turbine (CCGT) on a Siemens SGT-800 (62.5 MW) gas turbine.

[0301] Japan’s MHI, and JERA, its largest power company, are pursuing a 100% NH3 fired combined cycle plant on Jurong Island, Singapore. MHI is jointly researching an NH3 fired H-25 gas turbine with Indonesian Institute Teknologi Bandung (ITB). South Korea plans to use hydrogen and NH3 for 7.1% of its power by 2036.

[0302] Centrica and Mitsubishi Power Europe are exploring development, construction, and operation of the first NH3 fired power generation facility in Europe, at the Whitegate in Cork Ireland.

[0303] Best in Class Clean Technology Requirements.

[0304] The US Clean Air Act directs the US Environmental Protection Agency (herein “EPA”) to designate areas as requiring “Reasonable Attainment Clean Technology” (herein “RACT”), “Best Available Containment Technologies” (herein “BACT”), or the stringent “Lowest Available Emissions Requirement” (herein “LAER”).

[0305] California legislation requires even more stringent “California Best Available Containment Technology” (herein “CA-BACT”) in its non- attainment counties. The US EPA’s Green Book (1971) designates four California counties in the Los Angeles-South Coast Air Basin as Nitrogen Dioxide “non-attainment” areas for NO2 emissions per EPA (2023).

[0306] Ultra-clean Scalable Combustion Design and Operation

[0307] Accordingly, several technical features in this disclosure lead to reactors that deliver and more cleanly burn reactant, oxidant, and in some examples, adddiluent fluids. The techniques described herein include scalable combustors that combust fuel with an oxidant (e.g., air or oxygen), and that may add a diluent, such as water, carbon dioxide, nitrogen, and / or excess oxygen, in any phase and / or combination.

[0308] Such techniques enable features and methods that are more scalable than conventional gas turbine combustors, across broader ranges of commercial combustor pressures, temperatures, power levels, and / or power ramping rates, therein improving power system capabilities and economics.

[0309] The techniques described herein further address designing scalable combustor methods and systems for gas turbine systems, with fuel, oxidant, and diluent types, combinations, and mechanical, electrical, and / or thermal loads, therein enabling more reliable grid operation and backup, and offering major intermittent non-dispatchable renewable power penetration and growth rates.

[0310] The techniques described herein further offer breakthrough ultra-clean methane combustion without catalysts. Some configurations were modeled using Reactive Computational Fluid Dynamics (herein “RCFD”) by the U.S. Department of Energy’s Argonne National Laboratory (herein “ANL) across gas turbine operating temperatures, pressures, and specific power ranges. Some configurations modeled achieved <1 ppmvd NOx and CO emissions by volume diluted to 15% O2 dry (herein “pvmvd”).

[0311] The results from modeling these techniques indicate a high probability that the present scalable combustor innovation will achieve best-in-class combustion in a VAST cycle gas turbine with ultra-clean emissions relative to other commercial power turbines.

[0312] The techniques described offer ultra-clean best-in-class emissions on current fuels, sustainable fuels, and combinations of such fuels. These techniques may be used to design exemplary ultra-clean dual-fuel ammonia and / or natural gas combusting capability, and to provide major leading-edge advantages over existing gas turbines. Thus, these methods offer strategic sustainable power, and also Real Zero power (or Net-Zero without CO2 offsets), with more reliable, faster, dispatchable grid backup power.

[0313] The techniques herein enable “wet” cycle gas turbines, using the VAST power cycles, to displace a major portion of conventional cooling air (or oxidant) with diluent that recovers exhaust heat and recycles heated diluent backto the combustion system (such as water, steam, CO2, and N2). Such methods enable more cleanly and competitively supplying a major portion of the projected >$100 billion single gas turbine (“peaker”) portion of US gas turbine growth market, and >$250 billion international single gas turbine growth market by 2050.

[0314] Mandated Ultra-clean Combustion Priority

[0315] Applying the techniques herein to achieve ultra-clean commercial combustors for power turbines on “natural gas” (including methane), will likely earn: 1) US Federal BACT rating required in US emission attainment areas; 2) EPA’s stricter LAER rating required in emission non-attainment areas; and 3) California’s CA-BACT required for non-attainment California counties. Applying these techniques to achieve RACT, BACT, LAER and CA-BACT ratings will likely mandate purchase priority for power systems using these combustor techniques over other technologies in non-attainment regions.

[0316] NH3 Power with Stringent NOx and NH3 “slip” Emission Rules

[0317] Such techniques may be applied to ultra-clean combustion of sustainable fuels such as hydrogen, ammonia, ethanol, and methanol. Such techniques may combust ammonia (NH3) with far lower NOx emissions than conventionally formed by burning NH3, methane, or hydrogen etc. E.g., much cleaner than burning NH3 in General Electric’s (GE’s) lean turbine combustors which form ultra-high NOx.

[0318] E.g., with Reactive Computational Fluid Dynamics (RCFD) modeling, Gubbe et al. (2023) find that conventional single stage lean premixed combustion generates ~1,800 ppmvd NOx in gas turbines at a Turbine Inlet Temperature (herein “TIT” or combustor outlet temperature) of TIT =1,900 K (1,627ºC) at a combustor outlet pressure P = 20 Bar.

[0319] These techniques may further adjust residence time to accommodate major differences in fuel flame speed, including NH3 burning ~6 times slower than methane with much narrower combustion boundaries, increasing flameout challenges. These techniques may include reliably combusting hydrogen, which burns 33 times faster than ammonia, with much wider combustion boundaries, and with dangers of flash back and catastrophic explosion.

[0320] Such techniques may similarly be used to crack NH3, and to combust cracked NH3. Cracking NH3 may include heat and / or catalysts, externally, orin situ within the combustor system. Combustion may include using combinations of NH3, and cracked ammonia (3H2 + N2).

[0321] The techniques herein may be applied to achieve the US EPA’s (EPA Part 60 Subpart KKKK) requirement of 98% (60 times) lower gas turbine NOx emissions than conventional lean NH3 combustion.

[0322] That EPA regulation necessitates nationwide emission reductions especially for fuels such a NH3 to serve in the primary dispatchable power market. E.g., reducing emissions to <25 ppmvd (or 150 ng / J of useful output, or 1.2 lb / MWh) for the 14.7 MWt to 249 MWt (50 to 850 MMBtu / h) combustion range.

[0323] These techniques may be used to approach or meet emission regulations by California’s Counties with severe smog that require 783-fold lower NOx than caused by lean air (or oxidant) combustion, limiting NOx emissions to 2.3 ppmvd. By contrast, conventional gas turbines require expensive cleanup (such as Selective Catalytic Reduction (SCR) with ongoing ammonia operating costs) to reach these limits. Some California counties further limit the unburned NH3 (“slip”) to <10 ppmvd, and then to <2.5 ppmvd.

[0324] The techniques to develop novel scalable combustors as described herein may be configured to design and operate combustors to achieve these far more difficult RACT, BACT, LAER and CA-BACT ultra-clean combustion emission ratings, especially for burning sustainable fuels such as ammonia, and “cracked” ammonia (herein a mixture of hydrogen and nitrogen with residual ammonia, from 2 NH3=3 H2+N2).

[0325] Such techniques may further be used to develop dual fuel or multi-fuel use combustors, such as to use gaseous and / or liquid NH3, cracked NH3, hydrogen, and / or natural gas in various combinations.

[0326] Ultra-Clean Power Bidding Priority

[0327] The techniques may be used to achieve ultra-clean emissions sufficient to avoid emission cleanup costs. Industry personnel estimate that such NOx emission cleanup can cost 7%-10% of total Capital Expenditure (herein “CapEx”). Applying such techniques to achieve ultra-clean emission ratings would likely eliminate such cleanup.

[0328] These techniques may further eliminate ongoing catalyst and NH3 cleanup operating costs. Together, these techniques with scalable combustion cost breakthroughs would likely achieve power bidding priority to ensure gridreliability, strongly improve profitability, increase rapid commercialization, and offer major societal benefits.

[0329] Intermediate Dispatchable Power

[0330] The techniques herein may address the need to backup rapidly increasing renewable power and reduce fossil fuel usage. Rising renewable power is correspondingly reducing combined cycle turbines’ annual capacity factors and profitability. Rising solar and / or wind power is reducing gas turbine backup power to an intermediate < 50% annual capacity factor range.

[0331] Accordingly, applying the techniques herein is expected to achieve more profitable intermediate VAST cycle power to commercially displace both new Peakers and new Combined Cycle power turbines. The techniques promise to rapidly increase competitiveness of such clean power generation and increase the target market for such ultra-clean fast response dispatchable power.

[0332] The techniques may be used for quieter distributed scalable combustion and to avoid consequent high frequency fatigue. Such techniques may be used to reduce combustor turbine destroying noise by 30 dB or more. Using such independent temperature design and control techniques in scalable combustors may substantially reduce high temperature metal creep, cyclic thermal fatigue, maintenance, repair, downtime, and operating costs.

[0333] The techniques for scalable combustors combined with “wet” cycle VAST power cycle turbines may offer cleaner, cheaper, faster, more efficient, and more durable intermediate power than both conventional Brayton “peaker” turbines and combined cycle turbines. The techniques may be used to increase combustor and turbine life, profitability, and revenue.

[0334] The techniques include developing scalable dual-fuel ammonia and natural gas combustors. These will enable more rapid VAST cycle gas turbine power commercial-ization to ensure critical grid reliability with increasing solar and wind power penetration. Such techniques using sustainable ammonia fueled gas turbines promise far longer backup with better Economy, Energy, and Environment (E3) ranking than batteries.

[0335] The techniques may be further used to develop and operate scalable combustors burning gaseous and / or liquid ammonia (NH3), cracked ammonia (2 NH3=3 H2+N2), hydrogen, ethanol, and / or methanol, together with or instead of gaseous and / or liquid natural gas (or methane). The techniques mayenable flexible provision of more cost-effective practical intermediate gas turbine systems with conventional and / or sustainable fuels, including with higher efficiency and profitability than peaker turbines.

[0336] Increasing solar and / or wind power is reducing average annual capacity usage for Combined Cycle power turbines (hours used to total annual hours). Reducing annual capacity to <50% further gives VAST profitability advantages over Combined Cycle turbines.

[0337] Pressures to eliminate coal fired power portend a high demand for the techniques enabling rapid installation of ultra-clean ammonia fueled VAST power to prevent black-outs in Washington DC, and to ensure grid reliability across the US, Japan, and EU etc.

[0338] The techniques in designing scalable combustors address current and future fuels and operating trends in adapting to combusting future renewable and sustainable fuels to VAST power cycles providing greater flexibility than Brayton and / or combined cycle gas turbines to generate commercial mechanical or electrical power and / or combined heat and power (CHP). Such flexible multi- fuel scalable combustor design and operating techniques promise to meet this rapidly increasing demand for flexible power and CHP gas turbines.

[0339] Such techniques may be used to design and construct ultra-clean reliable combustion using current or future liquid and / or gaseous fuels, and / or with liquid and / or gaseous diluent, ranging in power from 10 MW to 100 MW, in D to G Class gas turbines. They may be used to scale such ultraclean combustion down to 100 kW gas microturbines or smaller, and up to 500 MW large gas turbines.

[0340] Such techniques may be used to design and construct ultra-clean combustion systems from 1,100ºC to 1,500ºC Combustor Outlet Temperatures, or Turbine Inlet Temperatures (TIT). Scalable combustor outlet temperatures may further extend to 700ºC to 1,700ºC, or from lower quenching temperatures, or up to combustion wall thermal limits.

[0341] Such techniques may be used to design and construct combustors with specific power over industrial ranges from ~50% turndown to maximum power, such as from 30-60 MW / bar / m3 specific power. Such techniques may similarly be used to extend such scalable combustion down to 10 MW / bar / m3 or lower, and up to 120 MW / bar / m3 or higher.

[0342] Such scalable techniques may be used to design and construct combustors with typical gas turbine combustion pressures ranging from 10 bar to 40 bar. These techniques may further be used to extend scalable combustion down to 1.1 bar or lower, and up to 100 bar or higher.

[0343] Such techniques may be used to cool walls of scalable combusting sections, including flowing liquid and / or oxidant, fuel, and / or diluent or combinations thereof, past or through scalable combustor walls. They may similarly provide cooling by flowing such fluids through multiple feeders about one or more walls of scalable combusting sections.

[0344] Such techniques may be used with scalable combustor walls for mean wall temperatures greater than or equal to about 1000ºC, and up to or great than about 1500ºC. Such techniques may similarly be used with scalable combustor wall temperatures down to about 500ºC or lower, and / or up to 2500 ºC or higher, with suitable materials and / or cooling.

[0345] Such techniques may be used to preheat and / or crack a portion of ammonia by flowing it past scalable combustor walls. These may similarly be used to preheat and / or crack a portion of liquid and / or gaseous ammonia by flowing it through feeders distributed across such scalable combustor walls.

[0346] Scalable combustor techniques may be used for combustion with about 0.75- 0.83 overall range of relative Fuel / Air Equivalence mass to stoichiometric mass ratio Phi ( or 1.33 to 1.20 Air / Fuel Equivalence mass to stoichiometric massratio Lambda), and independently control temperatures by the diluent (or water) / fuel mass ratio Omega (

[0347] Such scalability techniques may similarly be extended to Fuel / Air equivalence mass ratio Phi ( to 0.67 or lower, and 0.97 or higher (orequivalently for Air / Fuel equivalence ratio Lambda up to 1.50 or higher, and down to 1.03 or lower.) with corresponding independent control of temperature by diluent / fuel ratio Omega.

[0348] Such scalable combustor techniques may be used to displace 50% to 100% stoichiometric air (or oxidant) delivered as cooling fluid, by using recycled diluent such as steam and / or hot water. Such techniques may further help displace between 10% and 170% of stoichiometric air. Such methods may reduce the relative size of an air (or oxidant) compressor by 5% to 33% up to 67% or more depending on the gas turbine size.

[0349] Scalable combustor techniques may configure combusting and equilibration residence times from 100 ms to 700 ms. They may further extend combusting and equilibration residence time down to 30 ms and up to 3 seconds.

[0350] Scalable combustor techniques may correspondingly vary the combusting and / or equilibration system lengths relative to the specific fluid delivery rate of volumetric flow per combusting section outlet cross-sectional area. Adjusting such combustion system length may facilitate combustion of difficult fuels with slow flame speed such as ammonia. They may equally allow for typical combustion of common fuels like methane and natural gas. This also allows rapid combustion for fuels such as hydrogen.

[0351] Scalable combustor configuration techniques may configure the combusting system with lengths from 100 mm to 500 mm. They may extend down to 10 mm, or increase to 5 m in length. Blend-Trim regions may range from 20 mm to 100 mm. They may be varied from 5 mm to 5 m. Equilibrating system lengths may similarly extend from 0.2 m to 2m. Equilibrating system lengths may extend down to 0.04 m, and up to 10 m.

[0352] Power System Schematic Layout

[0353] Fig. 3A schematically shows a VAST Cycle Power System with a VAST Combustion System (herein “CMB”) receiving compressed oxidant fluid from an upstream Compressor (herein “CPR”) axially at CZ3 to feed a downstream gas turbine expander (herein “EXP”) axially at CZ4. This adapts the gas turbine numbering methodology of the American Society of Mechanical Engineers (herein “ASME”), along the Combustor axial flow Z direction (herein “CZ”).

[0354] This VAST Cycle Power System depicts a Compressor (CPR) with a Compressor Inlet CZ2 and a Compressor Outlet CZ3. Compressed fluid flow (herein “WX3”) may flow into a Diffuser (herein “DIF”). A portion of compressed oxidant (herein “WX31”) may flow into an upstream ignition system or Pilot 100 (herein “P”) at a Pilot or combustor inlet plane CZ31. Another portion of compressed oxidant fluid (herein “WX34”) may be delivered upstream into the combustor such as at plane CZ32. Diluent fluid may be delivered upstream to CZ32, such as liquid water as a spray WDL32 into oxidant flow WX34.

[0355] A portion of diluent WDL32 may be delivered into an upstream typically fuel rich combusting region 730 from a combusting region inlet at CZ34 up to aBlend-Trim region inlet and combusting region outlet plane CZ35 (marked here as a combustor reference plane CBQ).

[0356] Fig. 3A further schematically shows a “Blend-Trim” Region 850 extending from an upstream Blend-Trim inlet plane CZ35 (or combusting region outlet plane) through to a downstream Equilibrating Region inlet plane CZ39 (or Blend-Trim Region outlet plane).

[0357] Equilibrating Region

[0358] With reference to Fig. 3A and 3B, an Equilibrating Region 900 may be provided downstream of the Blend-Trim region 850. This Equilibrating Region 900 may extend from the Blend-Trim region outlet at plane CZ39 to a Transition Zone Inlet plane CZ394 (or an Equilibrating Region outlet plane) to provide residence time to further complete the reaction or combustion.

[0359] Transition Region

[0360] Per Fig.3A, a Transition Region or Zone 980 may follow the equilibrating region 900 to accelerate the hot flow to the combustor outlet. This may extend from the end of the equilibration region at plane CZ394 to a combustor outlet at CZ4 and into an expander (herein “EXP”) or Turbine Inlet, with an expander outlet at an outlet plane CZ5. The equilibrating and transition regions may be aerodynamically configured to reduce flow pressure losses.

[0361] The Turbine Inlet mass flow (herein “W4”) flows into the Expander EXP at axial plane CZ4 from the Combustor outlet. Cooling diluent liquid mass flow (herein “WDL45”) may be delivered into the expander to cool hot components such as blades, stators and / or walls. Expanded fluid mass flow (herein “W5”) may flow from the expander EXP at axial plane CZ5 into a downstream heat exchanger, here depicted as a Once Through Steam Generator (herein “OTSG”). The cooled mass flow (herein “W51”) exits out of the OTSG and into a downstream heat exchanger (herein “HX”) (at an axial mid heat exchanger flow stage CZ51 not shown).

[0362] A cooled heat exchanger outlet mass flow or exhaust flow (herein “W52”) (at an axial flow stage CZ52 downstream of the heat exchanger HX not shown) may be further cooled downstream as desired to further condense diluent vapor and / or to further cool diluent liquid and non-condensable flue gas, such as by using water- or air-cooled heat exchangers (not shown). In some VAST Power Cycle configurations, vapor may be condensed, forming sub-atmosphericpressure with a recompressor compressing the cooled expanded excess oxidant and non-condensed combustion products back to atmospheric pressure discharge as detailed in prior patents (not shown).

[0363] Fig. 3A further depicts upstream gas combusting temperatures being controlled by thermal diluent flows such as water and / or steam relative to fuel fluid delivery. Such diluent fluids may be delivered into multiple upstream combusting regions. E.g., shown here into seven Combusting regions (herein “C1” to “C7”) in Fig. 3A and Fig. 3G, six Combusting regions (C1-C6 not labeled) in Fig. 3I, and eight combusting regions (C1-C8 implied, not labeled) in Fig 3N to Fig. 3Q. These may range from two to twenty combusting regions or more.

[0364] Fig. 3A shows further mass flow of oxidant fluid (herein “MX”) and mass flow of diluent fluid (herein “MD”) may be delivered into the Blend-Trim region. E.g., further oxidant such as air, and diluent such as water and / or steam may be delivered into one or more Blend regions (herein shown as a first Blend Region One “B1” and a second Blend Region Two “B2”), and into one or more Trim regions (herein shown as a First Upstream Trim Region “T1” and a Second Downstream Trim Region “T2”).

[0365] The cooled exhaust mass flow (W52) at Heat Exchanger (HX) outlet (axial plane 52 not shown) may be further cooling as needed.

[0001] Fig. 3A shows further oxidant and diluent may be delivered into a Blend- Trim region. E.g., further oxidant such as air, and diluent such as water and / or steam may be delivered into the one or more Blend regions (e.g., B1 and B2), and into the one or more Trim regions (e.g. Upstream T1 and downstream T2).

[0002] Fig. 3A shows an inlet mass flow of oxidant (or air) (herein “WX2”) with an optional compressor inlet mass flow of liquid diluent (such as liquid water spray mass flow) (herein “WDL2”) into the inlet CZ2 of the compressor CPR, with an optional compressor cooling liquid spray mass flow (herein “WDL25”) into the compressor CPR itself.

[0003] The compressor CPR may feed a mass flow of compressed oxidant fluid flow (or air) (with optional vaporized diluent) (herein “WX3”) into the upstream inlet of a VAST scalable combustor CMB at an upstream flow location CZ3. The downstream combustor outlet at flow location CZ4 may flow into an expander EXP.

[0004] The scalable combustor CMB may include an upstream diffuser, DIF, that expands and slows the oxidant (or air) from the compressor outlet / diffuser inlet CZ3 to feed an upstream combusting section from CZ34 to CZ5 a VAST combustor (CMB) extending from a combustor pilot inlet plane CZ31 to the downstream outlet plane CZ4.

[0005] Fig.3A further depicts an upstream ignition authority or Pilot 100 (P). Pilot P may be fed with a pilot fuel mass flow (herein “WF31”), a pilot oxidant mass flow (herein “WX31”), and optionally pilot diluent (herein “WDL31”) such as pilot liquid water. Further fuel fluid (herein “WF32”), and further diluent fluid (herein “WDS32”) such as steam, may be mixed and delivered as a diluted fuel fluid mass flow (herein “MF”) into a diluted fuel manifold, to feed transverse fuel feeders into combusting regions (such as C1 to C7).

[0006] Further oxidant fluid (herein “WX34”) may be delivered together with various flows of upstream diluent fluid (herein “WDL32”) and / or mixtures may then be progressively fed into the combustor via multiple feeders (C1 through C7), delivering one or more mass flows of fuel fluid (MF), oxidant fluid (MX), and diluent fluid (MD) oriented generally across or transverse to the axial flow.

[0007] Fig.3A then depicts stoichiometric diluted oxidant and / or diluent mass flows being then fed into a Blend-Trim region 850 thru one or more transverse Blend region feeders (B1 and B2), with the remaining oxidant and / or diluent fluids delivered through one or more Trim region feeders, (upstream T1, and optional downstream T2 Trim regions etc., not shown) between combustor axial planes CZ35 and CZ39.

[0008] Fig. 3A further shows mass flows of liquid diluent (herein “WDL42”) into a heat exchanger HX. Heated liquid from HX flows (herein “WDL41”) into the Once Through Steam Generator (herein “OTSG”), and upstream into the upstream combustor (herein “WDL32”), into the Blend-Trim region (herein “WDL35”), and into the downstream combustor walls in the equilibrating region and transition region, (herein “WDL398”).

[0009] Fig. 3A shows a portion of heated liquid diluent WDL41 further recovering heat in the OTSG to form steam (herein “WDS4”). This vaporized diluent may be delivered back into the Blend Trim region as WDS35, and into the upstream region as WDS32 such as into the upstream fuel mass flow MF at CZ32.Premix Region

[0010] Referring to Fig. 3A, an upstream premix region may be provided between the compressor outlet / diffuser inlet CZ3 and the combusting region outlet at CZ35. This may deliver liquid diluent WDL32 into the oxidant mass flow MX feeding one or more combusting regions C1 through C7. This premix region may similarly be located between an upstream combustor inlet plane CZ31 near the inlet 100 pilot P and the combusting region inlet near CZ34.

[0011] The premix region may comprise perforated direct contact tubes 14 connected to a liquid diluent supply flow WDL31 to deliver diluent spray into the upstream oxidant fluid WX34. One or more Valves may be configured to control delivery of one or more flows of fuel and / or diluent into one or more of the diffuser DIF, the pilot P, combusting region 730, and Blend-Trim region 850, etc.

[0012] Valve VDL42 may control the return flow of diluent liquid through the heat exchanger HX. Valve VDL35 may control flow of heated liquid diluent WDL35 into the Blend-Trim region 850.Valve VDL32 may control liquid diluent WDL32 to the combusting region manifold 730. VF32 may control fuel fluid flow WF32 into the combusting system. Valve VF31 may control fuel fluid flow WF31 to the pilot P. Scalable Radial Annular (“Fan”) Combusting Array Configurations

[0013] With reference to generic schematic three-dimensional perspective Fig. 3B, some scalable combustor embodiments, may comprise a streamwise flow axis with transversely extended combusting sections 732 relative to shallowly separated opposed combustor walls 736. Such transversely extended walls 736 of extended combusting sections 732 may be bounded with side walls 734. The relative circumferential transverse wall elongation may be greater than 1.15 times the shallow spacing by radial depth of side walls 734. adjacent combustor wall between opposed transverse – axial combusting chamber walls.

[0014] In Fig. 3B, a portion of the Scalable Combustor, CMB is depicted extending from a flame authority 100 or pilot P at axial flow location CZ31 about the outlet of the upstream diffuser DIF through a combusting section 730 and a downstream Blend-Trim region 850 opening into the downstream equilibrating region 900.

[0015] Fig. 3B shows an embodiment of a Cylindrical-Axial (circumferentially- radially stacked) combustor 702 shown in cylindrical coordinates with a Radial axis (“R”) perpendicular to an Axial flow axis (Z) with a circumferential direction Theta ( ). In other configurations, scalable combustors may use acurvilinear flow axis with non-cylindrical walls.

[0016] Such embodiments may include multiple scalable (“fan”) combusting shells (or burners) configured generally about Radial - Circumferential Theta (R - ) cylindrical surfaces. These cylindrical combusting shells may be stacked radially, and generally perpendicularly, to the primary streamwise flow axis of oxidant fluid F5 through the scalable combustor, oriented along the axial (Z) flow direction, from an upstream fluid inlet 134 to a fluid flow outlet 136 for heated pressurized hot combusted fluid F20.

[0017] Per Fig. 3B, for operation in elevated pressures, such scalable circumferential combustor embodiments 702 may be configured within an outer Pressure Vessel Wall 172. A pilot fuel fluid flow F3, and a pilot oxidant fluid flow F6, may be delivered to an upstream Igniter, flame authority or Pilot 100, configured to combust these fluids and to form a hot pilot fluid flow F22.

[0018] Pilot diluent fluid F8 flow may be separately delivered to the Pilot 100, and / or mixed in with pilot fuel fluid F3, and / or pilot oxidant fluid F6 flowing into the Pilot 100 in an upstream pilot region 720.

[0019] Per Fig. 3B, such upstream hot pilot fluid flow F22 from Pilot 100 may be distributed in upstream pilot region 720 to an upstream end of a pilot fluid distribution system 722 comprising one or more scalable pilot fluid delivery ducts (or “fan” burner ducts) 728. Such pilot fluid delivery ducts (or “fan” burners) 728 may be configured circumferentially around the cylindrically stacked scalable combustor 702.

[0020] Pilot fluid delivery ducts 728 may deliver hot pilot fluid into one or more combusting systems (or mid-fan burners) 732 in an axially intermediate combusting region 730.

[0021] Further to Fig. 3B, each combusting system 732 generally comprises two radially opposing circumferential combusting radially outward side walls 736 (with corresponding radially inward side walls). These combusting radially outward side walls 736 may be bounded and connected by corresponding combusting (mid-fan) (circumferentially) end walls 734. In otherconfigurations, radial side walls 736 may be curved around to radially meet and transversely or circumferentially bound the combusting region.

[0022] Each combusting system radial side wall 736 may comprise numerous fluid delivery orifices 80 such as schematically depicted in Fig.3C. Pressurized oxidant fluid F5 may be delivered into the Cylindrical-Axial combusting system 702 and delivered into combusting system 732 through orifices 80 configured in combusting system radial side walls 736.

[0023] Similarly, per Fig. 3B, diluted fuel fluid F2 may be delivered through a similar axial Fuel Manifold 770 between circumferentially adjacent combusting regions on alternating sides of the combusting regions from the oxidant fluid F5 delivery.

[0024] In further configurations, premixed reactive fuel-oxidant mixture with optional diluent may be delivered into the cylindrical-axial combustor 702, and delivered through perforated combustor radial side walls 736 in combusting systems 732 within the combusting region 730.

[0025] Per Fig. 3B, energetic fluid from one or more combusting systems 732 in combusting region 730 may be delivered to circumferential downstream Blend- Trim region 850 comprising Blend-Trim oxidant-diluent delivery and reacting region manifold walls 857 feeding related Blend-Trim reacting regions. Each Blend-Trim reacting region 850 may comprise opposing circumferential Blend- Trim perforated side walls 857 to bound combustion within that region.

[0026] The Blend-Trim region side walls 857 may generally be connected by one or more far-fan end walls 746. The Blend-Trim side walls 857 may also be configured to join at their circumferentially transverse ends. Multiple sets of circumferential combustors 732 and Blend-Trim Regions 850 may be configured within combustor outer wall or pressure vessel 172.

[0027] Fig. 3C depicts an expanded view of a combustor wall section radial side wall 736 showing orifices 80 through a combustor fluid duct wall 132 protected by a thermal insulating barrier 150. Symmetric Combustor

[0028] Fig. 3D depicts a sample radial circumferential (R Theta) cross section of a portion of a comBusting region extending circumferentially by a Combusting section angle THC. This example shows an oXidant Manifold on the CCW side feeding oxidant fluid F5 with the THBMX CW portion shown as feeding twoCW adjacent combusting regions. On the CW side, Fig. 3D depicts a fuel manifold encompassing a THBMF CW portion correspondingly feeding the two radially adjacent combusting regions including a combusting feeder radial depth (Thickness) CR15T.

[0029] Fig.3D further depicts an outer oxidant fluid feeder extending radially with a radial depth (Thickness) CR12T inside of an outer circumferential wall having an inner radius CR12. That outer oxidant fluid feeder extends circumferentially over an included angle THBFX4 and feeds oxidant fluid through multiple orifices into a combusting region extending radially with a radial depth (or Thickness) CR15T from outer wall inner radius CR15 to inner wall outer radius CR16.

[0030] Oxidant fluid F5 optionally with diluent (such as water vapor or mist) may flow along the oXidant fluid feeder and through oXidant orifices with a typical diameter DXO into a radially adjacent outer combusting region extending radially with a depth (or Thickness) CR15T between combusting chamber outer radius CR15 and combusting chamber inner radius CR16. These oxidant orifices may be offset from the CCW manifold by a circumferential angle THBXO, and spaced apart by a circumferential angle THBXS, with an Jth orifice in an Ith oxidant feeder positioned at a circumferential angle THBXIJ.

[0031] Fig. 3D further depicts Fuel fluid flow F2 optionally diluted with diluent fluid, flowing though a CW comBusting region manifold extending through circumferential Theta angle THBMF. This CW fuel fluid manifold delivers fuel fluid through a fuel complementary feeder extending radially with a depth (Thickness) CR18T, and feeding fuel fluid through fuel fluid orifices with typical fuel orifice diameter DFO into the outer combusting region between CR15 and CR16 extending radially with a depth (Thickness) CR15T and circumferentially about an angle THBFF4. This fuel feeder with a depth CR18T may similarly feed fluid into an inwards combusting region extending radially between CR25 and CR26, and circumferentially across THBFF4.

[0032] Further to Fig. 3D, oxidant fluid F5 may similarly be delivered radially (and longitudinally) through the CCW manifold angle THBQX into a CCW combusting region. On the CW side, diluent fluid F7 may be delivered through a CW diluent manifold extending circumferentially by THMDS for each of the central and CW combusting regions and axially along the combusting region.

[0033] Fig. 3E depicts an axial circumferential (Z Theta) “unrolled” plan view of two adjacent symmetric combusting and Blend-Trim regions with circumferentially CCW bounding end walls 734 and CW bounding end walls 735. Such combusting regions may extend axially from an upstream Pilot 100 outlet or combusting inlet CZ34 to downstream axial boundary CZ35. The downstream Blend Trim region may extend from CZ35 to CZ39.

[0034] Per Fig. 3E, such adjacent symmetric combusting regions are shown here as having adjacent CCW oxidant fluid manifold regions ducting oxidant fluid F5 per combusting region. They may have adjacent CW fuel manifold regions ducting diluted fuel fluid F2.

[0035] Such CCW oxidant manifolds and adjacent CW fuel manifolds may be commonly bounded and divided by a sigmoidally curved longitudinal (radial) manifold divider 250 between upstream CZ34 and combusting downstream CZ35 bounds, and thence to the Blend-Trim region axially between planes CZ35 and the downstream CZ39.

[0036] Fig. 3E further depicts an upstream circumferentially increasing width region 731 with axial flow distance, downstream of the Pilot 100, having an increasing width with an outward wall curvature along the axial direction. This may beneficially accommodate an axially increasing volumetric flow from increasing mass flow and from rising temperature with combustion, thereby reducing fluid acceleration and pressure drop losses.

[0037] Fig. 3A and 3E similarly depict a configuration with a downstream circumferentially decreasing combusting region 733 with a circumferentially axially declining width wall curvature. This may beneficially provide an aerodynamically smoother junction with an equilibrating region extending downstream from planes CZ39 to CZ394. Fig. 3E further depicts an axially intermediate combusting transition region 732. This combusting intermediate transition region 732 may change with axial distance, from an axially increasing width wall curvature like in combusting upstream section 731, to an axially decreasing width wall curvature like combusting downstream section 733.

[0038] Fig. 3E depicts distributions of fuel fluid delivery orifices 81, and distributions of oxidant fluid delivery orifices 82 opening into the combusting region from CZ34 to CZ35. Further distributions of oxidant and / or diluentdelivery orifices 83 may be configured to open downstream in the Blend-Trim region from planes CZ35 to CZ39.

[0039] Per Fig. 3E, a downstream Blend-Trim manifold region may be provided to deliver oxidant fluid (F4 not shown) or diluted oxidant fluid F5 axially between axial planes CZ35 and CZ39, and bounded by circumferential manifold CCW wall 250 and manifold CW wall 734, with an axially upstream bounding wall 249 between the upstream delivery of diluted fuel flow F2 (or fuel fluid flow F1 not shown) and the downstream delivery of Blend-Trim diluted oxidant fluid F5. (See below for discussion of Fig. 3F showing exploratory NH3 combustion.)

[0040] Fig. 3G depicts a corresponding outward (or inward) axial circumferential (Z Theta) “unrolled” plan view of a symmetric combustor fluid feeder region. This extends axially in the flow direction from an upstream Pilot 100, with a CCW axial diluted oxidant fluid manifold region 244 ducting upstream diluted oxidant fluid F4 to upstream oxidant feeders. The fluid feeder region of Fig.3G may include a second CCW axial oxidant manifold 245 ducting diluted oxidant fluid F5 further downstream.

[0041] The Fig. 3G configuration similarly depicts a CW inward upstream first fuel manifold region 242 ducting first fuel fluid F1 comprising a fuel to upstream feeders. This may be divided by Upstream / Downstream Fuel Fluid Manifold Dividing wall 252 from a second intermediate CW outward fuel fluid manifold region 243, such as ducting a Diluted Fuel Fluid flow F2 (or another flow of Fuel Fluid) further downstream.

[0042] Further in Fig. 3G, similarly, an upstream to Downstream Fuel Feeder to Blend-Trim Dividing Wall 253 may divide and separate upstream diluted fuel fluid F2, flowing through the intermediate fuel fluid manifold region 243 between CZ34 and CZ35, from Blend-Trim diluent flow F7 flowing downstream to the Blend-Trim region 850 between planes CZ35 and CZ39. Manifold bounding wall 253 may adjoin the downstream diluted oxidant or diluent fluid feeder extending down to plane CZ39.

[0043] In Fig.3G, the CCW oxidant fluid manifolds and CW fuel fluid manifolds may be separated by a sigmoidally curved longitudinal radial manifold divider 250 that colds the downstream transverse Trim feeder ending axially at plane CZ39. Downstream Combusting-oxidant fluid manifold divider 248 may besimilarly curved and configured parallel to the manifold divider 250 and aerodynamically curved as it connects with the upstream of the transverse Blend-Trim feeder opening at CZ35.

[0044] An axial-radial manifold divider 253 bounding between diluted fuel fluid flow F2 and diluent fluid flow F7 may be curved or sigmoidal from upstream CZ34 to downstream at CZ35 where it adjoins oxidant feeder delivering oxidant fluid X7 (or optionally diluted oxidant fluid).

[0045] In Fig. 3G, and axial radial mid Upstream Combusting oXidant Manifold Dividing wall 247 may divide Diluted Rich oXidant Upstream Fluid Manifold 244 from second Diluted Rich oXidant Downstream Fluid Manifold 245. Similarly downstream axial radial oXidant-Blend-Trim manifold wall 248 may divide midstream second oxidant fluid manifold 245 from diluted oxidant Blend-Trim manifold 246. With radially extending adjacent walls with multiple circumferentially adjoining oxidant fluid and fuel fluid manifolds and an upstream Pilot 100.

[0046] In Fig. 3G, a first fuel fluid F1 (optionally diluted) may be delivered into fuel fluid manifold 242 bounded by Fuel Feeder Upstream / Downstream Manifold Dividing Wall 252, and be delivered as multiple fuel fluids, such as U1, U2, and U3, flowing through respective multiple transverse fluid fuel fluid feeders. These fuel fluid feeders may have an axially increasing number of fuel fluid orifices 81A per transverse fuel fluid feeder over that range.

[0047] Similarly, a second diluted fuel fluid F2 (or a second fuel fluid flow not shown) may be delivered into downstream fuel fluid manifold 243 and be delivered as multiple fuel fluid flows U4, U5, U6 and U7 flowing into multiple transverse fluid fuel fluid feeders and thence into the adjacent combusting region via fuel fluid orifices 81A. These fuel fluid feeders may have an axially increasing number of fuel fluid orifices 81A per transverse fuel fluid feeder over that axial range.

[0048] Per Fig. 3G, oxidant fluid F4 may be delivered via Diluted Oxidant Fluid Upstream Manifold 244 as oxidant fluid flows X1, X2, and X3 through multiple transverse oxidant fluid feeders and thence through oxidant fluid orifices 82A. Such oxidant fluid F4 delivery may interleave with delivery of first fuel fluid F1, such as through U1 to U3, through respective upstream transverse fuel fluid feeders.

[0049] Similarly, oxidant fluid F5 may be delivered via Diluted oXidant Fluid Downstream Manifold 245 as oxidant fluid flows such as X4, X5, X6, and X7 (or optionally diluted oxidant fluid) through multiple respective transverse oxidant fluid feeders, and thence into the adjacent combusting region via multiple oxidant fluid orifices 82B.

[0050] Such oxidant fluid delivery through oxidant feeders may interleave fuel fluid delivery flows, such as U4 to U7, through respective transverse fuel fluid feeders in the upstream combusting region from CZ34 to CZ35

[0051] Per Fig. 3G, diluted oxidant fluid F6 may be delivered via CCW Diluted Oxidant Blend-Trim Manifold 246 to downstream Blend-Trim feeders. E.g., as one or more Blend fluids such as B1 and B2, through transverse Blend feeders and through Upstream Blend-Trim orifices 83A, and Midstream Blend-Trim Orifices 83B into the radially adjacent Blend-Trim region downstream of the combusting region.

[0052] Similarly, a portion of diluted oxidant fluid F6 may be delivered as one or more Trim fluid flows, such as T1, through a transverse trim feeder and thence through Downstream Blend-Trim orifices 83C into the radially adjacent Blend- Trim region between planes CZ35 and CZ39, axially downstream of the combusting region.

[0053] Per Fig. 3G, correspondingly, Blend-Trim diluent fluid F7 may be delivered via CW Diluent-Trim manifold 238 downstream into Diluent-Trim region 850 between CZ35 and CZ39. Blend-Trim diluent fluid F7 may be delivered as one or more diluent fluids D1, D2, and D3 through transverse diluent feeders and thence through diluent fluid orifices 86A, 86B, and 86C, into the radially adjacent downstream Blend-Trim region of the combustor.

[0054] Per Fig.3G, Per Fig. 3G, walls 253 and 250 of CW diluent trim manifold 238 to the Blend-Trim feeder region may be outwardly curved in an axially upstream section 731. They may similarly be inwardly curved in axially downstream section 733.

[0055] The intermediate combusting region 732 may be sigmoidally curved section to aerodynamically connect upstream section 731 and downstream section 733. (In other configurations intermediate combusting region 732 may be linearly configured.) Downstream section 850 of bounding wall 250 maytransition from inwardly curved section 733 to connect aerodynamically with the downstream equilibrating region axial slope. Asymmetric Combusting Systems

[0056] Per Fig. 3H, and Fig. 3I, some combustor configurations may use an asymmetric combustor about a longitudinal oxidant manifold feeding transverse circumferential oxidant fluid feeders on the CCW and CW sides of the oxidant manifold. Such asymmetrical combusting configurations may similarly use a common longitudinal fuel manifold to feed corresponding multiple adjacent fuel feeders in adjacent combustors. Asymmetric Combusting Regions

[0057] Fig. 3H depicts a circumferentially (Z Theta) “unrolled” plan view of two adjacent asymmetric combusting regions with an axial fluid flow axis Z, and circumferential axis Theta perpendicular to a radial axis R. This may have combustor walls radially adjacent to the combusting region, with fuel fluid orifices 81, oxidant fluid orifices 82, and / or Blend-Trim region diluent fluid delivery orifices such as 83.

[0058] Per Fig. 3H, such asymmetric combusting region configurations may have circumferentially adjacent oxidant fluid manifold bounding Combustion Chamber Transverse CCW side End Wall 734 directing oxidant fluid F5 between upstream combusting region inlet CZ34 and combusting fluid downstream end CZ35. They may similarly have circumferentially adjacent bounding fuel fluid Combustion Chaber Transverse CW side End Wall 735 delivering fuel fluid F2 between CZ34 and combusting region Downstream Manifold End Dividing Wall 249.

[0059] Further per Fig. 3H, diluted oxidant fluid F7 may be delivered into the downstream Blend-Trim manifold region 850 bounded by side bounding manifold walls 735 and axially bounding Downstream Manifold End Dividing Wall 249, extending axially from planes CZ35 to CZ39. Some asymmetric combusting region configurations may include a common upstream Pilot 100 feeding adjacent combusting shells. This Pilot 100 may be fed by Pilot Fuel Fluid F3, Pilot Oxidant Fluid F6, and Pilot Diluent Fluid F8.

[0060] The asymmetric combustor configuration of Fig. 3H may have a sigmoidally curved oxidant fluid boundary such as described in Fig. 3H and adapted to such an asymmetric configuration. This may have a circumferentially(Theta) outwardly curving upstream manifold-combusting region bounding wall section 731 with axially increasing distance Z.

[0061] Per Fig. 3H, the asymmetric combustor may have a correspondingly circumferentially (Theta) inwardly curving downstream manifold with bounding Combustion Chamber Downstream Transverse End Wall section 733 with axially increasing distance Z. The asymmetric combustor configuration of Fig. 3H may have a connecting intermediate Combusting Chamber Midstream Transverse End Wall 732 transitioning from the outward to the inward circumferential-axial curvature.

[0062] The oxidant fluid manifold of Fig. 3H may further have a downstream Blend-Trim region 850 with a Blend-Trim diluent / oxidant fluid manifold wall 734 that may have an aerodynamically varying curvature between the axially upstream adjacent combusting region downstream transverse end wall 733 and the downstream equilibrating region wall beginning at CZ39 and extending into equilibrating region 900 per Fig. 3A.

[0063] The corresponding fuel fluid side bounding manifold walls 735 may have similar curvature with correspondingly more shallow curvature. In other configurations, side bounding fuel fluid manifold walls 735 may be straight. Asymmetric Manifolds and Transverse Fluid Delivery Regions

[0064] Fig. 3I depicts an example of a circumferentially “unrolled” circumferentially-axially (Z Theta) asymmetric combustor fluid feeder configuration. This shows the combusting walls from the radially outward exterior, with fluid axial (longitudinal) manifold walls, upstream transverse fuel feeders and oxidant fluid feeders, fuel, oxidant, and diluent fluid delivery orifices, an axially upstream Pilot 100 delivering pilot fluid into an upstream combusting region at CZ34, and a downstream outlet into the combustor equilibrating region at CZ39.

[0065] Such circumferentially axially asymmetric configurations may utilize fewer fuel fluid manifolds and oxidant fluid manifolds than used with symmetric combusting system scalable shell combustors described in Fig. 3B to Fig. 3E and Fig. 3G.

[0066] The configuration shown in Fig. 3I, may include pilot fuel fluid F3, pilot oxidant fluid F6, and pilot diluent fluid F8 feeding upstream Pilot 100. On the clockwise side, a portion of first fuel fluid flow F1 may be delivered into anupstream transverse fuel fluid feeder as fuel fluid U1 and thence into the combusting region through one or more fuel fluid orifices 81A.

[0067] Similarly, further portions of first fuel fluid F1 may be delivered into progressively downstream transverse fuel fluid feeders as to feed fuel fluids U2 and U3. These may be delivered from the transverse fuel fluid feeders through similar or increasing number of fuel fluid orifices 81A into the radially adjacent combusting region.

[0068] Fig. 3I, similarly depicts an oxidant fluid manifold axially feeding oxidant fluid F4 flows X1, X2 and X3 progressively axially into respective transverse oxidant fluid feeders and thence into oxidant fluid orifices 82A into the radially adjacent combusting chamber.

[0069] The size, (or area) and number of the respective fuel fluid orifices 81 and oxidant fluid orifices 82 may be configured to provide a desired range of relative fuel to oxidant composition relative to stoichiometric composition (PHI) (Or equivalently, the relative oxidant to fuel ratio LAMBDA).

[0070] Per Fig.3I, first fuel fluid F1 and / or oxidant fluid F4 may comprise gaseous and / or liquid diluent, such as steam, water vapor, and / or liquid water as delivered through transverse feeders and orifices into the combusting chamber.

[0071] Per Fig. 3I, diluted fuel fluid F2 may be axially delivered through a fuel fluid manifold and thence into one or more transverse fuel fluid feeders as fuel fluid flows U4, U5, U6 and / or U7. These may be delivered from the fuel fluid feeders through a plurality of fuel fluid orifices 81B into the radially adjacent combusting chamber in the downstream portion of the combusting region from combusting mid-732 midstream wall region through combusting downstream wall 733 region.

[0072] Further per Fig. 3I, oxidant fluid flow F5 may be delivered through the outer axial oxidant fluid manifold and then as one or more oxidant fluid feeder flows, such as X4, X5, X6, into respective transverse oxidant fluid feeders and thence through oxidant fluid orifices 82B into the radially adjacent combusting region. E.g., in the downstream combusting region from mid-region 732 through combusting downstream region 733.

[0073] Per Fig. 3I, diluent fluid F14, such as liquid water, may be delivered to downstream Blend-Trim region through one or more transverse feeders such as diluent fluid flows D1 and D2, and thence through orifices 86A into radiallyadjacent Blend-Trim region 850 in the combustor axially between planes CZ35 and CZ39.

[0074] Correspondingly per Fig. 3I, further oxidant fluid optionally with diluent fluid may be delivered through transverse Blend-Trim feeders as Blend-Trim fluids B1 and / or T1 and thence through Blend-Trim orifices 83A and 83C into the downstream Blend-Trim region 850 of the combusting chamber axially between planes CZ35 and CZ39. Cooling Upstream Combustion

[0075] The embodiments depicted herein enable further flexibility in configuring diluent delivery separately from oxidant and fluid delivery. This may be beneficially used to reduce combusting temperatures independently of relative fuel to oxidant composition (Phi) (or relative oxidant to fuel composition Lambda). This may reduce combusting temperature with higher oxidant compositions, and thus reduce harmful emissions such as NOx emissions.

[0076] Thus, in some further configurations, some to all of the gaseous and / or liquid diluent fluid D1 and D2 may be delivered with one or more fuel fluid flows U5 to U7. Similarly, some to all of such gaseous and / or liquid diluent fluid D1 and D2 may be delivered with oxidant fluids X4, X5, and / or X6.

[0077] Such increases in diluent fluid with the combusting fuel and oxidant fluid flows may be used to reduce the combusting temperatures and thence reduce emission formation such as NOx. In some configurations, this may be delivered with rich to stoichiometric portion of oxidant delivery to form associated rich to stoichiometric combusting regions.

[0078] In some configurations, one or more of axially upstream to downstream manifold walls may be fairly aligned axially between the upstream combusting region at CZ34, and the downstream connection with related transverse fluid delivery feeders. Such alignment may beneficially reduce the rate of change in axial fluid flow cross sectional area (expansion) and delivery flow rate, and thereby reduce related fluid pressure drops.

[0079] Fig. 3J depicts a schematic circumferentially (Z Theta) “unrolled” combusting section of a radially inward (or outward) wall configuration, depicting larger and more numerous upstream oxidant fluid delivery orifices 82 and downstream smaller and fewer fuel fluid delivery orifices 81. E.g., in a 2:1ratio. Oxidant fluid orifices may be circumferentially offset from fuel fluid orifices to improve mixing and reduce quenching.

[0080] Fig. 3K depicts a schematic circumferentially (Z Theta) “unrolled” combusting section radially inward (or outward) wall configuration with fewer upstream fuel fluid delivery orifices 81, and more numerous downstream oxidant fluid delivery orifices 82. E.g., in a 1:2 ratio. Fuel fluid orifices may be circumferentially offset from oxidant fluid orifices to improve mixing and reduce quenching probabilities.

[0081] Fig. 3L depicts a schematic circumferentially (Z Theta) “unrolled” configuration a downstream Blend-Trim region section having oxidant fluid orifices 83A and 83C in a radially outward (or inward) Blend-Trim region wall. Upstream Blend-Trim orifices 83A may be offset ClockWise (CW) from downstream Blend-Trim region orifices 83C.

[0082] Fig. 3M depicts a sample schematic configuration of a downstream Blend- Trim region section having oxidant fluid delivery orifices 83A and 83C in a radially inward (or outward) Blend-Trim region wall. Here upstream Blend- Trim orifices 83A may be offset CounterClockWise (CCW) from ClockWise (CW) downstream Blend-Trim orifices 83C.

[0083] Corresponding to Fig. 3L and Fig. 3M, Blend-Trim orifices 83A and 83C configured radially outward of a combusting region may be offset ClockWise (CW) and CounterClockWise (CCW) from Blend-Trim orifices 83A and 83C configured radially inward of the combusting shell. Similar methods may be used to improve mixing with fuel fluid orifices and / or oxidant fluid orifices in the combusting upstream (731), midstream (732), and downstream (733) wall regions of the combusting chamber.

[0084] Fig. 3N depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region upstream to downstream cut through a CounterClockWise (CCW) circumferentially outward combusting region wall 734.

[0085] This sample configuration Fig. 3N shows eight radially outward oxidant fluid delivery openings X1 through X8 for radially outward oxidant fluid feeders (or diluted oxidant fluid feeders). These may be complemented by and interspersed with eight radially inward oxidant fluid (or diluted oxidant fluid)passage openings X1 through X8, in radially inward transverse oxidant fluid feeders.

[0086] Fig. 3O depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region upstream to downstream cut inward of the CCW circumferentially outward end wall (734) having eight radially outward oxidant fluid delivery openings (X1 through X8) (or diluted oxidant fluid delivery openings) in outward transverse oxidant feeders.

[0087] Fig.3O further shows these outwardly oxidant fluid openings (X1-X8) may be complemented with eight interspersed radially inward oxidant fluid delivery openings (X1 through X8) (or diluted oxidant fluid delivery openings) in inward transverse oxidant feeders. These oxidant fluid passages (X1-X8 and X1-X8) may be interspersed with narrower fuel fluid delivery passages (unmarked).

[0088] Fig. 3Q depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region through a Clockwise (CW) circumferentially outward side bounding combusting region end wall 735 having eight radially outward fuel fluid delivery openings U1 through U8. These may be complemented by and interspersed with eight radially inward fuel fluid passage openings U1 through U8.

[0089] Fig. 3P depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region inward of the CW circumferentially outward end wall (735) having eight oxidant fluid feeder delivery passage openings (U1 through U8) interspersed with eight oxidant fluid feeder delivery passage openings (e.g., X1-X8 not labeled).

[0090] Figures 3N through 3Q further depict combustor radial height (or length) parameters labeled from the first outward combusting shell towards the next inward combusting shell. E.g., CR12 labels the radially outward oxidant fluid feeder wall outer radius. CR15 labels the radially outward combusting region wall radially inner radius. CR16 labels the radially inward combusting region wall outer radius. CR24 labels the radially inward oxidant fluid feeder wall radially inner radius.

[0091] Figures 3N through 3Q further depict combustor radial inner height parameters labeled from the first outward combusting shell towards the next inward combusting shell along the radial R axis. E.g., CR12T labels the radially inner depth (height or Thickness) of the outer oxidant fluid transverse feedersshown in Fig. 3N and Fig. 3O. CR12T similarly labels the radially inner height of the outer fuel fluid transverse feeders shown in Fig. 3P and Fig. 3Q.

[0092] The radial parameter CR15T labels the combusting region radially inner height (Thickness) between CR15 and CR16 shown in Fig. 3O and Fig. 3P. CR18T similarly labels the radial thickness of the radially inner oxidant and fuel transverse feeders between CR16 and CR24 shown in Fig.3N through Fig. 3Q.

[0093] Figures 3N though 3Q further depict the combustor axial boundaries from the upstream combusting region boundary at CZ34 to the downstream combusting fluid delivery boundary at CZ35 (at a reference plane CBQ) along the axial flow Z axis.

[0094] Fig. 3O further depicts typical Axially Inner Inlet Widths 810 of radially outer transverse oXidant fluid feeders X1 to X8 supplying the central combusting region near the outer open side (e.g., CounterClockWise CCW side near the oxidant fluid feeder opening from the adjacent oxidant manifold).

[0095] The axially inner axial widths of radially inner transverse oxidant fluid feeders X1 to X8 supplying oxidant fluid into the central combusting region in Fig. 3O may be similar and may be scaled according to the radial distance outward to the respective feeders from the combustor axis. Fig. 3O further depicts the corresponding Axially Inner Far End Widths 809 of radially outer transverse Fuel Fluid feeders U1 to U8 near the transversely closed end of the fuel fluid feeders near the adjacent oxidant fluid manifold (e.g., the CCW side).

[0096] Fig. 3P further depicts typical Axially Inner Inlet Widths 808 of radially outer transverse Fuel Fluid feeders U1 to U8 supplying the central combusting region near the outer open side (e.g., the Clockwise CW side near the fuel fluid feeder opening from the adjacent fluid manifold).

[0097] The inner axial widths of radially inner transverse fuel fluid feeders U1 to U8 supplying fuel fluid into the central combusting region in Fig. 3P may be similar and may be scaled according to the radial distance outward to the respective feeders from the combustor axis.

[0098] Fig. 3P further depicts the corresponding axially inner widths 811 of outer transverse oxidant fluid feeders (X1-X8 not labeled) near the transversely closed end of the oxidant fluid feeders near the adjacent fuel fluid manifold (e.g., the CW side). Fig. 3P similarly shows the inner transverse oxidant fluidfeeders (X1-X8 not labeled) between CR16 and CR24, with corresponding inner widths (811 not labeled) between fluid feeder walls.

[0099] Fig. 3R schematically depicts an axial circumferential (Z Theta) plan view perspective of a pair of transverse fluid feeders delivering oxidant fluid X into multiple oxidant fluid orifices 82 with typical oxidant fluid orifice diameters DXO, and delivering fluid F into multiple fuel fluid orifices 81 with typical fuel fluid orifice diameters DFO. The fuel fluid feeder is depicted with an axial width DFF compared to the wider Oxidant Fluid Feeder with an axial width DFX. In some configurations, diluent feeders may be utilized with a Diluent Fluid Feeder width DFD (not shown).

[0100] Per Fig. 3R, in some configurations, fuel fluid orifices 81 in the fuel fluid feeder may be circumferentially displaced by a circumferential angle THF from the vertical plane, ClockWise (CW) positive. In some configurations, oxidant fluid orifices 82 may be configured in pairs circumferentially positioned about fuel fluid orifices 81, with a narrower circumferential separation angle THXN between oxidant fluid between nearest centers of oxidant fluid orifices 82 of separated orifice pairs. Oxidant fluid orifices 82 may have a wider adjacent orifice circumferential separation angle THXW between oxidant orifice centers of wider separated orifice pairs.

[0101] In other configurations, oxidant orifices may be spaced further apart, or may be spaced uniformly apart. As schematically depicted in Fig. 3E, 3H, and Fig. 3I, circumferential spacing of orifices about the combustor may be further varied along axially differing fluid feeders. These may use one or both of circumferentially even spacing, and circumferentially asymmetric spacing.

[0102] In some configurations, circumferential spacing may be closer near one and / or both inner and outer combusting chamber boundaries than in circumferentially inner regions. Other configurations may provide more space between orifices near circumferential boundaries.

[0103] Fig. 3S shows another axial circumferential plan view of a fuel feeder feeding fuel fluid F through fuel fluid orifices 81 and an axially adjacent oxidant fluid feeder feeding oxidant fluid X through a multiplicity of oxidant fluid orifices 82. This configuration depicts the oxidant fluid orifices 82 as axially (Z) separated and radially (Theta) aligned.

[0104] Oxidant fluid orifices 82 may similarly be circumferentially aligned with fuel fluid orifices 82 as depicted here. Such configurations may improve jet penetration into the combusting fluid flow. In other configurations, the oxidant orifices may be axially aligned, and collectively circumferentially offset from the fuel fluid orifices 82.

[0105] Fig. 3T depicts a schematic radial circumferential (R Theta) cross section “elevation view” of an outer combusting region wall 736 with an insulating liner 738 bounding the combusting region with an outer radius CR15. Outer fuel fluid orifices 87 may be configured at a positive angle PhiX (or a negative angle - PhiX) from the radial axis R to deliver fuel fluid in the negative CCW direction.

[0106] Fig. 3T further shows an inner combusting region boundary wall at CR16 radially displaced by a radial thickness CR15T from the outer combusting region wall. The radially inner combusting wall may have an outer insulating liner 738 protecting a radially inner structural wall 737. Inner oxidant fluid orifices 88 may be configured at an opposing negative angle -PhiX (or an opposing positive angle PhiX) from the radial axis R to delivery oxidant fluid in the negative CCW direction.

[0107] The configuration of Fig. 3T may similarly be configured with fuel fluid orifices 87 oriented with a negative angle -PhiX, and oxidant fluid orifices 88 oriented in the opposite direction with a positive angle PhiX. Further configurations may comprise both fuel fluid orifices 87 and oxidant fluid orifices 88 configured with the same positive angle PhiX. Similar configurations may comprise fuel fluid orifices 87 and oxidant fluid orifices 88 configured with a similar negative angle -PhiX (or positive angle PhiX).

[0108] In the Fig. 3T configuration, some fuel fluid delivery orifices 87 and oxidant fluid delivery orifices 88 in axially offset fluid feeders may be circumferentially oriented with similar positive angle PhiX (or negative angle - PhiX). In other configurations generically upstream fluid delivery orifices 87 (or 88) and downstream fluid delivery orifices 88 (or 87) may be configured with opposing positive angles PhiX and negative angles -PhiX) oxidant (not shown).

[0109] Further generalizing configurations (such as in Fig. 3T) as shown in Fig. 3G, upstream fuel fluid orifices 81A may be circumferentially offset from (or aligned with) downstream oxidant fluid orifices 82B. Similarly, per Fig. 3G,upstream oxidant fluid orifices 82A may be circumferentially offset to (or aligned with) downstream oxidant fluid orifices 82B.

[0110] Fig. 3U depicts a radial circumferential (R Theta) “elevation” view of a sample configuration of outer transverse Fuel feeders marked F, and alternating outer oXidant transverse feeders marked X. These fuel and oxidant feeders may have a radially outer wall 802 bounded by an outer radius CR11. These feeders may have a radially inner wall 801 bounded by a feeder inner radius CR15, forming a radially outer surface of the inner first combusting region. The outer feeder inner wall 801 may comprise a radially outward (structural) side wall 736 covered on the inner combusting region side by a protective thermal insulating coating 738.

[0111] Fig. 3U further depicts fuel feeders F comprising fuel fluid orifices 87 to deliver fuel fluid into the adjacent inner combusting region. Similarly, oxidant feeders X may comprise orifices 88 delivering oxidant fluid into the adjacent combusting region radially inwards of the feeder inner 801 wall at CR15. As shown, oxidant feeders X may be circumferentially wider in the transverse (Theta) direction than fuel feeders F to accommodate the larger volumetric oxidant fluid flows versus smaller fuel fluid flows.

[0112] Per Fig. 3U in some configurations, outer fuel fluid orifices 87 and oxidant fluid orifices 88 may both be angled circumferentially with a negative angle (- PhiX) from the radial axis R. Other configurations may use fuel fluid orifices 87 and oxidant fluid orifices 88 with the opposite circumferential positive angle (PhiX) from the radial axis R.

[0113] Further configurations may alternate angles of fuel fluid orifices and oxidant fluid orifices positive (PhiX) and negative (-PhiX) angles between radially inward and outward orifices. (Such configurations may have orifices aligned with the combustor axial Z axis, similar to that shown in Fig. 3S.)

[0114] Further to Fig. 3U, shows a radially inward (“lower”) feeder array portion from the outer feeder wall radius CR16 (or radially inner combusting region boundary) with outer insulating layer 738 protecting combusting chamber radially inner wall 737, to radially inner feeder wall radius CR20. This depicts a cross section elevation view with Pairs of similar oxidant (X) fluid feeders of circumferential Passage Width PWX and Fuel (F) fluid feeders of circumferential Passage Width PWF. Joint fluid width widths of fluid feederpairs shown in Fig. 3U may include a first oxidant-fuel fluid pair width (FP1) and a second oxidant-fuel fluid pair width (FP2).

[0115] In the radially inward (“lower”) portion of Fig. 3U, inner oxidant (X) fluid feeders may be configured opposite outer fuel (F) fluid feeders, and inner fuel (F) fluid feeders may be configured opposite to outer oxidant (X) fluid feeders. In this configuration common circumferentially transverse (outer) walls 133 may be used for opposite outer CounterClockWise (CCW) (“transverse”) and ClockWise (CW) boundaries.

[0116] In Fig. 3U, fuel (F) fluid orifices 87 may be configured circumferentially about the middle of fuel fluid feeder (F) with a circumferential offset of about PWF / 2 from the fuel -oxidant feeder dividing wall 133. In the radially outer (“upper”) oxidant feeders X, the oxidant orifices 88 may be configured about midway (transversely) across the oxidant feeder displaced by a distance of about PWX / 2 from the fuel-oxidant feeder dividing wall 133 (such as circumferentially aligned oxidant fluid orifices 82 as shown in Fig. 3S).

[0117] Alternatively, Fig. 3U depicts a configuration where the radially inward (“lower”) oxidant feeders (X) may have two oxidant orifices 88 transversely configured within the oxidant feeder (X). For example, these two orifices 88 may be positioned transversely at about a distance PWX / 3 of about one third the passage Width of oXidant feeder from the oxidant feeder walls (similar to configurations of oxidant fluid orifices 82 of diameter DXO as shown in Fig. 3R.)

[0118] In some configurations, orifices may be aerodynamically configured to reduce combustor pressure drop and to improve efficiency. Orifice inlet and outlet corners may be rounded to improve flows F and reduce pressure drops and efficiency losses, such as that shown in Fig. 3V.

[0119] Fig. 3V depicts a detailed view of a fluid orifice in the Radial Circumferential (R Theta) plane with fluid flow F through an outer combustor wall. E.g. fluid F may flow in through an oxidant fluid orifice of diameter DXO through a feeder structural wall of thickness CR13T protected by a feeder wall insulating coating of thickness CR14T. The fluid inlet and outlet may have rounded corners.

[0120] In some configurations, the upper orifice inlet may have a smaller radius ROI while the lower orifice outlet may have a larger orifice outlet ROO.Similarly, the outlet radius ROO may be about twice as large or larger than the inlet radius ROI. Such configurations may be formed curing additive manufacturing (or “3D printing”.)

[0121] Fig. 3W depicts a detailed view of an angled orifice in the Radial Circumferential (R Theta) plane through the outer combustor wall of thickness CR13T with an insulation layer of thickness CR14T. The angled oxidant fluid orifice may be configured with a flow axis at an angle THM relative to the Radial axis R with a diameter DXO perpendicular to the orifice flow axis.

[0122] Inlet corners of such angled orifices may be configured about an acute angle with a smaller radius ROIA and about an obtuse angle with a larger radius ROIB. Corresponding outlets of such angled orifices may have smaller radius ROOA for an acute angled outlet radius and a larger radius ROOB for an obtuse angled outlet radius.

[0123] Fig. 3X depicts a closed end of an oxidant feeder in the axial circumferential plane (Z Theta) for some configurations, with a manifold fuel fluid flow FFM flowing axially past the closed end, and a fuel feeder flow portion FFF flowing around the closed end. The oxidant fluid manifold may have an outer oxidant feeder axial width PXWO, and an inner oxidant feeder axial width PXWI with feeder wall thickness FWT.

[0124] The oxidant feeder axially upstream radius RXU may be configured smaller than the downstream oxidant radius RXD. E.g., the downstream radius RXD may be twice that of the upstream radius RXU or more.

[0125] Fig.3Y depicts a closed end of a fuel fluid feeder in the axial circumferential plane (Z Theta) for some configurations, with a manifold oxidant fluid flow FXM flowing axially past the closed end, and an oxidant feeder flow portion FXF flowing around the closed end.

[0126] Per Fig.3Y, such fuel fluid feeders may have an outer fuel feeder axial width PFWO, and an inner fuel feeder axial width PFWI, with feeder wall thickness FWT. The oxidant feeder axially upstream radius RFU may be configured smaller than the downstream oxidant radius RFD. E.g., the downstream radius RFD may be twice that of the upstream radius RFU or more. Numerous Orifices to Improve Mixing

[0127] In some configurations, fuel, oxidant, and / or diluent orifices may be used. Orifice size may be correspondingly reduced, such as to maintain overallcumulative orifice area within a desired range of the downstream combusting system cross sectional area.

[0128] More numerous orifices may be used to beneficially improve mixing, increase combustion, further diluent mixing, assist in temperature control, reduce hot spots, improve uniformity, and / or facilitate equilibration.

[0129] For example, in some configurations, each combusting shell may use 50 to 100 oxidant orifices. In other configurations this may be increased to 101 to 200 oxidant orifices. Similarly, 201 to 400 oxidant orifices may be used. Further combustors may use 401 to 800 orifices or more, such as for difficult fuels like ammonia.

[0130] Such changes may beneficially be used to facilitate combustion of fuels with higher ignition energy, higher combusting temperature, slower flame speed, and / or slower combusting rates. E.g., in combusting one or more of ammonia, methane, methanol, ethanol, cracked ammonia (combinations of H2, N2, and NH3), and / or hydrogen. Modeling Combustion and Emissions

[0131] The applicant won two US Department of Energy High Performance For Computing Manufacturing supercomputer grants. Simplified scalable combustors (such as using an asymmetric combusting region and a cylindrical equilibrating region), were modeled using more than 110 independent parameters.

[0132] Of these, 23 parameters were selected to model combustion over typical gas turbine pressures, temperatures, and specific power rates. Argonne National Laboratory (herein ANL) conducted reactive computational fluid dynamic modeling (herein “RCFD”) to evaluate low, medium, and high values (0%, 50%, 100%) for each of these selected parameter ranges.

[0133] Applicant ranked those parameters by parameter importance to Unburned Hydrocarbons (UHC) (or equivalent fuel), Nitrogen Oxides (Nox), and Carbon Monoxide (CO) emissions. Then ANL conducted 312 RCFD runs using combinations of 5 values across low to high (0%, 25%, 50%, 75%, 100%), for the most significant 9 parameters.

[0134] Lawrence Livermore National Labs (herein “LLNL”) then used neural network methods to analyze the data and to create a software program to predictUHC, CO and NOx emissions, which can be run on a professional laptop computer.

[0135] Those methods and resulting software enabled the applicant to configure its scalable gas turbine combustor configurations so as to probably achieve less than 1 ppmvd each for UHC, Nox and CO emissions over commercial gas turbine operating conditions. This predicts emissions below the strictest California county emission requirements of 2.3 ppmvd Nox and CO without using catalysts.

[0136] Such very low emissions provide major advantages with typically 7% to 10% lower CapEx for commercial gas turbines operating on natural gas. It further promises substantially lower operating costs by eliminating ammonia delivery and associated “slip” emissions.

[0137] The techniques, configurations and methods as described herein further detail, extend, and / or adapt that initial modeling RCFD modeling on methane. They likely enable extending and / or improving the methods to further using the range of conventional to sustainable fuels. E.g., to include methane, natural gas, methanol, ethanol, ammonia, cracked ammonia (herein combinations of “H2 N2, and NH3”), and hydrogen. Diluent to the Blend Region

[0138] NOx formation is likely to increase as the product of (Fuel * O2) and exponentially with combusting temperature. Rich combustion cooled by steam and / or diluent in the upstream Blend region uniquely enables transitioning from rich hot upstream combustion to near stoichiometric combustion. This will likely be critically important to avoiding NOx formation. Ammonia Combustion

[0139] Fig. 3F depicts an example of modeling combusting ammonia (NH3) fuel with air, and diluent water and steam, along a flow axis from the upstream combusting inlet CZ34 to the downstream combustor outlet at CZ4. This exploratory reactive RCFD modeling of diluted NH3 air combustion was conducted in applicant’s prior simplified scalable combustor. The left axis shows the mean cross-sectional temperature, and the right axis the outlet NOx and NH3 emissions in PPMVD (parts per million diluted to 15% O2).

[0140] In this sample run, the mean upstream combusting hot gas temperature peaks near 1,830K (~1,557ºC) about the end of the Blend-Trim region T1. ForRCFD modeling, an assumed combustor wall cooling rate is prescribed, reducing the combustor outlet temperature at CZ4 to a prescribed 1,527K (1,300ºC) typical of a mid-range gas Turbine Inlet Temperature (TIT).

[0141] Per Fig. 3F, in this run, NH3 peaked at ~13,000 ppmvd (~40,000 ppm) in the rich combusting region. It then declined to ~78 ppmvd (~227 ppm) at the combustor outlet. Combustion NOx formation peaked at ~275 ppmvd (~800 ppm) downstream of the ammonia peak and upstream of the temperature peak. With excess NH3, and high H2O, the NOx declined to sub ~10 ppmvd (~29 ppm unadjusted) at the combustor outlet.

[0142] Such ~10 ppmvd Nox emissions in Fig. 3F from initial exploratory NH3 combustion already achieves NOx emissions 60% or more below the US EPA’s 25 ppmvd national emissions limit for mid-range gas turbines. These results appear remarkably lower than reported industrial and scientific combustion modeling reports found for this most difficult renewable or sustainable proposed fuel.

[0143] Applicant has identified means of further improving mixing and combustion by aerodynamic methods, improved orifice distributions and delivery staging, such as described herein. These promise to further improve combustion and lower both NH3 and Nox emissions.

[0144] With 24% higher efficiency for a single expander VAST cycle with exhaust heat recycling, this appears to offer a further 19% lower NOx emissions per electricity generated (ppmvd / MWh) relative to a conventional simple cycle (Brayton) peaker gas turbine. Cooling Combustion

[0145] In some configurations, remaining undelivered diluent may be moved from the downstream Trim region feeders T1 to be delivered up into the Blend region feeders (e.g., B1 and B2). A major portion of this remaining diluent may be delivered to the upstream Blend feeder B1 to provide cooler rich (sub stoichiometric) combustion, with temperature being controlled independently of the relative local fuel to oxidant ratio Phi (or the relative local oxidant to fuel ratio Lambda).

[0146] In further configurations, part of this diluent may further be delivered further upstream into the downstream end of the combusting region, such as to delivering with fuel U7 and / or oxidant fluid X7 (or optionally diluted oxidantfluid) in the axially downstream (or last) combusting region axial 733. Such diluent may further be delivered into the last two to last seven combusting regions upstream of CZ35.

[0147] Excess oxidant (or air) T1 may similarly be delivered in through the downstream Trim region. Such a combination of upstream diluent and downstream excess oxidant may achieve the coolest Blend region rich combustion with the least oxidant up to stoichiometric combustion. This may well form the lowest NOx emissions for such configurations, with no change in total oxidant or excess air delivered Phi (In Situ Ammonia Cracking

[0148] In further configurations ammonia may be delivered upstream under hot fuel rich (excess fuel, sub-stoichiometric oxygen) conditions (with Phi ( or Lambda < 1). Upstream combusting temperatures may be increased by reducing upstream diluent. Such conditions may increase upstream ammonia cracking to hydrogen and nitrogen. Such in situ rich cracking of ammonia to hydrogen and nitrogen may facilitate downstream rich combustion, thereby reducing overall NOx formation.

[0149] Some configurations may configure the temperature of transverse feeders adjacent to the combusting region, and / or in the upstream combusting region sufficient to thermally crack a portion of ammonia fuel to hydrogen and nitrogen. Catalysts may similarly be used within transverse fluid feeders to crack ammonia. Thermally Igniting Flows

[0150] In some configurations, an energetic fluid may be formed by heating one or more delivered fluids to temperatures such that the temperature and flow rate of the delivered energetic reactant and co-reactant mixture gas is sufficient to ignite the reactive fluid in the primary reaction zone. Manufacturing Methods

[0151] One or more of such scalable parametric combustor configurations depicted may be constructed using additive manufacturing (or “3D printing”) techniques. Such manufacturing techniques may facilitate forming the numerous oxidant fluid, fuel fluid, and diluent fluid transverse feeders with the corresponding orifices delivering fluid from the transverse feeders into the combusting chambers.

[0152] In some configurations, such scalable shell combustors may be formed in two halves with inner insulating coatings over outer structural walls. These may then be assembled and be suitably held, bonded or fastened together. In other configurations, such orifices may be formed by laser ablation, chemical etching, mechanical or fluid jet drilling, or similar material removal techniques. Turbulence generators

[0153] In some embodiments, turbulence generators may be configured along one or both surfaces bounding a combustion region within the scalable combustor. These may comprise undulations of the scalable combustor walls. Similarly, they may comprise protuberances into the gas flow on one or both of the scalable combustor walls. GENERALIZATION

[0154] From the foregoing description, it will be appreciated that a novel approach for distributed contacting, mixing and / or reacting of three or more fluids has been disclosed using one or more processes described herein. While the components, techniques and aspects of the techniques described herein have been described with a certain degree of particularity, it is manifest that many changes may be made in the specific designs, constructions and methodology herein above described without departing from the spirit and scope of this disclosure.

[0155] Where dimensions are given, they are generally for illustrative purposes, and are not prescriptive. Of course, as the skilled artisan will appreciate, other suitable sizes, orientations, configurations and distributions of fluid delivery orifices, fluid passages, and other components may be efficaciously utilized, as needed or desired, giving due consideration to the goals of achieving one or more of the benefits and advantages as taught or suggested herein.

[0156] Where duct, tube or array configurations are provided, similar two- or three-dimensional configurations or combinations of those configurations may be efficaciously utilized, including varying the nominal thicknesses, diameters, cross sectional shapes, spacings, orientations, and other dimensions and parameters for perforated ducts, perforated tubes, manifolds, sub-manifolds, feeders, combusting, blend, trim, equilibrating and transition regions, and tube arrays.

[0157] Where the terms fuel, reactant, diluent, water, steam, carbon dioxide, air, oxygen, and oxidant have been used, the processes are generally applicable to other combinations of those fluids or to other combinations of other reacting, co-reacting, and diluent or non-reacting fluids. Where fluid quantities are referred to, these processes are generally applicable to include quantities delivered at multiple times, and to continuous fluid flows. Where assembly processes are described, various alternative assembly processes may be efficaciously utilized to achieve configurations to achieve the benefits and advantages of one or more of the embodiments as taught or suggested herein.

[0158] Where transverse, axial, radial, circumferential, horizontal, perpendicular, normal, or other directions are referred to, it will be appreciated that any general coordinate system using curvilinear coordinates may be utilized including Cartesian, cylindrical, spherical or other specialized system, such as an annular system. Similarly, when one or more transverse or axial distributions or profiles are referred to, it will be appreciated that the configurations and processes similarly apply to spatial control in one or more curvilinear directions as desired or prescribed. Similarly, the contactor, array, device or duct orientations may be generally rearranged to achieve other beneficial combinations of the features and processes described.

[0159] Where fluid delivery controls refer to controlling the size and flow rate of fluids, ejecting drops, jets or micro-jets, it will be appreciated that the control measures may utilize one or more measures to control the differential ejection pressure distributions across the fluid orifices 80, to vibrate the orifices, and / or to control the electro-magnetic field about the orifices 80 using one or more measures described herein, and / or by using similar means of modulating the orifices’ location, the fluid pressure, and the surrounding electro-magnetic field.

[0160] Fig. 4A schematically shows a Scalable Gas Turbine Power System 1 with a Scalable ComBustion System (herein “CMB”) as used in a VAST Power Cycle. This Scalable Gas Turbine Power System 1 is shown receiving compressed oxidant fluid from an upstream Compressor 407 (herein “CPR”) axially to axially feed a downstream gas turbine expander 440 (herein “EXP”). This generally adapts the gas turbine location numbering methodology of the American Society of Mechanical Engineers (herein “ASME”), along the Combustor axial flow Z direction (herein “CZ”) as follows.

[0161] This VAST Cycle Scalable Gas Turbine Power System 1 depicts a Compressor 407 (CPR) with a Compressor Inlet at CZ2 and a Compressor Outlet at CZ3. Compressed oxidant fluid flow (herein “WX3”) may flow into a Diffuser (herein “DIF”). A portion of compressed oxidant (herein “WX31”) may flow into an upstream ignition system or Pilot 100 (herein “P”) at a Pilot or combustor inlet plane CZ31. Another portion of compressed oxidant fluid (herein “WX34”) may be delivered upstream into a hot ignitor fluid delivery at CZ31 into the combusting section such as at plane CZ32. Diluent fluid may be delivered upstream to CZ32, such as liquid water as a spray WDL32 into upstream inlet oxidant flow WX34.

[0162] A portion of diluent WDL32 may be delivered into an upstream typically fuel rich combusting region 730 from a combusting region inlet at CZ34 up to a Blend-Trim region inlet and combusting region outlet plane CZ35 (marked here as a combustor reference plane CBQ).

[0163] Fig.4A further schematically shows a “Blend-Trim” Region 850 extending from an upstream Blend-Trim inlet plane CZ35 (or combusting region outlet plane) through to a downstream Equilibrating Region inlet plane CZ39 (or Blend-Trim Region outlet plane). Equilibrating Region

[0164] With reference to Fig. 4A and 4B, an Equilibrating Region 900 may be provided downstream of the Blend-Trim region 850. This Equilibrating Region 900 may extend from the Blend-Trim region outlet at plane CZ39 to a Transition Zone Inlet plane CZ394 (or an Equilibrating Region outlet plane) to provide residence time to further complete the reaction or combustion. Transition Region

[0165] Per Fig.4A, a Transition Region or Zone 980 may follow the equilibrating region 900 to accelerate the hot flow to the combustor outlet. This may extend from the end of the equilibration region at plane CZ394 to a combustor outlet at CZ4 and into an expander (herein “EXP”) or Turbine Inlet, with an expander outlet at an outlet plane CZ5. The equilibrating and transition regions may be aerodynamically configured to reduce flow pressure losses.

[0166] The Turbine Inlet mass flow (or Combustor Outlet mass flow), (herein “W4”) flows into the Expander EXP from the Combustor outlet at axial plane CZ4. Cooling diluent liquid mass flow (herein “WDL45”) may be deliveredinto the expander to cool hot components such as blades, stators and / or walls. Expanded fluid mass flow (herein “W5”) may flow from the expander EXP at axial plane CZ5 into a downstream heat exchanger, here depicted as a Once Through Steam Generator (herein “OTSG”). The cooled mass flow (herein “W51”) exits out of the OTSG and into a downstream heat exchanger (herein “HX”) (at an axial mid heat exchanger flow stage CZ51 not shown).

[0167] A cooled heat exchanger outlet mass flow or exhaust flow (herein “W52”) (at an axial flow stage CZ52 downstream of the heat exchanger HX not shown) may be further cooled downstream as desired to further condense diluent vapor and / or to further cool diluent liquid and non-condensable flue gas, such as by using water- or air-cooled heat exchangers (not shown). In some VAST Power Cycle configurations, diluent vapor may be condensed, forming sub- atmospheric pressure, together with a recompressor compressing the cooled expanded excess oxidant and non-condensed combustion products back to atmospheric pressure discharge as detailed in prior patents (not shown).

[0168] Fig. 4A further depicts upstream gas combusting temperatures being controlled by thermal diluent flows such as water and / or steam (or similarly CO2) relative to fuel fluid delivery. Such diluent fluids may be delivered into multiple upstream combusting regions (from CZ34 to CZ35). E.g., shown here into seven Combusting regions (herein “C1” to “C7”) in Fig. 4A and Fig. 4G, six Combusting regions (C1-C6 not labeled) in Fig. 4I, and eight combusting regions (C1-C8 implied, not labeled) in Fig 4N to Fig. 4Q. These may range from two combusting regions to twenty combusting regions, or more.

[0169] Fig. 4A shows further mass flow of oxidant fluid (herein “MX”) and mass flow of diluent fluid (herein “MD”) may be delivered into the Blend-Trim region (from CZ35 to CZ39). E.g., further oxidant such as air, and diluent such as water and / or steam may be delivered into one or more Blend regions (herein shown as a first Blend Region One “B1” and a second Blend Region Two “B2”), and into one or more Trim regions (herein shown as a First Upstream Trim Region “T1” and optionally a Second Downstream Trim Region “T2”).

[0170] The cooled exhaust mass flow (W52) at Heat Exchanger (HX) outlet (axial plane 52 not shown) may be further cooling as needed.

[0171] Fig.4A shows further oxidant and / or diluent may be delivered into a Blend- Trim region. E.g., further oxidant such as air, and / or diluent such as water and / orsteam may be delivered into the one or more Blend regions (e.g., B1 and B2), and similarly into the one or more Trim regions (e.g. Upstream T1 and downstream T2).

[0172] Fig. 4A shows an inlet mass flow of oxidant (or air) (herein “WX2”) with an optional compressor inlet mass flow of liquid diluent (such as liquid water spray mass flow) (herein “WDL2”) into the inlet CZ2 of the compressor 407 (CPR). An optional compressor cooling liquid spray mass flow (herein “WDL25”) may be delivered into the compressor CPR itself between the inlet CZ2 and outlet CZ3 of the compressor 407 (CPR).

[0173] The compressor 407 (CPR) may feed a mass flow of compressed oxidant fluid flow (or air) (with optional vaporized diluent) (herein “WX3”) into the upstream inlet of a VAST scalable combustor CMB at an upstream flow location CZ3. The downstream combustor outlet may feed equilibrated and accelerated hot gas flow W4 at flow location CZ4 into an expander EXP.

[0174] The scalable combustor CMB may include an upstream diffuser, DIF, that expands and slows the oxidant (or air) from the compressor outlet / diffuser inlet CZ3 to feed an upstream combusting section from CZ34 to CZ5 a VAST combustor (CMB) that extends from the upstream diffuser (DIF) inlet at CZ3 (to a combustor pilot inlet plane CZ31) (to the transition zone at CZ394), and to the downstream outlet plane CZ4.

[0175] Fig.4A further depicts an upstream ignition authority or Pilot 100 (P). Pilot P may be fed with a pilot fuel mass flow (herein “WF31”), a pilot oxidant mass flow (herein “WX31”), and optionally pilot diluent (herein “WDL31”) such as pilot liquid water. Further fuel fluid (herein “WF32”), and further diluent fluid (herein “WDS32”) such as steam, may be mixed and delivered as a diluted fuel fluid mass flow (herein “MF”) into a diluted fuel manifold, to feed transverse fuel feeders into combusting regions (such as C1 to C7).

[0176] Further oxidant fluid (herein “WX34”) may be delivered together with various flows of upstream diluent fluid (herein “WDL32”) and / or mixtures may then be progressively fed into the combustor via multiple feeders (C1 through C7), delivering one or more mass flows of fuel fluid (MF), oxidant fluid (MX), and diluent fluid (MD) oriented generally across or transverse to the axial flow.

[0177] Fig. 4A then depicts stoichiometric diluted oxidant and / or diluent mass flows being then fed into a Blend-Trim region 850 thru one or more transverseBlend region feeders (B1 and B2), with the remaining oxidant and / or diluent fluids delivered through one or more Trim region feeders, (upstream T1, and optional downstream T2 Trim regions etc., not shown) between combustor axial planes CZ35 and CZ39.

[0178] Fig. 4A further shows mass flows of liquid diluent (herein “WDL42”) into a heat exchanger HX. Heated liquid from HX flows (herein “WDL41”) into the Once Through Steam Generator (herein “OTSG”), and upstream into the upstream combustor (herein “WDL32”), into the Blend-Trim region (herein “WDL35”), and into the downstream combustor walls in the equilibrating region and transition region, (herein “WDL398”).

[0179] Fig.4A shows a portion of heated liquid diluent WDL41 further recovering heat in the OTSG to form steam (herein “WDS4”). This vaporized diluent may be delivered back into the Blend Trim region as WDS35, and into the upstream region as WDS32 such as into the upstream fuel mass flow MF at CZ32. Premix Region

[0180] Referring to Fig. 4A, an upstream premix region may be provided between the compressor outlet / diffuser inlet CZ3 and the combusting region outlet at CZ35. This may deliver liquid diluent WDL32 into the oxidant mass flow MX feeding one or more combusting regions C1 through C7. This premix region may similarly be located between an upstream combustor inlet plane CZ31 near the inlet 100 pilot P and the combusting region inlet near CZ34.

[0181] The premix region may comprise perforated direct contact tubes 14 connected to a liquid diluent supply flow WDL31 to deliver diluent spray into the upstream oxidant fluid WX34. One or more Valves may be configured to control delivery of one or more flows of fuel and / or diluent into one or more of the diffuser DIF, the pilot P, combusting region 730, and Blend-Trim region 850, etc.

[0182] Valve VDL42 may control the return flow of diluent liquid through the heat exchanger HX. Valve VDL35 may control flow of heated liquid diluent WDL35 into the Blend-Trim region 850.Valve VDL32 may control liquid diluent WDL32 to the combusting region manifold 730. VF32 may control fuel fluid flow WF32 into the combusting system. Valve VF31 may control fuel fluid flow WF31 to the pilot P.Scalable Radial Annular (“Fan”) Combusting Array Configurations

[0183] With reference to a generic schematic three-dimensional perspective view Fig. 4B, some scalable combustor embodiments may comprise a cylindrical combustor 704, with an outer cylindrical outer pressure vessel 172, and an inner cylindrical axial pressure wall 147, with a common axis from an upstream inlet 134 to a downstream outlet 136, parallel to the combustion flow direction.

[0184] Fig.4B further depicts an upstream ignition (pilot) section 720, a fuel rich Combusting section 730, a Blend-Trim region 850 with residual diluent and oxidant delivery, and a downstream Equilibration region 900.

[0185] upstream to downstream axis streamwise flow axis with transversely extended combusting sections 732 relative to shallowly separated opposed combustor walls 736. Such transversely extended walls 736 of extended combusting sections 732 may be bounded with side walls 734. The relative circumferential transverse wall elongation may be greater than 1.15 times the shallow spacing by radial depth of side walls 734. adjacent combustor wall between opposed transverse – axial combusting chamber walls.

[0186] In Fig. 4B, a portion of the Scalable Combustor, CMB is depicted extending from a flame authority 100 or pilot P at axial flow location CZ31 from the outlet of the upstream diffuser through a combusting section 730 and a downstream Blend-Trim region 850 opening into the downstream equilibrating region 900.

[0187] Fig. 4B shows an embodiment of a Cylindrical-Axial (circumferentially- radially stacked) combustor 702 shown in cylindrical coordinates with a Radial axis (“R”) perpendicular to an Axial flow axis (Z) with a circumferential direction Theta ( ). In other configurations, scalable combustors may use acurvilinear flow axis with non-cylindrical walls.

[0188] Such embodiments may include multiple scalable (“fan”) combusting shells (or burners) configured generally about Radial - Circumferential Theta (R - ) cylindrical surfaces. These cylindrical combusting shells may be stacked radially, and generally perpendicularly, to the primary streamwise flow axis of oxidant fluid F5 through the scalable combustor, oriented along the axial (Z) flow direction, from an upstream fluid inlet 134 to a fluid flow outlet 136 for heated pressurized hot combusted fluid F20.

[0189] Per Fig. 4B, for operation in elevated pressures, such scalable circumferential combustor embodiments 702 may be configured within an outer Pressure Vessel Wall 172. A pilot fuel fluid flow F3, and a pilot oxidant fluid flow F6, may be delivered to an upstream Ignition Authority (Flame Igniter or Pilot) 100, configured to combust these fluids and to form a hot pilot fluid flow F22.

[0190] Pilot diluent fluid F8 flow may be separately delivered to the Pilot 100, and / or mixed in with pilot fuel fluid F3, and / or pilot oxidant fluid F6 flowing into the Pilot 100 in an upstream pilot region 720.

[0191] Per Fig. 4B, such upstream hot pilot fluid flow F22 from Pilot 100 may be distributed in upstream pilot region 720 to an upstream end of a pilot fluid distribution system 722 comprising one or more scalable pilot fluid delivery ducts (or “fan” burner ducts) 728. Such pilot fluid delivery ducts (or “fan” burners) 728 may be configured circumferentially around the cylindrically stacked scalable combustor 702.

[0192] Pilot fluid delivery ducts 728 may deliver hot pilot fluid into one or more combusting systems (or mid-fan burners) 732 in an axially intermediate combusting region 730.

[0193] Further to Fig. 4B, each combusting system 732 generally comprises two radially opposing circumferential combusting radially outward side walls 736 (with corresponding radially inward side walls). These combusting radially outward side walls 736 may be bounded and connected by corresponding combusting (mid-fan) (circumferentially) end walls 734. In other configurations, radial side walls 736 may be curved around to radially meet and transversely or circumferentially bound the combusting region.

[0194] Each combusting system radial side wall 736 may comprise numerous fluid delivery orifices 80 such as schematically depicted in Fig.4C. Pressurized oxidant fluid F5 may be delivered into the Cylindrical-Axial combusting system 702 and delivered into combusting system 732 through orifices 80 configured in combusting system radial side walls 736. Ref. to Fig. 4C, in some configurations, the diameter or size of orifices 80 may vary transversely to adjust the fluid delivery rate per orifice.

[0195] Similarly, per Fig. 4B, diluted fuel fluid F2 may be delivered through a similar axial Fuel Manifold 770 between circumferentially adjacent combustingregions on alternating sides of the combusting regions from the oxidant fluid F5 delivery.

[0196] In further configurations, premixed reactive fuel-oxidant mixture with optional diluent may be delivered into the cylindrical-axial combustor 702, and delivered through perforated combustor radial side walls 736 in combusting systems 732 within the combusting region 730.

[0197] Per Fig. 4B, energetic fluid from one or more combusting systems 732 in combusting region 730 may be delivered to circumferential downstream Blend- Trim region 850 comprising Blend-Trim oxidant-diluent delivery and reacting region manifold walls 857 feeding related Blend-Trim reacting regions. Each Blend-Trim reacting region 850 may comprise opposing circumferential Blend- Trim perforated side walls 857 to bound combustion within that region.

[0198] The Blend-Trim region side walls 857 may generally be connected by one or more far-fan end walls 746. The Blend-Trim side walls 857 may also be configured to join at their circumferentially transverse ends. Multiple sets of circumferential combustors 732 and Blend-Trim Regions 850 may be configured within combustor outer wall or pressure vessel 172.

[0199] Fig. 4C depicts an expanded view of a combustor wall section radial side wall 736 showing orifices 80 through a combustor fluid duct wall 132 protected by a thermal insulating barrier 150. Symmetric Combustor

[0200] Fig. 4D depicts a sample radial circumferential (R Theta) cross-section of a portion of a comBusting region extending circumferentially by a Combusting section angle THC. This example shows an oXidant Manifold on the CCW side feeding oxidant fluid F5 with the THBMX CW portion shown as feeding two CW adjacent combusting regions. On the CW side, Fig. 4D depicts a fuel manifold encompassing a THBMF CW portion correspondingly feeding the two radially adjacent combusting regions including a combusting feeder radial depth (Thickness) CR15T.

[0201] Fig.4D further depicts an outer oxidant fluid feeder extending radially with a radial depth (Thickness) CR12T inside of an outer circumferential wall having an inner radius CR12. That outer oxidant fluid feeder extends circumferentially over an included angle THBFX4 and feeds oxidant fluid through multiple orifices into a combusting region extending radially with a radial depth (orThickness) CR15T from outer wall inner radius CR15 to inner wall outer radius CR16.

[0202] Oxidant fluid F5 optionally with diluent (such as water vapor or mist) may flow along the oXidant fluid feeder and through oXidant orifices with a typical diameter DXO into a radially adjacent outer combusting region extending radially with a depth (or Thickness) CR15T between combusting chamber outer radius CR15 and combusting chamber inner radius CR16. These oxidant orifices may be offset from the CCW manifold by a circumferential angle THBXO, and spaced apart by a circumferential angle THBXS, with an Jth orifice in an Ith oxidant feeder positioned at a circumferential angle THBXIJ.

[0203] Fig. 4D further depicts Fuel fluid flow F2 optionally diluted with diluent fluid, flowing through a CW comBusting region manifold extending through circumferential Theta angle THBMF. This CW fuel fluid manifold delivers fuel fluid through a fuel complementary feeder extending radially with a depth (Thickness) CR18T, and feeding fuel fluid through fuel fluid orifices with typical fuel orifice diameter DFO into the outer combusting region between CR15 and CR16 extending radially with a depth (Thickness) CR15T and circumferentially about an angle THBFF4. This fuel feeder with a depth CR18T may similarly feed fluid into an inwards combusting region extending radially between CR25 and CR26, and circumferentially across THBFF4.

[0204] Further to Fig. 4D, diluted (“humid”) oxidant fluid F5 may similarly be delivered radially inward (and longitudinally) through the radial manifold feeder length RBFX4 and width Theta12T between circumferential angles Theta12 and Theta15 into a radial combusting region of circumferential width Theta15T. On the radially inward side, diluent fluid F12 may be delivered into axially extending region RBMF of width Theta18T and thence through orifices of diameter DFO a radial CCW diluent manifold extending circumferentially by Theta18T for each of the central combusting regions extending by Theta 15T and radially by RBFF4, axially along the combusting region.

[0205] Fig. 4E depicts a Radial Axial circumferential (R-Z) plan view of two radially adjacent symmetric combusting regions (CZ34 to CZ35) and Blend- Trim regions (CZ35 to CZ39). The radially lower (visually right or clockwise CW) region depicts radially outward (CCW) bounding end walls 734 and radially inward (CW) bounding end walls 735. Such combusting regions mayextend axially from the upstream Pilot 100 outlet or combusting region inlet CZ34 to combusting region downstream axial boundary CZ35. The downstream Blend Trim region may extend axially (Z) from CZ35 to CZ39.

[0206] Per Fig. 4E, such adjacent symmetric combusting regions may have radially outward adjacent (+R or CCW) oxidant fluid manifold regions, between manifold wall 250 and combusting wall 734 ducting oxidant fluid (or diluted oxidant fluid) F5 from upstream of inlet CZ34 into such adjacent combusting regions. Correspondingly, such symmetric combusting regions may have adjacent radially inward (-R or CW) fuel manifold regions, between manifold wall 250 and combusting wall 735, ducting fuel fluid (or diluted fuel fluid) F2.

[0207] Such outwardly adjacent (R+ CCW) oxidant manifolds and inwardly adjacent (-R CW) fuel manifolds may be commonly bounded and divided by a sigmoidally curved longitudinal (radial-axial R-Z) manifold divider wall 250 between combusting upstream inlet CZ34 and combusting midstream outlet CZ35 bounds, and thence to the Blend-Trim region axially between midstream Blend-Trim inlet planes CZ35 and the downstream Blend-Trim outlet planes CZ39.

[0208] The left (+R, CCW) portion of Fig. 4E further depicts an upstream region circumferentially increasing transverse (radial) width region 731 with axial flow distance, downstream of the Pilot 100, having an increasing radial (R) width with an outward wall curvature along the axial (Z) direction. This axially increasing combustion region volume may beneficially accommodate an axially increasing volumetric flow from increasing delivered oxidant, fuel and diluent mass flows, and from rising temperature with combustion, thereby reducing fluid acceleration and pressure drop losses.

[0209] Fig. 4A and 4E similarly depict a configuration with a downstream combusting region 733 with transversely increasing width (radially +R to -R) (or CCW-CW) but with decreasing radial-axial wall curvature. This may beneficially provide an aerodynamically smoother transition between the Blend-Trim region and an equilibrating region extending downstream from planes CZ39 to CZ394 (as shown in Fig.4A). Fig.4E further depicts an axially intermediate combusting transition region 732. This intermediate combusting transition region 732 transverse width (+R to -R) may increase downstreamwith axial (Z) distance, from an axially increasing width wall curvature from combusting upstream section 731, to an axially decreasing width wall curvature such as in combusting downstream section 733.

[0210] Fig. 4E depicts distributions of fuel fluid delivery orifices 81, and distributions of oxidant fluid delivery orifices 82 opening into the combusting region from CZ34 to CZ35. Further distributions of oxidant and / or diluent delivery orifices 83 may be configured downstream to open into the Blend-Trim region axially between planes CZ35 to CZ39. This Blend-Trim combusting region with delivery orifices 83 may be transversely bounded by radially outward combusting wall 734 and radially inward combusting wall 735.

[0211] Per Fig. 4E, a downstream Blend-Trim manifold region may be provided to deliver diluted oxidant fluid F5 (or oxidant fluid F4 not shown) axially between axial planes CZ35 and CZ39, and bounded by radially outward (+R) transverse manifold (CCW) wall 250 and radially inward (-R) manifold (CW) wall 734. This radially outward (+R) oxidant fluid delivery manifold between transverse manifold wall 250 and inward manifold wall 734 may bounded downstream at CZ39 by manifold wall 250 joining manifold wall 734. Inward manifold wall 734 may be bounded with transverse manifold wall 250 joining with an axially upstream bounding wall 249 between the upstream delivery of diluted fuel flow F2 (or fuel fluid flow F1 not shown) and the downstream delivery bound (between manifold wall 250 and combusting wall 734) for Blend-Trim diluted oxidant fluid F5. (See below for discussion of Fig. 4F showing exploratory NH3 combustion.)

[0212] Fig. 4E further depicts varying transverse positioning versus axial location of oxidant orifices 82, fuel orifices 81, and Blend-Trim diluted oxidant orifices 83

[0213] Fig. 4G depicts a corresponding outward (or inward) axial circumferential (Z Theta) “unrolled” plan view of a symmetric combustor fluid feeder region. This extends axially in the flow direction from an upstream Pilot 100, with a CCW axial diluted oxidant fluid manifold region 244 ducting upstream diluted oxidant fluid F4 to upstream oxidant feeders. The fluid feeder region of Fig.4G may include a second CCW axial oxidant manifold 245 ducting diluted oxidant fluid F5 further downstream.

[0214] The Fig. 4G configuration similarly depicts a CW inward upstream first fuel manifold region 242 ducting first fuel fluid F1 comprising a fuel to upstream feeders. This may be divided by Upstream / Downstream Fuel Fluid Manifold Dividing wall 252 from a second intermediate CW outward fuel fluid manifold region 243, such as ducting a Diluted Fuel Fluid flow F2 (or another flow of Fuel Fluid) further downstream.

[0215] Further in Fig. 4G, similarly, an upstream to Downstream Fuel Feeder to Blend-Trim Dividing Wall 253 may divide and separate upstream diluted fuel fluid F2, flowing through the intermediate fuel fluid manifold region 243 between CZ34 and CZ35, from Blend-Trim diluent flow F7 flowing downstream to the Blend-Trim region 850 between planes CZ35 and CZ39. Manifold bounding wall 253 may adjoin the downstream diluted oxidant or diluent fluid feeder extending down to plane CZ39.

[0216] In Fig.4G, the CCW oxidant fluid manifolds and CW fuel fluid manifolds may be separated by a sigmoidally curved longitudinal radial manifold divider 250 that colds the downstream transverse Trim feeder ending axially at plane CZ39. Downstream Combusting-oxidant fluid manifold divider 248 may be similarly curved and configured parallel to the manifold divider 250 and aerodynamically curved as it connects with the upstream of the transverse Blend-Trim feeder opening at CZ35.

[0217] An axial-radial manifold divider 253 bounding between diluted fuel fluid flow F2 and diluent fluid flow F7 may be curved or sigmoidal from upstream CZ34 to downstream at CZ35 where it adjoins oxidant feeder delivering oxidant fluid X7 (or optionally diluted oxidant fluid).

[0218] In Fig. 4G, and axial radial mid Upstream Combusting oXidant Manifold Dividing wall 247 may divide Diluted Rich oXidant Upstream Fluid Manifold 244 from second Diluted Rich oXidant Downstream Fluid Manifold 245. Similarly downstream axial radial oXidant-Blend-Trim manifold wall 248 may divide midstream second oxidant fluid manifold 245 from diluted oxidant Blend-Trim manifold 246. With radially extending adjacent walls with multiple circumferentially adjoining oxidant fluid and fuel fluid manifolds and an upstream Pilot 100.

[0219] In Fig. 4G, a first fuel fluid F1 (optionally diluted) may be delivered into fuel fluid manifold 242 bounded by Fuel Feeder Upstream / DownstreamManifold Dividing Wall 252, and be delivered as multiple fuel fluids, such as U1, U2, and U3, flowing through respective multiple transverse fluid fuel fluid feeders. These fuel fluid feeders may have an axially increasing number of fuel fluid orifices 81A per transverse fuel fluid feeder over that range.

[0220] Similarly, a second diluted fuel fluid F2 (or a second fuel fluid flow not shown) may be delivered into downstream fuel fluid manifold 243 and be delivered as multiple fuel fluid flows U4, U5, U6 and U7 flowing into multiple transverse fluid fuel fluid feeders and thence into the adjacent combusting region via fuel fluid orifices 81A. These fuel fluid feeders may have an axially increasing number of fuel fluid orifices 81A per transverse fuel fluid feeder over that axial range.

[0221] Per Fig. 4G, oxidant fluid F4 may be delivered via Diluted Oxidant Fluid Upstream Manifold 244 as oxidant fluid flows X1, X2, and X3 through multiple transverse oxidant fluid feeders and thence through oxidant fluid orifices 82A. Such oxidant fluid F4 delivery may interleave with delivery of first fuel fluid F1, such as through U1 to U3, through respective upstream transverse fuel fluid feeders.

[0222] Similarly, oxidant fluid F5 may be delivered via Diluted oXidant Fluid Downstream Manifold 245 as oxidant fluid flows such as X4, X5, X6, and X7 (or optionally diluted oxidant fluid) through multiple respective transverse oxidant fluid feeders, and thence into the adjacent combusting region via multiple oxidant fluid orifices 82B.

[0223] Such oxidant fluid delivery through oxidant feeders may interleave fuel fluid delivery flows, such as U4 to U7, through respective transverse fuel fluid feeders in the upstream combusting region from CZ34 to CZ35

[0224] Per Fig. 4G, diluted oxidant fluid F6 may be delivered via CCW Diluted Oxidant Blend-Trim Manifold 246 to downstream Blend-Trim feeders. E.g., as one or more Blend fluids such as B1 and B2, through transverse Blend feeders and through Upstream Blend-Trim orifices 83A, and Midstream Blend-Trim Orifices 83B into the radially adjacent Blend-Trim region downstream of the combusting region.

[0225] Similarly, a portion of diluted oxidant fluid F6 may be delivered as one or more Trim fluid flows, such as T1, through a transverse trim feeder and thence through Downstream Blend-Trim orifices 83C into the radially adjacent Blend-Trim region between planes CZ35 and CZ39, axially downstream of the combusting region.

[0226] Per Fig. 4G, correspondingly, Blend-Trim diluent fluid F7 may be delivered via CW Diluent-Trim manifold 238 downstream into Diluent-Trim region 850 between CZ35 and CZ39. Blend-Trim diluent fluid F7 may be delivered as one or more diluent fluids D1, D2, and D3 through transverse diluent feeders and thence through diluent fluid orifices 86A, 86B, and 86C, into the radially adjacent downstream Blend-Trim region of the combustor.

[0227] Per Fig. 4G, walls 253 and 250 of CW diluent trim manifold 238 to the Blend-Trim feeder region may be outwardly curved in an axially upstream section 731. They may similarly be inwardly curved in axially downstream section 733.

[0228] The intermediate combusting region 732 may be sigmoidally curved section to aerodynamically connect upstream section 731 and downstream section 733. (In other configurations intermediate combusting region 732 may be linearly configured.) Downstream section 850 of bounding wall 250 may transition from inwardly curved section 733 to connect aerodynamically with the downstream equilibrating region axial slope. Asymmetric Combusting Systems

[0229] Per Fig. 4H, and Fig. 4I, some combustor configurations may use an asymmetric combustor about a longitudinal oxidant manifold feeding transverse circumferential oxidant fluid feeders on the CCW and CW sides of the oxidant manifold. Such asymmetrical combusting configurations may similarly use a common longitudinal fuel manifold to feed corresponding multiple adjacent fuel feeders in adjacent combustors. Asymmetric Combusting Regions

[0230] Fig. 4H depicts a circumferentially (Z Theta) “unrolled” plan view of two adjacent asymmetric combusting regions with an axial fluid flow axis Z, and circumferential axis Theta perpendicular to a radial axis R. This may have combustor walls radially adjacent to the combusting region, with fuel fluid orifices 81, oxidant fluid orifices 82, and / or Blend-Trim region diluent fluid delivery orifices such as 83.

[0231] Per Fig. 4H, such asymmetric combusting region configurations may have circumferentially adjacent oxidant fluid manifold bounding CombustionChamber Transverse CCW side End Wall 734 directing oxidant fluid F5 between upstream combusting region inlet CZ34 and combusting fluid downstream end CZ35. They may similarly have circumferentially adjacent bounding fuel fluid Combustion Chaber Transverse CW side End Wall 735 delivering fuel fluid F2 between CZ34 and combusting region Downstream Manifold End Dividing Wall 249.

[0232] Further per Fig. 4H, diluted oxidant fluid F7 may be delivered into the downstream Blend-Trim manifold region 850 bounded by side bounding manifold walls 735 and axially bounding Downstream Manifold End Dividing Wall 249, extending axially from planes CZ35 to CZ39. Some asymmetric combusting region configurations may include a common upstream Pilot 100 feeding adjacent combusting shells. This Pilot 100 may be fed by Pilot Fuel Fluid F3, Pilot Oxidant Fluid F6, and Pilot Diluent Fluid F8.

[0233] The asymmetric combustor configuration of Fig. 4H may have a sigmoidally curved oxidant fluid boundary such as described in Fig. 4H and adapted to such an asymmetric configuration. This may have a circumferentially (Theta) outwardly curving upstream manifold-combusting region bounding wall section 731 with axially increasing distance Z.

[0234] Per Fig. 4H, the asymmetric combustor may have a correspondingly circumferentially (Theta) inwardly curving downstream manifold with bounding Combustion Chamber Downstream Transverse End Wall section 733 with axially increasing distance Z. The asymmetric combustor configuration of Fig. 4H may have a connecting intermediate Combusting Chamber Midstream Transverse End Wall 732 transitioning from the outward to the inward circumferential-axial curvature.

[0235] The oxidant fluid manifold of Fig. 4H may further have a downstream Blend-Trim region 850 with a Blend-Trim diluent / oxidant fluid manifold wall 734 that may have an aerodynamically varying curvature between the axially upstream adjacent combusting region downstream transverse end wall 733 and the downstream equilibrating region wall beginning at CZ39 and extending into equilibrating region 900 per Fig. 4A.

[0236] The corresponding fuel fluid side bounding manifold walls 735 may have similar curvature with correspondingly more shallow curvature. In other configurations, side bounding fuel fluid manifold walls 735 may be straight.Asymmetric Manifolds and Transverse Fluid Delivery Regions

[0237] Fig. 4I depicts an example of a circumferentially “unrolled” circumferentially-axially (Z Theta) asymmetric combustor fluid feeder configuration. This shows the combusting walls from the radially outward exterior, with fluid axial (longitudinal) manifold walls, upstream transverse fuel feeders and oxidant fluid feeders, fuel, oxidant, and diluent fluid delivery orifices, an axially upstream Pilot 100 delivering pilot fluid into an upstream combusting region at CZ34, and a downstream outlet into the combustor equilibrating region at CZ39.

[0238] Such circumferentially axially asymmetric configurations may utilize fewer fuel fluid manifolds and oxidant fluid manifolds than used with symmetric combusting system scalable shell combustors described in Fig. 4B to Fig. 4E and Fig. 4G.

[0239] The configuration shown in Fig. 4I, may include pilot fuel fluid F3, pilot oxidant fluid F6, and pilot diluent fluid F8 feeding upstream Pilot 100. On the clockwise side, a portion of first fuel fluid flow F1 may be delivered into an upstream transverse fuel fluid feeder as fuel fluid U1 and thence into the combusting region through one or more fuel fluid orifices 81A.

[0240] Similarly, further portions of first fuel fluid F1 may be delivered into progressively downstream transverse fuel fluid feeders as to feed fuel fluids U2 and U3. These may be delivered from the transverse fuel fluid feeders through similar or increasing number of fuel fluid orifices 81A into the radially adjacent combusting region.

[0241] Fig. 4I, similarly depicts an oxidant fluid manifold axially feeding oxidant fluid F4 flows X1, X2 and X3 progressively axially into respective upstream transverse oxidant fluid feeders and thence into oxidant fluid orifices 82A into the radially adjacent combusting chamber.

[0242] Combinations of the size, (or area), number of the respective fuel fluid orifices 81, oxidant fluid orifices 82, and relative fuel fluid and oxidant fluid delivery pressures may be configured to provide a desired range of relative fuel to oxidant composition relative to stoichiometric composition (PHI). (Or equivalently, the relative oxidant to fuel ratio LAMBDA).

[0243] Per Fig.4I, first fuel fluid F1 and / or oxidant fluid F4 may comprise gaseous and / or liquid diluent, such as steam, water vapor, and / or liquid water as delivered through transverse feeders and orifices into the combusting chamber.

[0244] Per Fig. 4I, diluted fuel fluid F2 may be axially delivered through a fuel fluid manifold and thence into one or more transverse fuel fluid feeders as fuel fluid flows U4, U5, U6 and / or U7. These may be delivered from the fuel fluid feeders through a plurality of fuel fluid orifices 81B into the radially adjacent combusting chamber in the downstream portion of the combusting region from combusting mid-732 midstream wall region through combusting downstream wall 733 region.

[0245] Further per Fig. 4I, oxidant fluid flow F5 may be delivered through the outer axial oxidant fluid manifold and then as one or more oxidant fluid feeder flows, such as X4, X5, X6, into respective transverse oxidant fluid feeders and thence through oxidant fluid orifices 82B into the radially adjacent combusting region. E.g., in the downstream combusting region from mid-region 732 through combusting downstream region 733.

[0246] Per Fig. 4I, diluent fluid F14, such as liquid water, may be delivered to downstream Blend-Trim region through one or more transverse feeders such as diluent fluid flows D1 and D2, and thence through orifices 86A into radially adjacent Blend-Trim region 850 in the combustor axially between planes CZ35 and CZ39.

[0247] Correspondingly per Fig. 4I, further oxidant fluid optionally with diluent fluid may be delivered through transverse Blend-Trim feeders as Blend-Trim fluids B1 and / or T1 and thence through Blend-Trim orifices 83A and 83C into the downstream Blend-Trim region 850 of the combusting chamber axially between planes CZ35 and CZ39. Cooling Upstream Combustion

[0248] The embodiments depicted herein enable further flexibility in configuring diluent delivery separately from oxidant and fluid delivery. This may be beneficially used to reduce and control combusting temperatures independently of relative fuel to oxidant composition (Phi) (or relative oxidant to fuel composition Lambda). This may beneficially reduce combusting temperatures while enabling higher oxidant compositions, particularly in upstream rich combustion conditions in the combusting region from CZ34 to CZ35. Suchmethods may beneficially reduce undesired emissions, particularly of NOx emissions.

[0249] Thus, in some further configurations, some to all of the gaseous and / or liquid diluent fluid D1 and D2 may be delivered with one or more fuel fluid flows U5 to U7. Similarly, some to all of such gaseous and / or liquid diluent fluid D1 and D2 may be delivered with oxidant fluids X4, X5, and / or X6.

[0250] Such increases in diluent fluid with the combusting fuel and oxidant fluid flows may be used to reduce the combusting temperatures and thence reduce emission formation such as NOx. In some configurations, this may be delivered with rich to stoichiometric portion of oxidant delivery to form associated rich to stoichiometric combusting regions.

[0251] In some configurations, one or more of axially upstream to downstream manifold walls may be fairly aligned axially between the upstream combusting region at CZ34, and the downstream connection with related transverse fluid delivery feeders. Such alignment may beneficially reduce the rate of change in axial fluid flow cross-sectional area (expansion) and delivery flow rate, and thereby reduce related fluid pressure drops.

[0252] Fig. 4J depicts a schematic circumferentially (Z Theta) “unrolled” combusting section of a radially inward (or outward) wall configuration, depicting larger and more numerous upstream oxidant fluid delivery orifices 82 and downstream smaller and fewer fuel fluid delivery orifices 81. E.g., in a 2:1 ratio. Oxidant fluid orifices may be circumferentially offset from fuel fluid orifices to improve mixing and reduce quenching.

[0253] Fig. 4K depicts a schematic circumferentially (Z Theta) “unrolled” combusting section radially inward (or outward) wall configuration with fewer upstream fuel fluid delivery orifices 81, and more numerous downstream oxidant fluid delivery orifices 82. E.g., in a 1:2 ratio. Fuel fluid orifices may be circumferentially offset from oxidant fluid orifices to improve mixing and reduce quenching probabilities.

[0254] Fig. 4L depicts a schematic circumferentially (Z Theta) “unrolled” configuration a downstream Blend-Trim region section having oxidant fluid orifices 83A and 83C in a radially outward (or inward) Blend-Trim region wall. Upstream Blend-Trim orifices 83A may be offset ClockWise (CW) from downstream Blend-Trim region orifices 83C.

[0255] Fig. 4M depicts a sample schematic configuration of a downstream Blend- Trim region section having oxidant fluid delivery orifices 83A and 83C in a radially inward (or outward) Blend-Trim region wall. Here upstream Blend- Trim orifices 83A may be offset CounterClockWise (CCW) from ClockWise (CW) downstream Blend-Trim orifices 83C.

[0256] Corresponding to Fig. 4L and Fig. 4M, Blend-Trim orifices 83A and 83C configured radially outward of a combusting region may be offset ClockWise (CW) and CounterClockWise (CCW) from Blend-Trim orifices 83A and 83C configured radially inward of the combusting shell. Similar methods may be used to improve mixing with fuel fluid orifices and / or oxidant fluid orifices in the combusting upstream (731), midstream (732), and downstream (733) wall regions of the combusting chamber.

[0257] Fig. 4N depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region upstream to downstream cut through a CounterClockWise (CCW) circumferentially outward combusting region wall 734.

[0258] This sample configuration Fig. 4N shows eight radially outward oxidant fluid delivery openings X1 through X8 for radially outward oxidant fluid feeders (or diluted oxidant fluid feeders). These may be complemented by and interspersed with eight radially inward oxidant fluid (or diluted oxidant fluid) passage openings X1 through X8, in radially inward transverse oxidant fluid feeders.

[0259] Fig. 4O depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region upstream to downstream cut inward of the CCW circumferentially outward end wall (734) having eight radially outward oxidant fluid delivery openings (X1 through X8) (or diluted oxidant fluid delivery openings) in outward transverse oxidant feeders.

[0260] Fig.4O further shows these outwardly oxidant fluid openings (X1-X8) may be complemented with eight interspersed radially inward oxidant fluid delivery openings (X1 through X8) (or diluted oxidant fluid delivery openings) in inward transverse oxidant feeders. These oxidant fluid passages (X1-X8 and X1-X8) may be interspersed with narrower fuel fluid delivery passages (unmarked).

[0261] Fig. 4Q depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region through a Clockwise (CW)circumferentially outward side bounding combusting region end wall 735 having eight radially outward fuel fluid delivery openings U1 through U8. These may be complemented by and interspersed with eight radially inward fuel fluid passage openings U1 through U8.

[0262] Fig. 4P depicts a sample (nominally radial-axial R-Z) schematic configuration of an upstream combusting region inward of the CW circumferentially outward end wall (735) having eight oxidant fluid feeder delivery passage openings (U1 through U8) interspersed with eight oxidant fluid feeder delivery passage openings (e.g., X1-X8 not labeled).

[0263] Figures 4N through 4Q further depict combustor radial height (or length) parameters labeled from the first outward combusting shell towards the next inward combusting shell. E.g., CR12 labels the radially outward oxidant fluid feeder wall outer radius. CR15 labels the radially outward combusting region wall radially inner radius. CR16 labels the radially inward combusting region wall outer radius. CR24 labels the radially inward oxidant fluid feeder wall radially inner radius.

[0264] Figures 4N through 4Q further depict combustor radial inner height parameters labeled from the first outward combusting shell towards the next inward combusting shell along the radial R axis. E.g., CR12T labels the radially inner depth (height or Thickness) of the outer oxidant fluid transverse feeders shown in Fig. 4N and Fig. 4O. CR12T similarly labels the radially inner height of the outer fuel fluid transverse feeders shown in Fig. 4P and Fig. 4Q.

[0265] The radial parameter CR15T labels the combusting region radially inner height (Thickness) between CR15 and CR16 shown in Fig. 4O and Fig. 4P. CR18T similarly labels the radial thickness of the radially inner oxidant and fuel transverse feeders between CR16 and CR24 shown in Fig.4N through Fig. 4Q.

[0266] Figures 4N though 4Q further depict the combustor axial boundaries from the upstream combusting region boundary at CZ34 to the downstream combusting fluid delivery boundary at CZ35 (at a reference plane CBQ) along the axial flow Z axis.

[0267] Fig. 4O further depicts typical Axially Inner Inlet Widths 810 of radially outer transverse oXidant fluid feeders X1 to X8 supplying the centralcombusting region near the outer open side (e.g., CounterClockWise CCW side near the oxidant fluid feeder opening from the adjacent oxidant manifold).

[0268] The axially inner axial widths of radially inner transverse oxidant fluid feeders X1 to X8 supplying oxidant fluid into the central combusting region in Fig. 4O may be similar and may be scaled according to the radial distance outward to the respective feeders from the combustor axis. Fig. 4O further depicts the corresponding Axially Inner Far End Widths 809 of radially outer transverse Fuel Fluid feeders U1 to U8 near the transversely closed end of the fuel fluid feeders near the adjacent oxidant fluid manifold (e.g., the CCW side).

[0269] Fig. 4P further depicts typical Axially Inner Inlet Widths 808 of radially outer transverse Fuel Fluid feeders U1 to U8 supplying the central combusting region near the outer open side (e.g., the Clockwise CW side near the fuel fluid feeder opening from the adjacent fluid manifold).

[0270] The inner axial widths of radially inner transverse fuel fluid feeders U1 to U8 supplying fuel fluid into the central combusting region in Fig. 4P may be similar and may be scaled according to the radial distance outward to the respective feeders from the combustor axis.

[0271] Fig. 4P further depicts the corresponding axially inner widths 811 of outer transverse oxidant fluid feeders (X1-X8 not labeled) near the transversely closed end of the oxidant fluid feeders near the adjacent fuel fluid manifold (e.g., the CW side). Fig. 4P similarly shows the inner transverse oxidant fluid feeders (X1-X8 not labeled) between CR16 and CR24, with corresponding inner widths (811 not labeled) between fluid feeder walls.

[0272] Fig. 4R schematically depicts an axial circumferential (Z Theta) plan view perspective of a pair of transverse fluid feeders delivering oxidant fluid X into multiple oxidant fluid orifices 82 with typical oxidant fluid orifice diameters DXO, and delivering fluid F into multiple fuel fluid orifices 81 with typical fuel fluid orifice diameters DFO. The fuel fluid feeder is depicted with an axial width DFF compared to the wider Oxidant Fluid Feeder with an axial width DFX. In some configurations, diluent feeders may be utilized with a Diluent Fluid Feeder width DFD (not shown).

[0273] Per Fig. 4R, in some configurations, fuel fluid orifices 81 in the fuel fluid feeder may be circumferentially displaced by a circumferential angle THF from the vertical plane, ClockWise (CW) positive. In some configurations, oxidantfluid orifices 82 may be configured in pairs circumferentially positioned about fuel fluid orifices 81, with a narrower circumferential separation angle THXN between oxidant fluid between nearest centers of oxidant fluid orifices 82 of separated orifice pairs. Oxidant fluid orifices 82 may have a wider adjacent orifice circumferential separation angle THXW between oxidant orifice centers of wider separated orifice pairs.

[0274] In other configurations, oxidant orifices may be spaced further apart, or may be spaced uniformly apart. As schematically depicted in Fig. 4E, 4H, and Fig. 4I, circumferential spacing of orifices about the combustor may be further varied along axially differing fluid feeders. These may use one or both of circumferentially even spacing, and circumferentially asymmetric spacing.

[0275] In some configurations, circumferential spacing may be closer near one and / or both inner and outer combusting chamber boundaries than in circumferentially inner regions. Other configurations may provide more space between orifices near circumferential boundaries.

[0276] Fig. 4S shows another axial circumferential plan view of a fuel feeder feeding fuel fluid F through fuel fluid orifices 81 and an axially adjacent oxidant fluid feeder feeding oxidant fluid X through a multiplicity of oxidant fluid orifices 82. This configuration depicts the oxidant fluid orifices 82 as axially (Z) separated and radially (Theta) aligned.

[0277] Oxidant fluid orifices 82 may similarly be circumferentially aligned with fuel fluid orifices 82 as depicted here. Such configurations may improve jet penetration into the combusting fluid flow. In other configurations, the oxidant orifices may be axially aligned, and collectively circumferentially offset from the fuel fluid orifices 82.

[0278] Fig. 4T depicts a schematic radial circumferential (R Theta) cross-section “elevation view” of an outer combusting region wall 736 with an insulating liner 738 bounding the combusting region with an outer radius CR15. Outer fuel fluid orifices 87 may be configured at a positive angle PhiX (or a negative angle - PhiX) from the radial axis R to deliver fuel fluid in the negative CCW direction.

[0279] Fig. 4T further shows an inner combusting region boundary wall at CR16 radially displaced by a radial thickness CR15T from the outer combusting region wall. The radially inner combusting wall may have an outer insulating liner 738 protecting a radially inner structural wall 737. Inner oxidant fluidorifices 88 may be configured at an opposing negative angle -PhiX (or an opposing positive angle PhiX) from the radial axis R to delivery oxidant fluid in the negative CCW direction.

[0280] The configuration of Fig. 4T may similarly be configured with fuel fluid orifices 87 oriented with a negative angle -PhiX, and oxidant fluid orifices 88 oriented in the opposite direction with a positive angle PhiX. Further configurations may comprise both fuel fluid orifices 87 and oxidant fluid orifices 88 configured with the same positive angle PhiX. Similar configurations may comprise fuel fluid orifices 87 and oxidant fluid orifices 88 configured with a similar negative angle -PhiX (or positive angle PhiX).

[0281] In the Fig. 4T configuration, some fuel fluid delivery orifices 87 and oxidant fluid delivery orifices 88 in axially offset fluid feeders may be circumferentially oriented with similar positive angle PhiX (or negative angle - PhiX). In other configurations generically upstream fluid delivery orifices 87 (or 88) and downstream fluid delivery orifices 88 (or 87) may be configured with opposing positive angles PhiX and negative angles -PhiX) oxidant (not shown).

[0282] Further generalizing configurations (such as in Fig. 4T) as shown in Fig. 4G, upstream fuel fluid orifices 81A may be circumferentially offset from (or aligned with) downstream oxidant fluid orifices 82B. Similarly, per Fig. 4G, upstream oxidant fluid orifices 82A may be circumferentially offset to (or aligned with) downstream oxidant fluid orifices 82B.

[0283] Fig. 4U depicts a radial circumferential (R Theta) “elevation” view of a sample configuration of outer transverse Fuel feeders marked F, and alternating outer oXidant transverse feeders marked X. These fuel and oxidant feeders may have a radially outer wall 802 bounded by an outer radius CR11. These feeders may have a radially inner wall 801 bounded by a feeder inner radius CR15, forming a radially outer surface of the inner first combusting region. The outer feeder inner wall 801 may comprise a radially outward (structural) side wall 736 covered on the inner combusting region side by a protective thermal insulating coating 738.

[0284] Fig. 4U further depicts fuel feeders F comprising fuel fluid orifices 87 to deliver fuel fluid into the adjacent inner combusting region. Similarly, oxidant feeders X may comprise orifices 88 delivering oxidant fluid into the adjacentcombusting region radially inwards of the feeder inner 801 wall at CR15. As shown, oxidant feeders X may be circumferentially wider in the transverse (Theta) direction than fuel feeders F to accommodate the larger volumetric oxidant fluid flows versus smaller fuel fluid flows.

[0285] Per Fig. 4U in some configurations, outer fuel fluid orifices 87 and oxidant fluid orifices 88 may both be angled circumferentially with a negative angle (- PhiX) from the radial axis R. Other configurations may use fuel fluid orifices 87 and oxidant fluid orifices 88 with the opposite circumferential positive angle (PhiX) from the radial axis R.

[0286] Further configurations may alternate angles of fuel fluid orifices and oxidant fluid orifices positive (PhiX) and negative (-PhiX) angles between radially inward and outward orifices. (Such configurations may have orifices aligned with the combustor axial Z axis, similar to that shown in Fig. 4S.)

[0287] Further to Fig. 4U, shows a radially inward (“lower”) feeder array portion from the outer feeder wall radius CR16 (or radially inner combusting region boundary) with outer insulating layer 738 protecting combusting chamber radially inner wall 737, to radially inner feeder wall radius CR20. This depicts a cross-section elevation view with Pairs of similar oxidant (X) fluid feeders of circumferential Passage Width PWX and Fuel (F) fluid feeders of circumferential Passage Width PWF. Joint fluid width widths of fluid feeder pairs shown in Fig. 4U may include a first oxidant-fuel fluid pair width (FP1) and a second oxidant-fuel fluid pair width (FP2).

[0288] In the radially inward (“lower”) portion of Fig. 4U, inner oxidant (X) fluid feeders may be configured opposite outer fuel (F) fluid feeders, and inner fuel (F) fluid feeders may be configured opposite to outer oxidant (X) fluid feeders. In this configuration common circumferentially transverse (outer) walls 133 may be used for opposite outer CounterClockWise (CCW) (“transverse”) and ClockWise (CW) boundaries.

[0289] In Fig. 4U, fuel (F) fluid orifices 87 may be configured circumferentially about the middle of fuel fluid feeder (F) with a circumferential offset of about PWF / 2 from the fuel -oxidant feeder dividing wall 133. In the radially outer (“upper”) oxidant feeders X, the oxidant orifices 88 may be configured about midway (transversely) across the oxidant feeder displaced by a distance of aboutPWX / 2 from the fuel-oxidant feeder dividing wall 133 (such as circumferentially aligned oxidant fluid orifices 82 as shown in Fig. 4S).

[0290] Alternatively, Fig. 4U depicts a configuration where the radially inward (“lower”) oxidant feeders (X) may have two oxidant orifices 88 transversely configured within the oxidant feeder (X). For example, these two orifices 88 may be positioned transversely at about a distance PWX / 3 of about one third the passage Width of oXidant feeder from the oxidant feeder walls (similar to configurations of oxidant fluid orifices 82 of diameter DXO as shown in Fig. 4R.)

[0291] In some configurations, orifices may be aerodynamically configured to reduce combustor pressure drop and to improve efficiency. Orifice inlet and outlet corners may be rounded to improve flows F and reduce pressure drops and efficiency losses, such as that shown in Fig. 4V.

[0292] Fig. 4V depicts a detailed view of a fluid orifice in the Radial Circumferential (R Theta) plane with fluid flow F through an outer combustor wall. E.g. fluid F may flow in through an oxidant fluid orifice of diameter DXO through a feeder structural wall of thickness CR13T protected by a feeder wall insulating coating of thickness CR14T. The fluid inlet and outlet may have rounded corners.

[0293] In some configurations, the upper orifice inlet may have a smaller radius ROI while the lower orifice outlet may have a larger orifice outlet ROO. Similarly, the outlet radius ROO may be about twice as large or larger than the inlet radius ROI. Such configurations may be formed curing additive manufacturing (or “3D printing”.)

[0294] Fig. 4W depicts a detailed view of an angled orifice in the Radial Circumferential (R Theta) plane through the outer combustor wall of thickness CR13T with an insulation layer of thickness CR14T. The angled oxidant fluid orifice may be configured with a flow axis at an angle THM relative to the Radial axis R with a diameter DXO perpendicular to the orifice flow axis.

[0295] Inlet corners of such angled orifices may be configured about an acute angle with a smaller radius ROIA and about an obtuse angle with a larger radius ROIB. Corresponding outlets of such angled orifices may have smaller radius ROOA for an acute angled outlet radius and a larger radius ROOB for an obtuse angled outlet radius.

[0296] Fig. 4X depicts a closed end of an oxidant feeder in the axial circumferential plane (Z Theta) for some configurations, with a manifold fuel fluid flow FFM flowing axially past the closed end, and a fuel feeder flow portion FFF flowing around the closed end. The oxidant fluid manifold may have an outer oxidant feeder axial width PXWO, and an inner oxidant feeder axial width PXWI with feeder wall thickness FWT.

[0297] The oxidant feeder axially upstream radius RXU may be configured smaller than the downstream oxidant radius RXD. E.g., the downstream radius RXD may be twice that of the upstream radius RXU or more.

[0298] Fig. 4Y depicts a closed end of a fuel fluid feeder in the axial circumferential plane (Z Theta) for some configurations, with a manifold oxidant fluid flow FXM flowing axially past the closed end, and an oxidant feeder flow portion FXF flowing around the closed end.

[0299] Per Fig. 4Y, such fuel fluid feeders may have an outer fuel feeder axial width PFWO, and an inner fuel feeder axial width PFWI, with feeder wall thickness FWT. The oxidant feeder axially upstream radius RFU may be configured smaller than the downstream oxidant radius RFD. E.g., the downstream radius RFD may be twice that of the upstream radius RFU or more. Numerous Orifices to Improve Mixing

[0300] In some configurations, fuel, oxidant, and / or diluent orifices may be used. Orifice size may be correspondingly reduced, such as to maintain overall cumulative orifice area within a desired range of the downstream combusting system cross-sectional area.

[0301] More numerous orifices may be used to beneficially improve mixing, increase combustion, further diluent mixing, assist in temperature control, reduce hot spots, improve uniformity, and / or facilitate equilibration.

[0302] For example, in some configurations, each combusting shell may use 50 to 100 oxidant orifices. In other configurations this may be increased to 101 to 200 oxidant orifices. Similarly, 201 to 400 oxidant orifices may be used. Further combustors may use 401 to 800 orifices or more, for more uniform combustion of difficult fuels like ammonia.

[0303] Such changes may beneficially be used to facilitate combustion of fuels with higher ignition energy, higher combusting temperature, slower flame speed, and / or slower combusting rates. E.g., in combusting one or more ofammonia, methane, methanol, ethanol, cracked ammonia (combinations of H2, N2, and NH3), and / or hydrogen. Modeling Combustion and Emissions

[0304] The applicant won a US Department of Energy High Performance For Computing Manufacturing (HPC4Mfg) supercomputer grant, and an HPC4EnergyInnovation supercomputer grant. Simplified VAST scalable combustors (such as using a scalable combusting region and a cylindrical equilibrating region), were modeled using more than 110 independent parameters.

[0305] Of these, 23 parameters were selected to model combustion over typical gas turbine pressures, temperatures, and specific power rates. Argonne National Laboratory (herein ANL) conducted reactive computational fluid dynamic modeling (herein “RCFD”) to evaluate low, medium, and high values (0%, 50%, 100%) for each of these selected parameter ranges.

[0306] Applicant ranked those parameters by parameter importance to Unburned Hydrocarbons (UHC) (or equivalent unburnt fuel), Nitrogen Oxides (NOx), and Carbon Monoxide (CO) emissions. Then ANL conducted 312 RCFD runs using combinations of 5 values across low to high (0%, 25%, 50%, 75%, 100%), for the most significant 9 parameters.

[0307] Lawrence Livermore National Labs (herein “LLNL”) then used neural network methods to analyze the data and to create a software program to predict UHC, CO and NOx emissions, which can be run on a professional laptop computer.

[0308] Those methods and resulting software enabled the applicant to configure its scalable gas turbine combustor configurations so as to probably achieve less than 1 ppmvd each for UHC, NOx and CO emissions over commercial gas turbine operating conditions. This predicts emissions below the strictest California county emission requirements of 2.3 ppmvd NOx and CO without using catalysts.

[0309] Such very low emissions provide major advantages with typically 7% to 10% lower CapEx for commercial gas turbines operating on natural gas with emissions control using Selective Catalytic Conversion (SCR). It further promises substantially lower operating costs by eliminating ammonia delivery and associated “slip” emissions.

[0310] The techniques, configurations and methods as described herein further detail, extend, and / or adapt that initial modeling RCFD modeling on methane. They likely enable extending and / or improving the methods to further using the range of conventional to sustainable fuels. E.g., to include methane, natural gas, methanol, ethanol, ammonia, cracked ammonia (herein combinations of “H2N2, and NH3”), and hydrogen. Diluent to the Blend Region

[0311] NOx formation is likely to increase as the product of (Fuel * O2) and exponentially with combusting temperature. Rich combustion cooled by steam and / or diluent in the upstream combusting region with residual combustion Blend region uniquely enables transitioning from rich hot upstream combustion to near stoichiometric combustion. This will likely be highly beneficial in avoiding NOx formation. Fig.4F schematically shows a typical combustor axial Temperature profile with 1,570K (1397°C) outlet temperature. Such runs reduced outlet NOx (and CO) emissions on Methane to sub 1 ppmvd (parts per million by volume diluted to 15% O2). Ammonia Combustion

[0312] Following VAST’s sub 1 ppmvd CO and NOx emissions achieved with CH4 combustion, preliminary modeling was conducted on Ammonia combustion. Conventional NH3 combustion can cause >1,000 ppmvd NOx. Published experiments have achieved 25 ppmvd NOx. Fig. 4F depicts an example of preliminary modeling of ammonia (NH3) combustion with air, and diluent water and steam. Temperature and emissions are depicted along a flow axis from the upstream combusting inlet CZ34 to the downstream combustor outlet at CZ4. This exploratory reactive RCFD modeling of diluted NH3 air combustion was conducted in applicant’s prior simplified scalable combustor.

[0313] The left axis shows the mean cross-sectional temperature, and the right axis the outlet NOx and NH3emissions in ppmvd (parts per million diluted to 15% O2). In this sample run, the mean upstream combusting hot gas temperature peaks near 1,830K (~1,557ºC) about the end of the Blend-Trim region T1. For RCFD modeling, an assumed combustor wall cooling rate is prescribed, reducing the combustor outlet temperature at CZ4 to a prescribed 1,527K (1,300ºC) typical of a mid-range gas Turbine Inlet Temperature (TIT).

[0314] Per Fig. 4F, in this run, NH3peaked at ~13,000 ppmvd (~40,000 ppm) in the rich combusting region. Residual NH3 then declined to ~78 ppmvd (~227 ppm) at the combustor outlet. Combustion NOx formation peaked at ~275 ppmvd (~800 ppm) downstream of the ammonia peak and upstream of the temperature peak. With excess NH3, and high H2O, the NOx declined to sub ~10 ppmvd (~29 ppm unadjusted) at the combustor outlet.

[0315] Such ~10 ppmvd NOx emissions in Fig. 4F from initial exploratory NH3combustion already achieves NOx emissions 60% or more below the US EPA’s 25 ppmvd national emissions limit for mid-range Brayton Cycle gas turbines. These results appear remarkably lower than reported industrial and scientific combustion modeling reports found for this most difficult renewable or sustainable proposed fuel.

[0316] Applicant has identified means of further improving mixing and combustion by aerodynamic methods, improved orifice distributions and delivery staging, such as described herein. These promise to further improve combustion and lower both NH3 and NOx emissions observed. With 24% higher efficiency for a single expander VAST cycle with exhaust heat recycling, this preliminary NH3combustion modeling appears to offer a further 19% lower NOx emissions per electricity generated (ppmvd / MWh) relative to a conventional simple cycle (Brayton) peaker gas turbine. Cooling Combustion

[0317] In some configurations, remaining undelivered diluent may be moved from the downstream Trim region feeders T1 to be delivered up into the Blend region feeders (e.g., B1 and B2). A major portion of this remaining diluent may be delivered to the upstream Blend feeder B1 to provide cooler rich (sub stoichiometric) combustion, with temperature being controlled independently of the relative local fuel to oxidant ratio Phi (or the relative local oxidant to fuel ratio Lambda).

[0318] In further configurations, part of this diluent may further be delivered further upstream into the downstream end of the combusting region, such as to delivering with fuel U7 and / or oxidant fluid X7 (or optionally diluted oxidant fluid) in the axially downstream (or last) combusting region axial 733. Such diluent may further be delivered into the last two to last seven combusting regions upstream of CZ35.

[0319] Excess oxidant (or air) T1 may similarly be delivered in through the downstream Trim region. Such a combination of upstream diluent and downstream excess oxidant may achieve the coolest Blend region rich combustion with the least oxidant up to stoichiometric combustion. This may well form the lowest NOx emissions for such configurations, with no change in total oxidant or excess air delivered Phi ( ).In Situ Ammonia Cracking

[0320] In further configurations ammonia may be delivered upstream under hot fuel rich (excess fuel, sub-stoichiometric oxygen) conditions (with Phi ( or Lambda < 1). Upstream combusting temperatures may be increased by reducing upstream diluent. Such conditions may increase upstream ammonia cracking to hydrogen and nitrogen. Such in situ rich cracking of ammonia to hydrogen and nitrogen may facilitate downstream rich combustion, thereby reducing overall NOx formation.

[0321] Referring to Fig. 4Z and heating / cracking section 853 within the Blend- Trim region 850. Ammonia fuel may be delivered as Fuel F1 into this region, (and / or as diluted Fuel F2, not shown). A portion Ammonia Fuel F1 may be cracked to hydrogen and nitrogen, with residual ammonia recovered from this region as cracked Fuel fluid F16. This region 853 may provide multiple serpentine passages without orifices to increase (or fewer to decrease) the residence time, or to modify it. Some combustor configurations may configure the temperature of transverse feeders without orifices, adjacent to the combusting region, and / or in the upstream combusting region.

[0322] One or more of the axial location, temperature, fuel F1 fluid flow rate, number of transverse passages, and contact duration may be adjusted sufficient to thermally crack a portion of ammonia fuel to hydrogen and nitrogen per Fig. 4Z. E.g. from 2% to 98% ammonia cracking, or 5% to 60% cracking, or from 10% to 40% cracking, and / or for 15% to 25% cracking etc. Catalysts may similarly be used within transverse fluid feeders to facilitate cracking of ammonia. Such cracking may further be configured together with diluent to then form diluted fuel fluid F2 for delivery into the combustor. Thermally Igniting Flows

[0323] In some configurations, an energetic fluid may be formed by heating one or more delivered fluids to temperatures such that the temperature and flow rateof the delivered energetic reactant and co-reactant mixture gas is sufficient to ignite the reactive fluid in the primary reaction zone. Manufacturing Methods

[0324] One or more of such scalable parametric combustor configurations depicted may be constructed using additive manufacturing (or “4D printing”) techniques. Such manufacturing techniques may facilitate forming the numerous oxidant fluid, fuel fluid, and diluent fluid transverse feeders with the corresponding orifices delivering fluid from the transverse feeders into the combusting chambers.

[0325] In some configurations, such scalable shell combustors may be formed in two halves with inner insulating coatings over outer structural walls. These may then be assembled and be suitably held, bonded or fastened together. In other configurations, such orifices may be formed by laser ablation, chemical etching, mechanical or fluid jet drilling, or similar material removal techniques. Radial Annular Multiple Scalable Combustors

[0326] Such Radial Annular Multiple Scalable Combustors (or “Multi-Fan burners”) may be designed to achieve ultra-clean combustion for gas turbines, combined heat and power systems, industrial heating and / or cooling, and other applications requiring ultra-clean well controlled combustion and / or similar chemical reaction.

[0327] In some configurations, walls with multiple fluid jets delivered through orifices may be configured with relatively shallow spacing between those walls to improve relative jet penetration. For example, the mass flow rates of fuel, oxidant, and diluent delivery, or any combination thereof, into an upstream combusting flow may be configured to increase reliable combustion operating range, combustion operational robustness, and / or the degree and / or uniformity of fluid mixing.

[0328] Further to the Annular – Radial configuration 704 of Fig. 4B with an upstream combusting section 730, having a cross section 740, Fig. 5A and Fig. 5C show an end on Downstream to Upstream view 740 of the downstream end of multiple Scalable Combustors Radially Oriented in the upstream portion of an Annular Gas Turbine Combustor 740 extending from a combusting region inlet 134 to a combusting region outlet 136 such as for use in a gas turbine combustion system.

[0329] Per Fig. 5A, and Fig. 5C, in context of Fig. 4A and Fig. 4B, one or more flame authorities 100 (ignition authorities, or pilot lights) may be configured to supply hot igniting gas F22 into an upstream flame authority duct (ignition authority duct or pilot feeder duct) configured about the upstream inlet region 720 of a combusting system 750. The upstream flame authority duct may feed the hot igniting gas F22 into the upstream region 730, (such as from CZ31 to CZ34) of one or more combusting shells (such as are shown schematically in Fig. 4A, in perspective in Fig. 4B, and from the downstream view looking upstream in Fig. 5A (looking downstream in Fig. 5B) and from a perspective upstream view in Fig. 5C.)

[0330] The one or more upstream flame authorities 100, such as depicted in Fig. 4B, (in cross section looking upstream and Fig. 5A, in cross section from upstream looking downstream in Fig. 5B), may be fed with Pilot Fuel fluid F3 comprising a fuel fluid (or first reactant fluid), a Pilot Oxidant Fluid F6 comprising an oxidant fluid (or second reactant fluid), and a Pilot Diluent Fluid F8 comprising a diluent fluid or thermal diluent.

[0331] With reference to plan view Fig. 5B looking downstream, some embodiments may configure a upstream region 730 of scalable combustor 704 section 730 with multiple scalable combustion sections (or combusting chambers or “fan burners”) as depicted in a downstream to upstream radial - circumferential (R-Theta) view. These may have a radial configuration of combusting chambers 730 between an inner annular duct wall 147, and an outer Pressure Vessel Wall 172, to form the radial multi-fan annular combustor 730.

[0332] Similarly, Fig. 5C shows a radial-circumferential (R-Theta) perspective view of multiple outwardly oriented combustion sections (or multi-fan burners) 740. Fig. 5B cross section shows upstream view of combustion sections as configured along a vector S at an angle Phi rotated clockwise from the radial vector R, to form a radial multi-fan annular combustor 740.

[0333] Fig. 5C further shows a more detailed perspective view of section 740 within upstream combustion section 730 as portion of the radial multi-fan annular combustor 704 (such as depicted in Fig. 4B). An upstream combusting section 740 is configured between an upstream combusting fluid duct inlet transverse plane 134, and a downstream combusting fluid duct outlet transverse plane 136. (The configuration of Fig. 5B has similar upstream detailedconfiguration section 730 of the radial multi-fan annular combustor 704 with outwardly oriented multi-fan burners configured along radial orientations, not shown.).

[0334] All or some of Fig. 5 curves may be cycloidal shaped curves. In summary, cycloidal curves can indeed improve flow efficiency by minimizing abrupt directional changes, reducing separation, and optimizing flow attachment. Their effectiveness is often most notable in systems where fluid needs to turn within constrained spaces or where maintaining laminar flow is advantageous. These cycloidal properties can also be beneficial for fluid dynamics in applications where maintaining flow velocity and smooth directional change is beneficial.

[0335] Fig. 5C shows an exploded outward to inward perspective view of Fig. 5B, (and correspondingly for Fig.5A) in context of Fig.4B. An upstream igniter or flame authority 100 receives, mixes, and reacts a pilot fuel fluid F3 mixed with pilot oxidant fluid F6, with one or both fluids optionally mixed with pilot diluent fluid F8, to form a hot pilot fluid F22.

[0336] Per Fig. 5C, the hot pilot fluid F22 from upstream flame authority 100 may then be distributed to the upstream end 134 of one or more mid-fan combusting sections or burners 74, via an optional hot pilot duct 138. One or more of the scalable combustors 740 within axial section 730 may be configured and extended between a inner surrounding duct wall 147 and / or a surrounding pressure vessel 172 as described herein with respect to the circumferential annular multi-combusting chamber scalable combustor 704 as depicted in Fig. 4B. Radial Annular Multi-Fan Combustor

[0337] With reference to Fig.4B, the orifice dimensions, side wall depth spacing and pressure drop across the circumferential annular scalable combustor upstream section 730 may be configured to deliver premix fluid into fan burners at a rate sufficient to feed and react with the incoming hot pilot fluid F22 to form more hot or energetic fluid F20 without quenching the reaction within the scalable combustor. The delivery rate of premix fluid F14 may similarly be configured to maintain the temperature of the reacting fluid within each fan burner above a prescribed reaction temperature quench limit. Transverse and Axial Composition and Temperature Distributions

[0338] One or more transverse distributions of one or more of fuel fluid delivery orifices, oxidant fluid delivery orifices, and / or diluent fluid delivery orifices, may be configured to achieve one or more of a prescribed transverse composition distribution, a prescribed transverse temperature distribution, and / or a prescribed transverse velocity distribution, about one or more prescribed axial planes normal to the combusting fluid flow, between the hot pilot fluid F22 inlet at CZ34, and the combustor outlet at CZ4.

[0339] Similarly, a plurality of transverse distributions of orifice size, spacing, and / or orientation may preferably be configured to achieve a desired change in transverse composition and / or temperature distributions in a plurality of curvilinear surfaces distributed across the streamwise flow direction within the combustor. Such transverse distributions of orifices in perpendicular planes and / or transverse curvilinear surfaces, may be configured at multiple locations along the streamwise flow.

[0340] Such as depicted in Figures 5D through 5G and 5H to 5J, some configurations may physically configure orifice distributions and size, and / or dynamically control fluid delivery to control the temperature T of the hot combusting gas at a radial location R in an axial plane at axial location CZ between the combustor inlet at CZ34 (as shown in Fig. 5D), into an upstream combusting fuel rich region between axial locations CZ34 and CZ35.

[0341] Similarly, some configurations may configure and / or control one or more oxidant and / or diluent fluid flows in a downstream oxygen rich (fuel lean) (Blend-Trim) region between downstream axial locations (CZ35 and CZ39). Such configurations may further configure fuel, oxidant and / or diluent orifices to control fluid flows compositions, and / or temperatures in an equilibrating region (from CZ39) to the combusting region outlet (at CZ4.)

[0342] Fig. 5D shows a schematic graph of combusting fluid Temperature at an axial transition location CZ35 between an upstream combusting fuel rich region and a downstream Blend-Trim region. The methods described herein may be used to control a temperature T35i at the inner radius Ri relative to (such as higher than) a desired corresponding radially outer temperature T35o at the outer radius Ro. E.g., to accommodate inner wall cooling from transition combustor transverse plane CZ35 to the outlet axial location CZ4 in the combustor outlet plane.

[0343] Such temperature control may be achieved by adjusting the diluent to fuel ratio Omega. E.g., the water to fuel mass ratio omega may be increased to reduce outlet temperatures and reduced to increase outlet temperatures. Such configurations may similarly control an outer temperature T35o at the outer radius Ro to be higher than a desired corresponding downstream outlet temperature. E.g., this may accommodate outer wall cooling at outer radius Ro from the transition axial location CZ35 to the combustor outlet axial location CZ4 in the combustor outlet plane.

[0344] Such combusting configurations per Fig. 5D may further control a first intermediate temperature T35j at a combustor intermediate radius Rj between the inner radius Ri and outer radius Ro. This first intermediate temperature T35j may be controlled relative to (such as below) one or both of the inner radial temperature T35i at the combustor inner radius Ri, and the outer radial temperature T35o at the outer radius Ro.

[0345] Such configurations may further control a second intermediate temperature T35k at a second intermediate radius Rk. E.g., the second intermediate temperature T35k may be controlled relative to (such as below) one or both of the inner temperature T35i at inner radius Ri, and the outer radial temperature T35o at the outer radius Ro (such as shown in Fig. 5D).

[0346] Such configurations as shown in Fig. 5E, may assist in controlling one or more corresponding downstream outlet temperatures in the outlet plane at CZ4 as shown in Fig.5F. E.g., to control an outlet temperature T4j at that combustor intermediate radius Rj. Such configurations may further control temperature T35J to assist in controlling a corresponding second intermediate outlet temperature T4k at the second intermediate radius Rk (as shown in Fig. 5E).

[0347] Per Fig.5D, the first intermediate temperature T35j at a first intermediate radius Rj, and second intermediate temperature T35k at the second intermediate radius Rk may further be configured to obtain a desired intermediate temperature gradient DT35jk between that first intermediate radius Rj and that second intermediate radius Rk in the combustor axial transition plane CZ35.

[0348] Fig. 5E shows a corresponding schematic graph of the hot gas outlet temperature T4 versus combustor radius R at an axial location CZ4 in the combustor outlet plane (or the turbine inlet plan) downstream of the equilibrating region. Some configurations may control upstream fluid deliveryof one or more of fuel fluid, oxidant fluid, and / or diluent fluid to control the outlet temperature T4 with a radially inner outlet temperature T4i at the inner radius Ri in the outlet plane at axial location CZ4.

[0349] Further to Fig. 5E, such configurations may similarly control the outlet temperature T4 to have a radially outer outlet temperature T4o at the outer radius Ro in the outlet plane at axial location CZ4. This outer temperature T4o may be configured relative to (such as higher than) the radially inner outlet temperature T4i at the inner radius Ri in the outlet plane.

[0350] Per Fig. 5E, upstream delivery of one or more of fuel fluid, oxidant fluid, and / or diluent fluid, may be further varied to control a first intermediate temperature T4j at a first intermediate radius Rj, in the combustor outlet. Similarly, upstream fluid delivery may be configured to control a second intermediate temperature T4k at a second intermediate radius Rk in the outlet plane at CZ4.

[0351] Further to Fig. 5D, and Fig. 5E, one or more upstream intermediate temperatures T35j and / or T35k (with the intermediate temperature gradient DT35jk of Fig. 5D) and / or corresponding diluent and oxidant fluid delivery orifices in the Blend-Trim region. These upstream orifices may be configured towards achieving desired downstream outlet temperatures shown in Fig. 5E. e.g. to achieve outlet temperature T4j at a first intermediate radius Rj, and / or the second intermediate temperature T4k at the second intermediate radius Rk with the corresponding temperature gradient DT4jk between those two intermediate outlet temperatures in the combustor outlet plane at the axial location CZ4.

[0352] Referring to Fig. 5D, some configurations may control one or both of an inner temperature T35i at the inner radius Ri, and / or an outer temperature T35o at the outer radius Ro relative to (such as higher than) a desired corresponding downstream outlet temperature T4o such as shown in Fig. 5E. Such configurations may be adjusted to accommodate outer wall cooling at outer radius Ro from the transition axial location CZ35 to the combustor outlet axial location CZ4 in the combustor outlet plane.

[0353] Fig. 5F shows a schematic graph of a hot Wall Temperature Tw versus combustor axial length Z, from an outer transition wall temperature TW35o at the transition boundary CZ35 at the downstream end of the fuel delivery region,to the outlet outer wall temperature TW4o the combustor outlet at axial outlet location CZ4.

[0354] Further to Fig. 5F, such temperatures may further be adjusted to control an inner wall temperature TW4i, and an outer wall temperature TWro. These may begin at an upstream inner wall temperature TW35i, and / or outer wall temperature of TW35o at the rich / blend-trim axial boundary CZ35. Such temperatures may include an intermediate inner wall temperature TW39i, and / or an outer wall temperature TW39o at the blend-Trim region outlet axially at CZ39. One or more temperature distributions may be varied to a downstream outer wall temperature of TW4i at the inner wall, and / or TW4o at the outer wall, at the combustor axial outlet at CZ4.

[0355] Fig. 5G shows a schematic graph of an axial Velocity V of combustion hot gas versus the combustor radius R, from radially inner to radially outer walls, at the combustor outlet, at the downstream axial location. This hot gas configuration may be adjusted by adjusting the radial distribution of the sum of CZ4 axial orifices in the upstream combustion region. E.g., these may be adjusted to have an axial velocity V of V4i near the combustor inner radius R4i near the inner wall (axially at CZ4). This mean velocity V may be increased up to a mean velocity V4j at the first intermediate radius R4j. The velocity V may further be increased (or decreased) to a value V4k at the second intermediate radius R4k. The velocity V may then be reduced to a radially outer value of V4o near the combustor outer radius R4o.

[0356] Fig. 5H is a graph showing an “unrolled” section of circumferential distribution of hot gas temperature T versus combustor circumferential angle Theta for a region encompassing a first radially oriented combustor located CounterClockWise (CCW) (left side) marked Theta1 . It further extends Clockwise (CW) to and similarly depicts a second radially oriented combustor located ClockWise (CW) (right side) marked Theta2 .

[0357] Fig. 5H shows radially inner temperatures in an upper (hotter) line between a fluid lower temperature Tsi and an upper fluid inlet temperature Ti, at a combustor inner radius Ri, marked “At Ri”. Fig. 5H similarly shows corresponding radially outer fluid temperatures between Tso and To versus circumferential angle Theta near or at a combustor outer radius Ro, marked “At Ro”. On the CounterClockWise (CCW) combusting region, these range fromcounterclockwise circumferential angle Theta1wo to clockwise angle Theta1co about the mid outer circumferential combusting angle Theta1o.

[0358] It shows a second combustion inner section displaced clockwise from the first inner section, and centered at Theta2o from a counterclockwise angle Theta2wo to a clockwise angle Theta2co.

[0359] Fig. 5H similarly shows a cooled counterclockwise (CCW) first combustion inner section at Ri centered at Theta1i. This covers a circumferential width of Delta Theta 1 from Theta1wi to Theta1ci. It shows a second combustion inner section displaced clockwise from the first inner section, and centered at Theta2i from a counterclockwise angle Theta2wi to a clockwise angle Theta2ci.

[0360] Fig. 5I Graph of hot gas temperature T versus combustor circumferential angle Theta, with temperatures between Ts and Ti, at inner radius Ri, and at outer radius Ro, with a heated counterclockwise first combustion section Theta1 and a second clockwise combustion section Theta2.

[0361] Fig. 5J Graph of hot gas velocity versus combustor circumferential angle Theta, between velocities Vs and V1, for values at inner radius Ri, and at outer radius Ro, with a cooled counterclockwise first combustion section at Theta1 and a clockwise second combustion section at Theta2.

[0362] Fig.5I further shows radially inner temperatures in an lower (cooler) line between a lower fluid temperature Tsi and upper fluid inlet temperature Ti, at a combustor inner radius Ri, marked “At Ri”. Fig. 5I similarly shows corresponding radially outer fluid temperatures between Tso and To versus circumferential angle Theta near or at a combustor outer radius Ro, marked “At Ro”. On the CounterClockWise (CCW) combusting region, these range from counterclockwise circumferential angle Theta1wo to clockwise angle Theta1co about the mid outer circumferential combusting angle Theta1o.

[0363] On the ClockWise (CW) combusting region, these range from counterclockwise circumferential angle Theta2wo to clockwise angle Theta2co about the mid outer circumferential combusting angle Theta2o.

[0364] Fig. 5I similarly shows a cooled counterclockwise (CCW) first combustion outer section at R1 centered at Theta1i. This covers acircumferential width of Delta Theta 1 from Theta1wi to Theta1ci. It shows a second combustion inner section displaced clockwise from the first inner section, and centered at Theta2i from a counterclockwise angle Theta2wi to a clockwise angle Theta2ci.

[0365] Fig. 5J is a graph showing an “unrolled” section of circumferential distribution of hot gas Velocity V versus combustor circumferential angle Theta for a region encompassing a first radially oriented combustor located CounterClockWise (CCW) (left side) marked Theta1 . It further extends Clockwise (CW) to and similarly depicts a second radially oriented combustor located ClockWise (CW) (right side) marked Theta2 .

[0366] Fig. 5J shows radially inner velocities in an upper (faster) line between a fluid lower velocity Vsi and an upper fluid inlet Velocity Vi, at a combustor inner radius Ri, marked “At Ri”. Fig.5H similarly shows corresponding radially outer fluid Velocities between Vso and Vo versus circumferential angle Theta near or at a combustor outer radius Ro, marked “At Ro”. On the CounterClockWise (CCW) combusting region, these range from counterclockwise circumferential angle Theta1wo to clockwise angle Theta1co about the mid outer circumferential combusting angle Theta1o.

[0367] It shows a second combustion inner section displaced clockwise from the first inner section, and centered at Theta2o from a counterclockwise angle Theta2wo to a clockwise angle Theta2co.

[0368] Fig. 5J similarly shows a slower Velocity counterclockwise (CCW) first combustion inner section at Ri centered at Theta1i. This covers a circumferential width of Delta Theta 1 from Theta1wi to Theta1ci. It shows a second combustion inner section displaced clockwise from the first inner section, and centered at Theta2i from a counterclockwise angle Theta2wi to a clockwise angle Theta2ci.Combustors Radially Oriented in the inlet of an Annular Gas Turbine Combustor.

[0369] In some configurations, combustors may be radially oriented about the inlet of an Annular Gas Turbine Combustor. For example, such configurations may use one or more cylindrical combustors extending outward from the compressor expander axis. Scalable Omega Combustor

[0370] One or more curves ranging from cycloidal to hyperbolic to parabolic may be used for portions of the diffuser, combustor, and / or transition zone walls. These may include curves from the family of brachistochrone or cycloidal curves. The Scalable Combustor may further be axially configured into an Omega shaped combustor as depicted in Fig.5K in the Radial-Axial (R-Z) Cross-Section Elevation View. This Scalable Combustor extends radially outward from the Turbine Axis, herein a Scalable Omega Combustor 707 (or Omega Combustor). Oxidant fluid flow WX34 may be delivered through an upstream diffuser into a generally axially oriented combusting region inlet CZ31 to the Scalable Omega Combustor (per the terminology of Fig. 4A and Fig. 4B). The walls and shape of the Omega Combustor 707 may be configured using one of the cycloidal family of curves.

[0371] Oxidant Fluid (or Second Fluid) F4 may be delivered from an upstream compressor 407 (CPR) and redirected radially outwardly (+R) and then outwardly upstream (+R -Z) through an outwardly reversing duct into scalable combusting and trim-blend region 704 between upstream combustor plane (e.g., CZ34) and downstream combustor plane (e.g., CZ39) (similarly to that depicted in Fig. 4A and Fig. 4B). Oxidant, fuel and diluent fluids may be delivered into the Combusting Region 704 (similarly to that shown schematically in Fig. 4A, Fig. 4B, and to other Figures and disclosure herein inclusively referencing these collectively as Combusting Region 704.)

[0372] Hot combusting fluid may then be delivered from Combusting Region 704 into Equilibrating Region 900 within an outer and inner pressure vessel wall 172. This pressure vessel wall 172 may be protected by a thermal barrier coating 34. Forming such an Omega combustor may increase the combusting fluid residence time for combustion between the shortened axial distance from CZ31 to CZ4 along the Turbine Axis. This may beneficially increases the ratio of Equilibrating volume per axial length. This may provide or increase residence time to reduce emissions while shortening the gas turbine shaft length. Fluid Premixing Chambers

[0373] Combustion may be improved and / or emissions reduced by premixing one or more of fuel, oxidant, and diluent fluids prior to delivery into the upstream combusting and / or downstream Blend-Trim regions such as in Fig. 5L shown in a Radial-Axial Plan View.

[0374] Fig. 5L depicts Premixing Chambers configured in the Scalable Combustor to Premix one or more of Fuel fluid F2, Oxidant fluid F5, and Diluent fluids F7. Fig. 5L shows a detailed circumferentially inward-looking Plan View in the Radial-Axial (R-Z) plane. A portion of the axially upstream combusting region, (e.g., between CZ34 and CZ35) is shown depicting multiple perforated transversely extended radial circumferential (R Theta) fuel feeder walls 842 and multiple perforated transversely extended radial circumferential (R Theta) oxidant feeder walls 844. These perforated transversely extended fuel feeder walls 842 and oxidant feeder walls 844 are in contrast with continuous radial circumferential fuel feeder walls and oxidant feeder walls such as shown in Fig. 4G and Fig. 4I.

[0375] A plurality of radial – circumferentially extending (R-Theta) walls 842 (such as at and upstream of CZ35) may be used to form one or more transverse fuel fluid feeder passages 751. Such fuel fluid feeders 751 may deliver fuel fluid F2 radially outward from fuel feeder manifold 770 such as bounded by radially inner manifold wall 253.

[0376] Similarly, a plurality of radial – circumferentially extending (R-Theta) walls 844 (such as between upstream bound CZ34 and downstream bound CZ35) may be used to form one or more transverse oxidant fluid feeder passages 761. Such oxidant fluid feeder passages 761 may deliver oxidant fluid F5 radially inward from an outer oxidant fluid feeder manifold 780 such as bounded by manifold wall 250.

[0377] Such radial-circumferential extending feeder walls 842 and 844 may be used to form one or more premixing regions radially bounded by radially inner end walls 828 and radially outer end walls 826. Such premixing regions may be formed into multiple smaller blended feeder premixing chambers 847 by separating them radially with axial-circumferential blended feeder divider walls 846 extending axially between radial-circumferential extending feeder walls 842 and 844.

[0378] One or more fuel fluid delivery orifices 81 may be configured between fuel fluid feeder 751 and premixing chambers 847. Such fuel fluid orifices 81 may deliver fuel fluid F2 into multiple fluid premixing chambers 847.

[0379] One or more premixed reactive fluid orifices 87 may be configured in the circumferential – radial (Theta – R) combusting region walls to deliver premixed fuel rich reactive fluid mixture F12 from such premixing chamber(s) into the circumferentially adjacent combusting region. The diameter of such premixed reactive fluid orifices 87 may be constrained to avoid flashback from the combustingregion back into such premixing chambers 847 under operating conditions with applicable fuels. For example, with one or more of ammonia, methane, ethanol, methanol, hydrogen, JP6, diesel, and / or gasoline fuels.

[0380] The number of premixed reactive fluid orifices 87 may be configured within a prescribed range to provide a prescribed range of cumulative premixed fluid delivery area to deliver into the adjacent combusting chamber the amount of premixed rich fluid F12 formed per such premixing regions formed between the fuel feeder 751 and oxidant feeder 761.

[0381] The number of such premixed reactive fluid orifices 87 and / or the related premixed fluid orifice delivery area may be configured relative to the premixed fluid formed to constrain one of a pressure drop across said premixing orifices to be below a prescribed premixing pressure drop, and a ratio of premixed fluid delivery distance per axial flow distance relative to the local combusting fluid axial velocity within the combusting region. Premixing Blend-Trim Feeder

[0382] As described above for reactive premixing chambers, non-reactive dilutive premixing chambers 851 may be configured in the Blend-Trim region downstream of CZ35. Oxidative Fluid F5 may be delivered oxidative orifices 83 into premixing dilutive chambers 851. Dilutive fluid F7 may similarly be fed through dilutive orifices 84 into such dilutive premixing chambers 851. Oxidative Fluid F5 and Dilutive Fluid F7 may be premixed with in such premixing chambers 851 and delivered through premixed dilutive orifices 852 into the Blend Trim region downstream of the Combusting to Blend Trim boundary CZ35. Controllable Flexible Scalable Ignition Authority

[0383] Referring to Fig. 5M depicts the outer fluid delivery region of a Controllable Flexible Scalable Ignition Authority 100, (or Pilot Authority). Igniter or Pilot Fuel fluid F3 may be delivered into a fuel fluid delivery feeder. Such a fluid delivery feeders may be semi-circular having an Inner Fuel Feeder Radius RFI and an Outer Fuel Feeder Radius RFO. One or more fuel Fluid Orifices 81 may be distributed about the upper fluid delivery feeder in an Ignition Authority 100.

[0384] Fig. 5M further depicts the Ignition Authority 100 as having an oXidant (or air) fluid delivery inlet port feeding an oxidant fluid delivery feeder axially upstream at CZ31. Such oxidant fluid may be delivered through an outerdelivery feeders such as depicted. This outer oXidant pilot feeder may be semi- circular having an Inner Oxidant Outer Feeder Inner Radius RXOI (similar to the outer Fuel Feeder Radius (RFO), and an Outer Oxidant Feeder Outer Radius RXOO.

[0385] Such oxidant fluid may similarly be delivered through an inner Oxidant delivery feeder. Such an inner oXidant pilot fluid feeder may be semi-circular having an Inner Oxidant Feeder Outer Radius RXIO.

[0386] Per Fig. 5M, one or more Oxidant Fluid Orifices 82 may be distributed about the upper oxidant fluid Outer delivery feeder in an Ignition Authority 100. Similarly, one or more Oxidant Fluid Orifices 82 may be distributed about the upper oxidant fluid Inner delivery feeder in an Ignition Authority 100. Alternatively, such an inner Oxidant pilot feeder may have an inner wall forming semi-circular inner oxidant Feeder.

[0387] Fig. 5N depicts a schematic Perspective View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices above an intermediate or middle Combusting Region. Fig. 5O through Fig. 5S show plan views of five cross-sections of such Ignition Authorities 100.

[0388] Fig.5O shows a Schematic Plan View of an Ignition Authority Outer Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the middle or central Combusting Region, similar to Fig. 5M.

[0389] Fig. 5P depicts Fuel Orifices 81 and Oxidant Orifices 82 in a Plan View of Ignition Authority Upper Inner Wall to the Ignition Authority’s central combusting chamber.

[0390] Fig.5Q Depicts a cross-section Plan View through Igniter Authority Mid- Section along the normal to the Ignition Authority outer and inner surfaces.

[0391] Fig. 5R depicts Fuel Orifices 81 and Oxidant Orifices 82 in a Plan View of Ignition Authority Lower Inner Wall to the Ignition Authority’s central combusting chamber.

[0392] Fig. 5S shows a Schematic Plan View of an Ignition Authority Inner Fuel and Oxidant Feeders with Fuel and Oxidant Orifices into the central Combusting Region, similar to Fig. 5M and Fig. 5O.

[0393] Fig. 5T depicts a Close-up schematic view of an Igniter in the Wall of the central Pilot Combusting Region. Such igniters may have two electrodes 124connected to an ignition source 126. Other igniters may similarly be used, such as glow plugs, spark plugs, and / or plasma sources.

[0394] Fig. 5U depicts methods for combustor wall cooling which may utilize a diluent, or provide for ammonia cracking, or combinations thereof. Such cooling with thermal ammonia cracking may be configured for the downstream Equilibrating region. E.g., this Fig. 5U depicts a Radial-Axial (R-Z) Cross-Section of an outer Combustor Wall such as between the Combusting region or oxidant rich (fuel lean) (Blend-Trim) region, the adjacently downstream Equilibrating region (900), and / or to the downstream transition region (980). E.g., such as axially between the combustor inlet (CZ34) and the equilibrating region outlet (CZ397). Such combustor wall cooling may similarly be configured further downstream through the transition zone (980 from equilibrating region outlet CZ397 down to the combustor outlet or expander inlet at CZ4.)

[0395] Fig. 5U further depicts an compound insulated combustor system wall having an outer pressure vessel 172 outside of an outer combustor wall 909 protected by an outer thermal insulating layer 910. Such compound combustor wall may have an equilibrating region inner wall 906, which may be protected by an Equilibrating Region Inner Insulation 905. The outer pressure wall may be cooled by flow of Pilot Diluent fluid F8, (or similarly cooled by flow of Thermal Diluent fluid F7 not shown) through an outer cooling passage 106.

[0396] Fig.5U further depicts an intermediate compound fluid delivery duct having an inner fluid distribution wall 907 and outer fluid distribution wall 908 forming an intermediate fluid distribution passage 104 configured between the inner combustor wall 906 and the outer combustor wall 910. Such intermediate compound fluid delivery passage may deliver a fluid comprising a reactant and / or fuel such as Diluted Fuel F2 (or Diluted Reactant Fluid).

[0397] Such diluted fuel F2 may be delivered through one or more orifices 81 into the passage 139 between combustor wall 906 and the inner fluid distribution wall 907. One or more thermal fins or posts 41 may be configured on or as part of the inner combustor wall 906. Such fins 41 may be configured near or opposite orifices 81 to increase the heat transfer surface area for Fluid F2 on the inner combustor wall 906 to facilitate such heat transfer.

[0398] Heated fluid F16 may then flow radially outward through fluid ducts 105 into an outer passage 105 between fluid deliver wall 908 and the outer combustor wall 910.

[0399] Fluid Cooling Capable of Ammonia Cracking.

[0400] Such delivery of fuel (or reactant) fluid F2 onto the combustor wall 906 having optional thermal fins or posts 41 may be used to thermally heat fluid F2 while cooling the combustor wall 906. This may be used to facilitate thermal cracking of fuel fluid F2, such as comprising ammonia, to form diluted cracked fuel fluid F16 having a portion of hydrogen (H2) and nitrogen (N2) formed by cracking ammonia (NH3). Such diluted cracked fuel fluid F16 may then be delivered to the upstream rich combusting region 730 and and / or to the Pilot 100.

[0401] Fig. 5V depicts a Radial profile of Inner Flow Temperature at the inner radius RWi to Outer radius R...

Claims

We Claim:

1. A gas turbine system, comprising: a pressurized fluid delivery system configured to deliver into a combustor system: a pressurized fuel fluid comprising a fuel; a pressurized oxidant fluid comprising an oxidant; and a pressurized diluent fluid comprising a diluent; an oxidant fluid discharge system configured to control a first flow of the pressurized oxidant fluid incoming from the pressurized fuel delivery system into the combustor system; a pressurized diluent injection system configured to control a second flow of the pressurized diluent fluid incoming from the pressurized fuel delivery system into an upstream diluted fuel rich combustion stage included in the combustor system, and into a downstream diluted oxidant combustion stage included in the combustor system, wherein the pressurized diluent fluid comprises a superheated fluid; and a control system configured to control delivery of the pressurized fuel fluid, the pressurized oxidant fluid, and the pressurized diluent fluid, and to control ignition of the pressurized fuel fluid with the pressurized oxidant fluid by controlling one or more fluid delivery rates of the pressurized fuel fluid, the pressurized oxidant fluid, the pressurized diluent fluid, or a combination thereof.

2. The gas turbine system of claim 1, wherein superheated fluid comprises a fluid having a temperature higher than the fluid’s vaporization point at an absolute pressure where the temperature is measured.

3. The gas turbine system of claim 2, wherein the temperature comprises at least 100°C at standard atmospheric pressure.

4. The gas turbine system of claim 2, wherein the superheated fluid comprises a water in steam form, in non-steam form, or a combination thereof.

5. The gas turbine system of claim 2, wherein the superheated fluid comprises a carbon dioxide (CO2).

6. The gas turbine system of claim 4, wherein the water in steam form is created by flashing the water in non-steam form via direct injection, oxidant blast injection, or a combination thereof.

7. The gas turbine system of claim 1, wherein the pressurized diluent fluid comprises a heated fluid.

8. The gas turbine system of claim 7, further comprising a heating system configured to produce the heated fluid.

9. The gas turbine system of claim 8, wherein the heating system comprises an induction heating system configured to heat the heated fluid.

10. The gas turbine system of claim 9, wherein the induction heating system comprises a coil configured to generate a magnetic field used to heat the heated fluid via electromagnetic induction.

11. The gas turbine system of claim 8, wherein the heating system comprises a heat recovery system that recovers heat generated via the gas turbine system, and wherein the heat recovery system is configured to produce the heated fluid.

12. The gas turbine system of claim 8, wherein the heating system comprises an external heating system comprising a solar energy storage, a mechanical energy storage, an electrical energy storage, or a combination thereof, and wherein the external heating system is configured to produce the heated fluid via the solar energy storage, the mechanical energy storage, the electrical energy storage, or the combination thereof.

13. The gas turbine system of claim 8, wherein the heating system is configured to heat the heated fluid to transform the heated fluid into the superheated fluid.

14. The gas turbine system of claim 1, further comprising a blend-trim oxidant- diluent delivery system configured to blend-trim delivery of the pressurized oxidant fluid, the pressurized diluent fluid, or a combination thereof, via an oxidant rich injection that is distributed, staged, or a combination thereof, and used to improve combustion, to reduce emissions, or a combination thereof.

15. The gas turbine system of claim 1, comprising an expander configured to expand a fluid for the generation of energy, wherein the control system is configured to direct a portion of the pressurized oxidant fluid into the expander to generate the energy.

16. The gas turbine system of claim 2, comprising a second expander configured to expand a second fluid for the generation of a second energy, wherein the control system is configured to direct a second portion of the pressurized oxidant fluid into the second expander to generate the second energy.

17. A method, comprising: operating a gas turbine system, the gas turbine system comprising: a pressurized fluid delivery system configured to deliver into a combustor system: a pressurized fuel fluid comprising a fuel; a pressurized oxidant fluid comprising an oxidant; and a pressurized diluent fluid comprising a diluent; an oxidant fluid discharge system configured to control a first flow of the pressurized oxidant fluid incoming from the pressurized fuel delivery system into the combustor system; a pressurized diluent injection system configured to control a second flow of the pressurized diluent fluid incoming from the pressurized fuel delivery system into an upstream diluted fuel rich combustion stage included in the combustor system, and into a downstream diluted oxidant combustion stage included in the combustor system, wherein the pressurized diluent fluid comprises a superheated fluid; and a control system configured to control delivery of the pressurized fuel fluid, the pressurized oxidant fluid, and the pressurized diluent fluid, and to control ignition of the pressurized fuel fluid with the pressurized oxidant fluid by controlling one or more fluid delivery rates of the pressurized fuel fluid, the pressurized oxidant fluid, the pressurized diluent fluid, or a combination thereof.

18. The method of claim 17, further comprising producing the superheated fluid via induction heating, via solar power, via wind power, via hydroelectric power, via a mechanical energy storage system, via an electrical power storage system, or a combination thereof.

19. The method of claim 17, further comprising blend-trimming a delivery of the pressurized oxidant fluid, the pressurized diluent fluid, or a combination thereof, via an oxidant rich injection that is distributed, staged, or a combination thereof, and used to improve combustion, to reduce emissions, or a combination thereof.

20. The method of claim 17, further comprising directing a portion of pressurized oxidant fluid from a gas turbine compressor system into a second combustor system used to drive an expander configured to expand a fluid for the production of energy.

21. A gas turbine system, comprising: a pressurized fluid delivery system configured to deliver into a combustor system: a pressurized fuel fluid comprising a fuel;a pressurized oxidant fluid comprising an oxidant; and a pressurized diluent fluid comprising a diluent; an oxidant fluid discharge system configured to control a first flow of the pressurized oxidant fluid incoming from the pressurized fuel delivery system into the combustor system; a pressurized diluent injection system configured to control a second flow of the pressurized diluent fluid incoming from the pressurized fuel delivery system into an upstream diluted fuel rich combustion stage included in the combustor system, and into a downstream diluted oxidant combustion stage included in the combustor system, wherein the pressurized diluent fluid comprises a heated fluid; and a control system configured to control delivery of the pressurized fuel fluid, the pressurized oxidant fluid, and the pressurized diluent fluid, and to control ignition of the pressurized fuel fluid with the pressurized oxidant fluid by controlling one or more fluid delivery rates of the pressurized fuel fluid, the pressurized oxidant fluid, the pressurized diluent fluid, or a combination thereof.

22. The gas turbine system of claim 21, wherein the combustor system comprises a scalable combustor comprising: a combusting chamber comprising: a first combusting chamber wall deposed axially and circumferentially; a radially opposed second combusting chamber wall; a plurality of fuel feeders comprising fuel orifices; and a plurality of oxidant feeders comprising oxidant orifices, configured about at least one of the first and second combusting chamber walls; an upstream flame authority; and a downstream combustor outlet, wherein the first and second combusting chamber walls are transversely elongated relative to a shallow spacing between the first and second combusting chamber walls, along directions transverse and perpendicular to a streamwise flow direction through the combustor, and wherein a ratio of transverse elongation to shallow spacing is greater than 1.15.

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