System and method for an expandable combustor

Abstract

A system and method for scalable combustion are provided. The scalable combustion system comprises a fuel fluid comprising fuel, an oxidizer fluid comprising an oxidizer; and a diluent fluid comprising a diluent, configured to deliver these into a combustion chamber in fluid communication with a fluid delivery system. The combustion chamber comprises a first combustion chamber wall and a second combustion chamber wall facing the first combustion chamber wall. The combustion chamber further comprises a plurality of orifices and combustion chamber outlets in at least one of the first and second combustion chamber walls. The first and second combustion chamber walls extend laterally along a direction transverse and perpendicular to the streamline flow direction passing through the combustion chamber, with respect to a shallow gap between the first and second combustion chamber walls.

Description

Technology Field

[0001] Claim of priority

[0002] This application was filed on November 8, 2023, and claims the benefit of priority of U.S. Provisional Application No. 63 / 547,814 titled “System and method for a scalable combustor,” the entirety of which is incorporated herein by reference.

[0003] Federally funded research and development

[0004] The present invention was made with U.S. Department of Energy High Performance Manufacturing (HPC4Mfg) grants from "Argonne National Laboratory, ANL Nos. A18179 and A21020" and "Lawrence Livermore National Laboratory, LLNL Nos. TC02306 and TC02380".

[0005] Joint research agreement

[0006] The present invention was made with government support under 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 retains the rights to the present invention.

[0007] Technology field

[0008] The present invention relates to a combustor or reactor system, and more specifically to an expandable combustor system. Background Technology

[0009] In certain combustion and power generation systems, such as conventional, eco-friendly, renewable, and / or sustainable energy systems, combustors are used to burn or react fuels useful for generating thermal energy. For example, a combustor can deliver and mix a fuel fluid containing fuel, an oxidizer fluid containing an oxidizer, and a diluent fluid containing a diluent, and combust a fluid mixture containing the fuel, oxidizer, and diluent to produce a working fluid containing useful thermal energy. The working fluid can then be used to generate heat and / or electricity through direct and / or indirect energy transfer, such as rotating a gas turbine system, heating, or cooling. It would be advantageous to improve such combustor systems, processes, and controls. Brief explanation of the drawing

[0010] FIG. 1a is an elevation view of a transversely extended vertical cubic "scalable combustor" having a fluid manifold that supplies to opposing combustor walls, according to some embodiments. FIG. 1b is a schematic detail of an upstream flame control mechanism in a cubic expandable combustor according to some embodiments. FIG. 1c is an elevation view of a combustion chamber and a blend-trim region within a cubic expandable combustor according to some embodiments. FIG. 1d is an elevation view of an upstream diluted oxidizer and downstream diluted oxidizer fluid manifold supplying to the first side of an adjacent combustion chamber and blend-trim area of ​​a cubic expandable combustor according to some embodiments. FIG. 1e is a detailed section of an insulated combustion chamber wall having a diluted fuel delivery orifice in a cubic expandable combustor according to some embodiments. FIG. 1f is a detailed section of an insulated combustion chamber wall having a diluted oxidizer delivery orifice in a cubic expandable combustor according to some embodiments. FIG. 1g is a detailed section of an insulated wall in a downstream blend-trim region having a diluted oxidizer and a diluent delivery orifice in a cubic expandable combustor according to some embodiments. FIG. 1h is an elevation view of an upstream diluted fuel and downstream diluted oxidizer fluid manifold in a vertical cubic expandable combustor supplying to a second side of an adjacent combustion chamber and blend-trim area, according to some embodiments. FIG. 1i is a plan view of a vertical cubic expandable combustor through plan A-A' according to some embodiments. FIG. 2a is a schematic diagram of an expandable combustor having a blower and a diluent delivery according to some embodiments. FIG. 2b is a perspective view of a horizontal cubic expandable combustor having a diluent spray and a common ignition control mechanism according to some embodiments. FIG. 2c is a detailed cross-sectional view of an insulated combustion chamber wall having a fluid transfer orifice according to some embodiments. FIG. 2d is a perspective view of a vertically oriented cubic expandable combustor section having downstream diluent delivery according to some embodiments. FIG. 2e is a perspective view of a vertically oriented cubic expandable segmented combustor section having multiple rich combustion delivery and intermediate diluent delivery according to some embodiments. FIG. 3a is an axial and transverse schematic diagram of an expandable gas turbine combustor according to some embodiments. FIG. 3b is an upstream view of a cylindrical expandable gas turbine combustor having a common pilot according to some embodiments. FIG. 3c is a detailed view of an insulated wall having a fluid transfer orifice in an expandable gas turbine combustor according to some embodiments. FIG. 3d is a radial circumferential outer cross-section of an expandable gas turbine combustor according to some embodiments. FIG. 3e is a circumferential axial view of a symmetric adjacent gas turbine combustion shell section according to some embodiments. FIG. 3f shows the axial combustor temperature, ammonia fuel, and NO according to some embodiments. x It is a graph of. FIG. 3g is a circumferential axial view of a symmetric gas turbine feeder manifold section according to some embodiments. FIG. 3h is a circumferential axial unfolded view of adjacent asymmetric gas turbine combustion shell sections having common adjacent oxidizer and fuel manifolds according to some embodiments. FIG. 3i is a circumferential axial view of an external asymmetric combustion blend-trim feeder according to some embodiments. FIG. 3j is an axial-circumferential detailed view of a fuel and oxidizer orifice offset axially and circumferentially from an outer feeder to a combustion chamber according to some embodiments. FIG. 3k is an axial-circumferential detail of fuel and oxidizer orifices offset axially and / or radially from an opposing feeder orifice from an inner feeder to a combustion chamber offset axially and / or radially, according to some embodiments. FIG. 3L is an axial and circumferential detail of a diluent and / or oxidizer orifice offset axially and circumferentially from the outer feeder(s) to the downstream combustor blend-trim area according to some embodiments. FIG. 3m is an axial-circumferential detail of a diluent and / or oxidizer orifice offset axially and / or circumferentially from a feeder orifice radially opposite from an inner feeder(s) to a combustor blend-trim area offset axially and / or radially, according to some embodiments. FIG. 3n is a radial-axial elevation view of the outer side of the counterclockwise wall of the radial outer combustion zone of a gas turbine expandable combustor according to some embodiments. FIG. 3o is a radial-axial elevation view adjacent inwardly to the counterclockwise outer wall of the outer combustion zone of a gas turbine expandable combustor according to some embodiments. FIG. 3p is a radial-axial elevation view adjacent inwardly to the clockwise outer wall of the outer combustion zone of a gas turbine expandable combustor according to some embodiments. FIG. 3q is a radial-axial elevation view of the clockwise wall outside the radial outer combustion zone of a gas turbine expandable combustor according to some embodiments. FIG. 3r is an axial-circumferential detail of the fuel and offset oxidizer delivery orifice spacing within a fuel and oxidizer feeder radially adjacent to an expandable combustion zone, according to some embodiments. FIG. 3s is an axial-circumferential detailed view of a fuel and aligned oxidizer orifice in a feeder adjacent to a combustion zone, according to some embodiments. FIG. 3t is a radial-circumferential detail of the fuel and oxidizer orifice orientation from an adjacent feeder to a combustion chamber according to some embodiments. FIG. 3u is a detailed radial-axial elevation view of fuel and oxidizer channels and orifices in outer and inner feeders adjacent to a radially outward combustion zone according to some embodiments. FIG. 3v is a radial-circumferential detailed view of an oxidizer orifice in the wall of a combustion chamber according to some embodiments. FIG. 3w is a radial-circumferential detailed view of an inclined oxidizer orifice within a combustion chamber wall according to some embodiments. FIG. 3x is a radial-circumferential detail view of an oxidant feeder closure end according to some embodiments. FIG. 3y is a radial-circumferential detail view of a fuel feeder closure end according to some embodiments. FIG. 4a is an axial and radial schematic diagram of a gas turbine system having an expandable combustor according to some embodiments. FIG. 4b is a perspective view of an upstream section of an annular expandable gas turbine combustor having a feeder including a multiple ignition control mechanism according to some embodiments. FIG. 4c is a detailed perspective view of an insulated wall having a fluid transfer orifice in an expandable gas turbine combustor according to some embodiments. FIG. 4d is a radial circumferential outer cross-section of an expandable gas turbine combustor according to some embodiments. FIG. 4e is a radial axial unfolded view of a symmetric adjacent gas turbine combustion shell section according to some embodiments. FIG. 4f shows the axial combustor temperature, ammonia fuel, and NO according to some embodiments. x It is a graph of. FIG. 4g is a radial axial view of a symmetric gas turbine feeder manifold section according to some embodiments. FIG. 4h is a radial axial view of adjacent asymmetric gas turbine combustion shell sections having common adjacent oxidizer and fuel manifolds according to some embodiments. FIG. 4i is a radial axial view of an outer asymmetric combustion blend-trim feeder according to some embodiments. FIG. 4j is a radial and axial detail of a fuel and oxidizer orifice offset axially and circumferentially from an outer feeder to a combustion chamber according to some embodiments. FIG. 4k is a radially and axially axially detailed view of a fuel and oxidizer orifice offset axially and / or radially from an opposing feeder orifice from an inner feeder to a combustion chamber offset axially and / or radially according to some embodiments. FIG. 4L is a radial and axial detail of a diluent and / or oxidizer orifice offset axially and circumferentially from the outer feeder(s) to the downstream combustor blend-trim area according to some embodiments. FIG. 4m is a radially axial detail of a diluent and / or oxidizer orifice offset axially and / or circumferentially from a feeder orifice radially opposite from an inner feeder(s) to a combustor blend-trim area offset axially and / or radially according to some embodiments. FIG. 4n is a radial axial elevation view of the outer side of the counterclockwise wall of the radial outer combustion zone of a gas turbine expandable combustor according to some embodiments. FIG. 4o is a radial axial elevation view adjacent inwardly to the counterclockwise outer wall of the outer combustion zone of a gas turbine expandable combustor according to some embodiments. FIG. 4p is a radial axial elevation view adjacent inwardly to the clockwise outer wall of the outer combustion zone of a gas turbine expandable combustor according to some embodiments. FIG. 4q is a radial axial elevation view of the clockwise wall outside the radial outer combustion zone of a gas turbine expandable combustor according to some embodiments. FIG. 4r is a radial axial detail of the fuel and offset oxidizer delivery orifice spacing within a fuel and oxidizer feeder radially adjacent to an expandable combustion zone according to some embodiments. FIG. 4s is a radial and axial detailed view of the fuel and aligned oxidizer orifices in the feeder adjacent to the combustion zone. FIG. 4t is a detailed radial and circumferential view of the fuel and oxidizer orifice orientation from an adjacent feeder to a combustion chamber according to some embodiments. FIG. 4u is a detailed radial circumferential elevation view of fuel and oxidizer channels and orifices in outer and inner feeders adjacent to a radially outward combustion zone according to some embodiments. FIG. 4v is a detailed radial and circumferential view of an oxidizer orifice in the wall of a combustion chamber according to some embodiments. FIG. 4w is a detailed radial circumferential view of an inclined oxidizer orifice within a combustion chamber wall according to some embodiments. FIG. 4x is a radial axial detail view of an oxidant feeder closure end according to some embodiments. FIG. 4y is a radial axial detail view of a fuel feeder closure end according to some embodiments. FIG. 5a is a circumferential-radial cross-section of a combustion chamber having a radial combustion region according to some embodiments. FIG. 5b is a circumferential-radial cross-section of a combustion chamber having a combustion region that forms a skew angle with respect to the radial axis, according to some embodiments. FIG. 5c is an enlarged perspective view of a combustion region forming a skew angle with respect to the radial axis according to some embodiments. FIG. 5d is a graph of the high gas temperature (T35) with respect to the combustor radius (R), from the temperature (T35i) at the inner radius (Ri) to the temperature (T35o) at the outer radius (Ro), at the downstream end of the fuel delivery zone at the axial position (CZ35), according to some embodiments. FIG. 5e is a graph of the high-temperature gas temperature (T4) with respect to the combustion radius (R), from the temperature (T4i) at the inner radius (Ri) to the temperature (T4o) at the outer radius (Ro), at the combustion outlet (CZ4), according to some embodiments. FIG. 5f is a graph of the high wall temperature (TW) with respect to the combustor axial length (Z), from the wall temperature (TW35) at the downstream end of the fuel delivery region (CZ35) to the wall temperature (TW4) at the combustor outlet (CZ4), according to some embodiments. FIG. 5g is a graph of the average high-temperature gas velocity (V4M) with respect to the combustor radius (R), from the inner velocity (V4i) at the inner radius (R4i) to the outer velocity (V4o) at the outer radius (Ro), at the combustor outlet (CZ4), according to some embodiments. FIG. 5h is a graph of the high-temperature gas temperature (T) for a circumferential angle theta (θ) of the combustor cooled near the downstream stator, having an inner temperature (Ti) at the inner radius (Ri) and an outer temperature (To) at the outer radius (Ro), from the first combustion section Theta1 (θ1) to the second clockwise combustion section Theta2 (θ2), according to some embodiments. FIG. 5i is a graph of the high-temperature gas temperature (T) for a circumferential angle theta (θ) of the combustor heated near the downstream stator, having an inner temperature (Ti) at the inner radius (Ri) and an outer temperature (To) at the outer radius (Ro), from the first combustion section Theta1 (θ1) to the second clockwise combustion section Theta2 (θ2), according to some embodiments. FIG. 5j is a graph of the hot gas velocity (V) for the circumferential angle theta of the combustor, with respect to the inner velocity (Vi) at the inner radius (Ri) and the outer velocity (Vo) at the outer radius (Ro), according to some embodiments, having a first counterclockwise combustion section cooled at Theta1 (θ1) and a second clockwise combustion section at Theta2 (θ2). FIG. 5k is a radial-axial cross-sectional elevation view of an expandable omega combustor equilibrium region according to some embodiments. FIG. 5L is a radial-axial plan view of an expandable combustor premix of fuel, oxidizer, and diluent according to some embodiments. FIG. 5m is a plan view of an ignition control mechanism external fuel and oxidizer feeder having fuel and oxidizer orifices into an intermediate combustion zone, according to some embodiments. FIG. 5n is a perspective view of an ignition control mechanism outside fuel and oxidizer feeder having fuel and oxidizer orifices into an intermediate combustion zone, according to some embodiments. FIG. 50 is a schematic plan view of an ignition control mechanism outside fuel and oxidizer feeder having fuel and oxidizer orifices into an intermediate combustion zone, according to some embodiments. FIG. 5p illustrates a fuel / oxidizer orifice within a top inner wall plan of an ignition control mechanism according to some embodiments. FIG. 5q is a mid-section plan view of an ignition control mechanism according to some embodiments. FIG. 5r illustrates a fuel / oxidizer orifice within a lower inner wall plan of an ignition control mechanism according to some embodiments. FIG. 5s is a schematic plan view of an internal fuel and oxidizer feeder of an ignition control mechanism having fuel and oxidizer orifices into an intermediate combustion zone, according to some embodiments. FIG. 5t is an enlarged schematic diagram of an igniter within the wall of a pilot combustion zone according to some embodiments. FIG. 5u is a radial-axial cross-section of a combustor wall fluid cooling capable of ammonia decomposition according to some embodiments. FIG. 5v is a radial inner versus outer temperature profile (T versus R) of the equilibrium zone flow temperature upstream of CZ39 and downstream of CZ4 according to some embodiments. FIG. 6a is a power versus temperature graph of a Brayton cycle and a VAST cycle according to some embodiments. FIG. 6b is a schematic diagram of the control system configuration of a controller subsystem according to some embodiments. FIG. 6c is a schematic graph of a control system having a control section according to some embodiments. FIG. 6d is a schematic graph of a control system having a sensor according to some embodiments. FIG. 6e is a schematic graph of low pilot and combustor temperatures, expander-generator speed, and power generation over time, showing flexible operation according to some embodiments. FIG. 6f is a schematic graph of high pilot and emergency combustor temperatures, expander-generator speed, and power generation over time, showing flexible operation according to some embodiments. FIG. 6g is a schematic graph of the combined flexible and emergency low and high pilot and combustor temperatures, expander-generator speed, and power generation over time, according to some embodiments. Specific details for implementing the invention

[0011] The delivery of fluids in conventional combustors is influenced by the capability of the combustor system and process used to spatially and / or temporally control the delivery of fuel (or reactants), oxidizers (or co-reactants), and diluent fluids. Combustion and emissions (or reactions and byproducts) are often affected by the distribution and velocity of conventional fluid delivery and mixing. These are typically limited by physical, thermal, and temporal devices, fluid design, delivery, cooling systems, control processes, and material thermal and strength constraints.

[0012] Micro to large Brayton gas turbines use nominally about 420% to 280% excess air to cool the combustion to acceptable turbine inlet temperatures (TITs) (in this specification, "TITs") above the range of about 1,000°C (1,832°F) to 1,500°C (2,732°F). This large volume of excess air flow increases the size and cost of the compressor, which is typically the most expensive component in a simple cycle gas turbine. Compressing and re-expanding this excess air fraction causes system losses in the Brayton turbine. The large volume of gas flow introduces uncertainty in TIT measurements.

[0013] Combustor systems (or reactor systems) deliver fluid through relatively few passages or orifices. Increasing fluid mixing typically results in a significant pressure drop, along with associated power losses, to achieve turbulence in the injected fluid. For example, gas turbine combustors can have a fluid flow pressure drop of 2.5% to 5% of the combustor inlet pressure, thereby reducing system output and efficiency while increasing compressor size and cost.

[0014] Reducing gas turbine emissions from high-temperature, lean-air diluted flames to specific levels (e.g., regulatory imposition levels) increases complexity and cost. Nitrogen oxides (NO, N2O, and NO2, collectively referred to herein as "NO x Brayton gas turbine emissions, such as (referred to as "...") and carbon monoxide (referred to as "CO" in this specification), are typically significantly higher than the limits stipulated by international and other jurisdictions. Certain large gas turbines emit NO x Inhibits production and NO x To ensure that catalytic emission purification remains below legal regulatory levels, operation may be limited to more than 50% of design output.

[0015] Commercial combustion spans up to magnitude 9, ranging from <1 watt to >1,000 MW turbine systems. However, combustor systems generally do not scale well. Combustion systems are more difficult to design with frequent shutdowns, across a wide range of varying temperatures, pressures, and power levels, as well as at rapid ramp-up rates.

[0016] Conventional or non-expanding combustors typically mix the volumes of heterogeneous fluids at pressures ranging from atmospheric pressure to above 4.5 MPa (44 atmospheres). High-performance gas turbines have a TIT limited by material strength and cooling capacity. For example, it is often below 1,500°C (2,732°F). Higher combustion temperatures typically result in NO xIt increases emissions. Conventional large simple-cycle (Brayton) gas turbines typically generate emissions with magnitudes that are orders of magnitude higher than strictly legally mandated emissions. For example, as in the state of California, USA, ~2.4 parts per million (referred herein to as "ppmvd" and O2) of NO diluted with 15% oxygen. x It is above the limits of legislation.

[0017] Combusting methane (referred to as "CH4" herein) or natural gas at higher temperatures typically increases CO and unburned hydrocarbon (referred to as "UHC" herein) emissions. x Emissions generally increase exponentially with temperature. Some gas turbines are designed with a TIT approaching 1,700°C (3,092°F), which is a potential NO x It will amplify emissions and increase CO emissions. NO x Reducing CO2 emissions typically involves catalytic reduction systems that increase system complexity and can cost between 4% and 7% of the installation capital. Reducing chemicals such as ammonia (referred to herein as “NH3”), along with pumping, maintenance, and catalyst replacement, generally adds to purification operating costs over the lifespan of the power generation system.

[0018] A very "dense" oxidant mixture with a high concentration of excess oxidant (e.g., air) NO x It has been used to reduce emissions. However, such lean operation can cause difficulties in maintaining combustion stability that approaches misfire. Combustion stability can limit the gas turbine's lower turndown ratio and minimum output. Operational variations in commercial natural gas delivery (e.g., differences in chemical composition and / or calorific value) have been reported to cause misfires, even leading to the shutdown of large gas turbines.

[0019] Conventional turbine combustion noise typically requires specific acoustic enclosures to meet legally mandated workspace or urban noise limits. Conventional enriched fuel delivery, particularly in conjunction with low-pressure gaseous fuel delivery, can generate violent combustion dynamics in the combustion system. Highly diluted diffusion flames operating near combustion stability limits can induce and amplify self-excited thermoacoustic instability. These factors make "noise" more difficult to control. Strong combustion acoustic resonance is known to increase regular and / or irregular maintenance activities for combustor liners, fatigue the combustor side, and mechanically deform combustor "cans."

[0020] Certain gas turbines may utilize a "Rich Quench Lean" combustion methodology featuring an initial fuel-rich combustion zone, an intermediate quenching zone, and a final lean combustion zone. Conventional inlet water injection, "fogging," or "humid" combustion results in gas turbine NO x Limited success was achieved in reducing emissions. Injecting water mixed with liquid kerosene caused quenching for mixtures having a water / kerosene mass ratio (omega) greater than 0.4 to 1.1 depending on the equivalent ratio.

[0021] Specific water and stream delivery efforts have degraded combustion performance, increasing CO and UHC emissions. For example, while ultrapure water can be used for water injection to reduce high-temperature deposits and corrosion, it can increase maintenance. This has been reported to increase system complexity and fuel consumption. The costs of such conventional water purification alone can be high.

[0022] Injecting the diluent from the outer wall of a cylindrical "can" combustor causes poor mixing and circulation, resulting in NO xThe reduction of can be limited. A higher steam fraction increases ignition delay and reduces laminar flame velocity. Quenching combustion can limit water and steam delivery in a typical Brayton gas turbine. Premixed fuel and oxidizer delivery increases the likelihood of combustion "flashback." Likewise, a higher flame velocity of hydrogen (referred to herein as "H2") can amplify flashback.

[0023] Efforts to transition to renewable fuels present challenges regarding cost-effective generation, delivery, storage, and use. The increasing use of renewable energy ("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"), can cause issues regarding combustion design, control, and durability. For example, the use of hydrogen increases the temperature within the combustion, extends flammability limits, and increases CO and NO x It can increase emissions such as

[0024] Ammonia (NH3) is generally available for agricultural use and is a leading candidate for renewable fuel. However, conventional ammonia combustion generally produces NO levels higher than legally mandated emission levels. x It generates. The low flame velocity of ammonia can further affect the combustion operating range. Breaking ammonia back into hydrogen and nitrogen typically requires additional equipment, heat, catalysts, and operating effort.

[0025] The increasing use of non-dispatched renewable power is rapidly increasing the frequency of backup power usage to maintain grid power frequency and minimize or prevent grid outages. Frequent, large-scale thermal cycling accompanied by high temperatures shortens the lifespan of insulation tiles within cylindrical "can" combustors and can additionally fatigue the combustor side.

[0026] Increasing ambient temperature typically reduces the power of conventional gas turbines. This results in a reduction in backup power capacity when cooling is most needed in high-temperature climates. For example, a Brayton cycle "peaker" gas turbine can lose about 13% of peak output and an additional 2.5% of efficiency as the ambient temperature increases by 25 Kelvin (degrees Celsius) from rated output under high ambient conditions of 15°C to 40°C (59°F to 104°F).

[0027] Higher combustion temperatures at peak output typically cause a sharp increase in blade creep, which reduces the effective lifespan of gas turbines. For example, in a conventional Brayton "peaker" gas turbine, the temperature increase alone as power increases from 70% to 100% can reduce the lifespan by approximately 300 times due to the rapid increase in creep associated with higher temperatures. A 10 Kelvin increase or decrease in TIT can halve or double the lifespan of some gas turbines. However, these high temperatures are difficult to accurately measure or control in conventional gas turbines.

[0028] Circulating power in conventional Brayton cycle turbines induces additional thermal creep along with higher cyclic strain fatigue. High TIT temperature sensors are negatively affected, which can lead to more frequent maintenance. Combustor failures result in unnecessary maintenance of the power system. Cooling of individual fuel injectors and combustor liners can cause combustor hot streaks that alter TIT and temperature distribution. Conventional combustion, its fluctuations, and higher TIT make it more difficult to accurately detect TIT temperatures.

[0029] Legislation requiring higher renewable energy levels is increasing the decommissioning of dispatchable coal-fired power generation systems. Higher renewable energy usage is increasing the use of standby power and backup gas turbines, along with more frequent starts and faster power ramps. Higher renewable energy usage is forcing additional combined cycle turbines to operate at lower annual capacity factors with more frequent power cycling. These trends are degrading grid resilience and reliability.

[0030] California’s 100 Percent Clean Energy Act of 2018 mandated the Renewable Power Standard (RPS), aiming for 60% of electricity to come from eligible renewable and carbon-free sources by 2030 and 100% by 2045. This legislated increase in renewable power is reducing the average annual consumption of combined-cycle baseload power. This reduced consumption, coupled with more frequent cycling, makes combined-cycle turbines more vulnerable to maintenance despite their higher efficiency and is reducing their availability. Increased cycling is similarly degrading peaker gas turbines and increasing backup costs.

[0031] The legislated increase in renewable power is expected to accelerate the "Duck Curve" of the rapid backup power demand ramp for the California Independent System Operator (CAISO). This ramp from afternoon peak solar to evening peak demand is projected to reach approximately 7,400 MW / hr (a rise of approximately 26,000 MW per 3.5 hours) on weekdays by 2030. Solar and wind supplied approximately 36% of CAISO's power in 2019.

[0032] Undispatched solar and wind power generation has already exceeded 97% of CIASO's demand. Due to the necessary decrease in reliable dispatchable generation, CIASO was left with a shortfall of 1,700 MW in its planned capacity for 2022. CIASO had to implement rolling blackouts during heatwaves in August 2020 and September 2022.

[0033] In addition to rapid 15-minute dispatch, CIASO has now added faster 5-minute dispatch. CIASO has even introduced 1-minute emergency dispatch to stabilize grid voltage and control grid frequency. The ramp-up rate for major combined cycle and industrial gas turbines was up to 8 hours to avoid turbine fatigue. Now, the ramp-up rate can be shortened from 30-minute dispatch to about 10 minutes for combined cycles, 5 minutes for industrial turbines, and even 2 minutes for aviation-derived turbines.

[0034] CAISO's increasingly frequent dispatching can induce higher thermal cyclic fatigue, which can shorten the lifespan of gas turbines and turbine blades. This requires more frequent inspections and overhauls, resulting in a significantly shorter service life. Consequently, the increased use of non-dispatching solar and wind power has raised California's retail electricity costs to approximately double that of other Western U.S. states.

[0035] Winter storm Uri in 2021 caused power outages on the Electric Reliability Council of Texas (ERCOT) grid. Renewable energy could not compensate for the failures in power generation and natural gas supply. In 2023, ERCOT warned, "On the hottest days of summer, there is no longer enough demand-driven dispatchable power generation to meet demand..."

[0036] The North American Electric Reliability Corp. (NERC) warns in its 2023 summer reliability assessment that two-thirds of North America is at risk of energy shortages accompanied by rolling blackouts during periods of extreme demand at summer peak temperatures and weak winds. Specifically, this applies to seven power regions: SPP and MISO (Western U.S.), ERCOT (Texas), SERC Central (particularly North and South Carolina), and NPCC (New England and Ontario).

[0037] The current trend of increasing non-dispatchable renewable power while reducing adequate rapid backup generation or storage capacity is increasing the likelihood of power outages. The U.S. Energy Information Agency (EIA) (2020) projected a loss of 46.5 GW in reliable electric capacity between 2022 and 2030 (a decrease of 72.3 GW and an addition of only 25.8 GW).

[0038] The U.S. Environmental Protection Agency's (EPA) 2023 "Proposed Rules for Greenhouse Gas Standards and Guidelines for Fossil Fuel-Burning Power Plants" aims to reduce or sequester 90% of CO2 emissions by 2030 from coal and natural gas power plants, which currently supply 20% and 40% of U.S. electricity, respectively. This could further reduce U.S. reliable electricity capacity.

[0039] Prolonged periods of low solar and wind power can lead to increased use of non-renewable power and / or energy storage to ensure grid reliability. For example, during Germany's dark and cold winter "Dunkleflaute" (windless period), there was a shortage of 18 days (27 TWh) of average load corresponding to wind and solar availability in 1996–1997. Germany's peak wind and solar power generation often drops to less than 3% of total demand during these windless periods.

[0040] This trend increases operation, maintenance, and refurbishment requirements, reduces availability, shortens system life, and NO in both simple Brayton cycle gas turbines and combined cycle (base load) gas turbines. x and can increase CO2 emissions. This trend may increase the need for cleaner and more reliable power with fast response rates, particularly for intermediate usage above peak loads and below conventional base loads.

[0041] Scalable Combustor Design and Operation

[0042] Accordingly, some technical features of the present disclosure lead to a reactor that delivers reactants and an oxidizer, burns them cleanly, and, in some embodiments, adds a diluent fluid. The technology described herein comprises a combustor that burns fuel with an oxidizer (e.g., air or oxygen) and may add a diluent, such as water, carbon dioxide, nitrogen, or excess oxygen, in any phase and / or combination, which is scalable over a wider range of commercial combustor pressures, temperatures, and / or output levels, thereby improving power system capabilities and economics.

[0043] The described technology designs the combustor to be further scalable for a wider operating range with fuel, oxidizer, and diluent types, combinations, and loads in gas turbine systems, enabling more reliable grid operation and backup with major intermittent non-fedable renewable power supply rates.

[0044] Technology can extensively expand combustor designs based on power. For example, it provides a range greater than the average power per combustion shell, ranging from 10:1 to 25:1 or even wider, and increases design capabilities and economics by using multiple shells.

[0045] Diffusion area

[0046] Diffusion zone technology involves changing the delivery of liquid and / or gaseous diluents through multiple orifices into an upstream fluid delivery zone, which improves fluid delivery rates, liquid evaporation, and / or combustion.

[0047] Pilot Ignition

[0048] The technology involves providing a diluted fuel-rich pilot to provide cleaner ignition for downstream fluid delivery, which includes NO x Initiates reliable combustion while reducing the generation of emissions.

[0049] Combustion zone manifold and feeder

[0050] The technology further includes providing an oxidizer-rich manifold and a fuel-rich manifold laterally adjacent to one or more combustion chambers, which improves scalability, mixing, combustion, and economy.

[0051] The technology includes providing a diluent manifold or duct adjacent to an oxidizer or fuel manifold, mixing gaseous and / or liquid diluents with oxidizer and / or fuel, and delivering the mixed fluid through an orifice, which facilitates fluid mixing and delivery.

[0052] The technology includes providing a diluted oxidizer-rich manifold between adjacent combustion chambers vertically or transversely, which reduces the number of oxidizer manifolds and improves manufacturability and economic efficiency.

[0053] The technology includes providing a diluted fuel-rich manifold between adjacent combustion chambers vertically or transversely, which reduces the number of fuel manifolds and improves manufacturability and economic efficiency.

[0054] Combustion chamber

[0055] The technology includes providing an upstream combustion chamber with a transversely extended distribution having a transverse width to vertical (or radial) depth ratio greater than 1.15 perpendicular to the flow axis, and providing fuel, oxidizer, and diluent fluid delivery through the extended walls, which improves fluid mixing into and / or within the combustion chamber.

[0056] The technology involves adjusting an inclined orifice that is transverse to the fluid flow relative to the normal of the combustion chamber wall surface, which improves the mixing of the combustion fluid.

[0057] The technology includes adjusting the number of fuel and oxidizer fluid delivery orifices distributed laterally through the opposing shallowly displaced sides of the combustor as a function of the axial distance from upstream to downstream, which improves combustion fluid mixing and combustion reliability.

[0058] The technology involves laterally offsetting the oxidizer-rich fluid orifice relative to the fuel-rich fluid orifice, which improves fluid mixing.

[0059] The technology involves changing or reducing the upstream diluent / oxidizer and / or diluent / fuel ratio for high-temperature pilot fluid delivery and / or downstream combustor orifices, which improves upstream combustibility and extends the combustion delivery limits.

[0060] Combustion quenching, stability, and flashback

[0061] The technology involves delivering a fuel-rich fluid through an adjacent transverse fuel feeder and delivering an oxidizer-rich fluid through a separate adjacent transverse oxidizer feeder to the combustion chamber through respective orifices, which improves combustion fluid mixing and reduces the risk of quenching or flashback.

[0062] The technology improves reliability and competitiveness by configuring the upstream transverse width to axial length profile of one or more combustion chambers within the goals of combustion stability, manufacturability, and aerodynamic flow efficiency.

[0063] Blend-Trim Area

[0064] The technology involves controlling residual diluent delivery and mixing in the blend-trim region to axially control the cumulative diluent-to-fuel mass ratio omega, which establishes an axial combustion and equilibrium temperature profile and reduces emissions below prescribed regulatory levels.

[0065] The technology involves controlling residual oxidizer delivery and mixing in the blend-trim region to control the cumulative relative oxidizer-to-fuel mass stoichiometric ratio lambda axially and / or transversely, which constitutes axial and / or transverse combustion and equilibrium oxidizer profiles and reduces emissions below prescribed regulatory levels.

[0066] Expandable pilot combustor

[0067] The technology additionally provides control of the upstream pilot combustion zone temperature, which is greater than or equal to the atmospheric ignition temperature of the downstream combustion chamber diluted fuel-oxidizer mixture, thereby improving pilot reliability.

[0068] The technology can improve combustion scalability, range, ramp rate, and / or reliability by providing multiple upstream pilot chambers that supply each scalable combustion chamber or area.

[0069] Combustor outlet temperature control and expansion

[0070] The technology can further improve the control of the combustor outlet temperature (COT) or turbine inlet temperature (TIT), reduce outlet temperature fluctuations, and / or reduce outlet temperature uncertainty.

[0071] The technology may include configuring fluid transfer to control the diluent-to-fuel mass ratio omega along with the relative oxidant-to-fuel ratio lambda across multiple orifices, which extends combustor designs over a wide temperature range, such as between about 700°C and 2,500°C, for commercial combustors and / or gas turbines.

[0072] The technology can control the fuel, oxidizer, and / or diluent fluid transfer rate (MW / m3-atm) per combustor volume and provide mainly axial laminar flow within the combustor, which improves transverse combustor outlet or turbine inlet temperature (TIT) control, expander durability, and economics.

[0073] NO x and scalable control of CO2 emissions

[0074] The technology is NO compared to conventional combustors x It provides designing the combustion fuel and / or oxidizer space fluid transfer rate to substantially reduce CO and NO emissions. In some configurations, these produce NO below legally mandated emission limits. x and can transfer CO emissions, for example, NO x and / or CO is 75 ppmvd or less.

[0075] The technology uses the thermal diluent space fluid transfer rate to control the combustor outlet temperature within the range of 500°C to 2,500°C while NO x It additionally includes reducing CO emissions, which increases application, thermal efficiency, and / or economics, for example, by controlling the H2O, CO2, N2, O2, and / or other diluent-to-fuel mass transfer ratio omega for omega greater than about 1.15 (or the corresponding enthalpy transfer ratio), and using lower amounts of catalyst and reducing agent than Brayton turbines.

[0076] Further technical and advantageous aspects of the present invention will become apparent from the considerations in the drawings and the following description.

[0077] Summary of the present disclosure

[0078] The technology described herein includes scalable ultra-clean combustion (or chemical reaction) and equilibration equipment, configurations, and processes. These can progressively deliver and burn a mixture of fuel, oxidizer, and thermal diluent along an axial flow direction. Such technology can deliver fluids through one or more fuel, oxidizer, and diluent fluid manifolds and through numerous fuel, oxidizer, and / or diluent orifices to one or more upstream combustion chambers and downstream blend-trim regions.

[0079] The technology described herein may include one or more upstream transversely elongated combustion chambers having combustion chamber walls separated relatively shallowly with respect to the axial flow direction (referred to herein as “transversely elongated”). The combustion technology may generally constitute a closed cross-sectional combustion area that increases along the axial flow direction. The technology may maintain the combustion temperature above the quench limit by configuring the fluid composition within the combustion zone, preferably while providing upstream fuel-rich conditions.

[0080] This technology can distribute a number of fuel fluid (or reactive fluid) orifices and oxidizer fluid (e.g., co-reactant fluid such as air or oxygen) orifices across a shallowly separated combustion chamber side that extends laterally. Fuel and / or oxidizer fluids can be supplied from respective fuel and / or oxidizer manifolds to the fuel and oxidizer fluid orifices.

[0081] Additional technology may configure a downstream blend-trim region having a similar transversely extended wall that is transversely configured and has a shallow gap perpendicular to the axial fluid flow axis. Blend-trim technology may similarly configure the delivery of oxidizer and / or diluent through multiple orifices within a transversely extended, shallowly spaced wall around the combustion flow. This technology may further enable combustion, control the combustor axial and outlet temperature(s), and control emissions (or byproducts).

[0082] The technology may further mix the diluent fluid with the fuel fluid, oxidizer fluid, and / or blend-trim oxidizer fluid and deliver it to the combustion chamber and / or blend-trim zone through respective fuel, oxidizer, and / or blend-trim orifices. Similar technology may use an upstream flame control mechanism containing fuel, oxidizer, and diluent with rich primary combustion and downstream oxidizer and diluent trim, where the combustion temperature is similarly limited to provide reliable combustion while limiting emissions.

[0083] These technologies can vary the composition of fuel, oxidizer, and / or diluent delivered to the upstream versus downstream combustion and / or blend-trim zones. These combustion and blend-trim zones can be replicated to expand the combustor (or reactor) to provide the desired combustion power (or reaction rate) while achieving improved mixing and low emissions (or byproducts).

[0084] Referring to FIGS. 1a and 1b, the combustion fluid temperature in the upstream combustion chamber (740) and / or downstream blend-trim area (850) can be controlled by controlling one or more of the ratio of the diluent fluid (F7) to the fuel fluid (F1), the ratio of the diluent fluid (F7) to the oxidizer fluid (F4), and / or the ratio of the diluent fluid (F7) to the blend-trim oxidizer fluid (F4) in the diluent fluid delivery (F2), upstream diluent fluid delivery (F5), and / or downstream blend-trim diluent fluid delivery (F15), and the diluent fluid (F7), and / or the liquid diluent fluid (F14) delivered to the blend-trim area. The cross-sectional area (XY axis) of the combustion chamber (740) is gradually increased along the axial fluid flow direction (Z axis) to gradually increase the combustion chamber volume and accommodate gas expansion from the increasing temperature. This can advantageously reduce axial fluid acceleration and fluid pressure drop across the combustor.

[0085] An upstream diluted ignition control mechanism or pilot (720) may be configured to provide a diluted pilot flame (F22) to reliably ignite the downstream fuel fluid (F2) and the diluted oxidizer fluid (F5). This may include controlling the pilot combustion temperature and pilot combustion emissions resulting from the pilot fluid (F22). A downstream diffuser (429) may be used to reduce the axial combustion fluid pressure drop while providing additional combustion (or reaction) residence time to reduce unburned fuel and combustion (or reaction) emissions such as oxides of carbon monoxide and nitrogen.

[0086] Referring to FIGS. 2a through 2e, the combustion fluid oxidizer concentration (or oxidizer-to-fuel ratio) within the combustion zone (740) may vary between the upstream combustion zone (742) and the downstream combustion zone (744). The order and magnitude of the residual oxidizer fluid and / or residual diluent fluid may vary in the blend-trim zone (850). For example, they may vary between the upstream blend-trim zone (852) and the downstream blend-trim zone (854).

[0087] details

[0088] Scalable Combustor Design and Operation

[0089] Specific embodiments of an expandable reactor or expandable combustor (700) are illustrated in FIG. 1a and further described in detail in FIG. 1b through 1i. These embodiments represent one or more transversely extended shallow combustion chambers (740) within a combustion section (730) that is disposed between the proximal and distal side feeder walls (737) and is shallowly spaced apart (along the Y-axis) at reference numeral (737), and is bounded transversely (along the X-axis) with respect to the longitudinal axial flow direction (along the Z-axis) by a combustion chamber proximal end wall (734) and a distal end wall (735) that are perpendicular to the longitudinal axial flow direction (along the Z-axis) from an upstream inlet region (134) to a downstream outlet (136).

[0090] Further embodiments of an expandable reactor or expandable combustor (706) having a combustion section (730) are illustrated in FIG. 2a and further described in detail in FIG. 2b through 2e. A blower (406) (BLW) may be used to compress an intake air or oxidizer mass flow rate (WX2) containing an optional liquid diluent (F7) into a pressurized oxidizer mass flow rate (WX3) and deliver it to the inlet of a diffuser (420) at an axial position (CZ31). This configuration may include an upstream diluent delivery section (710) comprising a diluent delivery spray system (24), an ignition section (720) comprising an ignition control mechanism or pilot (100), a combustion zone (740), a blend-trim zone (850) for additional oxidizer and diluent delivery, and an equilibrium zone (750). These can deliver a high-temperature fluid flow (W4) exiting the combustor (706) after the end of the equilibrium zone (750) in CZ 394.

[0091] Transversely extended porous combustor sidewall

[0092] A specific embodiment of the cubic configuration of an expandable reactor or combustor (700) is illustrated in FIG. 1a and further described in detail in FIG. 1b through 1i. In one embodiment, a rectangular expandable reactor or combustor (700) may be formed by creating one or more transversely extended shallow reaction zones or combustion chambers (740) in the upstream combustion section (730) of the expandable reactor or combustor. An embodiment of FIG. 1a, including the detailed view in FIG. 1b, shows an expandable combustor (700) oriented in a direction having an upstream inlet region (134) near the upstream combustor end wall (241) having an upstream pilot chamber (720). The expandable combustor (700) has a downstream combustor outlet (136) at the downstream combustor end (or top in the Z direction).

[0093] In this embodiment, the expandable combustor (700) is configured with a flow direction that follows a generally upward vertical direction (similar to the vertical Z-axis), from the upstream pilot fluid (F22) flow at the upstream inlet (134) to the high-energy fluid (F20) exiting the combustor outlet (136). In another embodiment, the flow axis of the expandable combustor (700) may be oriented horizontally, downward, or at some intermediate angle.

[0094] According to FIG. 1a, in this embodiment, the upstream combustion section (730) may generally include one or more extended shallow reaction or combustion chambers (740) that extend in the transverse direction (X-axis). In this embodiment, this is generally depicted as perpendicular to the main axial flow direction (along the Z direction). Correspondingly, these one or more combustion chambers (740) may generally be shallowly displaced in a normal direction (Y-axis) perpendicular to the transverse elongation direction (typically perpendicular to both the axial flow in the Z-axis and the transverse X direction).

[0095] Correspondingly, FIGS. 2B, 2D, and 2E describe in detail this expandable reactor configuration (706) illustrated herein in a similar cubic configuration. FIGS. 2B, 2D, and 2E similarly illustrate a combustion section (730) having a combustion chamber (740) bounded by an oxidizer feeder porous wall (737) extending laterally ("distal" side) and a fuel feeder porous wall (736) extending laterally ("proximal" side) of the opposing combustion chamber.

[0096] Similarly, according to FIG. 2d and FIG. 2e, the combustion chamber (740) may be further composed of an upstream combustion chamber (742) and a downstream combustion chamber (744). The upstream combustion chamber (742) may be bounded by an upstream porous fuel feeder (805) having an orifice (81) and an upstream porous oxidizer feeder (815) having an orifice (82). The downstream combustion chamber (744) may be bounded by a downstream porous fuel feeder (806) having an orifice (81) through a fuel feeder wall (736) and a downstream porous oxidizer feeder (816) having an orifice (82) through an oxidizer feeder wall (737).

[0097] Transverse end wall of the combustion chamber

[0098] Additionally, according to FIG. 1a, this transversely extended shallow combustion chamber (740) can generally be configured between a combustion chamber-side fuel feeder wall (736) and an oxidizer feeder wall (737) of corresponding size that are similarly transversely extended along the X direction. The combustion chamber (740) between these extended combustion-side fuel feeder walls (736) and the oxidizer feeder (737) can be transversely bounded by combustion chamber boundary end walls along the transverse X direction. These transverse end boundaries typically include a combustion chamber proximal end wall (734) (negative X direction) and a combustion chamber distal end wall (735) (positive X direction).

[0099] Additionally, according to the perspective views of FIG. 2d and FIG. 2e, a transversely extended shallow combustion chamber (740) having a combustion chamber-side feeder porous wall (736 and 737) may be transversely bounded by a combustion chamber boundary end wall, such as an end wall (734) similar to that shown in FIG. 1a, FIG. 1c and the elevation view FIG. 1d.

[0100] Shallowly separated combustion chamber sidewalls

[0101] According to FIG. 1a, the extended distal feeder wall (737) and the proximal feeder wall (736) may be separated by a shallow gap depth (748) in the Y direction which is perpendicular (normal) to both the axial flow and the transverse X direction. This shallow gap depth (748) may separate the proximal end wall (734) from the distal end wall (735) and separate the proximal feeder wall (736) and the distal feeder wall (737) relatively closer in the vertical Y direction than the transverse extension width (746) that delineates the combustion chamber (740) extended along the transverse X direction. This shallow separation gap (748) or vertical (normal) combustion chamber depth between the extended side feeder walls (736 and 737) demarcating the combustion chamber (740) may be provided by the corresponding shallow separation depth of the proximal boundary wall (734) and the distal boundary wall (735) separating the proximal side feeder wall (736) and the extended distal side feeder wall (737) along the Y-axis perpendicular to the Z-flow axis.

[0102] Combustion section manifold and duct

[0103] Opposing fuel and oxidizer ducts

[0104] Referring to FIG. 1d, which is an elevation view of the fuel fluid transfer, FIG. 1e, which is a cross-sectional view of the fuel fluid wall, FIG. 1f, which is a cross-sectional view of the oxidant fluid wall, and FIG. 1h, which is an elevation view of the oxidant manifold, in one embodiment, a separated fuel-oxidant expandable combustor may be formed to have at least one first fluid or fuel manifold (770) configured to transfer a first fuel fluid (F1) containing a fuel fluid (and / or reactant fluid) to one or more porous fuel feeders (750) (or first fluid reactant porous transfer ducts) as shown in FIG. 1d and FIG. 1i. As illustrated in FIG. 1a, FIG. 1c, FIG. 1h and FIG. 1i, these embodiments may include at least one second fluid or oxidizer manifold (780) configured to deliver a second oxidizer fluid (F4) containing an oxidizer fluid (or a second co-reactant) through an oxidizer manifold (780) to one or more porous second fluid or oxidizer delivery ducts or oxidizer feeders (760), wherein the oxidizer feeders (760) have a plurality of oxidizer orifices (82) for delivering the second oxidizer fluid (F4) to a combustion chamber (740).

[0105] Referring further to FIG. 1d and FIG. 1e, which are elevation views of fuel fluid delivery, in some configurations, a first fuel fluid (F1) may be mixed with a third diluent fluid (F7) to form and deliver a diluted fuel fluid (F2) to be delivered to a fuel manifold (770) and therefrom to a porous fuel feeder (750) (or porous reactant delivery duct). A second oxidant fluid (F4) comprising an oxidant fluid and / or co-reactant fluid may be diluted with the diluent fluid (F7) to form a diluted oxidant (and / or co-reactant) fluid (F5) to be delivered to an oxidant manifold (760).

[0106] As illustrated in FIG. 1a, a perspective view of the combustor; FIG. 1d, an elevation view of the fuel fluid transfer; FIG. 1h, an elevation view of the oxidizer fluid transfer; and FIG. 1i, a plan view of the combustor, a diluted first fluid or fuel fluid (F2) can similarly be transferred from the fuel manifold (770) to a porous fuel feeder (750) adjacent to the combustion chamber(s) (740). Similarly, a diluted second fluid, a diluted oxidizer (or co-reactant) fluid (F5) can be transferred from the oxidizer manifold(s) (780) to an oxidizer fluid feeder (porous duct(s)) (760) adjacent to the combustion chamber(s) (740).

[0107] As illustrated in FIG. 1i, which is a plan view of the combustor, the central combustion / feeder area (739) may include one or more fuel feeders (750) having porous adjacent fuel feeder wall(s) (736), and one or more oxidizer feeders (760) (porous second fluid ducts) having porous distal oxidizer feeder wall(s) (737). These fuel feeders (750) and oxidizer feeders (760) may form a combustion chamber (or zone(s)) (740) adjacent between the opposing fuel feeders (750) and oxidizer feeders (760), and are bounded by porous fuel feeder wall(s) (736) and oxidizer feeder wall(s) (737), and combustion chamber end wall(s) (734 and 735).

[0108] Referring to FIG. 1e, FIG. 1f, FIG. 1g and FIG. 1i, the fuel fluid orifice (81), oxidant fluid orifice (82), and blend-trim oxidant port or orifice (83) within each proximal fuel feeder wall (736) and distal oxidant feeder wall (737), blend-trim oxidant proximal feeder wall (856) and blend-trim oxidant distal feeder wall (857) may be configured to provide a distribution of one or more fluid port diameters and port spacings along the streamline flow direction. These may be configured to provide a desired streamline distribution of fuel fluid and oxidant fluid delivery to achieve a desired streamline composition distribution of high-energy fluid within a plurality of streamline reaction zones.

[0109] Similarly, as illustrated in FIG. 2d, which is a perspective view of a combustion chamber, a fuel fluid orifice (81) and an oxidizer fluid orifice (82) may be configured in the fuel feeder wall (736) and the oxidizer feeder wall (737). These deliver the fuel fluid (F2) through the diluted fuel feeder (804) and the oxidizer fluid (F5) through the diluted oxidizer feeder (814) to the combustion chamber or area (740).

[0110] As illustrated in FIG. 2e, which is a segmented combustor, upstream and downstream fuel and oxidizer fluid delivery feeders may be configured to supply fuel and oxidizer fluids having different diluent compositions to an upstream combustion zone (742) and a downstream combustion zone (744). For example, a fuel fluid (F1) may be delivered to an upstream combustion chamber(s) (742) via a porous fluid delivery feeder (805) through a fuel orifice (81). Similarly, a diluted fuel fluid (F2) may be delivered to a downstream combustion chamber(s) (744) via a downstream fuel fluid delivery feeder (806) through a fuel orifice (81).

[0111] Correspondingly, the oxidizer fluid (F4) can be delivered to the upstream combustion chamber (742) via the upstream porous oxidizer fluid delivery feeder (815) through the oxidizer orifice (82). Similarly, the diluted oxidizer fluid (F5) can be delivered to the downstream combustion chamber (744) via the downstream oxidizer fluid delivery feeder (816) through the oxidizer orifice (82).

[0112] Additionally, referring to FIG. 2e, in a similar configuration, the upstream and downstream fuel fluids (F1 and F2) may contain different diluent compositions. For example, the diluent-to-fuel ratios omega1 and omega2 of the fuel fluids (F1 and F2) may be configured differently in the upstream porous fuel feeder (805) versus the downstream porous fuel feeder (806). This allows the temperature of the upstream combustion zone (742) versus the downstream combustion zone (744) to be controlled differently according to the degree of diluent in the fluid composition.

[0113] Similarly, the upstream and downstream oxidizer fluids (F4 and F5) may contain different degrees of diluent-to-oxidizer composition. These fluids may be configured to control the relative oxidizer-to-fuel ratio with respect to the theoretical oxidizer-to-fuel ratio lambda of F4 in the upstream oxidizer feeder (815) entering the upstream combustion zone (742) differently from the relative oxidizer-to-fuel ratio lambda of the diluted oxidizer fluid (F5) in the downstream oxidizer feeder (816) entering the downstream combustion zone (744). This controls the combustion zone abundance (relative oxidizer-to-fuel ratio) and thus allows the fuel combustion or oxidation rate in the upstream combustion zone (742) to be controlled differently from that in the downstream combustion zone (744).

[0114] The separated fuel-oxidizer combustor may be configured with a shallow combustion chamber (740) (e.g., a rectangular configuration) that extends generally laterally between opposing porous duct sides (or liners) and an axial configuration along the fluid flow.

[0115] Referring further to FIG. 1a, FIG. 1c, FIG. 1d and FIG. 1h, the expandable combustor (700) may be configured to have a downstream transversely expanding (or hand "fan") shaped combustion chamber (740) between transversely bounding end walls (734 and 735) (in the X direction) and between shallowly separated side feeder walls (736 and 737), which generally has a fluid flow that increases transversely to the fluid flow (in the X direction), along the streamline flow direction (along the Z axis), and gradually increases.

[0116] This expandable combustor can be configured such that the cross-sectional area of ​​the combustion (or reaction) zone increases with increasing axial distance along the flow direction. Opposing fuel fluid and oxidizer fluid transfer through porous fuel and oxidizer feeders may include individually mixed ratios of diluents as desired to achieve the desired axial temperature distribution. The efficiency of the Thermal Barrier Coating (TBC) can be adjusted to configure the rate of heat transfer from the reaction zone to the fluid in one or both adjacent ducts (or the TBC can be removed).

[0117] Downstream blend-trim area

[0118] According to FIGS. 1a and 1c, a blend-trim section (426) comprising a blend-trim area (850) may be configured downstream of a combustion section (730) comprising a combustion chamber (740). This blend-trim area (860) may deliver one or both of an additional oxidizer fluid (F4) and / or an additional diluent fluid (F7). These oxidizer fluid (F4) and diluent fluid (F7) may be mixed, such as by delivering a diluted second reactant fluid or a diluted oxidizer fluid (F5) to the blend-trim area (860).

[0119] According to FIGS. 1d and 1h, the blend-trim region may begin axially at an adjacent upstream blend-trim manifold boundary wall (248) that separates fluid delivery to the upstream combustion chamber (or region) (740) from diluted oxidant fluid delivery to the downstream blend-trim region (850). The blend-trim region (850) may extend to the downstream blend-trim manifold and blend-trim feeder boundary wall (249).

[0120] The blend-trim area of ​​FIG. 1a further illustrates a portion of the downstream blend-trim area proximal sidewall (856) and blend-trim area distal sidewall (857) that extend laterally between the transversely bounding proximal end wall (734) and the transversely bounding circular end wall (735) (or between the counterclockwise wall (250) and the clockwise wall (251)) as illustrated in FIG. 1d and FIG. 1h. The downstream blend-trim area sidewall (856) and sidewall (857) may further extend between the axial boundaries of the blend-trim area upstream wall (248) and the blend-trim area downstream wall (249).

[0121] Referring to FIG. 1a, FIG. 1g and FIG. 1i, the blend-trim oxidizer ports or orifices (83) within the blend-trim oxidizer proximal feeder wall (856) and the equivalent blend-trim oxidizer distal feeder wall (857) may be configured to provide one or more fluid port diameters and port spacings, respectively, along the streamline flow direction. These may be configured to provide a desired streamline distribution of oxidizer fluid delivery and / or optional diluent fluid delivery to achieve a desired streamline composition distribution of high-energy fluid within a plurality of streamline reaction zones.

[0122] Boundary distance between transverse end walls

[0123] As illustrated in FIGS. 1a, 1c, 1d and 1h, in the upstream combustion section (730), the combustion chamber (740) has a transverse width (746) along the transverse X direction between the transverse proximal end wall (734) and the transverse distal end wall (735) that delineate the combustion chamber (740). This combustion chamber transverse width (746) generally increases along the Z-axis flow direction within the combustion section (730) from the upstream combustor inlet (or pilot outlet) (134) near the upstream combustor end wall (241), and increases progressively with downstream distance along the Z-flow direction.

[0124] As illustrated in FIGS. 1a, 1c, 1d and 1h, in the downstream blend-trim region (426), the blend-trim flow region (850) has a transverse boundary separation or combustion transverse width (746) between the proximal boundary end wall (734) and the distal boundary end wall (735). This transverse boundary width (746) may be further increased in the transverse X direction between the upstream blend-trim region manifold boundary (248) and the corresponding downstream blend-trim region boundary (249), and within the blend-trim fluid delivery region (426) of the downstream combustion chamber (740). In other configurations, the transverse boundary width (746) may be significantly uniform in the blend-trim region (426).

[0125] As additionally illustrated in FIG. 1c and FIG. 1i, in some configurations of the combustion section (730), the transverse end walls (734 and 735) may be composed of an upstream convex wall section (731), which provides a boundary separation width (746) that increases non-linearly between these transverse boundary walls. Similarly, according to FIG. 2d and FIG. 2e, the upstream transverse end walls (734) (and 735, not shown) may be composed of an upstream curved convex end wall section (731) having a radial versus axial slope that increases with downstream axial distance.

[0126] As additionally illustrated in FIG. 1c, the convex end wall section (731) of the boundary combustion section (730) may be followed downstream by an end wall section (732) having a maximum slope (or low curvature) of transverse increase with respect to axial distance. Similarly, according to FIG. 2d and FIG. 2e, the combustion section (740) may be axially demarcated by an end wall section (732) having a maximum slope of transverse increase with respect to axial distance or a similar section having low radial versus axial curvature.

[0127] These maximum slope end wall sections (732) within one or both of the boundary end walls (735 and / or 734) may be configured to provide a low curvature (or significantly linear) increase in the transverse boundary separation between these boundary end walls. These maximum slope (low curvature or significantly linear) sections may be utilized to accommodate overhang slope limitations in the 3D printing fabrication of these boundary end walls. For example, this is when 3D printing may be used to form the boundary end walls (735 and / or 735) when the combustion Z-axis is in the vertical gravity direction.

[0128] Similarly, according to FIG. 2d and FIG. 2e, the boundary end wall (734) (and similarly boundary end wall (735)) of the combustion section (740) may similarly have a maximum radial to axial inclination (732) having a significantly linear radial to axial inclination (or low curvature).

[0129] Additionally, according to FIG. 1c, in a portion of the combustion section (730), the transverse boundary end walls (734 and 735) may further form a downstream concave wall section (733) downstream of a largely linear boundary end wall section (732). This downstream generally concave and transversely boundary end wall section (733) provides a non-linear section having a boundary separation width (746) between these transverse boundary walls that further increases along the axial Z flow direction.

[0130] These concave nonlinear boundary end wall sections (733) within one or both of the boundary end walls (735 and / or 734) may be configured to provide a reduction rate of increase along the axial Z flow direction. This reduction rate of increase in the boundary separation having reference numeral (746) between the boundary end walls (735 and 734) may advantageously improve the expansion fluid dynamics in one or both of the combustion chamber (740) and the blend-trim transition region (850).

[0131] Similarly, according to FIGS. 2d and 2e, the boundary end wall (734) (and similar end wall (735)) of the combustion section (740) may similarly be configured with a downstream concave radially-to-axial sloped wall section (733) downstream of the transition boundary end wall section (732) having the maximum slope. The radially-to-axial slope of the boundary section (733) decreases toward zero curvature bordering the downstream blend-trim section (852) and can be connected thereto to the downstream equilibrium section (750). This advantageously reduces the transition turbulence and combustor pressure drop from the upstream combustor inlet (CZ31) to the combustor outlet (CZ394) according to FIG. 2a.

[0132] As illustrated in FIG. 2b, a diluent delivery section (710) near the inlet (134) may include delivering an oxidant fluid (F4) through an upstream oxidant manifold (242) and discharging it through a plurality of porous oxidant feeders (11) distributed across the upstream area. Similarly, a distributed fuel delivery system may inject a diluent (F7) through a downstream fuel manifold (244) and discharge it into the oxidant fluid (F4) entering through distributed porous oxidant feeders (14).

[0133] Pilot light or ignition control device

[0134] As schematically illustrated in FIG. 1b, which is an upstream enlarged view, the combustion chamber (740) may have an upstream pilot light, ignition source, or flame control mechanism (720), such as near the upstream end wall (241) of the combustor. The ignition source (720) may form a diluted high-temperature pilot flow (F22) at the pilot outlet flowing into the adjacent combustion chamber (740).

[0135] According to the schematic diagram in FIG. 2a, the combustion chamber (740) may have an upstream flame holder or ignition control mechanism (100) comprising a pilot (P) having an axial inlet at CZ33 and an axial outlet at CZ34. The perspective view in FIG. 2b illustrates a diluted pilot fuel (F10) being delivered to an ignition control mechanism or flame holder (100) located downstream of a diluted oxidizer delivery section (720). The diluted pilot fuel to be burned may be delivered to one or more combustion chambers within a combustion section (730) via a high-temperature gas delivery flame tube (116), wherein the chamber may have a radially outer side wall (736) of the combustion chamber.

[0136] Fluid transfer orifice

[0137] According to FIG. 1a, as illustrated in detail in the combustor wall sections of FIG. 1e, FIG. 1f, and FIG. 1g, at least one of the proximal feeder wall (or “fan” wall) (736) and the proximal feeder wall (737) extending transversely to an expandable combustion area bordering an adjacent combustion chamber (740) may include a plurality of fuel fluid orifices (81) or oxidizer fluid orifices (82). These orifices may be configured around one or more porous combustor sides (or liners) of the proximal oxidizer feeder wall (737) and the proximal fuel feeder wall (736) adjacent to at least one combustion chamber (740).

[0138] According to FIG. 1a (and FIG. 1b), these transversely extended fuel feeder walls (736) and distal oxidizer feeder walls (737) of the combustor may generally be shallowly opposed to each other around the reaction or combustion chamber (740).

[0139] As further illustrated in detail in FIG. 1e and FIG. 1f, one or more diluted fuel fluids (F2) (or fuel fluids (F1) not shown) and / or diluted oxidizer fluids (F5) (or oxidizer fluids (F4) not shown) may be delivered through a plurality of porous wall orifices (81 and 82) (in the Y or negative Y direction) formed in the fuel feeder (or liner) wall (736) and the oxidizer feeder (or liner) wall (737) on the side of the combustion zone to enter and into the transverse flow combustion fluid (F12) flowing axially (in the Z direction) along the combustion chamber (740). For example, FIG. 1f, a detailed view of an oxidizer wall section, illustrates a diluted oxidizer delivery combustion wall section (745) having multiple oxidizer fluid orifices (82) configured to deliver a diluted co-reactant or oxidizer fluid (F5) (or an oxidizer fluid (F4) not shown), which may be configured around the fluid duct feeder wall (737) section of the combustion chamber (740) of FIG. 1a. The proximal oxidizer fluid duct feeder wall (737) may have an optional thermal shielding coating (TBC) or thermal insulation coating (738) to protect the fluid duct wall (132) from the high-temperature reaction or combustion fluid (F12) flowing axially (Z direction) along the combustion chamber (740).

[0140] FIG. 1e illustrates a diluted fuel delivery wall section (743) extended from the combustion chamber wall of FIG. 1a. FIG. 1e illustrates a portion of the upstream combustion chamber proximal fuel feeder wall (736) extending transversely between the axial (Z-axis) boundaries of the upstream end wall (241) and the downstream wall (248). FIG. 1e, a detailed view of the combustion chamber wall section, is further located between the transverse proximal boundary wall (734) and the distal boundary wall (735) (along the X-axis), as further detailed in FIG. 1c, FIG. 1d, and FIG. 1h.

[0141] FIG. 1e describes in detail how multiple fuel fluid orifices (81) can be configured to deliver a first reaction fluid or fuel fluid (F2) (or fuel fluid (F1) not shown) diluted through a porous duct wall section (132) within a proximal fuel feeder wall (737) that combusts according to FIG. 1a and FIG. 1c to an adjacent combustion chamber (740). According to FIG. 1e, the fluid duct feeder wall section (736) may optionally have a thermal shielding coating (TBC) or an insulating coating (738) adjacent to the high-temperature combustion fluid (F12) flowing axially through the combustion chamber (740).

[0142] Similarly, FIG. 1g, a detailed view of a blend-trim wall section, illustrates a detailed view of an enlarged wall section (747) of a blend-trim area (850) within a blend-trim section (426) located downstream of a combustion chamber (740). This blend-trim area wall section (747) of FIG. 1g may include one or more blend-trim orifices (83). These blend-trim orifices (83) may be configured to deliver a blend-trim diluted oxidizer fluid (F5) (and / or an optional diluent fluid (F7) not shown) to an axially flowing rich reaction or combustion fluid (F12) entering the blend-trim area (860) from an upstream combustion chamber as illustrated in FIG. 1a.

[0143] According to FIG. 1g, which is a detailed view of the blend-trim wall section, these blend-trim orifices (83) may be distributed across the blend-trim area wall section (856) to deliver the blend-trim fluid (F7) from the blend-trim feeder (860) to the blend-trim area (850) within the downstream blend-trim section (426) as shown in FIG. 1a. This delivery of the oxidizer (F5) in the blend-trim diluted oxidizer fluid (F5) may increase the oxidizer concentration of the fuel-rich combustion fluid (F12) flowing laterally from the upstream combustion chamber (740). Then, the addition of the diluted oxidizer fluid (F5) (or an oxidizer fluid (F7) not shown) forms an oxidizer-rich blend-trim fuel-lean reaction fluid (F13) flowing downstream within the blend-trim area (850).

[0144] According to FIG. 1g, which is a detailed view of the blend-trim wall section, the fluid duct wall section (856) may have an optional thermal shielding coating (TBC) or thermal insulation coating (738) that protects the blend-trim wall section (856) from an adjacent high-temperature fuel-rich (oxidizer-lean) high-energy fluid (F12) flowing downstream into the blend-trim area (850). Delivering additional oxidizer fluid (F4) within the diluted fluid (F5) increases the oxidizer within the blend-trim area, promotes the combustion of the fuel-rich high-energy fluid (F12), and forms an oxidizer-rich high-energy fluid (F13) within the blend-trim area (850).

[0145] Similarly, the detail drawing FIG. 2c describes in detail a diluted fluid delivery wall section comprising a fluid orifice (80) extending through a fluid duct / combustion chamber wall (132) to deliver fuel, oxidizer, and / or diluent fluids as additionally illustrated in FIG. 2d and FIG. 2e, and an adjacent insulating coating (150) on the combustion chamber wall.

[0146] According to FIG. 2b, in some configurations, the delivery of pilot fuel fluid (F3) can be controlled by a fuel control valve (232) and delivered to a reserve unit (100) through a pilot fuel fluid tube or passage (101). Similarly, pilot oxidizer fluid (F6) can be controlled by a pilot oxidizer valve (232) and delivered to a reserve unit (100) through a pilot oxidizer fluid tube or passage (102). Correspondingly, pilot diluent fluid (F8) can be controlled by a pilot oxidizer valve (232) and delivered to a reserve unit (100) through a peripheral diluent fluid tube or passage (103).

[0147] Additionally, according to FIG. 2b, one or more of the pilot fuel fluid tube (101), pilot oxidizer 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 control mechanism (720) together with ground (302). These pilot fluid tubes (101, 102, and / or 103) may be located along the transverse end wall (734) (and / or 735) and / or the pilot high-temperature fluid feeder passage (116).

[0148] Orifice sizing

[0149] Referring to FIG. 1a, FIG. 1e and FIG. 1i, the vertical (normal) separation distance (748) (along the Y-axis) between the combustor proximal (or liner) fuel feeder wall (736) and the combustor distal oxidizer feeder wall (737) that are extended in opposite transverse directions can be configured with the size of the fuel fluid orifice (81) and the respective fuel fluid pressure to generally provide an average penetration distance (F71) of the combustion fuel fluid jet (or "fuel jet") of the diluted fuel fluid (F2) delivered to the combustor chamber (740) between the side walls through the combustor chamber side or feeder wall orifice (81).

[0150] Referring to FIG. 1a, FIG. 1f and FIG. 1i, the vertical (normal) separation distance (along the Y-axis) between one or more opposing transversely extended combustor proximal (or liner) feeder walls (736) and combustor distal feeder walls (737) may be configured together with the size of the oxidizer fluid orifice (82) and one or both of the respective fluid delivery pressures to generally provide an average penetration distance (F72) of the combustion oxidizer fluid jet (or "oxidizer jet") of the diluted oxidizer fluid (F5) delivered to the combustor chamber (740) between the side walls through the combustor chamber sidewall orifice (82).

[0151] Referring to FIG. 1a, FIG. 1g and FIG. 1i, the vertical (normal) blend-trim vertical (normal) separation distance (748) (along the Y-axis) between the combustor proximal (or liner) feeder wall (736) and the combustor distal feeder wall (737) that are extended in opposite transverse directions may be configured together with the size of the blend-trim diluted oxidant fluid orifice (83) and the respective fluid delivery pressure of the blend-trim diluted oxidant fluid (F15) to generally provide an average penetration distance (F73) of the blend-trim diluted oxidant fluid (F15) delivered to the blend-trim area (850) between the side walls through the combustor side wall orifice (83), and the respective fluid delivery pressure of the blend-trim diluted oxidant fluid (F15). As illustrated in FIG. 1g, in some configurations, a diluent fluid (F7) containing a liquid and / or gaseous diluent can be similarly transferred to a reaction fluid (F12) through an orifice (78) to form a diluted combustion (or reaction) fluid (F13).

[0152] For example, such sidewall spacing, orifice diameter (or area), and fluid pressure can generally be configured to deliver a fuel fluid jet of diluted fuel fluid (F2), an oxidizer fluid jet of diluted oxidizer fluid (F5), and / or a blend-trim diluted oxidizer fluid jet (F15), having an equivalent fluid penetration distance of about 0.1 to 10 times under similar conditions without opposing collision walls. Such design of the jet penetration distance (F72 and / or F71) can use one or more configurations of the combustor sidewall spacing (748), fuel orifice size (81), oxidizer orifice size (82), and blend-trim diluted oxidizer fluid orifice size (83), and / or control the delivery pressure of the fuel fluid (F2), oxidizer fluid (F5), and / or blend-trim oxidizer fluid (F14). The fluid penetration distance (F71), oxidizer fluid penetration distance (F72) and / or blend-trim diluted oxidizer fluid penetration distance (F73) may be configured to be about 20% to 200% of the shallow combustion wall separation (748). The fuel, oxidizer, and trim oxidizer fluid penetration distances (F71, F72 and / or F73) may be further configured to be between 40% and 100% of the shallow combustion wall separation distance (748).

[0153] Transverse end wall of the combustion chamber

[0154] According to FIGS. 1A, 1C, 1D, 1H and 1I, the combustion chamber outer (distal) side (liner) feeder wall (737) and the shallowly displaced inner (proximal) side feeder wall (736) may be joined or butted together along their extended transverse ends along the X-axis perpendicular to the axial fluid flow Z-axis. This joining may be achieved by forming a proximal end wall (734) and / or a distal end wall (735) of a fluid transfer duct between adjacent combustion side feeder (or liner) walls (736 and 737).

[0155] These combustion chamber transverse proximal end walls (734) and transverse distal end walls (735) may have a generally convex (outward) curvature toward downstream. They form one or more reaction or combustion zones between adjacent, shallowly opposing nearby combustion chamber-side feeder wall(s) (736) and distal-side feeder wall(s) (737). The upstream combustion chamber (740) may generally have an increased cross-sectional area perpendicular to the axial combustion flow direction, along with an increasing axial distance toward the reactor or combustor outlet (136). This increased combustor cross-section can advantageously accommodate the increasing temperature and increasing volume of the formed high-temperature combustion gas. This increased area with an increased combustion gas mass can advantageously reduce the fluid flow pressure drop across the combustor (700), which is extendable from the combustor inlet (134) to the combustor outlet (136).

[0156] The proximal feeder wall (736) of the transversely elongated opposing combustion section may include a generally increasing number of fuel fluid orifices (81) to deliver a fluid containing fuel fluid (F1) to the reaction or combustion chamber (740) between the opposing combustion chamber proximal sidewall (736) and the combustion chamber distal sidewall (737). The transversely extended combustion chamber distal feeder wall (737) may include a generally increasing number of oxidizer fluid orifices (82) to deliver a fluid containing oxidizer fluid (F4) to the reaction or combustion chamber between the opposing combustion chamber sidewalls.

[0157] The corresponding configuration of shallowly displaced transversely extended porous combustor proximal and distal feeder walls (736 and 737) having transverse combustor end walls (734 and 735) can form a combustion chamber (740) that expands upstream to downstream having a downstream expandable (hand "fan") shape.

[0158] Thermal resistance and insulation

[0159] The proximal and distal feeder walls (736 and 737) of the combustor chamber, and the proximal end wall (734) and distal end wall (735) bordering the combustor chamber transversely, may be formed of a sufficiently high-temperature material capable of withstanding the elevated combustion gas temperature within the reaction or combustion chamber (740).

[0160] One or more of these combustion chamber proximal feeder walls (736) and / or combustion chamber distal feeder walls (737) may be covered with a thermal shielding coating (TBC) or an insulating layer (738). This TBC insulating layer (738) may be used to protect the structural materials of the combustor proximal and distal feeder walls (736 and 737) from high-temperature adjacent reaction fluids or high-energy fluids and any corresponding radiation. This TBC insulating layer (738) may include a chemical protective material to protect the combustor side feeder walls (736 and 737) from elevated steam and / or oxygen and their corrosive or oxidizing properties.

[0161] At least one reactive fluid or fuel fluid (F1) can typically be delivered to a reaction or combustion chamber (or zone) (740) through a fuel fluid duct (770) and through a porous adjacent side (or liner) feeder wall (736).

[0162] In some configurations, the reactive fluid or fuel fluid (F1) may be a premixed fuel fluid comprising one or both of a fuel, an oxidizer, and a diluent, thereby forming a diluted reactive fluid or fuel fluid (F2) (not shown). For example, the fuel fluid (F2) may comprise a mixture of a diluent comprising one or more of natural gas, air, and water vapor, steam, and / or water mist formed from heated water. The diluted reactive fluid or diluted fuel (F2) may similarly comprise a chemical reactant having one or more other diluents, such as carbon dioxide (CO2) and / or nitrogen (N2).

[0163] The oxidizer feeder wall (737) on the distal side (or "liner") of the combustor and the fuel feeder wall (736) on the proximal side of the combustor may be configured between the outermost enclosure wall (not shown) of the combustor in a manner similar to the unperforated versions of the oxidizer side feeder wall (737) and the fuel side feeder wall (736).

[0164] The embodiments of FIGS. 1a and 1i allow for the use of a suitable differential pressure between the fluid in the reaction or combustion zone between the combustion oxidizer-side feeder wall(s) (737) and the combustion fuel-side feeder wall(s) (736) (each optionally coated with an insulating coating (738)) facing the fluid supply duct on one side of the combustion side (or liner) wall. The fluid jet can then penetrate a certain portion into the fluid between the combustion walls.

[0165] As further detailed in FIG. 1a, FIG. 1i and FIG. 1e, FIG. 1f, and FIG. 1g, a plurality of fuel fluid ports (81) and oxidizer fluid ports (82) to which pressurized fluid is supplied to form fluid jets may be configured to provide a significant penetration of 33% to 67% into a shallow combustion chamber depth under a significant combustion power level. The fuel and oxidizer fluid jet orifices (81 and 82) and the corresponding fluid delivery pressures may be similarly configured to provide a major penetration of 40% to 100% of the distance across the shallow combustion chamber while achieving a major portion of the combustion power. This generally provides a lateral distribution of the combustion (or reaction) fluid (F12) flowing axially within the shallow combustion chamber (740) extended laterally between the combustor fuel-side feeder wall (736) and the oxidizer-side feeder wall (737), and a good mixing of the injected fluid(s) (F2 and F5).

[0166] In some configurations, the scalable configuration can operate as a chemical reactor. In such configurations, numerous jets can form an effective mixing system for mixing the reaction fluid with the co-reaction fluid to form a product fluid or a high-energy fluid. This configuration can facilitate rapidly raising the injected reactive and co-reaction fluids to the desired reaction temperature and initiating the reaction.

[0167] According to FIG. 1e and FIG. 1g, in additional configurations, a thermal diluent may be delivered together with one or both of the reaction fluid and / or co-reaction fluid to form a first diluted reaction fluid (F2) and a second diluted co-reaction fluid (F5) to be delivered through port (81) and / or port (82), respectively. For example, the premixed wet fuel (F2) and air mist oxidizer fluid (F5) may be injected into an axially flowing reaction or combustion fluid (F22) or a high temperature or high energy fluid. Similarly, the diluent fluid (F7) may be delivered separately to the reaction fluid (F12) through the diluent orifice (78).

[0168] When using an expandable ("fan") combustor (700), multiple fuel orifices (81) and oxidizer orifices (82) may be configured to provide an axial distribution of net orifice area sufficient to deliver a flow rate of the reactive or fuel fluid (F1) and the co-reactive or oxidizer fluid (F4) having a desired axial flow rate distribution. For example, this may include an increasing number of orifices of similar size around a reaction zone that is transverse to the combustor flow axis.

[0169] Downstream transition or diffuser area

[0170] Referring to FIG. 1a, a downstream end transition or end diffuser (428) may be provided downstream of the combustion section (730) and, if present, the blend-trim equilibrium region (426). This may provide additional fluid residence time that can advantageously increase the degree of reaction or combustion. Such end diffuser (428) may reduce the pressure drop of the high-energy fluid (F20) discharged from the downstream combustor outlet (136) of the expandable combustor (700).

[0171] Ignition system or flame control device

[0172] Referring to FIG. 1b, in some embodiments, an ignition system or flame control mechanism (720) may be provided near the upstream end wall (241) of the combustion chamber (740). This flame control mechanism (720) may deliver a high-temperature ignition fluid (F22) to an upstream reaction zone or pilot zone or chamber (720) located between or more of the porous opposing pilot chamber sidewalls (722).

[0173] Pilot Ignition

[0174] Referring further to FIG. 1b, an igniter (124) may be provided near the upstream end of the flame control mechanism (720). The igniter (124) may include one or more of a spark igniter, pilot light, hot gas jet, plasma jet, laser beam, light pipe, glow plug, heated surface, microwave heater, or other igniter that can be used to ignite combustion or initiate a chemical reaction.

[0175] Combustion may also be initiated by providing a starter fuel or reactant fluid flow (F3) and a second reactant or oxidizer fluid flow (F6), which may include two or more spontaneously combustible fluids that ignite upon mutual contact.

[0176] Pilot diluent delivery

[0177] Referring to FIG. 1b, in some embodiments, additional diluent (F8) may be delivered via a pilot thermal diluent delivery system (373). In some configurations, the outlet of the pilot diluent delivery system (373) may be located downstream of the outlet of the pilot reactant or fuel delivery system (372) which delivers the pilot reactive fluid or fuel fluid (F3) to the upstream combustor inlet (or pilot outlet) (134) of the combustion chamber (740). The pilot diluent delivery system (373) may be located downstream of the delivery of the co-reactant or oxidant pilot fluid (F6) via the oxidant pilot delivery port (371). This configuration may reduce the possibility of quenching the pilot reaction or flame.

[0178] Additionally, according to FIG. 1b, the high-energy pilot fluid (F22) formed by the pilot reaction can be cooled using one or both of an additional pilot diluent fluid and / or a colder pilot diluent fluid (F8) through the pilot fluid delivery port (373). For example, this allows the upstream primary reaction to be carried out at a hotter temperature and / or in the presence of less oxidizer fluid (F6), such as a fuel-rich (and oxygen or air-lean) fluid mixture of pilot fuel / first fluid (F3) and pilot oxidizer / second fluid (F6).

[0179] This diluent delivery cooling the pilot is NO x By-product combustion emissions such as those can be advantageously reduced. This may additionally enable the operation of the reaction or combustion at hotter temperatures. This allows for the advantageous more rapid consumption of primary reactants and can selectively shorten the residence time required to achieve desired emissions of unburned reactants or fuels. Examples include residual unburned hydrocarbons, alcohols, or ammonia.

[0180] For example, one or more porous direct contactor porous wall sections as illustrated 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, inert gas, or one or more reacted fluids. These may use one or more of the processes described in various VAST patent applications attached or incorporated by reference, namely VAST.001 (Direct Contactor), VAST.002 (Trifluid), VAST.003 (Cycle), and / or Campbell (VAST.014) patents.

[0181] Referring to FIG. 1i, FIG. 1e, FIG. 1g (and correspondingly FIG. 1f), the orifices (81 and / or 82) within these porous wall sections may be further configured to orient a diluent jet at an angle transverse to a fuel-rich combustion fluid flow, such as F12, within an upstream combustion chamber (740) that generally flows axially along the Z-axis direction. Similarly, the orifice (83) may be oriented at an angle transverse to a blend-trim fuel-rich (oxidizer-lean) fluid flow (F12) and / or a fuel-lean (oxidizer-rich) fluid flow, such as F13, that generally flows along the Z-axis direction.

[0182] Correspondingly, one or more fluid transfer ducts are formed between the combustor sidewalls (or liners) to transfer one or more of these fluids through orifices within these sidewalls. This can help improve one or more of the mixing, increase the residence time in the fluid, and, if necessary, increase the time for liquid diluent evaporation.

[0183] Temperature control by diluent

[0184] Referring to Figures 1d and 1h for Figure 1a, downstream diluent delivery can be configured to provide a diluent flow distribution, and steam and / or steam can also be delivered through a direct contactor.

[0185] Plan view of the combustion chamber

[0186] FIG. 1i illustrates a transverse XY cross-sectional view through a combustion chamber (or region) (740) perpendicular to the axial flow in the Z-axis direction. This cross-sectional view is in the AA' plane shown in the elevation views FIG. 1c, FIG. 1d, and FIG. 1h. It illustrates the combustion chamber (740) between the diluted fuel feeder (750) and the diluted (rich) oxidizer feeder (760).

[0187] The combustion chamber (740) is bounded by the combustion chamber proximal feeder wall (736) and the combustion chamber distal feeder wall (737) along a shallow depth in the Y vertical direction. The combustion chamber (740) is further bounded by the combustion chamber transverse oxidizer-diluent end wall (734) along an extended transverse width in the positive X transverse direction. The combustion chamber (740) is further bounded by the combustion chamber transverse fuel-diluent end wall (735) in the negative X direction.

[0188] The proximal feeder wall (736) and distal feeder wall (737) of the combustion chamber may be protected by a thermal shielding coating or an insulating layer (738). The end walls (735 and 734) of the combustion chamber may be similarly protected by a combustion end wall thermal shielding coating or an insulating layer (TBC) (738) on the positive and negative X-axis sides.

[0189] The proximal (or internal) side feeder wall (736) of the combustion chamber is illustrated as having a plurality of fuel orifices (81) as illustrated in detail in FIG. 1e. The distal (or external) side feeder wall (737) of the combustion chamber is illustrated as having a plurality of oxidizer orifices (82) as illustrated in detail in FIG. 1f. One or more of the fuel orifices (81) and / or oxidizer orifices (82) may be oriented at a transverse angle with respect to the transverse X direction.

[0190] Diluted fuel / reactant fluid transfer

[0191] The reactant and / or fuel fluid (F1) can be delivered to a fuel feeder (750) as shown in the elevation view of FIG. 1d, the perspective view of FIG. 1a, and the plan view of FIG. 1i. As shown in the perspective view FIG. 1e and the plan view FIG. 1i, the fuel fluid orifice (81) can be inclined laterally with respect to the axial fluid flow (F12) through the combustion chamber-side feeder wall (736) and the thermal shielding coating (TBC) (738).

[0192] Diluted oxidant / co-reactant fluid transfer

[0193] The co-reactant and / or oxidant fluid (F4) can be delivered to an oxidant manifold (760) as shown in the elevation view Fig. 1h, the perspective view Fig. 1a, and the plan view Fig. 1i. As additionally shown in the perspective view Fig. 1e and the plan view Fig. 1i, the oxidant fluid orifice (82) can be inclined laterally with respect to the axial fluid flow (F12) through the oxidant feeder wall (737) and the thermal shielding coating (TBC) (738) on the side of the combustion chamber distal to the combustion chamber.

[0194] The fuel fluid orifice (81) and the oxidizer fluid orifice (82) may be oriented circumferentially around the axial flow axis with the same clockwise (CW) orientation as shown in FIG. 1i. Similarly, they may be oriented equivalently counterclockwise (counterclockwise) around the fluid flow axis (perpendicular to the plan view of FIG. 1i). In a further embodiment (not shown), the fuel fluid orifice (81) may be oriented clockwise (CW) and may be opposed to the opposite counterclockwise (counterclockwise) orientation of the oxidizer fluid orifice (82) around the fluid flow axis (perpendicular to the plane of FIG. 1i). Equivalently, the fuel fluid orifice (81) may be oriented counterclockwise (counterclockwise) to be opposed to the clockwise (CW) orientation of the oxidizer fluid orifice (82) around the fluid flow axis.

[0195] Blend-Trim Area

[0196] Downstream oxidizer and diluent delivery

[0197] Referring to FIG. 1d, FIG. 1f, and FIG. 1h in relation to FIG. 1a, in some embodiments, additional diluent and oxidizer containing fluid (F5) may be delivered as a high-energy fluid to a blend-trim area (850) downstream of the combustion chamber (740). This oxidizer fluid (F5) may be delivered to the downstream blend-trim area (860) through a diluent oxidizer fluid duct (860) and / or a diluent oxidizer fluid duct (870). As shown in FIG. 1f, the diluent oxidizer fluid duct (860 and / or 870) may have porous walls containing multiple orifices (83) to deliver the diluted oxidizer fluid (F5). These may be similar to the upstream fuel feeder (750) and oxidizer feeder (760) of the upstream combustion section (730) adjacent to the upstream combustor side (or liner) wall. For example, it has a suitable thermal shielding coating (738) to protect the wall as needed.

[0198] With further reference to FIG. 1f, FIG. 1d, FIG. 1g and FIG. 1h, the downstream diluted oxidizer duct (860) and / or the diluted oxidizer duct (870) may have a thermal shielding coating (TBC) (738) that protects the blend-trim duct wall (856) from high reaction or combustion temperatures. A fluid duct having a feeder wall (856) similar to a porous direct contactor combustor-side feeder wall (736 and / or 737) may be used.

[0199] Similarly, according to FIG. 1f and FIG. 1i, the diluted oxidant fluid delivery orifice (83) may be configured at a clockwise (CW) and / or counterclockwise (counterclockwise) angle with respect to the reaction or combustion flow fluid flow axis, similar to the fuel fluid orifice (81) and / or oxidant fluid orifice (82), which improves fluid mixing of the injected diluted oxidant fluid (F5) with the incoming reaction fluid (F12) and blend-trim fluid (F13). The number and size of the diluted oxidant orifices (83) and the relative delivery pressure of the diluted oxidant fluid (F5) may be configured to achieve effective jet penetration into the high-energy fluid (F12).

[0200] The delivery of the blend-trim diluted oxidant fluid (F5) can be achieved with an appropriate differential pressure compared to a conventional combustor. This downstream oxidant fluid can help reduce the oxygen concentration during most of the combustion, and thus NO x Emissions can be reduced. However, downstream oxidizer delivery can provide sufficient excess oxidizer to enable the efficient conversion of fuel, unburned hydrocarbons, and carbon monoxide into carbon dioxide.

[0201] With reference to FIGS. 2a, 2d, and 2e, the downstream blend-trim combustor region (850) can be distinguished into an upstream blend-trim region (852) and a downstream blend-trim region (854). FIG. 2d illustrates the delivery of a diluted oxidizer (F5) to the upstream blend-trim region (852) through a diluted oxidizer delivery porous feeder (856). Correspondingly, a diluent fluid (F7) can be delivered to the downstream blend-trim region (854) through a downstream porous thermal diluent tube (106) and a diluent orifice (78).

[0202] Correspondingly, FIG. 2e illustrates the delivery of a diluent fluid (F44) to an upstream blend-trim area (852) through a porous thermal diluent tube (106) via a diluent orifice (78). The porous thermal diluent tube (106) can similarly deliver the diluent fluid (F44) to a downstream blend-trim area duct (858) via the diluent orifice (78). The upstream blend-trim area duct (858) can deliver the diluent fluid (F44) to a downstream blend-trim area duct (858). This diluent fluid (F44) can be delivered from thereto to a downstream blend-trim area (854) via an orifice (83) together with a blend-trim oxidant fluid (F42).

[0203] FIG. 2e similarly illustrates the delivery of a diluent fluid (F46) to an upstream blend-trim area (852) through a porous thermal diluent duct or tube (107) via a diluent orifice (78). A porous thermal diluent tube (107) can similarly deliver the diluent fluid (F46) to a downstream blend-trim area duct (857) via the orifice (78). The upstream blend-trim area duct (857) can deliver the diluent fluid (F46) to the downstream blend-trim area duct (857). The diluent fluid (F46) can be delivered from there, together with the blend-trim oxidant fluid (F45), through a downstream blend-trim area duct (859) and from there through a diluted oxidant orifice (83) to a downstream blend-trim area (854).

[0204] In additional configurations, the fluid delivery methods to the blend-trim region illustrated in FIGS. 2d and 2e can be combined and coordinated. For example, by alternating the delivery of the diluent fluid and / or diluted oxidant fluid (F5 and F7), and the diluent and / or diluted oxidant fluid (F42 and F44, and F45 and F46), alternating the upstream-to-downstream configuration of the blend-trim delivery ducts (856 and 858) transversely, and alternating between the blend-trim delivery ducts (857 and 859). These methods allow for the configuration of the axial concentration (lambda) of the trim oxidant delivery relative to the upstream fuel delivery. Similarly, these can be used to configure the average axial concentration (omega) of the balance-trim residual diluent relative to the upstream fuel delivery.

[0205] This scalable combustor invention is designed to achieve ultra-clean combustion for gas turbines, combined heat and power systems, industrial heating, cooling, and other applications requiring clean controlled combustion and / or chemical reactions.

[0206] In some configurations, the multi-fluid jet may be configured with shallower gaps between the walls to improve relative jet penetration. The ratio of diluted oxidizer and fuel delivery to the upstream combustion flow may be configured to increase the operating range and operational robustness.

[0207] Rapidly Changing Gas Turbine Power Market

[0208] Electricity demand is increasing due to a growing population, economic growth, and a rise in electric vehicles. Rapidly growing solar and wind power generation requires larger, faster reserve power to meet this demand. The rapid growth in the use of artificial intelligence (AI) is increasing power consumption in data centers that require ultra-high reliability.

[0209] Consequently, the long-term power assessment in the Annual Energy Outlook (AEO 2022) by the U.S. Energy Information Agency (hereinafter referred to as the EIA) forecasts approximately 331 GW more U.S. gas turbine power by 2050. The EIA forecasts 175 GW of simple-cycle "peaker" turbines and 156 GW of combined-cycle turbines. This creates a U.S. market of $195 billion ($7.5 billion annually) for intermediate or reserve power by 2050. The International Energy Agency (hereinafter referred to as the IEA, 2020) stated that the United States possesses 500 GW of gas-fired power plants, accounting for approximately 28% of the global gas-fired power plants comprising approximately 1,785 GW.

[0210] Demand for reliable power is growing at a much faster rate in China, India, Southeast Asia, and Africa than in the U.S. and EU. The IEA (2023) reports that gas turbines produce 21.8% of global electricity. The EIA (AEO 2022) forecasts that global power capacity will grow by approximately 55% to 108% by 2050 (i.e., a much faster rate than generation growth of 30% to 76%).

[0211] The EIA estimates that natural gas turbines will supply 15% to 20% of total global electricity. This indicates a potential increase in global power gas turbines to 982 GW to 1,938 GW by 2050. This indicates a potential global gas turbine growth market of $1.1 trillion to $2.15 trillion. This suggests a potential global market share of $550 billion to $1.07 trillion for the applicant’s ultra-clean gas turbine power innovations described in this specification.

[0212] Due to the finite supplies of natural gas, oil, and coal, there is a strategic need to develop alternative sustainable power using renewable fuels. There are also concerns regarding climate change and greenhouse gases. These factors are driving efforts to develop and use sustainable fuels such as hydrogen (H2 in this specification), ammonia (NH3 in this specification), methanol (CH3OH in this specification), and ethanol (CH3CH2OH in this specification).

[0213] Ensuring grid reliability with dispatchable backup power

[0214] Grid collapses caused by failures in medium-sized power plants resulted in a loss of 78.64 GW of power in 2003, caused a blackout in the northeastern United States affecting 7.37 million people, and caused damages ranging from $4 billion to $10 billion (Borenstein et al. 2023). California's CAISO power grid already has a ~24 GW "duck curve" demand, rising from no demand (excessive midday solar and wind) to evening peak demand under calm conditions after sunset.

[0215] Ensuring reliable power from increasing solar and wind generation requires installed dispatchable reserve power (or high-cost storage) greater than peak demand to guarantee grid reliability at night with weak winds. This is particularly stringent when considering power delivery limits during peak winter or summer loads. Existing grids can no longer support CO2-free daytime or national substantive-zero renewable energy targets (referred to herein as "substantive-zero" or "net-zero" without CO2 credits) distribution demand. These pressures create strategic power system vulnerabilities.

[0216] For reliable power, the grid must strategically maintain local dispatchable reserve power exceeding approximately 120% of peak output. This must accommodate plant maintenance and breakdowns while allowing for nighttime use, cloudy periods, and light winds. Almost all current gas turbines rely on natural gas. Underground natural gas storage provides an energy buffer for current. However, extreme winter conditions in Texas, coupled with equipment failures, have challenged that reliability.

[0217] To achieve future truly zero renewable energy (without offset), reliable and cost-effective backups are required along with long-term energy storage (Long Duration Energy Storage > 4 hours). A 100% truly zero renewable power grid must additionally accommodate long-term climate variability. According to Ruhnau and Qvist (2022) and Fekete et al. (2023), it must provide 300% of the worst two-week shortage spread over a four-month period.

[0218] Batteries generally advertised are too expensive. Biofuels have production and backup capacities with relatively few constraints. Liquid NH3 storage utilizes existing transportation and storage infrastructure to provide small-scale, long-term, and cost-effective backup energy. However, high NO x The difficult NH3 paradox regarding emissions and potential ammonia slip must be resolved reliably, economically, and rapidly.

[0219] Ammonia Power Growth and Opportunities

[0220] With an annual production of 202 million tons (183 M t / yr), ammonia (NH3) is the second most manufactured chemical after sulfuric acid (H2SO4). The energy density of ammonia (22.5 MJ / kg) is similar to that of methanol (22 MJ / kg). Extensive fertilizer production, agricultural infrastructure, and the transport of inexpensive liquid fuels favor sustainable NH3 fuel over hydrogen. Transport dominates costs in energy-importing countries.

[0221] Strategically, NH3 has the potential to replace depleting hydrocarbon fuels and become a major sustainable fuel, particularly in energy-influx regions and countries. NH3 is 29 times cheaper to store than H2. MacFarlane et al. (2020) provide an "Ammonia Economy Roadmap." Nazemi et al. (2021) review the Georgia Institute of Technology's Micro-NH3 Production System (MAPS). Hydrofuel acquired Kontak and licensed Georgia Tech's MAPS technology. They promise the production of sustainable NH3 at a lower cost than natural gas.

[0222] The industry is constructing eco-friendly NH3 production plants. Martin (2023) reports that Brazil's Unigel Chemicals plans to quadruple its output to 240,000 tons / year of NH3 by 2025. Saudi Arabia's NEOM complex will produce 1.2 million tons / year of eco-friendly NH3 by its completion in 2026. China's Jilin Province aims to produce 2 million tons / year of NH3 by 2030. Global ammonia production is projected to grow by 250% by 2050 (from 200 Mt / year to 700 Mt / year) (GPCA 2023).

[0223] The International Energy Agency (2023) updated its ammonia technology roadmap and projected that NH3 will supply 44% of global ship fuel by 2050, while biofuels and hydrogen will each account for 19%. Laursen et al. (2023) extensively detail the advantages and challenges of using NH3 as ship fuel for EMSA. Wood McKenzie (2022) projected global NH3 usage in gas / coal-fired power generation to be approximately 50 Mt per year by 2050, increasing to 100 Mt per year under advanced scenarios. Adeli et al. (2023) examine the potential for synthesizing and using eco-friendly H2 and NH3 for fuel and energy storage.

[0224] With limited natural energy resources, Japan is strategically seeking sustainable fuel imports. Japan plans to import 3 metric tons of NH3 annually by 2030 and increase this to 30 metric tons by 2050. At the G20 meeting held in India in 2023, Japan pledged to issue 20 trillion yen (approx. $136 billion) in Green Transformation (GX) economy transition bonds backed by future financial assets. This will encourage over 150 trillion yen (approx. $1 trillion) in public and private investment in the GX economy. G20 (2023).

[0225] large gas turbine company

[0226] According to a joint study by IHI and General Electric, transportation costs for imported hydrogen into Japan were reported to be 50% higher than those for ammonia (Patel 2024). IHI and GE are developing NH3 combustion technology. Japan funded IHI to co-fire up to 70% NH3 in a 2 MW gas turbine (Patel 2024). Amogy (2023) and Mitsubishi Heavy Industries (MHI) in the U.S. are exploring the use of Amogy's NH3 decomposition technology. Mitsubishi is developing a 40 MW H-25 gas turbine with 100% NH3 combustion. Cesaro et al. (2024) model a Combined Cycle Gas Turbine (CCGT) based on the Siemens SGT-800 (62.5 MW) gas turbine.

[0227] Japan's MHI and its largest power company, JERA, are pursuing a 100% NH3 combustion combined cycle power plant on Jurong Island in Singapore. MHI is conducting joint research on NH3 combustion H-25 gas turbines with the Indonesian Institute of Technology (ITB). South Korea plans to use hydrogen and NH3 for 7.1% of its electricity by 2036.

[0228] Centrica and Mitsubishi Electric Power Europe are seeking to develop, construct, and operate Europe's first NH3 combustion power plant at Whitegate, Cork, Ireland.

[0229] Best-in-class clean technology requirements

[0230] The U.S. Clean Air Act directs the U.S. Environmental Protection Agency (US Environmental Protection Agency: "EPA") to designate areas requiring "Reasonable Attainment Clean Technology" ("RACT"), "Reasonable Attainment Clean Technology" ("BACT"), or strict "Lowest Available Emissions Requirement" ("LAER").

[0231] California law requires much stricter "California Best Available Containment Technology" (California Best Available Containment Technology: "CA-BACT" in this specification) in non-achieved counties. The U.S. EPA's Greenway Book (1971) designates four California counties in the Los Angeles-South Coast Air Basin as "non-achieved" nitrogen dioxide areas for NO2 emissions under the EPA (2023).

[0232] Ultra-clean, scalable combustion design and operation

[0233] Accordingly, some technical features of the present invention lead to a reactor that adds reactants, an oxidizer, and, in some embodiments, a diluent fluid to deliver and burn more cleanly. The technology described herein comprises an expandable combustor that burns fuel together with an oxidizer (e.g., air or oxygen), and may add a diluent, such as water, carbon dioxide, nitrogen, and / or excess oxygen, in any phase and / or combination.

[0234] These technologies enable features and methods that are more scalable over a wider range of commercial combustor pressure, temperature, output level, and / or output ramping rate than conventional gas turbine combustors, thereby improving power system capabilities and economics.

[0235] The technology described herein further covers scalable combustor methods and system designs for gas turbine systems having fuel, oxidizer, and diluent types, combinations, and mechanical, electrical, and / or thermal loads, which enable more reliable grid operation and backup and provide major intermittent non-monetary renewable power coverage and growth rates.

[0236] The technology described herein further provides catalyst-free, ultra-clean methane combustion. Some configurations were modeled by the U.S. Department of Energy’s Argonne National Laboratory (hereinafter Argonne National Laboratory: “ANL”) using Reactive Computational Fluid Dynamics (hereinafter Reactive Computational Fluid Dynamics: “RCFD”) across gas turbine operating temperature, pressure, and specific power ranges. Some of the modeled configurations have <1 ppmvd NO₂ at a volume diluted with 15% O₂ dry (hereinafter “pvmvd”). x and achieved CO2 emissions.

[0237] The results of modeling these technologies indicate a high probability that current scalable combustor innovations will achieve best-in-class combustion in VAST cycle gas turbines with ultra-clean emissions compared to other commercial power turbines.

[0238] The technology of the present invention provides ultra-clean best-in-class emissions for current fuels, sustainable fuels, and combinations of these fuels. This technology can be used to design exemplary ultra-clean dual-fuel ammonia and / or natural gas combustion capabilities and to provide key state-of-the-art advantages over existing gas turbines. Thus, this method provides strategic sustainable power and also substantively zero power (or net-zero without CO2 offset) along with higher reliability, faster, dispatchable grid reserve power.

[0239] The technology of this specification, which enables "wet" cycle gas turbines using VAST power cycle turbines, can replace a major portion of conventional cooling air (or oxidizer) with a diluent (e.g., water, steam, CO2, and N2) that recovers exhaust heat and recirculates the heated diluent back into the combustion system. This method can help supply a cleaner and more competitive portion of the single gas turbine ("picker") segment of the US gas turbine growth market of over $100 billion and the major portion of the international single gas turbine growth market of over $250 billion by 2050.

[0240] Mandatory ultra-clean combustion priority

[0241] "Applying the technology of this specification to achieve an ultra-clean commercial combustor for power turbines for natural gas (including methane) may result in the following possible outcomes: 1) the U.S. federal BACT rating required in U.S. emission-achieved regions; 2) the EPA's stricter LAER rating required in non-emission-achieved regions; and 3) California's CA-BACT rating required in non-emission-achieved California counties. Applying this technology to achieve RACT, BACT, LAER, and CA-BACT ratings will likely mandate a purchase priority for power systems using this combustor invention over other technologies in non-emission-achieved regions.

[0242] Strict NO x and NH 3 NH with "slip" emission rules 3 electrical energy

[0243] These technologies can be applied to the ultra-clean combustion of sustainable fuels such as hydrogen, ammonia, ethanol, and methanol. These technologies burn NH3, methane, or hydrogen, etc., to produce NO levels much lower than those previously formed. x Ammonia (NH3) can be burned as an exhaust gas. For example, ultra-high NO x It is much cleaner than burning NH3 in General Electric (GE)'s lean turbine combustor that forms it.

[0244] For example, through Reactive Computational Fluid Dynamics (RCFD) modeling, Gubbe et al. (2023) showed that a conventional single-stage lean premixed combustion in a gas turbine at a combustor outlet pressure P = 20 Bar and a turbine inlet temperature (Turbine Inlet Temperature: "TIT" or combustor outlet temperature) TIT = 1,900 K (1,627°C) yields ~1,800 ppmvd NO x I discovered that it generates

[0245] These technologies can further adjust residence times to accommodate major differences in fuel flame rates, including NH3, which burns ~6 times slower than methane, has a much narrower combustion boundary, and increases the flame loss challenge. These technologies may include reliably burning hydrogen, which burns 33 times faster than ammonia, has a much wider combustion boundary, and poses a risk of flashback and catastrophic explosion.

[0246] These techniques can be similarly used to decompose NH3 and burn the decomposed NH3. NH3 decomposition may involve heat and / or a catalyst externally or in-situ within a combustion system. Combustion may involve the use of a combination of NH3 and decomposed ammonia (3H2 + N2).

[0247] The technology of this specification provides gas turbine NO that is 98% (60 times) lower than conventional lean NH3 combustion. x It can be applied to meet the requirements of the U.S. EPA (EPA Part 60 Subpart KKKK) regarding emissions.

[0248] The relevant EPA regulations require nationwide emission reductions, particularly for fuel, to enable NH3 to play a role in major dispatchable power markets. For example, reduce emissions to <25 ppmvd (or 150 ng / J of useful output, or 1.2 lb / MWh) for a combustion range of 14.7 MWt to ​​249 MWt (50 MMBtu / h to 850 MMBtu / h).

[0249] This technology produces NO levels 783 times lower than those caused by lean air (or oxidizer) combustion. x It can be used to approach or meet emission regulations in California counties with severe smog requiring, and NO x Emissions are limited to 2.3 ppmvd. In contrast, conventional gas turbines require costly purification (e.g., Selective Catalytic Reduction: SCR) accompanied by the cost of continuous ammonia operation) to reach these limits. Some California counties additionally limit unburned NH3 ("slip") to <10 ppmvd and <2.5 ppmvd.

[0250] As described in this specification, the technology for developing a novel scalable combustor can be configured to design and operate the combustor to achieve these much more difficult RACT, BACT, LAER, and CA-BACT ultra-clean combustion emission grades, particularly for burning sustainable fuels such as ammonia and "decomposed" ammonia (in this specification, a mixture of hydrogen and nitrogen with residual ammonia from 2 NH3=3 H2+N2).

[0251] These technologies can be further used to develop dual-fuel or multi-fuel combustors, such as those using various combinations of gaseous and / or liquid NH3, decomposed NH3, hydrogen, and / or natural gas.

[0252] Priority for ultra-premium power bidding

[0253] Technology can be used to achieve ultra-clean emissions sufficient to avoid emission cleanup costs. Industrial personnel use these NO x It is estimated that emission cleanup may cost 7%–10% of total capital expenditure (Capital Expenditure: "CapEx" in this specification). Applying these technologies to achieve ultra-clean emission grades may potentially eliminate such cleanup.

[0254] These technologies can further eliminate ongoing catalyst and NH3 purification operating costs. Collectively, along with scalable combustion cost innovations, these technologies will likely achieve power bidding priorities to ensure grid reliability, significantly improve profitability, increase rapid commercialization, and deliver major social benefits.

[0255] Intermediate power supply available

[0256] The technology described herein can address the need to back up rapidly increasing renewable power and reduce fossil fuel consumption. Increasing renewable power is correspondingly reducing the annual capacity factor and profitability of combined cycle turbines. Increasing solar and / or wind power is reducing gas turbine reserve power to an intermediate annual installed utilization rate range of <50%.

[0257] Therefore, the application of the technology described in this specification is expected to achieve more profitable intermediate VAST cycle power to commercially replace new pickers and new combined cycle power turbines. The technology promises to dramatically increase the competitiveness of such clean power generation and expand the target market for such ultra-clean, high-speed response, dispatchable power.

[0258] The technology can be used for quieter, dispersed, scalable combustion and avoid resulting high-frequency fatigue. This technology can be used to reduce combustor turbine breakdown noise by more than 30 dB. Using this independent temperature design and control technology in scalable combustors can substantially reduce high-temperature metal creep, cyclic thermal fatigue, maintenance, repairs, downtime, and operating costs.

[0259] Technology for scalable combustors combined with "wet" cycle VAST power cycle turbines can provide cleaner, cheaper, faster, more efficient, and more durable intermediate output than conventional Brayton "picker" turbines and combined cycle turbines. The technology can be used to increase combustor and turbine life, profitability, and returns.

[0260] The technology involves the development of scalable dual-fuel ammonia and natural gas combustors. These will enable faster commercialization of VAST cycle gas turbine power to ensure critical grid reliability alongside the increasing adoption of solar and wind power. Using sustainable ammonia-fueled gas turbines, this technology promises a much longer backup with better economic, energy, and environmental (E3) rankings than batteries.

[0261] The technology can be further used to develop and operate scalable combustors that burn gaseous and / or liquid ammonia (NH3), decomposed ammonia (2 NH3 = 3 H2 + N2), hydrogen, ethanol, and / or methanol with or instead of gaseous and / or liquid natural gas (or methane). The technology can enable the flexible supply of more cost-effective and practical intermediate gas turbine systems with conventional and / or sustainable fuels, including higher efficiency and profitability than picker turbines.

[0262] The increase in solar and / or wind power generation is reducing the average annual capacity usage (times used in total annual time) of combined cycle power turbines. Reducing annual capacity to <50% provides additional VAST profitability benefits over combined cycle turbines.

[0263] Pressure to eliminate coal-fired power generation signals high demand for technology that enables the rapid installation of ultra-clean ammonia-fueled VAST power to prevent blackouts in Washington, D.C., and ensure grid reliability across the United States, Japan, and the European Union (EU).

[0264] The technology of scalable combustor design addresses current and future fuel and operating trends that adapt to burning future renewable and sustainable fuels in VAST power cycles, providing greater flexibility than Brayton and / or combined heat and power (CHP) gas turbines to generate commercial mechanical or electric power and / or combined heat and power (CHP). This flexible multi-fuel scalable combustor design and operating technology promises to meet this rapidly increasing demand for flexible power and CHP gas turbines.

[0265] These technologies can be used to design and configure ultra-clean, reliable combustion using current or future liquid and / or gaseous fuels and / or liquid and / or gaseous diluents with power in the range of 10 MW to 100 MW in D to G class gas turbines. These can be used to scale down these ultra-clean combustions to 100 kW gas microturbines or smaller, and to scale up to 500 MW large gas turbines.

[0266] These techniques can be used to design and construct ultra-clean combustion systems having a combustor outlet temperature or turbine inlet temperature (TIT) of 1,100°C to 1,500°C. The scalable combustor outlet temperature can be further extended from 700°C to 1,700°C, or from a lower quenching temperature, or to the combustion wall thermal limit.

[0267] These technologies can be used to design and configure combustors with specific power over the industrial range from about 50% turndown to maximum power, such as about 30 MW / bar / m³ to 60 MW / bar / m³ specific power. These technologies can 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.

[0268] This scalable technology can be used to design and construct combustors with conventional gas turbine combustion pressures in the range of 10 bar to 40 bar. This technology can be further used to extend scalable combustion to 1.1 bar or less, and to 100 bar or more.

[0269] These technologies can be used to cool the walls of an expandable combustion section, including a flowing liquid and / or an oxidizer, fuel, and / or a diluent or a combination thereof, passing through or over the walls of the expandable combustor. They can similarly provide cooling by flowing these fluids through multiple feeders across about one or more walls of the expandable combustion section.

[0270] This technology can be used with expandable combustor walls for average wall temperatures of about 1000°C or higher and about 1500°C or higher. This technology can similarly be used with expandable combustor wall temperatures of about 500°C or lower and / or 2500°C or higher with suitable materials and / or cooling.

[0271] These techniques can be used to preheat and / or decompose a portion of ammonia by flowing it through the walls of an expandable combustor. They can similarly be used to preheat and / or decompose a portion of liquid and / or gaseous ammonia by flowing it through feeders distributed across the walls of these expandable combustors.

[0272] Scalable combustor technology can be used for combustion in the entire range of about 0.75 to 0.83 relative fuel / air equivalent mass to stoichiometric mass ratio phi (Φ) (or 1.33 to 1.20 air / fuel equivalent mass to stoichiometric mass ratio lambda), and the temperature can be independently controlled by the diluent (or water) / fuel mass ratio omega (Ω).

[0273] This scalability technology can extend the fuel / air equivalent mass ratio phi (Φ) to 0.67 or less and 0.97 or more (or equivalently extend the air / fuel equivalent ratio lambda to 1.50 or more and 1.03 or less), and has corresponding independent control of temperature by the diluent / fuel ratio omega.

[0274] This scalable combustor technology can be used to replace 50% to 100% of the stoichiometric air (or oxidizer) delivered to the cooling fluid using a recirculated diluent such as steam and / or hot water. This technology can further help replace 10% to 170% of the stoichiometric air. Depending on the size of the gas turbine, this method can reduce the relative size of the air (or oxidizer) compressor from 5% to 33% to more than 67%.

[0275] Scalable combustor technology can configure the combustion and equilibrium residence times to be between 100 ms and 700 ms. These can shorten the combustion and equilibrium residence times to 30 ms and extend them to 3 seconds.

[0276] Scalable combustor technology allows for corresponding variations in the combustion and / or equilibrium system lengths relative to the specific fluid transfer rate of the volumetric flow rate per combustion section outlet cross-sectional area. Adjusting these combustion system lengths facilitates the combustion of difficult fuels with slow flame velocities, such as ammonia. They can equally allow for the conventional combustion of common fuels, such as methane and natural gas. This also enables rapid combustion of fuels such as hydrogen.

[0277] The expandable combustor configuration technology can configure combustion systems with lengths ranging from 100 mm to 500 mm. These can be extended up to 10 mm or increased in length up to 5 m. The blend-trim area can vary from 20 mm to 100 mm. These can vary from 5 mm to 5 m. The equilibrium system length can similarly be extended from 0.2 m to 2 m. The equilibrium system length can be extended up to 0.04 m and up to a maximum of 10 m.

[0278] Power System Schematic Layout

[0279] FIG. 3a schematically illustrates a VAST cycle power system in which a VAST combustion system (VAST Combustion System: "CMB") receives oxidizer fluid compressed from an upstream compressor (Compressor: "CPR") axially at CZ3 and supplies it axially to a downstream gas turbine expander (expander: "EXP") at CZ4. This applies the gas turbine numbering methodology of the American Society of Mechanical Engineers (ASME) along the combustor axial flow Z direction ("CZ").

[0280] This VAST cycle power system illustrates a compressor (CPR) having a compressor inlet (CZ2) and a compressor outlet (CZ3). The compressed fluid flow (in this specification “WX3”) may flow into a diffuser (in this specification “DIF”). A portion of the compressed oxidizer (in this specification “WX31”) may flow from the pilot or combustor inlet plane (CZ31) to an upstream ignition system or pilot (100) (in this specification “P”). Another portion of the compressed oxidizer fluid (in this specification “WX34”) may be delivered upstream to the combustor, such as through the plane (CZ32). The diluent fluid may be delivered upstream to CZ32, such as liquid water as a spray (WDL32) into the oxidizer flow (WX34).

[0281] A portion of the diluent (WDL32) can be delivered upstream to a conventional fuel-rich combustion zone (730) from the combustion zone inlet of CZ34 to the blend-trim zone inlet and combustion zone outlet plane (CZ35) (indicated here as the combustor reference plane (CBQ)).

[0282] FIG. 3a further schematically illustrates a “blend-trim” region (850) extending through from the upstream blend-trim inlet plane (CZ35) (or combustion region outlet plane) to the downstream equilibrium region inlet plane (CZ39) (or blend-trim region outlet plane).

[0283] Equilibrium zone

[0284] Referring to FIGS. 3a and 3b, an equilibrium region (900) may be provided downstream of the blend-trim region (850). This equilibrium region (900) may extend from the blend-trim region outlet of plane (CZ39) to the transition region inlet plane (CZ394) (or equilibrium region outlet plane) to provide a residence time to further complete a reaction or combustion.

[0285] Transition zone

[0286] According to FIG. 3a, a transition region or zone (980) may follow an equilibrium region (900) to accelerate the high-temperature flow to the combustor outlet. This may extend from the end of the equilibrium region of plane (CZ394) to the combustor outlet of CZ4 and to the expander ("EXP" in this specification) or turbine inlet where the expander outlet is located in the outlet plane (CZ5). The equilibrium and transition regions may be aerodynamically configured to reduce flow pressure loss.

[0287] The turbine inlet mass flow ("W4") in this specification flows from the combustor outlet to the expander (EXP) in the axial plane (CZ4). The cooling diluent liquid mass flow ("WDL45") in this specification may be delivered to the expander to cool high-temperature parts such as blades, stators, and / or walls. The expanded fluid mass flow ("W5") in this specification may flow from the expander (EXP) in the axial plane (CZ5) to a downstream heat exchanger, which is shown herein as a Once Through Steam Generator ("OTSG"). The cooled mass flow ("W51") in this specification exits the OTSG and enters a downstream heat exchanger ("HX") (at an axial intermediate heat exchanger flow stage (CZ51) not shown).

[0288] The cooled heat exchanger outlet mass flow or exhaust flow ("W52" in this specification) (at the axial flow stage (CZ52) downstream of the heat exchanger (HX) not shown) may be further cooled downstream as desired to further condense the diluent vapor and / or further cool the diluent liquid and non-condensable flue gas, for example by using a water-cooled or air-cooled heat exchanger (not shown). In some VAST power cycle configurations, the vapor may be condensed, and a recompressor may compress the cooled-expanded excess oxidant and non-condensable combustion products back to an atmospheric pressure discharge, creating a sub-atmosphere pressure, as described in detail in a prior art patent (not shown).

[0289] FIG. 3a further illustrates upstream gas combustion temperatures controlled by a thermal diluent flow, such as water and / or steam, for fuel fluid delivery. Such diluent fluids may be delivered to multiple upstream combustion zones. For example, seven combustion zones ("C1" to "C7" herein) are illustrated in FIG. 3a and FIG. 3g, six combustion zones (unlabeled C1 to C6) in FIG. 3i, and eight combustion zones (implied but unlabeled C1 to C8) in FIG. 3n to FIG. 3q. These may be two to twenty or more combustion zones.

[0290] FIG. 3a illustrates that additional mass flow rates of an oxidizer fluid (“MX”) and a diluent fluid (“MD”) may be delivered to blend-trim regions. For example, additional oxidizers such as air, and diluents such as water and / or steam may be delivered to one or more blend regions (here denoted as one first blend region “B1” and two second blend regions “B2”) and one or more trim regions (here denoted as a first upstream trim region “T1” and a second downstream trim region “T2”).

[0291] The cooled exhaust mass flow rate (W52) at the heat exchanger (HX) outlet (axial plane (52) not shown) can be further cooled as needed.

[0292] FIG. 3a illustrates that additional oxidizers and diluents can be delivered to blend-trim regions. For example, additional oxidizers such as air, and diluents such as water and / or steam can be delivered to one or more blend regions (e.g., B1 and B2), and one or more trim regions (e.g., upstream (T1) and downstream (T2)).

[0293] FIG. 3a illustrates that an inlet mass flow rate of an oxidizing agent (or air) (here, "WX2") is introduced into the inlet (CZ2) of a compressor (CPR) along with an optional compressor inlet mass flow rate of a liquid diluent (e.g., liquid water spray mass flow rate) (here, "WDL2"), and an optional compressor cooling liquid spray mass flow rate (here, "WDL25") is introduced into the compressor (CPR) itself.

[0294] The compressor (CPR) can supply a mass flow rate of compressed oxidizer fluid flow (or air) (with optional vaporized diluent) (here "WX3") to the upstream inlet of the VAST expandable combustor (CMB) at the upstream flow position (CZ3). The downstream combustor outlet at the flow position (CZ4) can be fed into the expander (EXP).

[0295] The expandable combustor (CMB) may include an upstream diffuser (DIF) that expands and decelerates an oxidizer (or air) from the compressor outlet / diffuser inlet (CZ3) and supplies it to the upstream combustion section from CZ34 to CZ5 of the VAST combustor (CMB), which extends from the combustor pilot inlet plane (CZ31) to the downstream outlet plane (CZ4).

[0296] FIG. 3a additionally illustrates an upstream ignition control mechanism or pilot (100)(P). The pilot (P) may be supplied with a pilot fuel mass flow rate (here, "WF31"), a pilot oxidizer mass flow rate (here, "WX31"), and optionally a pilot diluent such as pilot liquid water (here, "WDL31"). An additional fuel fluid (here, "WF32") and an additional diluent fluid such as steam (here, "WDS32") may be mixed and delivered to a diluted fuel manifold as a diluted fuel fluid mass flow rate (here, "MF") to supply a transverse fuel feeder to a combustion zone (e.g., C1 to C7).

[0297] An additional oxidizer fluid (here, "WX34") is delivered along with various flows of an upstream diluent fluid (here, "WDL32") and / or, the mixture is subsequently fed progressively to a combustor through multiple feeders (C1 to C7) to deliver one or more mass flows of fuel fluid (MF), oxidizer fluid (MX), and diluent fluid (MD) that are largely oriented across or transversely to the axial flow.

[0298] Next, FIG. 3a illustrates that a stoichiometric diluted oxidizer and / or diluent mass flow is fed into a blend-trim area (850) through one or more transverse blend area feeders (B1 and B2), and the remaining oxidizer and / or diluent fluid is transferred between the combustor axial planes (CZ35 and CZ39) through one or more trim area feeders (upstream (T1), and optional downstream (T2) trim area, etc., not shown).

[0299] FIG. 3a further illustrates the mass flow rate of the liquid diluent (here "WDL42") into the heat exchanger (HX). The heated liquid from HX flows to the one-through steam generator (here "OTSG"), to the upstream combustor (here "WDL32"), to the blend-trim zone (here "WDL35"), and to the downstream combustor wall (here "WDL41") within the equilibrium and transition zones (here "WDL398").

[0300] FIG. 3a illustrates that a portion of the heated liquid diluent (WDL41) is further heated in the OTSG to form steam (referred to herein as "WDS4"). This vaporized diluent is transferred back to the blend-trim zone as WDS35 and can be transferred to the upstream zone as WDS32, such as to the upstream fuel mass flow rate (MF) in CZ32.

[0301] Premixed area

[0302] Referring to FIG. 3a, an upstream premixing zone may be provided between the compressor outlet / diffuser inlet (CZ3) and the combustion zone outlet (CZ35). This may deliver a liquid diluent (WDL32) at an oxidizer mass flow rate (MX) to one or more combustion zones (C1 to C7). This premixing zone may similarly be located between the upstream combustor inlet plane (CZ31) near the inlet (100) pilot (P) and the combustion zone inlet (CZ34).

[0303] The premixing zone may include a porous direct contact tube (14) connected to a liquid diluent supply flow (WDL31) to deliver a diluent spray to an upstream oxidizer fluid (WX34). One or more valves may be configured to control the delivery of one or more flows of fuel and / or diluent to one or more of a diffuser (DIF), a pilot (P), a combustion zone (730), and a blend-trim zone (850).

[0304] Valve (VDL42) can control the reflux flow of the diluent liquid through the heat exchanger (HX). Valve (VDL35) can control the flow of the heated liquid diluent (WDL35) into the blend-trim area (850). Valve (VDL32) can control the liquid diluent (WDL32) into the combustion area manifold (730). VF32 can control the fuel fluid flow (WF32) into the combustion system. Valve (VF31) can control the fuel fluid flow (WF31) into the pilot (P).

[0305] Expandable radial annular ("fan") combustion array configuration

[0306] Referring to FIG. 3b, a general schematic three-dimensional perspective view, some expandable combustor embodiments may include a streamlined flow axis having a combustion section (732) that extends laterally with respect to a shallowly separated opposing combustor wall (736). This laterally extended wall (736) of the extended combustion section (732) may be bounded by a side wall (734). The relative circumferential transverse wall extension may be greater than 1.15 times the shallow gap due to the radial depth of the side wall (734) of the adjacent combustor wall between the opposing transverse-axial combustion chamber walls.

[0307] In FIG. 3b, a portion of the expandable combustor (CMB) is shown opening and extending from the flame control mechanism (100) or pilot (P) located at the axial flow position (CZ31) around the outlet of the upstream diffuser (DIF) to the downstream equilibrium area (900) through the combustion section (730) and downstream blend-trim area (850).

[0308] FIG. 3b illustrates one embodiment of a cylindrical-axial (circumferentially-radially stacked) combustor (702) plotted in cylindrical coordinates having a radial axis ("R") perpendicular to an axial flow axis (Z) having circumferential theta (θ). In other configurations, the expandable combustor may use a curved flow axis having non-cylindrical walls.

[0309] These embodiments may include multiple expandable ("fan") combustion shells (or burners) configured generally around a radial-circumferential theta (R-θ) cylindrical surface. These cylindrical combustion shells may be stacked radially and generally perpendicularly with respect to the primary streamline flow axis of an oxidizing fluid (F5) passing through an expandable combustor, oriented along the axial (Z) flow direction from an upstream fluid inlet (134) to a fluid flow outlet (136) for a heated and pressurized high-temperature combusted fluid (F20).

[0310] According to FIG. 3b, in order to operate at elevated pressure, this expandable cylindrical combustor embodiment (702) may be configured within the outer pressure vessel wall (172). The pilot fuel fluid flow (F3) and the pilot oxidizer fluid flow (F6) may be delivered to an upstream igniter, flame control mechanism, or pilot (100) configured to combust these fluids to form a high-temperature pilot fluid flow (F22).

[0311] The pilot diluent fluid (F8) flow can be delivered separately to the pilot (100) and / or mixed with the pilot fuel fluid (F3) and / or pilot oxidizer fluid (F6) flowing into the pilot (100) from the upstream pilot area (720).

[0312] According to FIG. 3b, this upstream high-temperature pilot fluid flow (F22) from the pilot (100) can be distributed to the upstream end of a pilot fluid distribution system (722) comprising one or more expandable pilot fluid transfer ducts (or “fan” burner ducts) (728) in an upstream pilot area (720). These pilot fluid transfer ducts (or “fan” burners) (728) can be configured circumferentially around a cylindrically stacked expandable combustor (702).

[0313] The pilot fluid transfer duct (728) can transfer high-temperature pilot fluid from the axial intermediate combustion zone (730) to one or more combustion systems (or intermediate fan burners) (732).

[0314] Referring further to FIG. 3b, each combustion system (732) includes two radially opposing circumferential combustion radial outer sidewalls (736) (generally together with corresponding radial inner sidewalls). These combustion radial outer sidewalls (736) may be bounded and connected by corresponding combustion (mid-fan) (circumferentially) end walls (734). In other configurations, the radial sidewalls (736) may be curved around to meet the combustion area radially and to define the boundary laterally or circumferentially.

[0315] Each combustion system radial sidewall (736) may include a plurality of fluid transfer orifices (80) as schematically illustrated in FIG. 3c. Pressurized oxidizer fluid (F5) may be transferred to a cylindrical-axial combustion system (702) and transferred to a combustion system (732) through the orifices (80) configured in the combustion system radial sidewall (736).

[0316] Similarly, according to FIG. 3b, the diluted fuel fluid (F2) can be delivered through a similar axial fuel manifold (770) between circumferentially adjacent combustion zones on the alternating side of the combustion zone from the oxidizer fluid (F5) delivery.

[0317] In an additional configuration, a premixed reactive fuel-oxidizer mixture having an optional diluent is delivered to a cylindrical-axial combustor (702) and can be delivered through the porous combustor radial sidewall (736) within a combustion system (732) in a combustion zone (730).

[0318] According to FIG. 3b, high-energy fluid from one or more combustion systems (732) within a combustion zone (730) can be delivered to a circumferential downstream blend-trim zone (850) comprising a blend-trim oxidizer-diluent delivery and reaction zone manifold wall (857) that supplies the relevant blend-trim reaction zone. Each blend-trim reaction zone (850) may include opposing circumferential blend-trim porous sidewalls (857) that demarcate combustion within the zone.

[0319] The blend-trim area sidewalls (857) can generally be connected by one or more distal-fan end walls (746). The blend-trim sidewalls (857) can also be configured to be joined at their circumferential transverse ends. Multiple sets of circumferential combustors (732) and blend-trim areas (850) can be configured within the combustor outer wall or pressure vessel (172).

[0320] FIG. 3c shows an enlarged view of a radial side wall (736) of a combustion chamber wall section showing an orifice (80) penetrating a combustion chamber fluid duct wall (132) protected by an insulating barrier (150).

[0321] Symmetric combustor

[0322] FIG. 3d illustrates a sample radial circumferential (R theta) cross-section of a portion of the combustion zone extending circumferentially by the combustion section angle (THC). This embodiment illustrates an oxidizer manifold on the CCW side supplying an oxidizer fluid (F5), and a THBMX CW portion supplying to two adjacent CW combustion zones. On the CW side, FIG. 3d illustrates a fuel manifold including a THBMF CW portion supplying to two radially adjacent combustion zones including a combustion feeder radial depth (thickness) (CR15T).

[0323] FIG. 3d further illustrates an outer oxidizer fluid feeder extending radially with a radial depth (thickness) (CR12T) inside an outer circumferential wall having an inner radius (CR12). The outer oxidizer fluid feeder extends circumferentially over an inner angle (THBFX4) and supplies oxidizer fluid through multiple orifices into a combustion zone extending radially with a radial depth (or thickness) (CR15T) from the inner radius (CR15) of the outer wall to the outer radius (CR16) of the inner wall.

[0324] An oxidizing fluid (F5) having an optional diluent (e.g., water vapor or mist) may flow along an oxidizing fluid feeder and through an oxidizing orifice having a typical diameter (DXO) into a radially adjacent outer combustion zone extending radially with a depth (or thickness) (CR15T) between the outer radius (CR15) and the inner radius (CR16) of the combustion chamber. These oxidizing orifices are offset from the CCW manifold by a circumferential angle (THBXO) and spaced apart by a circumferential angle (THBXS), and the J-th orifice within the I-th oxidizing feeder is located at a circumferential angle (THBXIJ).

[0325] FIG. 3d further illustrates a fuel fluid flow (F2) that is optionally diluted with a diluent fluid and flows through a CW combustion zone manifold extending through a circumferential theta angle (THBMF). This CW fuel fluid manifold delivers the fuel fluid through a fuel supplement feeder extending radially with a depth (thickness) (CR18T) and supplies the fuel fluid through a fuel fluid orifice having a typical fuel orifice diameter (DFO) to an outer combustion zone between CR15 and CR16 extending radially with a depth (thickness) (CR15T) and spanning approximately a circumferential angle (THBFF4). This fuel feeder with a depth (CR18T) can similarly supply fluid to an inward combustion zone extending radially between CR25 and CR26 and extending circumferentially across THBFF4.

[0326] Additionally, referring to FIG. 3d, the oxidizer fluid (F5) can be similarly delivered radially (and longitudinally) into the CCW combustion zone through the CCW manifold angle (THBQX). On the CW side, the diluent fluid (F7) can be delivered circumferentially and axially along the combustion zone by THMDS for each of the central and CW combustion zones.

[0327] FIG. 3e illustrates an axial circumferential (Z theta) “unfolded” plan view of two adjacent symmetric combustion and blend-trim regions having circumferential CCW boundary end walls (734) and CW boundary end walls (735). These combustion regions may extend axially from an upstream pilot (100) outlet or combustion inlet (CZ34) to a downstream axial boundary (CZ35). The downstream blend-trim region may extend from CZ35 to CZ39.

[0328] According to FIG. 3e, these adjacent symmetric combustion zones are illustrated here as having adjacent CCW oxidizer fluid manifold zones that transport oxidizer fluid (F5) per combustion zone to a duct. They may have adjacent CW fuel manifold zones that transport diluted fuel fluid (F2) to a duct.

[0329] These CCW oxidizer manifolds and adjacent CW fuel manifolds are commonly demarcated and divided between the upstream (CZ34) and downstream (CZ35) combustion boundaries by an S-shaped longitudinal (radial) manifold distributor (250), and can extend axially from there to the blend-trim area between the plane (CZ35) and downstream (CZ39).

[0330] FIG. 3e further illustrates an upstream circumferentially increasing width region (731) having an axial flow distance downstream of the pilot (100) and an increasing width having an outer wall curvature along the axial direction. This can advantageously accommodate an increasing mass flow rate and an increasing volumetric flow rate axially from the rising temperature due to combustion, thereby reducing fluid acceleration and pressure drop losses.

[0331] FIGS. 3a and 3e illustrate a configuration having a downstream circumferentially decreasing combustion zone (733) having a wall curvature of width that decreases axially in the circumferential direction. This can advantageously provide an aerodynamically smoother joint having an equilibrium zone extending downstream from plane (CZ39) to plane (CZ394). FIG. 3e illustrates an additional axial intermediate combustion transition zone (732). This combustion intermediate transition zone (732) can change, depending on the axial distance, from a wall curvature of width that increases axially, such as in the combustion upstream section (731), to a wall curvature of width that decreases axially, such as in the combustion downstream section (733).

[0332] FIG. 3e illustrates the distribution of fuel fluid delivery orifices (81) and oxidizer fluid delivery orifices (82) that open to the combustion zone from CZ34 to CZ35. An additional distribution of oxidizer and / or diluent delivery orifices (83) may be configured to open downstream from the blend-trim zone from plane (CZ35) to plane (CZ39).

[0333] According to FIG. 3e, a downstream blend-trim manifold region may be provided to axially deliver an oxidizer fluid (F4 not shown) or a diluted oxidizer fluid (F5) between axial planes (CZ35 and CZ39), and is bounded by a circumferential manifold CCW wall (250) and a manifold CW wall (734), and has an axial upstream boundary wall (249) between the upstream delivery of the diluted fuel flow (F2) (or fuel fluid flow (F1) not shown) and the downstream delivery of the blend-trim diluted oxidizer fluid (F5) (see below for discussion of FIG. 3f illustrating exploratory NH3 combustion).

[0334] FIG. 3g illustrates an “unfolded” plan view in the axial circumferential direction (Z theta) corresponding outward (or inward) to the symmetrical combustor fluid feeder region. This extends axially in the flow direction from the upstream pilot (100), together with a CCW axial diluted oxidant fluid manifold region (244) that transports the upstream diluted oxidant fluid (F4) to the upstream oxidant feeder via a duct. The fluid feeder region of FIG. 3g may further include a second CCW axial oxidant manifold (245) that transports the downstream diluted oxidant fluid (F5) to a duct.

[0335] The configuration of FIG. 3g illustrates a first fuel fluid (F1) containing fuel to an upstream feeder, similarly shown in a first fuel manifold region (242) inside the CW that transports the first fuel fluid (F1) to the duct. This can be split from the fuel fluid manifold region (243) to a second intermediate CW outside, such as by an upstream / downstream fuel fluid manifold dividing wall (252), that transports an additional downstream diluted fuel fluid flow (F2) (or other flow of fuel fluid) to the duct.

[0336] In FIG. 3g, additionally, similarly, the fuel feeder to blend-trim split wall (253) from upstream to downstream can split and separate the upstream diluted fuel fluid (F2) flowing through the intermediate fuel fluid manifold region (243) between CZ34 and CZ35 from the blend-trim diluent flow (F7) flowing downstream into the blend-trim region (850) between plane (CZ35) and plane (CZ39). The manifold boundary wall (253) may be adjacent to a downstream diluted oxidant or diluent fluid feeder extending down to plane (CZ39).

[0337] In FIG. 3g, the CCW oxidizer fluid manifold and the CW fuel fluid manifold can be separated by an S-shaped longitudinal radial manifold distributor (250) that cools a downstream transverse trim feeder ending axially in a plane (CZ39). The downstream combustion-oxidizer fluid manifold distributor (248) can be similarly curved and configured parallel to the manifold distributor (250) and aerodynamically curved as it connects upstream of the transverse mixing-trim feeder opening in CZ35.

[0338] The axial-radial manifold distributor (253) forming the boundary between the diluted fuel fluid flow (F2) and the diluent fluid flow (F7) may be curved or S-shaped from upstream (CZ34) to downstream of CZ35 adjacent to the oxidant feeder delivering the oxidant fluid (X7) (or optionally diluted oxidant fluid).

[0339] In FIG. 3g, an axial radial mid-upstream combustion oxidizer manifold split wall (247) can split the diluted oxidizer-rich upstream fluid manifold (244) from the second diluted oxidizer-rich downstream fluid manifold (245). Similarly, a downstream axial radial oxidizer-mix-trim manifold wall (248) can split the intermediate stream second oxidizer fluid manifold (245) from the diluted oxidizer-mix-trim manifold (246), together with a radially extending adjacent wall having multiple circumferentially adjacent oxidizer fluid and fuel fluid manifolds and an upstream pilot (100).

[0340] In FIG. 3g, the first fuel fluid (F1) (optionally diluted) can be delivered into a fuel fluid manifold (242) bounded by a fuel feeder upstream / downstream manifold dividing wall (252) and can be delivered as multiple fuel fluids such as U1, U2 and U3 flowing through each of the 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 the range.

[0341] Similarly, the second diluted fuel fluid (F2) (or the second fuel fluid flow not shown) is delivered to the downstream fuel fluid manifold (243) and enters the multiple transverse fluid fuel fluid feeders as multiple fuel fluid flows (U4, U5, U6 and U7), and then can enter the adjacent combustion zone through the fuel fluid orifice (81A). These fuel fluid feeders may have an axially increasing number of fuel fluid orifices (81A) per transverse fuel fluid feeder over the axial range.

[0342] According to FIG. 3g, the oxidizer fluid (F4) can be delivered as oxidizer fluid flows (X1, X2 and X3) through a diluted oxidizer fluid upstream manifold (244) via multiple transverse oxidizer fluid feeders and subsequently through an oxidizer fluid orifice (82A). This delivery of the oxidizer fluid (F4) can be intersected with the delivery of the first fuel fluid (F1) through each upstream transverse fuel fluid feeder, for example, through U1 to U3.

[0343] Similarly, the oxidizer fluid (F5) can be delivered through multiple transverse oxidizer fluid feeders as oxidizer fluid flows (or optionally diluted oxidizer fluid) such as X4, X5, X6, and X7 through a diluted oxidizer fluid downstream manifold (245), and then introduced into adjacent combustion zones through multiple oxidizer fluid orifices (82B).

[0344] This oxidizer fluid delivery through the oxidizer feeder can interleave fuel fluid delivery flows such as U4 to U7 through each transverse fuel fluid feeder in the upstream combustion zone from CZ34 to CZ35.

[0345] According to FIG. 3g, the diluted oxidizer fluid (F6) can be delivered to a downstream blend-trim feeder, as one or more blend fluids such as B1 and B2, through a CCW diluted oxidizer blend-trim manifold (246), through a transverse blend feeder, and through an upstream blend-trim orifice (83A) and an intermediate stream blend-trim orifice (83B) to a radially adjacent blend-trim area downstream of the combustion zone.

[0346] Similarly, a portion of the diluted oxidizer fluid (F6) can be delivered as one or more trim fluid flows, such as T1, through a transverse trim feeder and then through a downstream blend-trim orifice (83C) to a radially adjacent blend-trim area between plane (CZ35) and plane (CZ39) axially downstream of the combustion zone.

[0347] According to FIG. 3g, correspondingly, the blend-trim diluent fluid (F7) can be delivered through the CW diluent-trim manifold (238) to the diluent-trim area (850) between CZ35 and CZ39 downstream. The blend-trim diluent fluid (F7) can be delivered as one or more diluent fluids (D1, D2 and D3) through a transverse diluent feeder and then through diluent fluid orifices (86A, 86B and 86C) to the radially adjacent downstream blend-trim area of ​​the combustor.

[0348] According to FIG. 3g, the walls (253 and 250) of the CW diluent trim manifold (238) into the blend-trim feeder area may be curved outward in the axial upstream section (731). They may similarly be curved inward in the axial downstream section (733).

[0349] The intermediate combustion zone (732) may be an S-shaped curved section to aerodynamically connect the upstream section (731) and the downstream section (733) (in other configurations, the intermediate combustion zone (732) may be linear). The downstream section (850) of the boundary wall (250) may be transitioned from the inwardly curved section (733) to aerodynamically connect with the downstream equilibrium zone axial slope.

[0350] Asymmetric combustion system

[0351] According to FIGS. 3h and 3i, some combustor configurations may use an asymmetric combustor with respect to a longitudinal oxidizer manifold that supplies transverse circumferential oxidizer fluid feeders to the CCW and CW sides of the oxidizer manifold. Such asymmetric combustor configurations may similarly use a common longitudinal fuel manifold to supply corresponding multiple adjacent fuel feeders in adjacent combustors.

[0352] Asymmetric combustion zone

[0353] FIG. 3h illustrates a circumferentially “unfolded” plan view of two adjacent asymmetric combustion zones having a circumferential axis theta perpendicular to the axial fluid flow axis (Z) and the radial axis (R). This may have radially adjacent combustor walls in the combustion zones and have a fuel fluid orifice (81), an oxidizer fluid orifice (82), and / or a blend-trim zone diluent fluid delivery orifice such as reference numeral (83).

[0354] According to FIG. 3h, this asymmetric combustion zone configuration may have circumferentially adjacent oxidizer fluid manifolds bordered by a combustion chamber transverse CCW side end wall (734) that directs the oxidizer fluid (F5) between the upstream combustion zone inlet (CZ34) and the downstream combustion fluid end (CZ35). They may similarly have circumferentially adjacent boundary fuel fluid combustion chamber transverse CW side end wall (735) that delivers the fuel fluid (F2) between CZ34 and the downstream combustion zone manifold end split wall (249).

[0355] Additionally, according to FIG. 3h, the diluted oxidizer fluid (F7) can be delivered to a downstream blend-trim manifold region (850) that is bounded by a lateral boundary manifold wall (735) and an axially bounding downstream manifold end split wall (249) and extends axially from plane (CZ35) to plane (CZ39). Some asymmetric combustion region configurations may include a common upstream pilot (100) that supplies to adjacent combustion shells. This pilot (100) may be supplied by a pilot fuel fluid (F3), a pilot oxidizer fluid (F6), and a pilot diluent fluid (F8).

[0356] The asymmetric combustor configuration of FIG. 3h may have an S-shaped curved oxidizer fluid boundary suitable for such an asymmetric configuration as described in FIG. 3h. This may have an upstream manifold-combustion zone boundary wall section (731) that curves outwardly in the circumferential direction (theta) with an axially increasing distance (Z).

[0357] According to FIG. 3h, the asymmetric combustor may have a downstream manifold that is correspondingly curved inwardly in the circumferential direction (theta), bounded by a downstream transverse end wall section (733) of the combustion chamber having an increasing distance (Z) in the axial direction. The asymmetric combustor configuration of FIG. 3h may have a connecting intermediate combustion chamber intermediate stream transverse end wall (732) that transitions from the outside to the inner circumferential-axial curvature.

[0358] The oxidizer fluid manifold of FIG. 3h may additionally have a downstream blend-trim region (850) having a blend-trim diluent / oxidizer fluid manifold wall (734) that may have an aerodynamically changing curvature between the axial upstream adjacent combustion region downstream transverse end wall (733) and the downstream equilibrium region wall extending from CZ39 according to FIG. 3a to the equilibrium region (900).

[0359] The corresponding fuel fluid side boundary manifold wall (735) may have a similar curvature with a correspondingly shallower curvature. In other configurations, the side boundary fuel fluid manifold wall (735) may be straight.

[0360] Asymmetric manifold and transverse fluid transfer region

[0361] FIG. 3i illustrates an example of a circumferentially "stretched" circumferential-axial (Z theta) asymmetric combustor fluid feeder configuration. This illustrates a fluid axial (longitudinal) manifold wall, an upstream transverse fuel feeder and an oxidizer fluid feeder, fuel, oxidizer and diluent fluid delivery orifices, an axial upstream pilot (100) delivering pilot fluid from CZ34 to an upstream combustion zone, and a combustion wall having a downstream outlet to a combustor equilibrium zone from CZ39, shown radially outward.

[0362] This circumferentially and axially asymmetric configuration allows for the use of fewer fuel fluid manifolds and oxidizer fluid manifolds than those used in the symmetric combustion system expandable shell combustors described in FIGS. 3b to 3e and FIG. 3g.

[0363] The configuration illustrated in FIG. 3i may include a pilot fuel fluid (F3), a pilot oxidizer fluid (F6), and a pilot diluent fluid (F8) supplied to an upstream pilot (100). On the clockwise side, a portion of the first fuel fluid flow (F1) may be delivered as fuel fluid (U1) to an upstream transverse fuel fluid feeder and then delivered to a combustion zone through one or more fuel fluid orifices (81A).

[0364] Similarly, additional portions of the first fuel fluid (F1) can be gradually transferred to a downstream transverse fuel fluid feeder to supply fuel fluids (U2 and U3). These can be transferred from the transverse fuel fluid feeder to a radially adjacent combustion zone through a similar or increasing number of fuel fluid orifices (81A).

[0365] FIG. 3i illustrates an oxidizer fluid manifold that similarly supplies oxidizer fluid (F4) flows (X1, X2 and X3) to respective transverse oxidizer fluid feeders and thereto gradually axially to radially adjacent combustion chambers through oxidizer fluid orifices (82A).

[0366] The size (or area) and number of each fuel fluid orifice (81) and oxidant fluid orifice (82) can be configured to provide a desired range of relative fuel to the oxidant composition relative to the stoichiometric composition (PHI) (or equivalently, relative oxidant to the fuel ratio (LAMBDA)).

[0367] According to FIG. 3i, the first fuel fluid (F1) and / or oxidizer fluid (F4) may include a gaseous and / or liquid diluent, such as steam, water vapor, and / or liquid water, which is delivered to the combustion chamber through a transverse feeder and an orifice.

[0368] According to FIG. 3i, the diluted fuel fluid (F2) can be delivered axially through a fuel fluid manifold and subsequently delivered as a fuel fluid flow (U4, U5, U6 and / or U7) to one or more transverse fuel fluid feeders. These can be delivered from the fuel fluid feeders through a plurality of fuel fluid orifices (81B) from the combustion intermediate stream wall region (732) through the combustion downstream wall region (733) to a radially adjacent combustion chamber located in the downstream portion of the combustion region.

[0369] According to FIG. 3i, the oxidizer fluid flow (F5) can be delivered through an outer axial oxidizer fluid manifold and then to each transverse oxidizer fluid feeder as one or more oxidizer fluid feeder flows such as X4, X5, X6, and therefrom to a radially adjacent combustion zone through an oxidizer fluid orifice (82B). For example, it can be delivered from an intermediate zone (732) to a radially adjacent combustion zone in a downstream combustion zone passing through a downstream combustion zone (733).

[0370] According to FIG. 3i, a diluent fluid (F14), such as liquid water, is delivered to a downstream blend-trim area through one or more transverse feeders, such as diluent fluid flows (D1 and D2), and then can be delivered to an axially and radially adjacent blend-trim area (850) between planes (CZ35) and (CZ39) within the combustor through an orifice (86A).

[0371] Accordingly, according to FIG. 3i, an additional oxidizer fluid optionally containing a diluent fluid can be delivered as a blend-trim fluid (B1 and / or T1) through a transverse blend-trim feeder, and then axially between plane (CZ35) and plane (CZ39) through blend-trim orifices (83A and 83C) to a downstream blend-trim area (850) of the combustion chamber.

[0372] Cooling upstream combustion

[0373] The embodiments described herein enable additional flexibility in configuring diluent delivery separately from oxidant and fluid delivery. This can be advantageously used to reduce combustion temperature regardless of the relative fuel (or relative oxidant for fuel composition lambda) to the oxidant composition (Phi). This allows for reducing combustion temperature with higher oxidant compositions, and thus NO x Reduces harmful emissions such as emissions.

[0374] Accordingly, in some additional configurations, some or all of the gaseous and / or liquid diluent fluids (D1 and D2) may be delivered together with one or more fuel fluid flows (U5 to U7). Similarly, some or all of these gaseous and / or liquid diluent fluids (D1 and D2) may be delivered together with oxidizer fluids (X4, X5 and / or X6).

[0375] This increase in diluent fluid along with the flow of combustion fuel and oxidizer fluids lowers the combustion temperature, and consequently NO x It can be used to reduce the formation of emissions such as. In some configurations, this can be delivered along with an oxidizer-rich or stoichiometric portion to form an associated oxidizer-rich or stoichiometric combustion region.

[0376] In some configurations, one or more of the axial upstream and downstream manifold walls may be axially significantly aligned between the upstream combustion zone in the CZ34 and the downstream connection with the associated transverse fluid transfer feeder. This alignment can advantageously reduce the rate of change of the axial fluid flow cross-sectional area (expansion) and the transfer flow rate, and consequently reduce the associated fluid pressure drop.

[0377] FIG. 3j illustrates a schematic diagram of a combustion section “stretched” circumferentially (Z theta) with a radially inner (or outer) wall configuration, showing a larger and more numerous upstream oxidizer fluid delivery orifice (82) and a smaller and fewer downstream fuel fluid delivery orifice (81). For example, the ratio is 2:1. The oxidizer fluid orifice may be circumferentially offset from the fuel fluid orifice to improve mixing and reduce quenching.

[0378] FIG. 3k illustrates a schematic circumferential (Z theta) "spread" combustion section radially inward (or outward) wall configuration having fewer upstream fuel fluid delivery orifices (81) and more downstream oxidizer fluid delivery orifices (82). For example, a ratio of 1:2. The fuel fluid orifices may be circumferentially offset from the oxidizer fluid orifices to improve mixing and reduce the probability of quenching.

[0379] FIG. 31 illustrates a schematic circumferential (Z theta) "stretched" configuration of a downstream blend-trim area section having oxidant fluid orifices (83A and 83C) on the blend-trim area wall radially outward (or inward). The upstream blend-trim orifice (83A) may be offset clockwise (CW) from the downstream blend-trim area orifice (83C).

[0380] FIG. 3m illustrates a schematic configuration of a sample of a downstream blend-trim section having oxidant fluid delivery orifices (83A and 83C) on the radially inner (or outer) blend-trim area wall. Here, the upstream blend-trim orifice (83A) may be offset clockwise (CW) from the downstream blend-trim orifice (83C) in a counterclockwise (CCW) direction.

[0381] Corresponding to FIG. 3L and FIG. 3M, the blend-trim orifices (83A and 83C) configured radially outward of the combustion zone may be offset clockwise (CW) and counterclockwise (CCW) from the blend-trim orifices (83A and 83C) configured radially inward of the combustion shell. A similar method may be used to improve mixing with the fuel fluid orifice and / or oxidizer fluid orifice in the combustion upstream wall region (731), midstream wall region (732), and downstream wall region (733) of the combustion chamber.

[0382] FIG. 3n illustrates a schematic configuration of a sample (nominal radial-axial (RZ)) from upstream to downstream of an upstream combustion zone passing through a counterclockwise (CCW) circumferential outer combustion zone wall (734).

[0383] FIG. 3n, which is this sample configuration, illustrates eight radially outer oxidizer fluid delivery openings (X1 to X8) for a radially outer oxidizer fluid feeder (or diluted oxidizer fluid feeder). These are eight radially inner oxidizer fluid (or diluted oxidizer fluid) passage openings ( X1 inside X8 It can be supplemented by ) and scattered with them.

[0384] FIG. 3o illustrates a schematic configuration of a sample (nominal radial-axial (RZ)) from upstream to downstream of an upstream combustion zone located inside the outer end wall (734) of the CCW circumferential direction, having eight radial outer oxidizer fluid delivery openings (X1 to X8) (or diluted oxidizer fluid delivery openings) within an outer transverse oxidizer feeder.

[0385] FIG. 3o shows eight scattered radial inner oxidizer fluid delivery openings (X1 to X8) in an inner transverse oxidizer feeder ( X1 inside X8 It is further illustrated that these may be supplemented with )(or diluted oxidant fluid delivery openings). These oxidant fluid channels (X1 to X8 and X1 to X8 ) may be interspersed with narrower fuel fluid delivery paths (not shown).

[0386] FIG. 3q illustrates a schematic configuration of a sample (nominal radial-axial (RZ)) of an upstream combustion zone through a clockwise (CW) circumferentially outer side boundary combustion zone end wall (735) having eight radially outer fuel fluid delivery openings (U1 to U8). These are eight radially inner fuel fluid passage openings ( U1 insideU8 It can be supplemented by ) and scattered together with it.

[0387] FIG. 3p illustrates a schematic configuration of a sample (nominal radial-axial (RZ)) of an upstream combustion zone located inside the outer end wall (735) in the circumferential direction of the CW, having eight oxidizer fluid feeder delivery passage openings (U1 to U8) interspersed with eight oxidizer fluid feeder delivery passage openings (e.g., unlabeled X1 to X8).

[0388] FIGS. 3n through 3q further illustrate combustor radial height (or length) parameters labeled from the first outward combustion shell toward the next inward combustion shell. For example, CR12 represents the outer radius of the radially outer oxidizer fluid feeder wall. CR15 represents the radially inner radius of the radially outer combustion zone wall. CR16 represents the outer radius of the radially inner combustion zone wall. CR24 represents the radially inner radius of the radially inner oxidizer fluid feeder wall.

[0389] FIGS. 3n through 3q further illustrate combustor radial internal height parameters labeled along the radial R-axis from the first outward combustion shell toward the next inward combustion shell. For example, CR12T labels the radial internal depth (height or thickness) of the outer oxidizer fluid transverse feeder illustrated in FIGS. 3n and 3o. CR12T similarly labels the radial internal height of the outer fuel fluid transverse feeder illustrated in FIGS. 3p and 3q.

[0390] The radial parameter (CR15T) labels the radially inner height (thickness) of the combustion zone between CR15 and CR16 as shown in FIGS. 3o and 3p. CR18T similarly labels the radially inner thickness of the oxidizer and fuel transverse feeders between CR16 and CR24 as shown in FIGS. 3n through 3q.

[0391] FIGS. 3n to 3q further illustrate the combustor axial boundaries along the axial flow Z-axis from the upstream combustion zone boundary at CZ34 to the downstream combustion fluid transfer boundary at CZ35 in the reference plane (CBQ).

[0392] FIG. 3o further illustrates the typical axial inner inlet width (810) of radially outer transverse oxidizer fluid feeders (X1 to X8) supplying to a central combustion zone near the outer open side (e.g., the counterclockwise (CCW) side near the oxidizer fluid feeder opening from an adjacent oxidizer manifold).

[0393] A radially inner transverse oxidizer fluid feeder supplying oxidizer fluid to the central combustion zone in Fig. 3o ( X1 inside X8 The axial inner axial width of ) may be similar and may extend outwardly according to the radial distance from the combustor axis to each feeder. FIG. 3o further illustrates the corresponding axial inner distal end width (809) of the radially outer transverse fuel fluid feeders (U1 to U8) near the transversely closed end of the fuel fluid feeder near the adjacent oxidizer fluid manifold (e.g., CCW side).

[0394] FIG. 3p further illustrates the typical axial inner inlet width (808) of a radially outer transverse fuel fluid feeder (U1 to U8) supplying to a central combustion zone near the outer open side (e.g., the clockwise (CW) side near the fuel fluid feeder opening from an adjacent fluid manifold).

[0395] A radially inner transverse fuel fluid feeder supplying fuel fluid to the central combustion zone in FIG. 3p ( U1 inside U8 The inner axial width of ) may be similar and may be extended according to the radial distance outward from the combustor axis to each feeder.

[0396] FIG. 3p further illustrates the corresponding axial inner width (811) of the outer transverse oxidizer fluid feeder (unlabeled X1 to X8) near the transversely closed end of the oxidizer fluid feeder located near the adjacent fuel fluid manifold (e.g., CW side). FIG. 3p similarly illustrates the inner transverse oxidizer fluid feeder (unlabeled 811) having a corresponding inner width between the fluid feeder walls between CR16 and CR24. X1 to X8 It shows (not labeled).

[0397] FIG. 3r schematically illustrates an axial circumferential (Z theta) planar perspective view of a pair of transverse fluid feeders that deliver an oxidant fluid (X) to multiple oxidant fluid orifices (82) having a typical oxidant fluid orifice diameter (DXO) and deliver a fluid (F) to multiple fuel fluid orifices (81) having a typical fuel fluid orifice diameter (DFO). The fuel fluid feeders are shown having an axial width (DFF) compared to a wider oxidant fluid feeder having an axial width (DFX). In some configurations, a diluent feeder having a diluent fluid feeder width (DFD) may be used (not shown).

[0398] According to FIG. 3r, in some configurations, the fuel fluid orifice (81) in the fuel fluid feeder may be circumferentially displaced by a positive clockwise (CW) circumferential angle (THF) from the vertical plane. In some configurations, the oxidizer fluid orifice (82) may be configured as a pair located circumferentially around the fuel fluid orifice (81), having a narrower circumferential separation angle (THXN) between the nearest centers of the oxidizer fluid orifices (82) of the separated orifice pair. The oxidizer fluid orifice (82) may have a wider adjacent orifice circumferential separation angle (THXW) between the centers of the oxidizer orifices of the more widely separated orifice pair.

[0399] In other configurations, the oxidizer orifices may be spaced further apart or spaced uniformly. As schematically illustrated in FIGS. 3e, 3h, and 3i, the circumferential spacing of the orifices around the combustor may be further varied along different fluid feeders in the axial direction. These may use either or both of the circumferential uniform spacing and the circumferential asymmetric spacing.

[0400] In some configurations, the circumferential gap may be closer to the inner and outer combustion chamber boundaries of one and / or both than to the inner circumferential region. Other configurations may provide more space between the orifices near the circumferential boundaries.

[0401] FIG. 3s illustrates a different axial circumferential plan view of a fuel feeder that supplies fuel fluid (F) through a fuel fluid orifice (81) and an axially adjacent oxidizer fluid feeder that supplies oxidizer fluid (X) through a plurality of oxidizer fluid orifices (82). This configuration is illustrated with the oxidizer fluid orifices (82) separated in the axial direction (Z) and aligned in the radial direction (theta).

[0402] The oxidizer fluid orifice (82) may be aligned circumferentially similarly to the fuel fluid orifice (82) as illustrated herein. This configuration can improve jet penetration into the combustion fluid flow. In another configuration, the oxidizer orifice may be aligned axially and collectively offset circumferentially from the fuel fluid orifice (82).

[0403] FIG. 3t illustrates a schematic radial circumferential (R theta) cross-sectional “elevation” of an outer combustion zone wall (736) having an insulating liner (738) that delineates the combustion zone by an outer radius (CR15). The outer fuel fluid orifice (87) may be configured to deliver fuel fluid in a negative CCW direction at a positive angle (PhiX) (or a negative angle (-PhiX)) from the radial axis (R).

[0404] FIG. 3t further illustrates an inner combustion zone boundary wall in CR16 that is radially displaced by a radial thickness (CR15T) from the outer combustion zone wall. The radial inner combustion wall may have an outer insulating liner (738) protecting the radial inner structural wall (737). The inner oxidizer fluid orifice (88) may be configured at a negative angle (-PhiX) (or a positive angle (PhiX)) opposite the radial axis (R) to deliver the oxidizer fluid in a negative CCW direction.

[0405] The configuration of FIG. 3t may be similarly configured to have a fuel fluid orifice (87) oriented at a negative angle (-PhiX) and an oxidizer fluid orifice (88) oriented in the opposite direction at a positive angle (PhiX). Additional configurations may include both fuel fluid orifices (87) and oxidizer fluid orifices (88) configured at the same positive angle (PhiX). Similar configurations may include fuel fluid orifices (87) and oxidizer fluid orifices (88) configured at similar negative angles (-PhiX) (or positive angles (PhiX)).

[0406] In the configuration of FIG. 3t, some fuel fluid delivery orifices (87) and oxidizer fluid delivery orifices (88) within the axially offset fluid feeder may be circumferentially oriented at similar positive angles (PhiX) (or negative angles (-PhiX)). In other configurations, generally, the upstream fluid delivery orifice (87 (or 88)) and downstream fluid delivery orifice (88 (or 87)) may be composed of opposing positive angles (PhiX) and negative angles (-PhiX) of the oxidizer (not shown).

[0407] In a further generalized configuration as illustrated in FIG. 3g (as in FIG. 3t), the upstream fuel fluid orifice (81A) may be circumferentially offset from (or aligned with) the downstream oxidizer fluid orifice (82B). Similarly, according to FIG. 3g, the upstream oxidizer fluid orifice (82A) may be circumferentially offset from (or aligned with) the downstream oxidizer fluid orifice (82B).

[0408] FIG. 3u illustrates a radial circumferential (R theta) "elevation view" of a sample configuration of an outer transverse fuel feeder labeled F and an alternating outer oxidizer transverse feeder labeled X. These fuel and oxidizer feeders may have a radial outer wall (802) bounded by an outer radius (CR11). These feeders may have a radial inner wall (801) bounded by an inner feeder radius (CR15) and forming a radial outer surface of an inner first combustion zone. The outer feeder inner wall (801) may include a radially outer side wall (736) that is covered with a protective insulating coating (738) on the inner combustion zone side.

[0409] FIG. 3u further illustrates a fuel feeder (F) comprising a fuel fluid orifice (87) for delivering fuel fluid to an adjacent inner combustion zone. Similarly, an oxidizer feeder (X) may comprise an orifice (88) for delivering oxidizer fluid to an adjacent combustion zone radially inner to the inner wall (801) of the feeder in CR15. As illustrated, the oxidizer feeder (X) may be circumferentially wider in the transverse direction (theta) than the fuel feeder (F) to accommodate a larger volume of oxidizer fluid flow compared to a smaller fuel fluid flow.

[0410] According to FIG. 3u, in some configurations, both the outer fuel fluid orifice (87) and the oxidizer fluid orifice (88) may be inclined at a negative angle (-PhiX) circumferentially from the radial axis (R). In other configurations, the fuel fluid orifice (87) and the oxidizer fluid orifice (88) may have opposite circumferential positive angles (PhiX) from the radial axis (R).

[0411] Additional configurations may alternate positive (PhiX) and negative (-PhiX) angles of the fuel fluid orifice and the oxidizer fluid orifice between the radially inner and outer orifices (such configurations may have orifices aligned with the combustor axial Z-axis similar to that shown in FIG. 3s).

[0412] In addition to FIG. 3u, a portion of the radially inner ("lower") feeder arrangement from the outer feeder wall radius (CR16) (or radially inner combustion zone boundary) to the radially inner feeder wall radius (CR20) is illustrated, having an outer insulation layer (738) protecting the radially inner wall (737) of the combustion chamber. This illustrates a cross-sectional elevation view having a pair of oxidizer (X) fluid feeders with a circumferential passage width (PWX) and a fuel (F) fluid feeder with a circumferential passage width (PWF). The joint fluid width of the fluid feeder pairs illustrated in FIG. 3u may include a first oxidizer-fuel fluid pair width (FP1) and a second oxidizer-fuel fluid pair width (FP2).

[0413] In the radially inner ("lower") portion of FIG. 3u, the inner oxidizer (X) fluid feeder may be configured to face the outer fuel (F) fluid feeder, and the inner fuel (F) fluid feeder may be configured to face the outer oxidizer (X) fluid feeder. In this configuration, the common circumferential transverse (outer) wall (133) may be used at the facing outer counterclockwise (CCW) ("transverse") and clockwise (CW) boundaries.

[0414] In FIG. 3u, the fuel (F) fluid orifice (87) may be configured circumferentially around the middle of the fuel fluid feeder (F) so as to have a circumferential offset of about PWF / 2 from the fuel-oxidizer feeder split wall (133). In the radially outer ("upper") oxidizer feeder (X), the oxidizer orifice (88) may be configured midway across (transversely) the oxidizer feeder, displaced by a distance of about PWX / 2 from the fuel-oxidizer feeder split wall (133) (as the circumferentially aligned oxidizer fluid orifice (82) as shown in FIG. 3s).

[0415] Alternatively, FIG. 3u illustrates a configuration in which a radially inner ("lower") oxidant feeder (X) may have two oxidant orifices (88) arranged transversely within the oxidant feeder (X). For example, these two orifices (88) may be positioned transversely from the oxidant feeder wall at a distance (PWX / 3) that is about one-third of the passage width of the oxidant feeder (similar to the configuration of the oxidant fluid orifice (82) of diameter (DXO) as shown in FIG. 3r).

[0416] In some configurations, the orifice may be aerodynamically configured to reduce the combustor pressure drop and improve efficiency. The orifice inlet and outlet corners may be rounded to improve flow (F) and reduce pressure drop and efficiency loss, as shown in FIG. 3v.

[0417] FIG. 3v illustrates a detailed view of a fluid orifice in the plane of the radial circumferential direction (R theta) having fluid flow (F) through the outer combustor wall. For example, the fluid (F) may be introduced through an oxidizer 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.

[0418] 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 as or greater than the inlet radius (ROI). These configurations can be formed during additive manufacturing (or "3D printing").

[0419] FIG. 3w illustrates a detailed view of an inclined orifice in a radial circumferential plane (R theta) passing through an outer combustor wall of thickness (CR13T) having an insulating layer of thickness (CR14T). The inclined oxidizer fluid orifice may be configured to have a diameter (DXO) perpendicular to the orifice flow axis and a flow axis of angle (THM) with respect to the radial axis (R).

[0420] The entrance corners of such inclined orifices can be configured for an acute angle with a smaller radius (ROIA) and an obtuse angle with a larger radius (ROIB). The corresponding exits of such inclined orifices can have a smaller radius (ROOA) for the acute exit radius and a larger radius (ROOB) for the obtuse exit radius.

[0421] FIG. 3x illustrates the closed end of an oxidizer feeder in the axial circumferential plane (Z theta) for some configuration, where the manifold fuel fluid flow (FFM) flows axially past the closed end and the fuel feeder flow portion (FFF) flows around the closed end. The oxidizer fluid manifold may have an outer oxidizer feeder axial width (PXWO) and an inner oxidizer feeder axial width (PXWI) having a feeder wall thickness (FWT).

[0422] The axial upstream radius (RXU) of the oxidizer feeder can be configured to be smaller than the downstream oxidizer radius (RXD). For example, the downstream radius (RXD) can be more than twice the upstream radius (RXU).

[0423] FIG. 3y illustrates a closed end of a fuel fluid feeder in an axial circumferential plane (Z theta) for some configurations, where the manifold oxidizer fluid flow (FXM) flows axially past the closed end and the oxidizer feeder flow portion (FXF) flows around the closed end.

[0424] According to FIG. 3y, such a fuel fluid feeder may have an outer fuel feeder axial width (PFWO) and an inner fuel feeder axial width (PFWI), and a feeder wall thickness (FWT). The oxidizer feeder axial upstream radius (RFU) may be configured to be smaller than the downstream oxidizer radius (RFD). For example, the downstream radius (RFD) may be more than twice the upstream radius (RFU).

[0425] Multiple orifices to improve mixing

[0426] In some configurations, fuel, oxidizer, and / or diluent orifices may be used. The orifice size may be correspondingly reduced to maintain the total accumulated orifice area within the desired range of the downstream combustion system cross-sectional area.

[0427] More orifices can be used to advantageously improve mixing, increase combustion, further support diluent mixing, assist in temperature control, reduce hot spots, improve uniformity, and / or promote equilibration.

[0428] For example, in some configurations, each combustion shell may use 50 to 100 oxidizer orifices. In other configurations, this may be increased to 101 to 200 oxidizer orifices. Similarly, 201 to 400 oxidizer orifices may be used. Additional combustors may use 401 to 800 or more orifices for hard fuels such as ammonia.

[0429] These changes can be advantageously used to promote the combustion of fuels having higher ignition energy, higher combustion temperature, slower flame velocity, and / or slower combustion rate. For example, this applies when combusting one or more of ammonia, methane, methanol, ethanol, decomposed ammonia (a combination of H2, N2, and NH3), and / or hydrogen.

[0430] Combustion and Emission Modeling

[0431] The applicant won two high-performance computing manufacturing supercomputer grants from the U.S. Department of Energy. A simplified scalable combustor (such as one using an asymmetric combustion zone and a cylindrical equilibrium zone) was modeled using more than 110 independent parameters.

[0432] Of these, 23 parameters were selected to model combustion across typical gas turbine pressure, temperature, and specific power rate. Argonne National Laboratory (hereinafter Argonne National Laboratory: ANL) performed reactive computational fluid dynamic modeling (hereinafter reactive computational fluid dynamic modeling: "RCFD") to evaluate low, medium, and high values ​​(0%, 50%, 100%) for each of these selected parameter ranges.

[0433] The applicant [describes] the parameters as unburned hydrocarbons (UHC) (or equivalent fuel), nitrogen oxides (NO₂). x Parameters were ranked according to their importance for ) and carbon monoxide (CO) emissions. Then, ANL performed 312 RCFD runs for the nine most significant parameters using combinations of five values ​​ranging from low to high (0%, 25%, 50%, 75%, 100%).

[0434] Subsequently, Lawrence Livermore National Laboratory (here referred to as Lawrence Livermore National Labs: "LLNL") analyzed the data and UHC, CO, and NO x Neural network methods were used to create a software program that predicts emissions, and this software program can be run on a professional laptop computer.

[0435] These methods and the resulting software allow the applicant to [manage] UHC, NO₂ across commercial gas turbine operating conditions. x This allows the scalable gas turbine combustor configuration to be configured to likely achieve less than 1 ppmvd for CO and NO emissions, respectively. This meets the strictest California County emission requirement of 2.3 ppmvd NO without the use of a catalyst. x and predict emissions below CO.

[0436] These very low emissions provide a major advantage of typically 7% to 10% lower CapEx for commercial gas turbines operating on natural gas. This promises the potential for significantly lower operating costs by eliminating ammonia delivery and associated "slip" emissions.

[0437] The techniques, configurations, and methods described herein further detail, extend, and / or modify the initial RCFD modeling for methane. They enable the methods to be extended and / or improved to include, for example, methane, natural gas, methanol, ethanol, ammonia, decomposed ammonia (combinations of “H2, N2, and NH3” in this specification), and hydrogen by further utilizing a range from conventional fuels to sustainable fuels.

[0438] Diluent for the blend area

[0439] NO xFormation occurs as a product of (fuel * O2) and has the potential to increase exponentially with combustion temperature. Rich combustion cooled by steam and / or diluent in the upstream blend region uniquely enables the transition from rich high-temperature upstream combustion to quasi-stoichiometric combustion. This is NO x It is possible that this could be critically important in avoiding formation.

[0440] Ammonia combustion

[0441] FIG. 3f illustrates an example modeling the combustion of ammonia (NH3) fuel using air, diluted water, and steam along the flow axis from the upstream combustion inlet (CZ34) to the downstream combustor outlet (CZ4). This exploratory reactivity RCFD modeling of diluted NH3-air combustion was performed on the applicant's previous simplified scalable combustor. The left axis represents the average cross-sectional temperature, and the right axis represents the outlet NO in PPMVD (parts per million diluted with 15% O2). x and represents NH3 emissions.

[0442] In this sample run, the average upstream combustion hot gas temperature peaks at 1,830 K (~1,557°C) near the end of the blend-trim region (T1). For RCFD modeling, the assumed combustor wall cooling rate is specified, reducing the combustor outlet temperature at CZ4 to the typical specified Turbine Inlet Temperature (TIT) of 1,527 K (1,300°C).

[0443] According to Fig. 3f, in this run, NH3 peaked at ~13,000 ppmvd (~40,000 ppm) in the abundant combustion region. It then decreased to ~78 ppmvd (~227 ppm) at the combustor outlet. Combustion NO x Formation peaked at ~275 ppmvd (~800 ppm) downstream of the ammonia peak and upstream of the temperature peak. Due to excess NH3 and high H2O, NOx It decreased to less than ~10 ppmvd (~29 ppm unadjusted) at the combustor outlet.

[0444] In Fig. 3f, these ~10 ppmvd NO from the initial exploratory NH3 combustion x Emissions are NO that is more than 60% lower than the U.S. EPA's 25 ppmvd national emission limit for medium-sized gas turbines. x Emissions are already achieved. These results appear to be significantly lower than reported industrial and scientific combustion modeling reports found for these most challenging proposed renewable or sustainable fuels.

[0445] The applicant has identified means for further improving mixing and combustion by aerodynamic methods, improved orifice distribution, and delivery staging as described herein. These further improve combustion and NH3 and NO x There is a possibility of lowering all emissions.

[0446] A single expander VAST cycle with exhaust heat recycling achieves 24% higher efficiency, resulting in 19% lower NO per generated electricity (ppmvd / MWh) compared to a conventional simple cycle (Brayton) picker gas turbine. x It appears to provide emissions.

[0447] Cooling combustion

[0448] In some configurations, the remaining unsupplied diluent may be transferred from the downstream trim zone feeder (T1) to the blend zone feeders (e.g., B1 and B2). A major portion of this remaining diluent may be transferred to the upstream blend feeder (B1) to provide a colder, rich (quasi-stoichiometric) combustion, and the temperature is controlled independently of the relative local fuel-to-oxidizer ratio (Phi) (or relative local oxidizer-to-fuel ratio Lambda).

[0449] In an additional configuration, a portion of this diluent may be further delivered upstream to the downstream end of the combustion zone, for example, along with the fuel (U7) and / or oxidizer fluid (X7) (or optionally diluted oxidizer fluid) in the axial downstream (or last) combustion zone axial (733). This diluent may be further delivered to the last two to last seven combustion zones upstream of (CZ35).

[0450] Excess oxidizer (or air) (T1) can similarly be delivered through the downstream trim region. This combination of upstream diluent and downstream excess oxidizer can achieve the coldest blend region-rich combustion with the minimum oxidizer up to stoichiometric combustion. This results in the lowest NO for this configuration without changing the total oxidizer or excess air of the delivered Phi (Φ). x It can form discharges well.

[0451] In situ ammonia decomposition

[0452] In additional configurations, ammonia can be delivered upstream under high-temperature fuel-rich (excess fuel, quasi-stoichiometric oxygen) conditions (Phi(Φ) > 1 or Lambda < 1). The upstream combustion temperature can be increased by reducing the upstream diluent. These conditions can increase the upstream decomposition of ammonia into hydrogen and nitrogen. This abundant in-situ decomposition of ammonia into hydrogen and nitrogen promotes downstream abundant combustion, thereby increasing total NO x It can reduce formation.

[0453] Some configurations may set the temperature of the transverse feeder adjacent to the combustion zone and / or the upstream combustion zone sufficient to thermally decompose a portion of the ammonia fuel into hydrogen and nitrogen. A catalyst may similarly be used within the transverse fluid feeder to decompose ammonia.

[0454] Thermally ignited fluid

[0455] In some configurations, the high-energy fluid can be formed by heating one or more delivered fluids to temperatures such that the temperature and flow rate of the delivered high-energy reactant and co-reactant mixture gas are sufficient to ignite the reactive fluid in the main reaction zone.

[0456] manufacturing method

[0457] One or more of such scalable parametric combustor configurations described may be constructed using additive manufacturing (or "3D printing") technology. Such manufacturing technology may facilitate the formation of multiple oxidizer fluid, fuel fluid, and diluent fluid transverse feeders having corresponding orifices for transferring fluid from the transverse feeders to the combustion chamber.

[0458] In some configurations, this expandable shell combustor may be formed of two halves having an internal insulating coating on the outer structural wall. These can then be assembled and appropriately fixed, bonded, or fastened together. In other configurations, these orifices may be formed by laser ablation, chemical etching, mechanical or fluid jet drilling, or similar material removal techniques.

[0459] Turbulence generator

[0460] In some embodiments, turbulence generators may be configured along one or both surfaces demarcating the combustion zone within an expandable combustor. These may include waves in the walls of the expandable combustor. Similarly, they may include protrusions into the gas flow on one or both walls of the expandable combustor.

[0461] generalization

[0462] From the foregoing description, it can be understood that a new approach for dispersed contact, mixing, and / or reaction of three or more fluids using one or more processes described herein is disclosed. Although the components, techniques, and aspects of the invention have been described with some specificity, it is evident that many variations may be made from the specific designs, structures, and methodologies described herein without departing from the spirit and scope of the disclosure.

[0463] Where dimensions are given, they are generally for illustrative purposes only and are not prescriptive. Of course, as understood by a person skilled in the art, other suitable sizes, orientations, configurations, and distributions of fluid transfer orifices, fluid channels, and other components may be effectively utilized as needed or desired, with due consideration given to the objective of achieving one or more of the benefits and advantages taught or suggested herein.

[0464] When duct, tube, or array configurations are provided, similar two-dimensional or three-dimensional configurations or combinations of such configurations can be effectively utilized, including varying the nominal thickness, diameter, cross-sectional shape, spacing, orientation, and other dimensions and parameters for porous ducts, porous tubes, manifolds, sub-manifolds, feeders, combustion, mixing, trim, equilibrium and transition zones and tube arrays.

[0465] Where the terms fuel, reactant, diluent, water, steam, carbon dioxide, air, oxygen, and oxidizer are used, the processes may generally be applied to other combinations of such fluids or other reactions, co-reactions, and other combinations of diluents or non-reactive fluids. Where fluid volumes are mentioned, these processes may generally be applied to include volumes delivered over multiple times and continuous fluid flow. Where assembly processes are described, various alternative assembly processes may be effectively utilized to achieve the configurations, in order to achieve one or more of the advantages and benefits of the embodiments as taught or suggested herein.

[0466] It is understood that when transverse, axial, radial, circumferential, horizontal, vertical, normal, or other directions are mentioned, any general coordinate system using curved coordinates may be used, including orthogonal coordinate systems such as annular systems, cylindrical, spherical, or other special systems. Similarly, when one or more transverse or axial distributions or profiles are mentioned, it is understood that the configuration and process are similarly applied to spatial control in one or more curved directions as desired or specified. Similarly, contactors, arrangements, devices, or duct orientations may generally be rearranged to achieve other advantageous combinations of the described features and processes.

[0467] It can be understood that if fluid delivery control refers to controlling the size and flow rate of a fluid, injection drop, jet, or micro-jet, the control means may use one or more means to control the differential injection pressure distribution across the fluid orifice (80), vibrate the orifice, and / or control the electromagnetic field around the orifice (80) using one or more means described herein, and / or use similar means to modulate the position of the orifice, fluid pressure, and the surrounding electromagnetic field.

[0468] FIG. 4a schematically illustrates an expandable gas turbine power system (1) having an expandable combustion system (here, "CMB") as used in a VAST power cycle. This expandable gas turbine power system (1) is illustrated as receiving oxidizer fluid compressed from an upstream compressor (407) (here, "CPR") axially and supplying it axially to a downstream gas turbine expander (440) (here, "EXP"). This generally applies the American Society of Mechanical Engineers (ASME) gas turbine position numbering methodology along the combustor axial flow Z direction (here, "CZ") as follows.

[0469] This VAST cycle expandable gas turbine power system (1) illustrates a compressor (407) (CPR) having a compressor inlet at CZ2 and a compressor outlet at CZ3. The compressed oxidizer fluid flow (here "WX3") can flow into a diffuser (here "DIF"). A portion of the compressed oxidizer (here "WX31") can flow from the pilot or combustor inlet plane (CZ31) to an upstream ignition system or pilot (100) (here "P"). Another portion of the compressed oxidizer fluid (here "WX34") can be delivered upstream from CZ31 to the hot igniter fluid delivery and to the combustion section, as in plane (CZ32). The diluent fluid can be delivered upstream to CZ32, for example, as liquid water as a spray (WDL32) into the upstream inlet oxidizer flow (WX34).

[0470] A portion of the diluent (WDL32) can be delivered upstream to a conventional fuel-rich combustion zone (730) from the combustion zone inlet (CZ34) to the blend-trim zone inlet and combustion zone outlet plane (CZ35) (indicated here as the combustor reference plane (CBQ)).

[0471] FIG. 4a additionally schematically illustrates a “blend-trim” region (850) extending from an upstream blend-trim inlet plane (CZ35) (or combustion region outlet plane) to a downstream equilibrium region inlet plane (CZ39) (or blend-trim region outlet plane).

[0472] Equilibrium zone

[0473] Referring to FIGS. 4a and 4b, an equilibrium region (900) may be provided downstream of the blend-trim region (850). This equilibrium region (900) may extend from the blend-trim region exit at plane (CZ39) to the transition region inlet plane (CZ394) (or equilibrium region outlet plane) to provide a residence time for further completing a reaction or combustion.

[0474] Transition zone

[0475] According to FIG. 4a, a transition region or zone (980) may follow an equilibrium region (900) to accelerate the high-temperature flow to the combustor outlet. This may extend from the end of the equilibrium region of plane (CZ394) to the combustor outlet of CZ4 and to the expander ("EXP" in this specification) or turbine inlet where the expander outlet is located in the outlet plane (CZ5). The equilibrium and transition regions may be aerodynamically configured to reduce flow pressure loss.

[0476] The turbine inlet mass flow (or combustor outlet mass flow) ("W4" in this specification) flows from the combustor outlet to the expander (EXP) in the axial plane (CZ4). The cooling diluent liquid mass flow ("WDL45" in this specification) may be delivered to the expander to cool high-temperature parts such as blades, stators, and / or walls. The expanded fluid mass flow ("W5" in this specification) may flow from the expander (EXP) in the axial plane (CZ5) to a downstream heat exchanger, which is shown herein as a Once Through Steam Generator ("OTSG"). The cooled mass flow ("W51" in this specification) exits the OTSG and enters a downstream heat exchanger ("HX" in this specification) (at an axial intermediate heat exchanger flow stage (CZ51) not shown).

[0477] The cooled heat exchanger outlet mass flow or exhaust flow ("W52" in this specification) (at the axial flow stage (CZ52) downstream of the heat exchanger (HX) not shown) may be further cooled downstream as desired to further condense the diluent vapor and / or further cool the diluent liquid and non-condensable flue gas, for example by using a water-cooled or air-cooled heat exchanger (not shown). In some VAST power cycle configurations, the diluent vapor may be condensed, and a recompressor may recompress the cooled-expanded excess oxidant and non-condensable combustion products together to an atmospheric pressure discharge, which is described in detail in a prior patent (not shown).

[0478] FIG. 4a further illustrates upstream gas combustion temperatures controlled by a thermal diluent flow, such as water and / or steam (or similarly CO2), for fuel fluid delivery. This diluent fluid may be delivered to multiple upstream combustion zones (from CZ34 to CZ35). For example, seven combustion zones ("C1" to "C7" herein) are illustrated in FIG. 4a and FIG. 4g, six combustion zones (unlabeled C1 to C6) in FIG. 4i, and eight combustion zones (implied but unlabeled C1 to C8) in FIG. 4n to FIG. 4q. These may be two to twenty combustion zones or more.

[0479] FIG. 4a illustrates that additional mass flow rates of an oxidizing fluid (“MX”) and a diluent fluid (“MD”) may be delivered to blend-trim regions (from CZ35 to CZ39). For example, additional oxidizing agents such as air, and diluents such as water and / or steam may be delivered to one or more blend regions (here denoted as one first blend region “B1” and two second blend regions “B2”) and one or more trim regions (here denoted as a first upstream trim region “T1” and optionally a second downstream trim region “T2”).

[0480] The cooled exhaust mass flow rate (W52) at the heat exchanger (HX) outlet (axial plane (52) not shown) can be further cooled as needed.

[0481] FIG. 4a illustrates that additional oxidizers and diluents can be delivered to blend-trim regions. For example, additional oxidizers such as air, and diluents such as water and / or steam can be delivered to one or more blend regions (e.g., B1 and B2), and similarly to one or more trim regions (e.g., upstream (T1) and downstream (T2)).

[0482] FIG. 4a illustrates the inlet mass flow rate of an oxidizer (or air) (here, “WX2”) introduced into the inlet (CZ2) of the compressor (407) (CPR) along with the optional compressor inlet mass flow rate of a liquid diluent (same as the liquid water spray mass flow rate) (here, “WDL2”). The optional compressor cooling liquid spray mass flow rate (here, “WDL25”) can be delivered to the compressor (CPR) itself between the inlet (CZ2) and outlet (CZ3) of the compressor (407) (CPR).

[0483] The compressor (407)(CPR)) can supply a mass flow of compressed oxidant fluid (or air) along with an optional vaporized diluent (here "WX3") to the upstream inlet of the VAST expandable combustor (CMB) at the upstream flow position (CZ3). The downstream combustor outlet can supply an equilibrated and accelerated high-temperature gas flow (W4) to the expander (EXP) at the flow position (CZ4).

[0484] The expandable combustor (CMB) may include an upstream diffuser (DIF) that expands and decelerates an oxidizer (or air) from a compressor outlet / diffuser inlet (CZ3) and supplies it to an upstream combustion section from CZ34 to CZ5, and the upstream diffuser may include a VAST combustor (CMB) that extends from the upstream diffuser (DIF) inlet (CZ3) (to the combustor pilot inlet plane (CZ31)), (to the transition zone (CZ394)), and downstream outlet plane (CZ4).

[0485] FIG. 4a additionally illustrates an upstream ignition control mechanism or pilot (100)(P). The pilot (P) may be supplied with a pilot fuel mass flow rate (here, "WF31"), a pilot oxidizer mass flow rate (here, "WX31"), and optionally a pilot diluent such as pilot liquid water (here, "WDL31"). An additional fuel fluid (here, "WF32") and an additional diluent fluid such as steam (here, "WDS32") may be mixed and delivered to a diluted fuel manifold as a diluted fuel fluid mass flow rate (here, "MF") to supply a transverse fuel feeder to combustion zones (e.g., C1 to C7).

[0486] An additional oxidizer fluid (here, "WX34") is delivered along with various flows of an upstream diluent fluid (here, "WDL32") and / or, the mixture is subsequently fed progressively to a combustor through multiple feeders (C1 to C7) to deliver one or more mass flows of fuel fluid (MF), oxidizer fluid (MX), and diluent fluid (MD) that are largely oriented across or transversely to the axial flow.

[0487] Next, FIG. 4a illustrates that a stoichiometric diluted oxidizer and / or diluent mass flow is fed into a blend-trim area (850) through one or more transverse blend area feeders (B1 and B2), and the remaining oxidizer and / or diluent fluid is transferred between the combustor axial planes (CZ35 and CZ39) through one or more trim area feeders (upstream (T1), and optional downstream (T2) trim area, etc., not shown).

[0488] FIG. 4a further illustrates the mass flow rate of the liquid diluent (here "WDL42") into the heat exchanger (HX). The heated liquid from HX flows to the one-through steam generator (here "OTSG"), to the upstream combustor (here "WDL32"), to the blend-trim zone (here "WDL35"), and to the downstream combustor wall (here "WDL41") within the equilibrium and transition zones (here "WDL398").

[0489] FIG. 4a illustrates that a portion of the heated liquid diluent (WDL41) recovers additional heat in the OTSG to form steam (referred to herein as "WDS4"). This vaporized diluent is transferred back to the blend-trim area as WDS35 and can be transferred to the upstream area as WDS32, such as to the upstream fuel mass flow rate (MF) in CZ32.

[0490] Premixed area

[0491] Referring to FIG. 4a, an upstream premixing zone may be provided between the compressor outlet / diffuser inlet (CZ3) and the combustion zone outlet (CZ35). This may deliver a liquid diluent (WDL32) with an oxidizer mass flow rate (MX) to one or more combustion zones (C1 to C7). This premixing zone may similarly be located between the upstream combustor inlet plane (CZ31) near the inlet (100) pilot (P) and the combustion zone inlet (CZ34).

[0492] The premixing zone may include a porous direct contact tube (14) connected to a liquid diluent supply flow (WDL31) to deliver a diluent spray to an upstream oxidizer fluid (WX34). One or more valves may be configured to control the delivery of one or more flows of fuel and / or diluent to one or more of a diffuser (DIF), a pilot (P), a combustion zone (730), and a blend-trim zone (850).

[0493] Valve (VDL42) can control the reflux flow of the diluent liquid through the heat exchanger (HX). Valve (VDL35) can control the flow of the heated liquid diluent (WDL35) into the blend-trim area (850). Valve (VDL32) can control the liquid diluent (WDL32) into the combustion area manifold (730). VF32 can control the fuel fluid flow (WF32) into the combustion system. Valve (VF31) can control the fuel fluid flow (WF31) into the pilot (P).

[0494] Expandable radial annular ("fan") combustion array configuration

[0495] Referring to FIG. 4b, a general schematic three-dimensional perspective view, some expandable combustor embodiments may include a cylindrical combustor (704) having a common axis parallel to the direction of combustion flow from an upstream inlet (134) to a downstream outlet (136), an outer cylindrical outer pressure vessel (172), and an inner cylindrical axial pressure wall (147).

[0496] FIG. 4b further illustrates an upstream ignition (pilot) section (720), a fuel-rich combustion section (730), a blend-trim area (850) with residual diluent and oxidizer delivery, and a downstream equilibrium area (900).

[0497] Some expandable combustor embodiments may include an upstream-downstream streamline flow axis having a combustion section (732) that extends transversely with respect to a shallowly separated opposing combustor wall (736). This transversely extended wall (736) of the extended combustion section (732) may be bounded by a side wall (734). The relative circumferential transverse wall extension may be greater than 1.15 times the shallow gap due to the radial depth of the side wall (734) of the adjacent combustor wall between the opposing transverse-axial combustion chamber walls.

[0498] In FIG. 4b, a portion of the expandable combustor (CMB) is shown opening and extending from the outlet of the upstream diffuser to the downstream equilibrium region (900) through the combustion section (730) and downstream blend-trim region (850) from the flame control mechanism (100) or pilot (P) at the axial flow position (CZ31).

[0499] FIG. 4b illustrates an embodiment of a cylindrical-axial (circumferentially-radially stacked) combustor (702) plotted in cylindrical coordinates having a radial axis ("R") perpendicular to an axial flow axis (Z) having circumferential theta (θ). In other configurations, the expandable combustor may use a curved flow axis having non-cylindrical walls.

[0500] These embodiments may include multiple expandable ("fan") combustion shells (or burners) configured generally around a radial-circumferential theta (R-θ) cylindrical surface. These cylindrical combustion shells may be stacked radially and generally perpendicularly with respect to the primary streamline flow axis of an oxidizing fluid (F5) passing through an expandable combustor, oriented along the axial (Z) flow direction from an upstream fluid inlet (134) to a fluid flow outlet (136) for a heated and pressurized high-temperature combusted fluid (F20).

[0501] According to FIG. 4b, in order to operate at elevated pressure, this expandable cylindrical combustor embodiment (702) can be configured within the outer pressure vessel wall (172). The pilot fuel fluid flow (F3) and the pilot oxidizer fluid flow (F6) can be delivered to an upstream ignition control mechanism (flame igniter or pilot (100)) configured to burn these fluids to form a high-temperature pilot fluid flow (F22).

[0502] The pilot diluent fluid (F8) flow can be delivered separately to the pilot (100) and / or mixed with the pilot fuel fluid (F3) and / or pilot oxidizer fluid (F6) flowing into the pilot (100) from the upstream pilot area (720).

[0503] According to FIG. 4b, this upstream high-temperature pilot fluid flow (F22) from the pilot (100) can be distributed to the upstream end of a pilot fluid distribution system (722) comprising one or more expandable pilot fluid transfer ducts (or “fan” burner ducts) (728) in an upstream pilot area (720). These pilot fluid transfer ducts (or “fan” burners) (728) can be configured circumferentially around a cylindrically stacked expandable combustor (702).

[0504] The pilot fluid transfer duct (728) can transfer high-temperature pilot fluid from the axial intermediate combustion zone (730) to one or more combustion systems (or intermediate fan burners) (732).

[0505] Referring further to FIG. 4b, each combustion system (732) includes two radially opposing circumferential combustion radial outer sidewalls (736) (generally together with corresponding radial inner sidewalls). These combustion radial outer sidewalls (736) may be bounded and connected by corresponding combustion (mid-fan) (circumferential) end walls (734). In other configurations, the radial sidewalls (736) may be curved around to radially meet the combustion area and to define the boundary laterally or circumferentially.

[0506] Each combustion system radial sidewall (736) may include a plurality of fluid delivery orifices (80) as schematically illustrated in FIG. 4c. Pressurized oxidizer fluid (F5) is delivered to the cylindrical-axial combustion system (702) and can be delivered to the combustion system (732) through the orifices (80) configured in the combustion system radial sidewall (736). Referring to FIG. 4c, in some configurations, the diameter or size of the orifices (80) may vary laterally to control the fluid delivery rate per orifice.

[0507] Similarly, according to FIG. 4b, the diluted fuel fluid (F2) can be delivered through a similar axial fuel manifold (770) between circumferentially adjacent combustion zones on the alternating side of the combustion zone from the oxidizer fluid (F5) delivery.

[0508] In an additional configuration, a premixed reactive fuel-oxidizer mixture having an optional diluent is delivered to a cylindrical-axial combustor (702) and can be delivered through the porous combustor radial sidewall (736) within a combustion system (732) in a combustion zone (730).

[0509] According to FIG. 4b, high-energy fluid from one or more combustion systems (732) within a combustion zone (730) can be delivered to a circumferential downstream blend-trim zone (850) comprising a blend-trim oxidizer-diluent delivery and reaction zone manifold wall (857) that supplies the relevant blend-trim reaction zone. Each blend-trim reaction zone (850) may include opposing circumferential blend-trim porous sidewalls (857) that demarcate combustion within the zone.

[0510] The blend-trim area sidewalls (857) can generally be connected by one or more distal-fan end walls (746). The blend-trim sidewalls (857) can also be configured to be joined at their circumferential transverse ends. Multiple sets of circumferential combustors (732) and blend-trim areas (850) can be configured within the combustor outer wall or pressure vessel (172).

[0511] FIG. 4c shows an enlarged view of a radial side wall (736) of a combustion chamber wall section showing an orifice (80) penetrating a combustion chamber fluid duct wall (132) protected by an insulating barrier (150).

[0512] Symmetric combustor

[0513] FIG. 4d illustrates a sample radial circumferential (R theta) cross-section of a portion of the combustion zone extending circumferentially by the combustion section angle (THC). This embodiment illustrates an oxidizer manifold on the CCW side supplying an oxidizer fluid (F5), and a THBMX CW portion supplying to two adjacent CW combustion zones. On the CW side, FIG. 4d illustrates a fuel manifold including a THBMF CW portion supplying to two radially adjacent combustion zones including a combustion feeder radial depth (thickness) (CR15T).

[0514] FIG. 4d further illustrates an outer oxidizer fluid feeder extending radially with a radial depth (thickness) (CR12T) inside an outer circumferential wall having an inner radius (CR12). The outer oxidizer fluid feeder extends circumferentially over an inner angle (THBFX4) and supplies oxidizer fluid through multiple orifices into a combustion zone extending radially with a radial depth (or thickness) (CR15T) from the inner radius (CR15) of the outer wall to the outer radius (CR16) of the inner wall.

[0515] An oxidizing fluid (F5) having an optional diluent (e.g., water vapor or mist) may flow along an oxidizing fluid feeder and through an oxidizing orifice having a typical diameter (DXO) into a radially adjacent outer combustion zone extending radially with a depth (or thickness) (CR15T) between the outer radius (CR15) and the inner radius (CR16) of the combustion chamber. These oxidizing orifices are offset from the CCW manifold by a circumferential angle (THBXO) and spaced apart by a circumferential angle (THBXS), and the J-th orifice within the I-th oxidizing feeder is located at a circumferential angle (THBXIJ).

[0516] FIG. 4d further illustrates a fuel fluid flow (F2) that is optionally diluted with a diluent fluid and flows through a CW combustion zone manifold extending through a circumferential theta angle (THBMF). This CW fuel fluid manifold delivers the fuel fluid through a fuel supplement feeder extending radially with a depth (thickness) (CR18T) and supplies the fuel fluid through a fuel fluid orifice having a typical fuel orifice diameter (DFO) to an outer combustion zone between CR15 and CR16 extending radially with a depth (thickness) (CR15T) and spanning approximately a circumferential angle (THBFF4). This fuel feeder with a depth (CR18T) can similarly supply fluid to an inward combustion zone extending radially between CR25 and CR26 and extending circumferentially across THBFF4.

[0517] In addition to FIG. 4d, the diluted ("wet") oxidizer fluid (F5) can similarly be delivered radially inward (and longitudinally) to a radial combustion zone of circumferential width (Theta15T) through a radial manifold feeder length (RBFX4) and width (Theta12T) between circumferential angles (Theta12 and Theta15). Radially inward, the diluent fluid (F12) can be delivered to a region (RBMF) extending axially with a width (Theta18T), and then, through an orifice of diameter (DFO), to a radial CCW diluent manifold extending circumferentially by Theta18T for each central combustion zone extending axially by Theta15T and radially by RBFF4 along the combustion zone.

[0518] FIG. 4e illustrates a radially axial circumferential (RZ) plan view of two radially adjacent symmetric combustion zones (CZ34 to CZ35) and blend-trim zones (CZ35 to CZ39). The radially lower (visually right or clockwise CW) zones are illustrated with a radially outer (CCW) boundary end wall (734) and a radially inner (CW) boundary end wall (735). These combustion zones may extend axially from an upstream pilot (100) outlet or combustion zone inlet (CZ34) to a downstream axial boundary (CZ35) of the combustion zone. The downstream blend-trim zone may extend axially (Z) from CZ35 to CZ39.

[0519] According to FIG. 4e, such adjacent symmetrical combustion zones may have a radially outwardly adjacent (+R or CCW) oxidizer fluid manifold zone between the manifold wall (250) and the combustion wall (734) to transport an oxidizer fluid (or diluted oxidizer fluid) (F5) from upstream of the inlet (CZ34) to such adjacent combustion zones via a duct. Correspondingly, such symmetrical combustion zones may have a radially inwardly adjacent (-R or CW) fuel manifold zone between the manifold wall (250) and the combustion wall (735) to transport a fuel fluid (or diluted fuel fluid) (F2) via a duct.

[0520] These externally adjacent (R+ CCW)) oxidizer manifold and internally adjacent (-R CW)) fuel manifold can be commonly bordered and divided by an S-shaped longitudinal (radial-axial (RZ)) manifold distributor wall (250) between the combustion upstream inlet (CZ34) and the combustion intermediate stream outlet (CZ35) boundary, and then extend axially to the blend-trim area between the intermediate stream blend-trim inlet plane (CZ35) and the downstream blend-trim outlet plane (CZ39).

[0521] The left (+R, CCW) portion of FIG. 4e is located downstream of the pilot (100) and additionally illustrates a transverse (radial) width region (731) that increases circumferentially with the axial flow distance, having a radial (R) width that increases with the axial flow distance and an outer wall curvature along the axial (Z) direction. This axially increasing combustion region volume favorably accommodates an axially increasing volumetric flow rate from the increased mass flow rates of the delivered oxidizer, fuel, and diluent, and from the temperature rise due to combustion, thereby reducing fluid acceleration and pressure drop losses.

[0522] FIGS. 4a and 4e similarly illustrate a configuration having a downstream combustion zone (733) having a width that increases laterally (radially from +R to -R) (or CCW-CW) but a decreasing radial-axial wall curvature. This can advantageously provide a smoother aerodynamic transition between the blend-trim zone and the equilibrium zone extending downstream from plane (CZ39) to plane (CZ394) (as illustrated in FIG. 4a). FIG. 4e additionally illustrates an axial intermediate combustion transition zone (732). The lateral width (from +R to -R) of this intermediate combustion transition zone (732) can increase downstream along the axial (Z) distance from an axially increasing width wall curvature from the combustion upstream section (731) to an axially decreasing width wall curvature as in the combustion downstream section (733).

[0523] FIG. 4e illustrates the distribution of fuel fluid transfer orifices (81) and oxidizer fluid transfer orifices (82) that open to combustion zones from CZ34 to CZ35. An additional distribution of oxidizer and / or diluent transfer orifices (83) may be configured downstream to open to a blend-trim zone axially between plane (CZ35) and plane (CZ39). Such blend-trim combustion zones having transfer orifices (83) may be transversely bounded by a radially outer combustion wall (734) and a radially inner combustion wall (735).

[0524] According to FIG. 4e, a downstream blend-trim manifold region may be provided to axially deliver a diluted oxidant fluid (F5) (or an oxidant fluid (F4) not shown) between an axial plane (CZ35) and a plane (CZ39), and is bounded by a transverse manifold (CCW) wall (250) radially outward (+R) and a radially inward (-R) manifold (CW) wall (734). This radially outward (+R) oxidant fluid delivery manifold between the transverse manifold wall (250) and the inward manifold wall (734) may be bounded downstream from CZ39 by a manifold wall (250) that joins to the manifold wall (734). The inner manifold wall (734) may be bounded by a transverse manifold wall (250) that joins an axial upstream boundary wall (249) between the upstream delivery of the diluted fuel flow (F2) (or fuel fluid flow (F1) not shown) and the downstream delivery boundary for the blend-trim diluted oxidizer fluid (F5) (between the manifold wall (250) and the combustion wall (734)) (see below for the discussion of FIG. 4f illustrating exploratory NH3 combustion).

[0525] FIG. 4e further illustrates the axial position versus variable transverse positioning of the oxidizer orifice (82), fuel orifice (81), and mixed-trim diluted oxidizer orifice (83).

[0526] FIG. 4g illustrates an “unfolded” plan view in the axial circumferential direction (Z theta) corresponding outward (or inward) to the symmetrical combustor fluid feeder region. This extends axially in the flow direction from the upstream pilot (100), together with a CCW axial diluted oxidant fluid manifold region (244) that transports the upstream diluted oxidant fluid (F4) to the upstream oxidant feeder via a duct. The fluid feeder region of FIG. 4g may further include a second CCW axial oxidant manifold (245) that transports the downstream diluted oxidant fluid (F5) to a duct.

[0527] The configuration of FIG. 4g illustrates a first fuel fluid (F1) containing fuel to an upstream feeder, similarly shown in a first fuel manifold region (242) inside the CW that transports the first fuel fluid (F1) to the duct. This can be split from the fuel fluid manifold region (243) to a second intermediate CW outside, such as by an upstream / downstream fuel fluid manifold dividing wall (252), that transports an additional downstream diluted fuel fluid flow (F2) (or other flow of fuel fluid) to the duct.

[0528] In FIG. 4g, additionally, similarly, the fuel feeder to blend-trim split wall (253) from upstream to downstream can split and separate the upstream diluted fuel fluid (F2) flowing through the intermediate fuel fluid manifold region (243) between CZ34 and CZ35 from the blend-trim diluent flow (F7) flowing downstream into the blend-trim region (850) between plane (CZ35) and plane (CZ39). The manifold boundary wall (253) may be adjacent to a downstream diluted oxidant or diluent fluid feeder extending down to plane (CZ39).

[0529] In FIG. 4g, the CCW oxidizer fluid manifold and the CW fuel fluid manifold can be separated by an S-shaped longitudinal radial manifold distributor (250) that cools a downstream transverse trim feeder ending axially in a plane (CZ39). The downstream combustion-oxidizer fluid manifold distributor (248) can be similarly curved and configured parallel to the manifold distributor (250) and aerodynamically curved as it connects upstream of the transverse mixing-trim feeder opening in CZ35.

[0530] The axial-radial manifold distributor (253) forming the boundary between the diluted fuel fluid flow (F2) and the diluent fluid flow (F7) may be curved or S-shaped from upstream (CZ34) to downstream of CZ35 adjacent to the oxidant feeder delivering the oxidant fluid (X7) (or optionally diluted oxidant fluid).

[0531] In FIG. 4g, an axial radial mid-upstream combustion oxidizer manifold split wall (247) can split a diluted oxidizer-rich upstream fluid manifold (244) from a second diluted oxidizer-rich downstream fluid manifold (245). Similarly, a downstream axial radial oxidizer-mix-trim manifold wall (248) can split an intermediate stream second oxidizer fluid manifold (245) from a diluted oxidizer-mix-trim manifold (246), together with a radially extending adjacent wall having multiple circumferentially adjacent oxidizer fluid and fuel fluid manifolds and an upstream pilot (100).

[0532] In FIG. 4g, the first fuel fluid (F1) (optionally diluted) can be delivered into a fuel fluid manifold (242) bounded by a fuel feeder upstream / downstream manifold dividing wall (252) and can be delivered as multiple fuel fluids such as U1, U2 and U3 flowing through each of the 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 the range.

[0533] Similarly, the second diluted fuel fluid (F2) (or the second fuel fluid flow not shown) is delivered to the downstream fuel fluid manifold (243) and enters the multiple transverse fluid fuel fluid feeders as multiple fuel fluid flows (U4, U5, U6 and U7), and then can enter the adjacent combustion zone through the fuel fluid orifice (81A). These fuel fluid feeders may have an axially increasing number of fuel fluid orifices (81A) per transverse fuel fluid feeder over the axial range.

[0534] According to FIG. 4g, the oxidizer fluid (F4) can be delivered as oxidizer fluid flows (X1, X2 and X3) through a diluted oxidizer fluid upstream manifold (244) via multiple transverse oxidizer fluid feeders and subsequently through an oxidizer fluid orifice (82A). This delivery of the oxidizer fluid (F4) can be intersected with the delivery of the first fuel fluid (F1) through each upstream transverse fuel fluid feeder, for example, through U1 to U3.

[0535] Similarly, the oxidizer fluid (F5) can be delivered through multiple transverse oxidizer fluid feeders as oxidizer fluid flows (or optionally diluted oxidizer fluid) such as X4, X5, X6, and X7 through a diluted oxidizer fluid downstream manifold (245), and then introduced into adjacent combustion zones through multiple oxidizer fluid orifices (82B).

[0536] This oxidizer fluid delivery through the oxidizer feeder can interleave fuel fluid delivery flows such as U4 to U7 through each transverse fuel fluid feeder in the upstream combustion zone from CZ34 to CZ35.

[0537] According to FIG. 4g, the diluted oxidizer fluid (F6) can be delivered to a downstream blend-trim feeder, as one or more blend fluids such as B1 and B2, through a CCW diluted oxidizer blend-trim manifold (246), through a transverse blend feeder, and through an upstream blend-trim orifice (83A) and an intermediate stream blend-trim orifice (83B) to a radially adjacent blend-trim area downstream of the combustion zone.

[0538] Similarly, a portion of the diluted oxidizer fluid (F6) can be delivered as one or more trim fluid flows, such as T1, through a transverse trim feeder and then through a downstream blend-trim orifice (83C) to a radially adjacent blend-trim area between plane (CZ35) and plane (CZ39) axially downstream of the combustion zone.

[0539] According to FIG. 4g, correspondingly, the blend-trim diluent fluid (F7) can be delivered through the CW diluent-trim manifold (238) to the diluent-trim area (850) between CZ35 and CZ39 downstream. The blend-trim diluent fluid (F7) can be delivered as one or more diluent fluids (D1, D2 and D3) through a transverse diluent feeder and then through diluent fluid orifices (86A, 86B and 86C) to the radially adjacent downstream blend-trim area of ​​the combustor.

[0540] According to FIG. 4g, the walls (253 and 250) of the CW diluent trim manifold (238) into the blend-trim feeder area may be curved outward in the axial upstream section (731). They may similarly be curved inward in the axial downstream section (733).

[0541] The intermediate combustion zone (732) may be an S-shaped curved section to aerodynamically connect the upstream section (731) and the downstream section (733) (in other configurations, the intermediate combustion zone (732) may be linear). The downstream section (850) of the boundary wall (250) may be transitioned from the inwardly curved section (733) to aerodynamically connect with the downstream equilibrium zone axial slope.

[0542] Asymmetric combustion system

[0543] According to FIGS. 4h and 4i, some combustor configurations may use an asymmetric combustor with respect to a longitudinal oxidizer manifold that supplies transverse circumferential oxidizer fluid feeders to the CCW and CW sides of the oxidizer manifold. Such asymmetric combustor configurations may similarly use a common longitudinal fuel manifold to supply corresponding multiple adjacent fuel feeders in adjacent combustors.

[0544] Asymmetric combustion zone

[0545] FIG. 4h illustrates a circumferentially “unfolded” plan view of two adjacent asymmetric combustion zones having a circumferential axis theta perpendicular to the axial fluid flow axis (Z) and the radial axis (R). This may have radially adjacent combustor walls in the combustion zones and have a fuel fluid orifice (81), an oxidizer fluid orifice (82), and / or a blend-trim zone diluent fluid delivery orifice such as reference numeral (83).

[0546] According to FIG. 4h, this asymmetric combustion zone configuration may have circumferentially adjacent oxidizer fluid manifolds bordered by a combustion chamber transverse CCW side end wall (734) that directs the oxidizer fluid (F5) between the upstream combustion zone inlet (CZ34) and the downstream combustion fluid end (CZ35). They may similarly have a circumferentially adjacent boundary fuel fluid combustion chamber transverse CW side end wall (735) that delivers the fuel fluid (F2) between CZ34 and the downstream combustion zone manifold end split wall (249).

[0547] Additionally, according to FIG. 4h, the diluted oxidizer fluid (F7) can be delivered to a downstream blend-trim manifold region (850) that is bounded by a lateral boundary manifold wall (735) and an axially bounded downstream manifold end split wall (249) and extends axially from plane (CZ35) to plane (CZ39). Some asymmetric combustion region configurations may include a common upstream pilot (100) that supplies to adjacent combustion shells. This pilot (100) may be supplied by a pilot fuel fluid (F3), a pilot oxidizer fluid (F6), and a pilot diluent fluid (F8).

[0548] The asymmetric combustor configuration of FIG. 4h may have an S-shaped curved oxidizer fluid boundary suitable for such an asymmetric configuration as described in FIG. 4h. This may have an upstream manifold-combustion zone boundary wall section (731) that curves outwardly in the circumferential direction (theta) with an axially increasing distance (Z).

[0549] According to FIG. 4h, the asymmetric combustor may have a downstream manifold that is correspondingly curved inwardly in the circumferential direction (theta), bounded by a downstream transverse end wall section (733) of the combustion chamber having an increasing distance (Z) in the axial direction. The asymmetric combustor configuration of FIG. 4h may have a connecting intermediate combustion chamber intermediate stream transverse end wall (732) that transitions from the outside to the inner circumferential-axial curvature.

[0550] The oxidizer fluid manifold of FIG. 4h may additionally have a downstream blend-trim region (850) having a blend-trim diluent / oxidizer fluid manifold wall (734) that may have an aerodynamically changing curvature between the axial upstream adjacent combustion region downstream transverse end wall (733) and the downstream equilibrium region wall extending from CZ39 according to FIG. 4a to the equilibrium region (900).

[0551] The corresponding fuel fluid side boundary manifold wall (735) may have a similar curvature with a correspondingly shallower curvature. In other configurations, the side boundary fuel fluid manifold wall (735) may be straight.

[0552] Asymmetric manifold and transverse fluid transfer region

[0553] FIG. 4i illustrates an example of a circumferentially "stretched" circumferential-axial (Z theta) asymmetric combustor fluid feeder configuration. This illustrates a fluid axial (longitudinal) manifold wall, an upstream transverse fuel feeder and an oxidizer fluid feeder, fuel, oxidizer and diluent fluid delivery orifices, an axial upstream pilot (100) delivering pilot fluid from CZ34 to an upstream combustion zone, and a combustion wall having a downstream outlet to a combustor equilibrium zone from CZ39, shown radially outward.

[0554] This circumferentially and axially asymmetric configuration allows for the use of fewer fuel fluid manifolds and oxidizer fluid manifolds than those used in the symmetric combustion system expandable shell combustors described in FIGS. 4b through 4e and FIG. 4g.

[0555] The configuration illustrated in FIG. 4i may include a pilot fuel fluid (F3), a pilot oxidizer fluid (F6), and a pilot diluent fluid (F8) supplied to an upstream pilot (100). On the clockwise side, a portion of the first fuel fluid flow (F1) may be delivered as fuel fluid (U1) to an upstream transverse fuel fluid feeder and then delivered to a combustion zone through one or more fuel fluid orifices (81A).

[0556] Similarly, additional portions of the first fuel fluid (F1) can be gradually transferred to a downstream transverse fuel fluid feeder to supply fuel fluids (U2 and U3). These can be transferred from the transverse fuel fluid feeder to a radially adjacent combustion zone through a similar or increasing number of fuel fluid orifices (81A).

[0557] FIG. 4i illustrates an oxidizer fluid manifold that similarly supplies oxidizer fluid (F4) flows (X1, X2 and X3) to respective transverse oxidizer fluid feeders and thereto gradually axially to radially adjacent combustion chambers through oxidizer fluid orifices (82A).

[0558] The combination of each fuel fluid orifice (81), oxidizer fluid orifice (82), and the size (or area) and number of relative fuel fluid and oxidizer fluid transfer pressures can be configured to provide a desired range of relative fuel to oxidizer composition relative to stoichiometric composition (PHI) (or equivalently, relative oxidizer to fuel ratio (LAMBDA)).

[0559] According to FIG. 4i, the first fuel fluid (F1) and / or oxidizer fluid (F4) may include a gaseous and / or liquid diluent, such as steam, water vapor, and / or liquid water, which is delivered to the combustion chamber through a transverse feeder and an orifice.

[0560] According to FIG. 4i, the diluted fuel fluid (F2) can be delivered axially through a fuel fluid manifold and subsequently delivered as a fuel fluid flow (U4, U5, U6 and / or U7) to one or more transverse fuel fluid feeders. These can be delivered from the fuel fluid feeders through a plurality of fuel fluid orifices (81B) from the combustion intermediate stream wall region (732) through the combustion downstream wall region (733) to a radially adjacent combustion chamber located in the downstream portion of the combustion region.

[0561] According to FIG. 4i, the oxidizer fluid flow (F5) can be delivered through an outer axial oxidizer fluid manifold and then to each transverse oxidizer fluid feeder as one or more oxidizer fluid feeder flows such as X4, X5, X6, and therefrom to a radially adjacent combustion zone through an oxidizer fluid orifice (82B). For example, it can be delivered from an intermediate zone (732) to a radially adjacent combustion zone in a downstream combustion zone passing through a downstream combustion zone (733).

[0562] According to FIG. 4i, a diluent fluid (F14), such as liquid water, is delivered to a downstream blend-trim area through one or more transverse feeders, such as diluent fluid flows (D1 and D2), and then can be delivered to an axially and radially adjacent blend-trim area (850) between planes (CZ35) and (CZ39) within the combustor through an orifice (86A).

[0563] Accordingly, according to FIG. 4i, an additional oxidizer fluid optionally containing a diluent fluid can be delivered as a blend-trim fluid (B1 and / or T1) through a transverse blend-trim feeder, and then axially between plane (CZ35) and plane (CZ39) through blend-trim orifices (83A and 83C) to a downstream blend-trim area (850) of the combustion chamber.

[0564] Cooling upstream combustion

[0565] The embodiments described herein enable additional flexibility in configuring diluent delivery separately from oxidant and fluid delivery. This can be advantageously used to reduce and control combustion temperatures regardless of the relative fuel (or relative oxidant for fuel composition lambda) to the oxidant composition (Phi). This allows for advantageous reduction of combustion temperatures while enabling higher oxidant compositions, particularly under upstream rich combustion conditions within the combustion zones from CZ34 to CZ35. Such methods reduce unwanted emissions, particularly NO x Emissions can be advantageously reduced.

[0566] Accordingly, in some additional configurations, some or all of the gaseous and / or liquid diluent fluids (D1 and D2) may be delivered together with one or more fuel fluid flows (U5 to U7). Similarly, some or all of these gaseous and / or liquid diluent fluids (D1 and D2) may be delivered together with oxidizer fluids (X4, X5 and / or X6).

[0567] This increase in diluent fluid along with the flow of combustion fuel and oxidizer fluids lowers the combustion temperature, and consequently NO x It can be used to reduce the formation of emissions such as. In some configurations, this can be delivered along with an oxidizer-rich or stoichiometric portion to form an associated oxidizer-rich or stoichiometric combustion region.

[0568] In some configurations, one or more of the axial upstream and downstream manifold walls may be axially significantly aligned between the upstream combustion zone in the CZ34 and the downstream connection with the associated transverse fluid transfer feeder. This alignment can advantageously reduce the rate of change of the axial fluid flow cross-sectional area (expansion) and the transfer flow rate, and consequently reduce the associated fluid pressure drop.

[0569] FIG. 4j illustrates a schematic diagram of a combustion section “stretched” circumferentially (Z theta) with a radially inner (or outer) wall configuration, showing a larger and more numerous upstream oxidizer fluid delivery orifice (82) and a smaller and fewer downstream fuel fluid delivery orifice (81). For example, the ratio is 2:1. The oxidizer fluid orifice may be offset circumferentially from the fuel fluid orifice to improve mixing and reduce quenching.

[0570] FIG. 4k illustrates a schematic circumferential (Z theta) "spread" combustion section radially inward (or outward) wall configuration having fewer upstream fuel fluid delivery orifices (81) and more downstream oxidizer fluid delivery orifices (82). For example, a ratio of 1:2. The fuel fluid orifices may be circumferentially offset from the oxidizer fluid orifices to improve mixing and reduce the probability of quenching.

[0571] FIG. 41 illustrates a schematic circumferential (Z theta) "stretched" configuration of a downstream blend-trim region section having oxidant fluid orifices (83A and 83C) on the blend-trim region wall radially outward (or inward). The upstream blend-trim orifice (83A) may be offset clockwise (CW) from the downstream blend-trim region orifice (83C).

[0572] FIG. 4m illustrates a sample schematic configuration of a downstream blend-trim section having oxidant fluid delivery orifices (83A and 83C) on the radially inner (or outer) blend-trim area wall. Here, the upstream blend-trim orifice (83A) may be offset clockwise (CW) from the downstream blend-trim orifice (83C) in a counterclockwise (CCW) direction.

[0573] Corresponding to FIGS. 4L and FIGS. 4M, the blend-trim orifices (83A and 83C) configured radially outward of the combustion zone may be offset clockwise (CW) and counterclockwise (CCW) from the blend-trim orifices (83A and 83C) configured radially inward of the combustion shell. A similar method may be used to improve mixing with the fuel fluid orifice and / or oxidizer fluid orifice in the combustion upstream wall region (731), midstream wall region (732), and downstream wall region (733) of the combustion chamber.

[0574] FIG. 4n illustrates a schematic configuration of a sample (nominal radial-axial (RZ)) from upstream to downstream of an upstream combustion zone passing through a counterclockwise (CCW) circumferential outer combustion zone wall (734).

[0575] FIG. 4n, which is this sample configuration, illustrates eight radially outer oxidizer fluid delivery openings (X1 to X8) for a radially outer oxidizer fluid feeder (or diluted oxidizer fluid feeder). These are eight radially inner oxidizer fluid (or diluted oxidizer fluid) passage openings ( X1 inside X8 It can be supplemented by ) and scattered with them.

[0576] FIG. 4o illustrates a schematic configuration of a sample (nominal radial-axial (RZ)) from upstream to downstream of an upstream combustion zone located inside the outer end wall (734) of the CCW circumferential direction, having eight radial outer oxidizer fluid delivery openings (X1 to X8) (or diluted oxidizer fluid delivery openings) within an outer transverse oxidizer feeder.

[0577] FIG. 4o shows eight scattered radial inner oxidizer fluid delivery openings (X1 to X8) in an inner transverse oxidizer feeder ( X1 inside X8It is further illustrated that these may be supplemented with )(or diluted oxidant fluid delivery openings). These oxidant fluid channels (X1 to X8 and X1 to X8 ) may be interspersed with narrower fuel fluid delivery paths (not shown).

[0578] FIG. 4q illustrates a schematic configuration of a sample (nominal radial-axial (RZ)) of an upstream combustion zone through a clockwise (CW) circumferentially outer side boundary combustion zone end wall (735) having eight radially outer fuel fluid delivery openings (U1 to U8). These are eight radially inner fuel fluid passage openings ( U1 inside U8 It can be supplemented by ) and scattered together with it.

[0579] FIG. 4p illustrates a schematic configuration of a sample (nominal radial-axial (RZ)) of an upstream combustion zone located inside the outer end wall (735) in the circumferential direction of the CW, having eight oxidizer fluid feeder delivery passage openings (U1 to U8) interspersed with eight oxidizer fluid feeder delivery passage openings (e.g., unlabeled X1 to X8).

[0580] FIGS. 4n through 4q further illustrate combustor radial height (or length) parameters labeled from the first outward combustion shell toward the next inward combustion shell. For example, CR12 represents the outer radius of the radially outer oxidizer fluid feeder wall. CR15 represents the radially inner radius of the radially outer combustion zone wall. CR16 represents the outer radius of the radially inner combustion zone wall. CR24 represents the radially inner radius of the radially inner oxidizer fluid feeder wall.

[0581] FIGS. 4n through 4q further illustrate combustor radial internal height parameters labeled along the radial R axis from the first outward combustion shell toward the next inward combustion shell. For example, CR12T labels the radial internal depth (height or thickness) of the outer oxidizer fluid transverse feeder illustrated in FIGS. 4n and 4o. CR12T similarly labels the radial internal height of the outer fuel fluid transverse feeder illustrated in FIGS. 4p and 4q.

[0582] The radial parameter (CR15T) labels the radially inner height (thickness) of the combustion zone between CR15 and CR16 as shown in FIGS. 4o and 4p. CR18T similarly labels the radially inner thickness of the oxidizer and fuel transverse feeders between CR16 and CR24 as shown in FIGS. 4n through 4q.

[0583] FIGS. 4n to 4q further illustrate the combustor axial boundaries along the axial flow Z-axis from the upstream combustion zone boundary at CZ34 to the downstream combustion fluid transfer boundary at CZ35 in the reference plane (CBQ).

[0584] FIG. 4o further illustrates the typical axial inner inlet width (810) of radially outer transverse oxidizer fluid feeders (X1 to X8) supplying to a central combustion zone near the outer open side (e.g., the counterclockwise (CCW) side near the oxidizer fluid feeder opening from an adjacent oxidizer manifold).

[0585] A radially inner transverse oxidizer fluid feeder supplying oxidizer fluid to the central combustion zone in FIG. 40 ( X1 inside X8The axial inner width of the ) may be similar and may extend according to the radial distance outward from the combustor axis to each feeder. FIG. 4o further illustrates the corresponding axial inner distal end width (809) of the radially outer transverse fuel fluid feeders (U1 to U8) near the transversely closed end of the fuel fluid feeder near the adjacent oxidizer fluid manifold (e.g., CCW side).

[0586] FIG. 4p further illustrates the typical axial inner inlet width (808) of a radially outer transverse fuel fluid feeder (U1 to U8) supplying to a central combustion zone near the outer open side (e.g., the clockwise (CW) side near the fuel fluid feeder opening from an adjacent fluid manifold).

[0587] A radially inner transverse fuel fluid feeder supplying fuel fluid to the central combustion zone in FIG. 4p ( U1 inside U8 The inner axial width of ) may be similar and may be extended according to the radial distance outward from the combustor axis to each feeder.

[0588] FIG. 4p further illustrates the corresponding axial inner width (811) of the outer transverse oxidizer fluid feeder (unlabeled X1 to X8) near the transversely closed end of the oxidizer fluid feeder located near the adjacent fuel fluid manifold (e.g., CW side). FIG. 4p similarly illustrates the inner transverse oxidizer fluid feeder (unlabeled 811) having a corresponding inner width between the fluid feeder walls between CR16 and CR24. X1 to X8 It shows (not labeled).

[0589] FIG. 4r schematically illustrates an axial circumferential (Z theta) planar perspective view of a pair of transverse fluid feeders that deliver an oxidizer fluid (X) to multiple oxidizer fluid orifices (82) having a typical oxidizer fluid orifice diameter (DXO) and deliver a fluid (F) to multiple fuel fluid orifices (81) having a typical fuel fluid orifice diameter (DFO). The fuel fluid feeders are shown having an axial width (DFF) compared to a wider oxidizer fluid feeder having an axial width (DFX). In some configurations, a diluent feeder having a diluent fluid feeder width (DFD) may be used (not shown).

[0590] According to FIG. 4r, in some configurations, the fuel fluid orifice (81) in the fuel fluid feeder may be displaced circumferentially by a positive clockwise (CW) angle (THF) from the vertical plane. In some configurations, the oxidizer fluid orifice (82) may be configured as a pair positioned circumferentially around the fuel fluid orifice (81), having a narrower circumferential separation angle (THXN) between the oxidizer fluids between the nearest centers of the oxidizer fluid orifices (82) of the separated orifice pair. The oxidizer fluid orifice (82) may have a wider adjacent orifice circumferential separation angle (THXW) between the centers of the oxidizer fluids of the more widely separated orifice pairs.

[0591] In other configurations, the oxidizer orifices may be spaced further apart or spaced uniformly. As schematically illustrated in FIGS. 4e, 4h, and 4i, the circumferential spacing of the orifices around the combustor may be further varied along different fluid feeders in the axial direction. These may use either or both of the circumferential uniform spacing and the circumferential asymmetric spacing.

[0592] In some configurations, the circumferential gap may be closer to the inner and outer combustion chamber boundaries of one and / or both than to the inner circumferential region. Other configurations may provide more space between the orifices near the circumferential boundaries.

[0593] FIG. 4s illustrates a different axial circumferential plan view of a fuel feeder that supplies fuel fluid (F) through a fuel fluid orifice (81) and an axially adjacent oxidizer fluid feeder that supplies oxidizer fluid (X) through a plurality of oxidizer fluid orifices (82). This configuration is illustrated with the oxidizer fluid orifices (82) separated in the axial direction (Z) and aligned in the radial direction (theta).

[0594] The oxidizer fluid orifice (82) may be aligned circumferentially similarly to the fuel fluid orifice (82) as illustrated herein. This configuration can improve jet penetration into the combustion fluid flow. In another configuration, the oxidizer orifice may be aligned axially and collectively offset circumferentially from the fuel fluid orifice (82).

[0595] FIG. 4t illustrates a schematic radial circumferential (R theta) cross-sectional “elevation” of an outer combustion zone wall (736) having an insulating liner (738) that delineates the combustion zone by an outer radius (CR15). The outer fuel fluid orifice (87) may be configured to deliver fuel fluid in a negative CCW direction at a positive angle (PhiX) (or a negative angle (-PhiX)) from the radial axis (R).

[0596] FIG. 4t further illustrates an inner combustion zone boundary wall in CR16 that is radially displaced by a radial thickness (CR15T) from the outer combustion zone wall. The radial inner combustion wall may have an outer insulating liner (738) that protects the radial inner structural wall (737). The inner oxidizer fluid orifice (88) may be configured at a negative angle (-PhiX) (or a positive angle (PhiX)) opposite the radial axis (R) to deliver the oxidizer fluid in a negative CCW direction.

[0597] The configuration of FIG. 4t can be similarly configured to have a fuel fluid orifice (87) oriented at a negative angle (-PhiX) and an oxidizer fluid orifice (88) oriented in the opposite direction at a positive angle (PhiX). Additional configurations may include both fuel fluid orifices (87) and oxidizer fluid orifices (88) configured at the same positive angle (PhiX). Similar configurations may include fuel fluid orifices (87) and oxidizer fluid orifices (88) configured at similar negative angles (-PhiX) (or positive angles (PhiX)).

[0598] In the configuration of FIG. 4t, some fuel fluid delivery orifices (87) and oxidizer fluid delivery orifices (88) within the axially offset fluid feeder may be circumferentially oriented at similar positive angles (PhiX) (or negative angles (-PhiX)). In other configurations, generally, the upstream fluid delivery orifice (87 (or 88)) and downstream fluid delivery orifice (88 (or 87)) may be composed of opposing positive angles (PhiX) and negative angles (-PhiX) of the oxidizer (not shown).

[0599] In a further generalizing configuration as illustrated in FIG. 4g (as in FIG. 4t), the upstream fuel fluid orifice (81A) may be circumferentially offset from (or aligned with) the downstream oxidizer fluid orifice (82B). Similarly, according to FIG. 4g, the upstream oxidizer fluid orifice (82A) may be circumferentially offset from (or aligned with) the downstream oxidizer fluid orifice (82B).

[0600] FIG. 4u illustrates a radial circumferential (R theta) "elevation view" of a sample configuration of an outer transverse fuel feeder labeled F and an alternating outer oxidizer transverse feeder labeled X. These fuel and oxidizer feeders may have a radial outer wall (802) bounded by an outer radius (CR11). These feeders may have a radial inner wall (801) bounded by an inner feeder radius (CR15) and forming a radial outer surface of an inner first combustion zone. The outer feeder inner wall (801) may include a radially outer side wall (736) that is covered with a protective insulating coating (738) on the inner combustion zone side.

[0601] FIG. 4u further illustrates a fuel feeder (F) comprising a fuel fluid orifice (87) for delivering fuel fluid to an adjacent inner combustion zone. Similarly, an oxidizer feeder (X) may comprise an orifice (88) for delivering oxidizer fluid to an adjacent combustion zone radially inner to the inner wall (801) of the feeder in CR15. As illustrated, the oxidizer feeder (X) may be circumferentially wider in the transverse direction (theta) than the fuel feeder (F) to accommodate a larger volume of oxidizer fluid flow compared to a smaller fuel fluid flow.

[0602] According to FIG. 4u, in some configurations, both the outer fuel fluid orifice (87) and the oxidizer fluid orifice (88) may be inclined at a negative angle (-PhiX) circumferentially from the radial axis (R). In other configurations, the fuel fluid orifice (87) and the oxidizer fluid orifice (88) may have opposite circumferential positive angles (PhiX) from the radial axis (R).

[0603] An additional configuration may alternate positive (PhiX) and negative (-PhiX) angles of the fuel fluid orifice and the oxidizer fluid orifice between the radially inner and outer orifices (such a configuration may have an orifice aligned with the combustor axial Z-axis similar to that shown in FIG. 4s).

[0604] In addition to FIG. 4u, a portion of the radially inner ("lower") feeder arrangement from the outer feeder wall radius (CR16) (or radially inner combustion zone boundary) to the radially inner feeder wall radius (CR20) is illustrated, having an outer insulation layer (738) protecting the radially inner wall (737) of the combustion chamber. This illustrates a cross-sectional elevation view having a pair of oxidizer (X) fluid feeders with a circumferential passage width (PWX) and a fuel (F) fluid feeder with a circumferential passage width (PWF). The joint fluid width of the fluid feeder pairs illustrated in FIG. 4u may include a first oxidizer-fuel fluid pair width (FP1) and a second oxidizer-fuel fluid pair width (FP2).

[0605] In the radially inner ("lower") portion of FIG. 4u, the inner oxidizer (X) fluid feeder may be configured to face the outer fuel (F) fluid feeder, and the inner fuel (F) fluid feeder may be configured to face the outer oxidizer (X) fluid feeder. In this configuration, the common circumferential transverse (outer) wall (133) may be used at the facing outer counterclockwise (CCW) ("transverse") and clockwise (CW) boundaries.

[0606] In FIG. 4u, the fuel (F) fluid orifice (87) may be configured circumferentially around the middle of the fuel fluid feeder (F) so as to have a circumferential offset of about PWF / 2 from the fuel-oxidizer feeder split wall (133). In the radially outer ("upper") oxidizer feeder (X), the oxidizer orifice (88) may be configured midway across (transversely) the oxidizer feeder, displaced by a distance of about PWX / 2 from the fuel-oxidizer feeder split wall (133) (as the circumferentially aligned oxidizer fluid orifice (82) as shown in FIG. 4s).

[0607] Alternatively, FIG. 4u illustrates a configuration in which a radially inner ("lower") oxidizer feeder (X) may have two oxidizer orifices (88) arranged transversely within the oxidizer feeder (X). For example, these two orifices (88) may be positioned transversely from the oxidizer feeder wall at a distance (PWX / 3) that is about one-third of the passage width of the oxidizer feeder (similar to the configuration of the oxidizer fluid orifice (82) of diameter (DXO) as shown in FIG. 4r).

[0608] In some configurations, the orifice may be aerodynamically configured to reduce combustor pressure drop and improve efficiency. The orifice inlet and outlet corners may be rounded to improve flow (F) and reduce pressure drop and efficiency loss, as shown in FIG. 4v.

[0609] FIG. 4v illustrates a detailed view of a fluid orifice in the plane of the radial circumferential direction (R theta) having fluid flow (F) through the outer combustor wall. For example, the fluid (F) may be introduced through an oxidizer 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.

[0610] 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 as or greater than the inlet radius (ROI). These configurations can be formed during additive manufacturing (or "3D printing").

[0611] FIG. 4w illustrates a detailed view of an inclined orifice in a radial circumferential plane (R theta) passing through an outer combustor wall of thickness (CR13T) having an insulating layer of thickness (CR14T). The inclined oxidizer fluid orifice may be configured to have a diameter (DXO) perpendicular to the orifice flow axis and a flow axis of angle (THM) with respect to the radial axis (R).

[0612] The entrance corners of such inclined orifices can be configured for an acute angle with a smaller radius (ROIA) and an obtuse angle with a larger radius (ROIB). The corresponding exits of such inclined orifices can have a smaller radius (ROOA) for the acute exit radius and a larger radius (ROOB) for the obtuse exit radius.

[0613] FIG. 4x illustrates the closed end of an oxidizer feeder in the axial circumferential plane (Z theta) for some configuration, where the manifold fuel fluid flow (FFM) flows axially past the closed end and the fuel feeder flow portion (FFF) flows around the closed end. The oxidizer fluid manifold may have an outer oxidizer feeder axial width (PXWO) and an inner oxidizer feeder axial width (PXWI) having a feeder wall thickness (FWT).

[0614] The axial upstream radius (RXU) of the oxidizer feeder can be configured to be smaller than the downstream oxidizer radius (RXD). For example, the downstream radius (RXD) can be more than twice the upstream radius (RXU).

[0615] FIG. 4y illustrates a closed end of a fuel fluid feeder in an axial circumferential plane (Z theta) for some configurations, where the manifold oxidizer fluid flow (FXM) flows axially past the closed end and the oxidizer feeder flow portion (FXF) flows around the closed end.

[0616] According to FIG. 4y, such a fuel fluid feeder may have an outer fuel feeder axial width (PFWO) and an inner fuel feeder axial width (PFWI), and a feeder wall thickness (FWT). The oxidizer feeder axial upstream radius (RFU) may be configured to be smaller than the downstream oxidizer radius (RFD). For example, the downstream radius (RFD) may be more than twice the upstream radius (RFU).

[0617] Multiple orifices to improve mixing

[0618] In some configurations, fuel, oxidizer, and / or diluent orifices may be used. The orifice size may be correspondingly reduced to maintain the total accumulated orifice area within the desired range of the downstream combustion system cross-sectional area.

[0619] More orifices can be used to advantageously improve mixing, increase combustion, further support diluent mixing, assist in temperature control, reduce hot spots, improve uniformity, and / or promote equilibration.

[0620] For example, in some configurations, each combustion shell may use 50 to 100 oxidizer orifices. In other configurations, this may be increased to 101 to 200 oxidizer orifices. Similarly, 201 to 400 oxidizer orifices may be used. Additional combustors may use 401 to 800 or more orifices for hard fuels such as ammonia.

[0621] These changes can be advantageously used to promote the combustion of fuels having higher ignition energy, higher combustion temperature, slower flame velocity, and / or slower combustion rate. For example, this applies when combusting one or more of ammonia, methane, methanol, ethanol, decomposed ammonia (a combination of H2, N2, and NH3), and / or hydrogen.

[0622] Combustion and Emission Modeling

[0623] The applicant received the U.S. Department of Energy’s High Performance For Computing Manufacturing (HPC4Mfg) supercomputer grant and the HPC4 Energy Innovation supercomputer grant. A simplified VAST scalable combustor (such as using a scalable combustion zone and a cylindrical equilibrium zone) was modeled using more than 110 independent parameters.

[0624] Of these, 23 parameters were selected to model combustion across typical gas turbine pressure, temperature, and specific power rate. Argonne National Laboratory (hereinafter Argonne National Laboratory: ANL) performed reactive computational fluid dynamic modeling (hereinafter reactive computational fluid dynamic modeling: "RCFD") to evaluate low, medium, and high values ​​(0%, 50%, 100%) for each of these selected parameter ranges.

[0625] The applicant [describes] the parameters as unburned hydrocarbons (UHC) (or equivalent non-burned fuel), nitrogen oxides (NO₂). xParameters were ranked according to their importance for ) and carbon monoxide (CO) emissions. Then, ANL performed 312 RCFD runs for the nine most significant parameters using combinations of five values ​​ranging from low to high (0%, 25%, 50%, 75%, 100%).

[0626] Subsequently, Lawrence Livermore National Laboratory (here referred to as Lawrence Livermore National Labs: "LLNL") analyzed the data and UHC, CO, and NO x Neural network methods were used to create a software program that predicts emissions, and this software program can be run on a professional laptop computer.

[0627] These methods and the resulting software allow the applicant to [manage] UHC, NO₂ across commercial gas turbine operating conditions. x This allows the scalable gas turbine combustor configuration to be configured to likely achieve less than 1 ppmvd for CO and NO emissions, respectively. This meets the strictest California County emission requirement of 2.3 ppmvd NO without the use of a catalyst. x and predict emissions below CO.

[0628] These very low emissions provide a major advantage of typically 7% to 10% lower CapEx for commercial gas turbines operating on natural gas using Selective Catalytic Conversion (SCR). This promises the potential for significantly lower operating costs by eliminating ammonia delivery and associated "slip" emissions.

[0629] The techniques, configurations, and methods described herein further detail, extend, and / or modify the initial RCFD modeling for methane. They enable the methods to be extended and / or improved to include, for example, methane, natural gas, methanol, ethanol, ammonia, decomposed ammonia (combinations of “H2, N2, and NH3” in this specification), and hydrogen by further utilizing a range from conventional fuels to sustainable fuels.

[0630] Diluent for the blend area

[0631] NO x Formation occurs as a product of (fuel * O2) and has the potential to increase exponentially with combustion temperature. Rich combustion cooled by steam and / or diluent in the upstream blend region, which has a residual combustion blend region, uniquely enables the transition from rich high-temperature upstream combustion to quasi-stoichiometric combustion. This is NO x It is likely to be a significant advantage in avoiding formation. Fig. 4f schematically illustrates a typical combustor axial temperature profile with an outlet temperature of 1,570 K (1,397 °C). This implementation results in outlet NO for methane. x (And CO) emissions were reduced to less than 1 ppmvd (parts per million volume diluted with 15% O2).

[0632] Ammonia combustion

[0633] CO and NO less than 1 ppmvd achieved by VAST with CH4 combustion x Following the emissions, preliminary modeling for ammonia combustion was performed. Conventional NH3 combustion produces NO exceeding 1,000 ppmvd. x It can cause. Published experiments show 25 ppmvd NO x[This was achieved.] Fig. 4f illustrates an example of preliminary modeling of ammonia (NH3) combustion using air, diluted water, and steam. Temperature and emissions are plotted along the flow axis from the upstream combustion inlet (CZ34) to the downstream combustor outlet (CZ4). This exploratory reactivity RCFD modeling of diluted NH3-air combustion was performed on the applicant's previous simplified scalable combustor.

[0634] The left axis represents the average cross-sectional temperature, and the right axis represents the outlet NO x and NH3 emissions are expressed in ppmvd (parts per million diluted with 15% O2). In this sample run, the average upstream combustion hot gas temperature peaks at approximately 1,830 K (~1,557°C) centered at the end of the blend-trim region (T1). For RCFD modeling, the assumed combustor wall cooling rate is specified, reducing the combustor outlet temperature at CZ4 to a specified 1,527 K (1,300°C), which is a typical value for the intermediate gas turbine inlet temperature (TIT).

[0635] According to Fig. 4f, in this run, NH3 peaked at ~13,000 ppmvd (~40,000 ppm) in the abundant combustion region. Residual NH3 then decreased to ~78 ppmvd (~227 ppm) at the combustor outlet. Combustion NO x Formation peaked at ~275 ppmvd (~800 ppm) downstream of the ammonia peak and upstream of the temperature peak. Due to excess NH3 and high H2O, NO x It decreases to less than ~10 ppmvd (~29 ppm uncorrected) at the combustor outlet.

[0636] In Fig. 4f, these ~10 ppmvd NO from the initial exploratory NH3 combustion x Emissions are NO that are already more than 60% lower than the U.S. EPA's 25 ppmvd national emission limit for medium-sized Brayton cycle gas turbines. xIt achieves emissions. These results appear to be significantly lower than reported industrial and scientific combustion modeling reports found for these most challenging proposed renewable or sustainable fuels.

[0637] The applicant has identified means for further improving mixing and combustion by aerodynamic methods, improved orifice distribution, and delivery staging as described herein. These further improve combustion and the observed NH3 and NO x There is a possibility of lowering all emissions. It features 24% higher efficiency for a single expander VAST cycle with exhaust heat recycling, and this preliminary NH3 combustion modeling results in 19% lower NO compared to conventional simple cycle (Brayton) picker gas turbines, with an additional generated per unit of electricity (ppmvd / MWh). x It appears to provide emissions.

[0638] Cooling combustion

[0639] In some configurations, the remaining unsupplied diluent may be transferred from the downstream trim zone feeder (T1) to the blend zone feeders (e.g., B1 and B2). A major portion of this remaining diluent may be transferred to the upstream blend feeder (B1) to provide a colder, rich (quasi-stoichiometric) combustion, and the temperature is controlled independently of the relative local fuel-to-oxidizer ratio (Phi) (or relative local oxidizer-to-fuel ratio Lambda).

[0640] In an additional configuration, a portion of this diluent may be further delivered upstream to the downstream end of the combustion zone, for example, along with the fuel (U7) and / or oxidizer fluid (X7) (or optionally diluted oxidizer fluid) in the axial downstream (or last) combustion zone axial (733). This diluent may be further delivered to the last two to last seven combustion zones upstream of (CZ35).

[0641] Excess oxidizer (or air) (T1) can similarly be delivered through the downstream trim region. This combination of upstream diluent and downstream excess oxidizer can achieve the coldest blend region-rich combustion with the minimum oxidizer up to stoichiometric combustion. This results in the lowest NO for this configuration without changing the total oxidizer or excess air of the delivered Phi (Φ). x It can form discharges well.

[0642] In situ ammonia decomposition

[0643] In additional configurations, ammonia can be delivered upstream under high-temperature fuel-rich (excess fuel, quasi-stoichiometric oxygen) conditions (Phi(Φ) > 1 or Lambda < 1). The upstream combustion temperature can be increased by reducing the upstream diluent. These conditions can increase the upstream decomposition of ammonia into hydrogen and nitrogen. This abundant in-situ decomposition of ammonia into hydrogen and nitrogen promotes downstream abundant combustion, thereby increasing total NO x It can reduce formation.

[0644] Refer to FIG. 4z and the heating / decomposition section (853) within the blend-trim area (850). Ammonia fuel may be delivered to this area as fuel (F1) (and / or as a diluted fuel (F2) not shown). A portion of the ammonia fuel (F1) may be decomposed into hydrogen and nitrogen, and the residual ammonia is recovered from this area as decomposed fuel fluid (F16). This area (853) may provide multiple serpentine flow paths without orifices to increase (or decrease) the residence time or to modify it. Some combustor configurations may configure the temperature of an orifice-free transverse feeder adjacent to and / or upstream of the combustion area.

[0645] One or more of the axial position, temperature, fuel (F1) fluid flow rate, number of transverse passages, and contact time can be controlled sufficiently to thermally decompose a portion of the ammonia fuel into hydrogen and nitrogen. For example, 2% to 98% ammonia decomposition, or 5% to 60% decomposition, or 10% to 40% decomposition, and / or 15% to 25% decomposition. A catalyst may similarly be used in a transverse fluid feeder to facilitate the decomposition of ammonia. This decomposition may be further configured with a diluent to form a diluted fuel fluid (F2) for delivery to a combustor.

[0646] Thermally ignited fluid

[0647] In some configurations, the high-energy fluid can be formed by heating one or more delivered fluids to temperatures such that the temperature and flow rate of the delivered high-energy reactant and co-reactant mixture gas are sufficient to ignite the reactive fluid in the main reaction zone.

[0648] manufacturing method

[0649] One or more of such scalable parametric combustor configurations described may be constructed using additive manufacturing (or "4D printing") technology. Such manufacturing technology may facilitate the formation of multiple oxidizer fluid, fuel fluid, and diluent fluid transverse feeders having corresponding orifices for transferring fluid from the transverse feeders to the combustion chamber.

[0650] In some configurations, this expandable shell combustor may be formed of two halves having an internal insulating coating on the outer structural wall. These can then be assembled and appropriately fixed, bonded, or fastened together. In other configurations, these orifices may be formed by laser ablation, chemical etching, mechanical or fluid jet drilling, or similar material removal techniques.

[0651] Radial annular multi-expandable combustor

[0652] These radial annular multi-scalable combustors (or "multi-fan burners") can 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 precision-controlled combustion and / or similar chemical reactions.

[0653] In some configurations, walls having multiple fluid jets delivered through an orifice may be configured with relatively shallow gaps between the walls to improve relative jet penetration. For example, the mass flow rates of fuel, oxidizer, and diluent delivery to the upstream combustion flow, or any combination thereof, may be configured to increase the reliable combustion operating range, combustion operating robustness, and / or the degree and / or uniformity of fluid mixing.

[0654] Similar to the annular-radial configuration of FIG. 4b, FIG. 5a illustrates a downstream to upstream view of the downstream end of a multi-extendable combustor radially oriented in the upstream section of an annular gas turbine combustor (750) extending from the combustion zone inlet (134) to the combustion zone outlet (136), as for use in a gas turbine combustion system.

[0655] According to FIG. 5a, one or more flame control mechanisms (100) (ignition control mechanisms or pilot lights) may be configured to supply high-temperature ignition gas (F22) into an upstream flame control mechanism duct (ignition control mechanism duct or pilot feeder duct) configured around an upstream inlet area (720) of a combustion system (750). The upstream flame control mechanism duct may supply the high-temperature ignition gas (F22) to an upstream area, for example, from CZ31 to CZ34 of one or more combustion shells (as shown in the perspective view FIG. 4b, and in the downstream view of FIG. 5b and the upstream view of FIG. 5c).

[0656] One or more upstream flame control mechanisms (100) as illustrated in FIGS. 4b and 5b may be supplied with a pilot fuel fluid (F3) containing a fuel fluid (or a first reactant fluid), a pilot oxidizer fluid (F6) containing an oxidizer fluid (or a second reactant fluid), and a pilot diluent fluid (F8) containing a diluent fluid or a thermal diluent.

[0657] Referring to FIG. 5b, some embodiments may configure an expandable combustor (730) having multiple expandable combustion sections (or combustion chambers or "fan burners") as illustrated in the radial-circumferential (R-theta) drawing from downstream to upstream. These may form a radial multi-fan annular combustor (730) by having a radial configuration of the combustion chambers (730) between the inner annular duct wall (147) and the outer pressure vessel wall (172).

[0658] Similarly, FIG. 5c illustrates a radial-circumferential (R-theta) diagram of multiple outward combustion sections (or multiple fan burners). These combustion sections are configured along a vector (S) at an angle (Phi) rotated clockwise from the radial vector (R) to form a radial multiple-fan annular combustor (741).

[0659] FIG. 5c further illustrates a more detailed perspective view of the combustion section (730) as part of the radial multi-fan annular combustor (741) (as configured in FIG. 5c). The upstream combustion section (741) is configured between the upstream combustion fluid duct inlet transverse plane (134) and the downstream combustion fluid duct outlet transverse plane (136) (the configuration of FIG. 5b has a similar detailed configuration of the radial multi-fan annular combustor (730) having an outwardly oriented multi-fan burner configured along the radial orientation, which is not illustrated).

[0660] All or part of the curves in Fig. 5 may be cycloid-shaped curves. In summary, cycloid curves can actually improve flow efficiency by minimizing abrupt changes in direction, reducing separation, and optimizing flow attachment. Their efficiency is often most pronounced in systems where the fluid must rotate within a confined space or where maintaining laminar flow is advantageous. These cycloid characteristics can also be advantageous for fluid dynamics in applications where maintaining flow velocity and smooth changes in direction is beneficial.

[0661] FIG. 5c illustrates a disassembled perspective view from the outside to the inside of FIG. 5b (and likewise for FIG. 5a). An upstream igniter or flame control mechanism (100) receives, mixes, and reacts a pilot fuel fluid (F3) mixed with a pilot oxidizer fluid (F6) in a state where one or both fluids are optionally mixed with a pilot diluent fluid (F8) to form a high-temperature pilot fluid (F22).

[0662] According to FIG. 5c, the high-temperature pilot fluid (F22) from the upstream flame control mechanism (100) may then be distributed through an optional high-temperature pilot duct (138) to one or more mid-fan combustion sections or upstream ends (134) of the burner (74), as in the plane (134). One or more of the expandable combustors (732 *** and 742 ***) may be configured and extended between the surrounding duct walls (132 ***) and / or the surrounding pressure vessel (172) as described herein with respect to the circumferential annular multi-combustion chamber expandable combustor (750) as illustrated in FIG. ***.

[0663] Radial annular multi-fan ***

[0664] Referring to FIG. ***, the orifice dimensions, sidewall depth gap (Ld){***}, and pressure drop across the circumferentially annular expandable combustor (730 ***) can be configured to deliver a premixed fluid (F14 ***) to the fan burner at a rate sufficient to feed and react with the incoming high-temperature pilot fluid (F22) to form more high-temperature or high-energy fluid (F20) without quenching the reaction within the expandable combustor. The delivery rate of the premixed fluid (F14) can be similarly configured to maintain the temperature of the reaction fluid within each fan burner above a specified reaction temperature quench limit.

[0665] Transverse and axial composition and temperature distribution

[0666] One or more transverse distributions of one or more of the fuel fluid transfer orifices, oxidizer fluid transfer orifices, and / or diluent fluid transfer orifices may be configured to achieve one or more of a predetermined transverse composition distribution, a predetermined transverse temperature distribution, and / or a predetermined transverse velocity distribution with respect to one or more defined axial planes perpendicular to the combustion fluid flow between the high-temperature pilot fluid (F22) inlet in CZ34 and the combustor outlet in CZ4.

[0667] Similarly, multiple transverse distributions of orifice sizes, spacing, and / or orientations can be preferably configured to achieve desired variations in transverse composition and / or temperature distribution on multiple curved surfaces distributed along the streamline flow direction within the combustor. These transverse distributions of orifices on vertical planes and / or transverse curved surfaces can be configured at multiple locations along the streamline flow.

[0668] As illustrated in FIGS. 5d to 5g and FIGS. 5h to 5j, some configurations physically configure the orifice distribution and size and / or dynamically control fluid delivery to control the temperature (T) of the hot combustion gas at the radial position (R) within the axial plane between the combustor inlet in CZ34 (as illustrated in FIG. 5d) and the axial position (CZ), which enters the upstream combustion fuel-rich region between the axial positions (CZ34 and CZ35).

[0669] Similarly, some configurations may configure and / or control one or more oxidizer and / or diluent fluid flows in the downstream blend-trim region between axial positions (CZ35 and CZ39 ***). These configurations may further configure fuel, oxidizer, and / or diluent orifices to control the fluid flow composition and / or temperature in the equilibrium region from CZ39 to the combustion zone outlet in CZ4.

[0670] FIG. 5d illustrates a schematic graph of the combustion fluid temperature at an axial transition location (CZ35) between an upstream combustion fuel-rich region and a downstream blend-trim region. The methods described herein can be used to control the temperature (T35i) at the inner radius (Ri) relative (e.g., higher) to a desired corresponding radial outer temperature (T35o) at the outer radius (Ro) in order to accommodate inner wall cooling from the transition combustor transverse plane (CZ35) to the outlet axial location (CZ4), for example, at the combustor outlet plane.

[0671] Such temperature control can be achieved by adjusting the diluent-to-fuel ratio omega. For example, the water-to-fuel mass ratio omega can be increased to lower the outlet temperature and decreased to raise the outlet temperature. This configuration can similarly control the outer temperature (T35o) at the outer radius (Ro) to be higher than the desired corresponding downstream outlet temperature. For example, this can accommodate outer wall cooling at the outer radius (Ro) from the transition axial position (CZ35) in the combustor outlet plane to the combustor outlet axial position (CZ4).

[0672] This combustion configuration according to FIG. 5d can further control a first intermediate temperature (T35j) at the intermediate radius (Rj) of the combustor between the inner radius (Ri) and the outer radius (Ro). This first intermediate temperature (T35j) can be controlled relatively to one or both of the inner radial temperature (T35i) at the inner radius (Ri) of the combustor and the outer radial temperature (T35o) at the outer radius (Ro) (e.g., as follows).

[0673] This configuration allows for additional control of the second intermediate temperature (T35k) at the second intermediate radius (Rk). For example, the second intermediate temperature (T35k) can be controlled relatively to one or both of the inner temperature (T35i) at the inner radius (Ri) and the outer radial temperature (T35o) at the outer radius (Ro) (e.g., as shown below) (as illustrated in FIG. 5d).

[0674] This configuration, as illustrated in FIG. 5e, can assist in controlling one or more corresponding downstream outlet temperatures at the outlet plane in CZ4 as illustrated in FIG. 5f. For example, to control the outlet temperature (T4j) at the combustor intermediate radius (Rj). This configuration can further control a temperature (T35J) to assist in controlling a corresponding second intermediate outlet temperature (T4k) at the second intermediate radius (Rk) (as illustrated in FIG. 5e).

[0675] According to FIG. 5d, the first intermediate temperature (T35j) at the first intermediate radius (Rj) and the second intermediate temperature (T35k) at the second intermediate radius (Rk) can be further configured to obtain a desired intermediate temperature gradient (DT35jk) between the first intermediate radius (Rj) and the second intermediate radius (Rk) in the combustor axial transition plane (CZ35).

[0676] FIG. 5e illustrates a corresponding schematic graph of the hot gas outlet temperature (T4) for the combustor radius (R) at an axial position (CZ4) within the combustor outlet plane (or turbine inlet plane) downstream of the equilibrium region. Some configurations may control the upstream fluid delivery of one or more of the fuel fluid, oxidizer fluid, and / or diluent fluid to control the outlet temperature (T4) to a radial inner outlet temperature (T4i) at an inner radius (Ri) within the outlet plane at the axial position (CZ4).

[0677] Referring further to FIG. 5e, this configuration can similarly control the outlet temperature (T4) to have a radial outer outlet temperature (T4o) at an outer radius (Ro) within the outlet plane of the axial position (CZ4). This outer temperature (T4o) can be configured relative to (e.g., higher) the radial inner outlet temperature (T4i) at an inner radius (Ri) within the outlet plane.

[0678] According to FIG. 5e, one or more of the upstream delivery of the fuel fluid, oxidizer fluid, and / or diluent fluid may be further modified to control the first intermediate temperature (T4j) at the first intermediate radius (Rj) at the combustor outlet. Similarly, the upstream fluid delivery may be configured to control the second intermediate temperature (T4k) at the second intermediate radius (Rk) at the outlet plane in CZ4.

[0679] Referring further to FIGS. 5d and 5e, one or more upstream intermediate temperatures (T35j and / or T35k) (having the intermediate temperature gradient (DT35jk) of FIG. 5d) and / or corresponding diluent and oxidizer fluid transfer orifices within the blend-trim region are illustrated. These upstream orifices may be configured to achieve the desired downstream outlet temperature illustrated in FIG. 5e. For example, this is to achieve an outlet temperature (T4j) at a first intermediate radius (Rj) and / or a second intermediate temperature (T4k) at a second intermediate radius (Rk) having a corresponding temperature gradient (DT4jk) between these two intermediate outlet temperatures at the combustor outlet plane at the axial position (CZ4).

[0680] Referring to FIG. 5d, some configurations can control one or both of the inner temperature (T35i) at the inner radius (Ri) and / or the outer temperature (T35o) at the outer radius (Ro) relative (e.g., higher) to the desired corresponding downstream outlet temperature (T4o) as illustrated in FIG. 5e. Such configurations can be adjusted to accommodate outer wall cooling at the outer radius (Ro) from the transition axial position (CZ35) in the combustor outlet plane to the combustor outlet axial position (CZ4).

[0681] FIG. 5f illustrates a schematic graph of the hot wall temperature (Tw) versus the combustor axial length (Z), from the 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) at the combustor outlet at the axial outlet position (CZ4).

[0682] Referring further to FIG. 5f, these temperatures can be further adjusted to control the inner wall temperature (TW4i) and the outer wall temperature (TWro). These can start at the outer wall temperature of the upstream inner wall temperature (TW35i and / or TW35o) at the rich / blend-trim axial boundary (CZ35). These temperatures may include the intermediate inner wall temperature (TW39i) and / or outer wall temperature (TW39o) at the blend-trim area outlet in CZ39 axially. One or more temperature distributions can change from the inner wall (TW4i) and / or outer wall (TW4o) to the downstream outer wall temperature at the combustor axial outlet in CZ4.

[0683] FIG. 5g illustrates a schematic graph of the axial velocity (V) of the combustion hot gas versus the combustor radius (R) from the radially inner wall to the radially outer wall at the combustor outlet at the downstream axial position. This hot gas composition can be adjusted by adjusting the radial distribution of the sum of the CZ4 axial orifices within the upstream combustion zone. For example, they can be adjusted to have an axial velocity (V) of V4i near the combustor inner radius (R4i) near the inner wall (axially in CZ4). This average velocity (V) can be increased to an average velocity (V4j) at the first intermediate radius (R4j). The velocity (V) can be further increased (or decreased) to a value (V4k) at the second intermediate radius (R4k). Next, the velocity (V) can be decreased to a radially outer value of V4o near the combustor outer radius (R4o).

[0684] FIG. 5h is a graph showing an “unfolded” section of the circumferential distribution of the hot gas temperature (T) versus the combustor circumferential angle theta for a region containing a first radially oriented combustor located in the counterclockwise direction (CCW) (left), labeled Theta1. This is extended clockwise to additionally show a second radially oriented combustor located in the clockwise direction (CW) (right), similarly labeled Theta2.

[0685] FIG. 5i additionally illustrates the radial inner temperature within the upper (hotter) line between the lower fluid temperature (Tsi) and the upper fluid inlet temperature (Ti) at the inner radius of the combustor (Ri), labeled "At Ri". FIG. 5i similarly illustrates the corresponding radial outer fluid temperature versus the circumferential angle theta between Tso and To near or at the outer radius of the combustor (Ro), labeled "At Ro". In the counterclockwise (CCW) combustion region, these range from the counterclockwise circumferential angle (Theta1wo) to the clockwise angle (Theta1co) for the intermediate outer circumferential combustion angle (Theta1o).

[0686] FIG. 5i similarly illustrates a first combustion inner section centered in a counterclockwise (CCW) direction at R1 and Theta1I. This extends along the circumferential width of Delta Theta1(1) from Theta1WI to Theta1WO. It illustrates a second combustion inner section centered in Theta2I, which is displaced clockwise from the first inner section and extends from a counterclockwise angle (Theta2WI) to a clockwise angle (Theta2CI).

[0687] FIG. 5i is a graph of the high-temperature gas temperature (T) versus the circumferential angle theta of the combustor, having a temperature between Ts and Ti at the inner radius (Ri) and outer radius (Ro), and having a heated first counterclockwise combustion section (Theta1) and a second clockwise combustion section (Theta2).

[0688] FIG. 5j is a graph of the hot gas velocity versus the combustor circumferential angle theta between velocity (Vs) and velocity (V1) for values ​​at inner radius (Ri) and outer radius (Ro), having a first combustion section cooled at Theta1 in a counterclockwise direction and a second combustion section cooled at Theta2 in a clockwise direction.

[0689] ***

[0690] A combustor radially oriented at the inlet of an annular gas turbine combustor

[0691] ***

[0692] Expandable Omega Combustor

[0693] One or more curves ranging from cycloid to hyperbolic to parabolic may be used for parts of the diffuser, combustor, and / or transition zone walls. These may include curves of the brachystocron or cycloid curve series. The expandable combustor may be further axially configured as an omega-shaped combustor, as shown in FIG. 5k in the radial-axial (RZ) section elevation view. This expandable combustor extends radially outward from the turbine axis and is referred to herein as the expandable omega combustor (707) (or omega combustor). Oxidizer fluid flow (WX34) may be delivered to the expandable omega combustor through an upstream diffuser into a combustion zone inlet (CZ31) that is generally axially oriented (according to the terms of FIG. 4a and 4b). The walls and shape of the omega combustor (707) may be configured using one of the cycloid series curves.

[0694] The oxidizer fluid (or second fluid) (F4) can be delivered from the upstream compressor (407(CPR)), redirected radially outward (+R), and then delivered outwardly upstream (+R -Z) through an outwardly inverted duct to an expandable combustion and trim-blend area (704) between the upstream combustor plane (CZ34) and the downstream combustor plane (CZ39) (similar to what is shown in FIG. 4a and 4b). The oxidizer, fuel, and diluent fluids can be delivered to the combustion area (704) (synthetically illustrated in FIG. 4a and 4b, and similar to other drawings and disclosures in this specification that refer to the combustion area (704)).

[0695] The high-temperature combustion fluid c...

Claims

Claim 1 A scalable combustor system comprises a fluid delivery system configured to deliver a fuel fluid containing fuel, an oxidizer fluid containing an oxidizer, and a diluent fluid containing a diluent into the combustor; said combustor: Combustion fluid flow axis ― The above combustion fluid flow axis is: A combustion chamber having first combustion chamber walls arranged axially and circumferentially; A second combustion chamber wall arranged radially; A plurality of fuel feeders including fuel orifices; A plurality of oxidizer feeders comprising an oxidizer orifice disposed around at least one of the first combustion chamber wall and the second combustion chamber wall; Upstream flame control mechanism; and As a downstream combustor outlet, the first and second combustion chamber walls extend laterally with respect to a shallow gap between the first and second combustion chamber walls along directions transverse and perpendicular to the streamline flow direction passing through the combustor, and the ratio of the transverse extension to the shallow gap is greater than 1.15, and the combustor is configured to deliver the fuel fluid through a plurality of fuel feeders and fuel orifices and the oxidizer fluid through a plurality of oxidizer feeders and oxidizer orifices to the combustion chamber, and to deliver the diluent fluid together with at least one of the fuel fluid and the oxidizer fluid through one or more of the plurality of fuel orifices and through one or more of the oxidizer orifices to burn the fuel with the oxidizer in the combustion chamber; and the combustor comprises a downstream combustor outlet configured to deliver a combustion fluid comprising the products of combustion, the diluent, and the residual oxidizer to the combustor outlet—; and An expandable combustor system comprising a control system configured to control the delivery of a fuel fluid, an oxidizer fluid, and a diluent fluid, and to ignite the fuel with the oxidizer by controlling one or more fluid delivery rates to maintain the combustion temperature within the combustion chamber above the combustion quench limit. Claim 2 In claim 1, an expandable combustor system in which the cross-sectional area of ​​a combustion chamber positioned perpendicular to the streamline flow increases along the streamline flow direction within a predetermined fuel fluid delivery area. Claim 3 An expandable combustor system according to claim 1, wherein the combustion chamber further comprises a first end wall and a second end wall, the first and second end walls are joined to the transverse outer ends of the first and second shallowly spaced combustor walls, and the second combustor wall comprises a second plurality of orifices. Claim 4 In claim 2, an expandable combustor system in which the rate of increase of the cross-sectional area of ​​the combustion chamber is limited to or less than the maximum rate of increase. Claim 5 In claim 4, an expandable combustor system in which the rate of increase of the combustion chamber cross-sectional area decreases downstream of the axial position of the maximum axial rate of increase. Claim 6 In claim 1, an expandable combustor system in which one of the portion of the diluent fluid and the portion of the oxidizer fluid is delivered downstream of the total fuel delivery. Claim 7 In claim 1, an expandable combustor system in which the oxidizer fluid is delivered through a plurality of oxidizer orifices downstream of a major portion of fuel-oxidizer combustion sufficient to provide residual oxidizer at the combustor outlet. Claim 8 In claim 1, an expandable combustor system in which a diluent fluid is delivered through one of a plurality of oxidizer orifices and a plurality of diluent orifices downstream of a major portion of fuel-oxidizer combustion. Claim 9 In claim 1, an expandable combustor system in which a gaseous diluent fluid is delivered together with a fuel fluid through an orifice. Claim 10 An expandable combustor system according to claim 1, which controls diluent delivery to limit the outlet high-energy fluid temperature at the combustor outlet to below a predetermined outlet temperature. Claim 11 In claim 1, an expandable combustor that changes one of the ratio of oxidizer delivery to fuel delivery and the ratio of diluent delivery to fuel delivery between the upstream and downstream parts of the combustion chamber. Claim 12 An expandable combustor system according to claim 1, which changes either the ratio of excess oxidizer delivery to total fuel delivery and the ratio of diluent to fuel delivery in the upstream and downstream parts of the downstream blend-trim region. Claim 13 An expandable combustor system according to claim 1, further comprising a plurality of diluent orifices in one of the combustor walls and one or more diluent feeders for supplying a diluent fluid through one or more of the diluent orifices. Claim 14 A combustion system comprises a fluid transfer system configured to transfer a fuel fluid containing fuel, an oxidizer fluid containing an oxidizer, and a diluent fluid containing a diluent into a combustion system fluidly communicating with a fluid transfer system; said combustion system: Combustion chamber having an upstream flame control mechanism; First combustion chamber wall; Opposing second combustion chamber wall; A plurality of orifices in at least one of the first and second combustor walls; A plurality of fluid feeders supplying one or more of the fuel fluid, oxidizer fluid, and / or diluent fluid to the plurality of orifices; and A combustor system comprising a combustor outlet — wherein the first and second combustor walls extend laterally along a direction transverse and perpendicular to the streamline flow direction passing through the combustor with respect to the shallow gap between the first and second combustor walls. Claim 15 In Clause 14, a combustor system in which the ratio of transverse extension to shallow gap is greater than 1.

15. Claim 16 In claim 1, the control system is configured to control one of the wall temperature, residence time, and catalyst within a transverse fuel feeder to decompose a portion of the ammonia fuel into hydrogen and nitrogen. Claim 17 In a combustion system, the combustion chamber — said combustion chamber is: First combustion chamber wall; Second combustion chamber wall; Multiple fluid feeders; and A combustor system comprising: a plurality of orifices in at least one of the first and second combustor walls; and a combustor outlet; wherein the first and second combustor walls extend laterally with respect to the shallow gap between the first and second combustor walls along directions transverse and perpendicular to the streamline flow direction passing through the combustor system. Claim 18 In an expandable combustion system, the combustion unit comprises: Combustion fluid flow axis; As a combustion chamber, the combustion chamber is: First combustion chamber walls arranged axially and circumferentially; Radially opposite second combustion chamber wall; A plurality of fuel feeders including fuel orifices; and A combustion chamber comprising a plurality of oxidizer feeders, each comprising an oxidizer orifice, configured around at least one of the walls of the first and second combustion chambers; Upstream flame control mechanism; and Downstream combustor outlet — The walls of the first and second combustion chambers extend laterally with respect to the shallow gap between the walls of the first and second combustion chambers along directions transverse and perpendicular to the streamline flow direction passing through the combustor, and the ratio of the transverse extension to the shallow gap is greater than 1.15, expandable combustor system. Claim 19 In claim 18, the system comprises a control system configured to control fuel flow and ammonia flow, said ammonia flow being an expandable combustor system directed toward a heat generator. Claim 20 In claim 19, the above-mentioned heat generator is NO x An expandable combustion system configured to decompose the ammonia into at least water to reduce emissions.

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