Gas turbine engine including fuel nozzle assembly

Abstract

A gas turbine engine includes: a compressor section, a combustion section, and a turbine section in a serial flow arrangement wherein the combustion section includes: a combustor liner at least partially defining a combustion chamber; and a fuel nozzle assembly, the fuel nozzle assembly comprising: a liquid fuel supply portion, the liquid fuel supply portion supplying liquid fuel; a hydrogen fuel supply unit that supplies gaseous hydrogen fuel; and a fuel nozzle body fluidly coupled with the liquid fuel supply and the hydrogen fuel supply to provide liquid fuel and gaseous hydrogen fuel to the combustion chamber.

Description

Technical Field

[0001] This topic generally relates to gas turbine engines with fuel nozzle assemblies. Background Technology

[0002] A turbine engine is driven by a flow of combustion gases through the engine to rotate multiple turbine blades, which in turn rotates a compressor, thus supplying compressed air to the combustor for combustion. The combustor can be located within the turbine engine and fluidly connected to the turbine through which the combustion gases flow.

[0003] Historically, hydrocarbon fuels have been used in the combustors of turbine engines. Typically, air and fuel are fed into the combustion chamber, mixed, and then the fuel is burned in the presence of air to produce hot gases. These hot gases are then fed into the turbine, where they are cooled and expanded to generate power. Byproducts of fuel combustion often include environmentally undesirable byproducts such as nitrogen oxides and nitrogen dioxide (collectively known as NO). x Carbon monoxide (CO), unburned hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides including sulfur oxides (e.g., SO2 and SO3).

[0004] To reduce unwanted environmental byproducts, other fuels, such as hydrogen, are being explored. Hydrogen, or hydrogen mixed with another element, has a higher flame temperature than conventional hydrocarbon fuels. In other words, hydrogen or hydrogen-blended fuels typically have a wider combustible range and a faster combustion rate than conventional hydrocarbon-based fuels. Attached Figure Description

[0005] In the attached diagram:

[0006] Figure 1 This is a schematic diagram of a gas turbine engine having a compression section, a combustion section, and a turbine section, based on the various aspects described herein.

[0007] Figure 2 It is based on the various aspects described in this article along line II-II. Figure 1 A schematic diagram of the combustion zone.

[0008] Figure 3 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0009] Figure 3A This is a schematic cross-sectional view showing a portion of the fuel nozzle body, including portions of the first fuel conduit and the second fuel conduit, according to various aspects described herein.

[0010] Figure 4This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0011] Figure 5 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0012] Figure 6 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0013] Figure 7 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0014] Figure 8 This is a schematic cross-sectional view showing the outer wall of the fuel nozzle assembly as viewed from the rear, according to the various aspects described herein.

[0015] Figure 9 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0016] Figure 10 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0017] Figure 11 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0018] Figure 12 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0019] Figure 13 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0020] Figure 14 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0021] Figure 15 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0022] Figure 16 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0023] Figure 17 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0024] Figure 18 This is a flowchart that generally illustrates a method for operating a gas turbine engine according to the various aspects described herein. Detailed Implementation

[0025] The aspects disclosed herein relate to burners. In some aspects, the disclosed burners and fuel nozzle assemblies can be used with gaseous fuels, such as hydrogen. Gaseous fuels, including hydrogen, diffuse / disperse at a faster rate than atomized liquid fuels. This can result in less mixing time for the gaseous fuel, shorter fuel mixing tube lengths, and a flame from the gaseous fuel is more likely to spread further and faster. This increases the risk of flashback and flame persistence (e.g., in the nozzle or mixer) and enhances flame control and flame propagation limitation by controlling the dispersion of the gaseous fuel.

[0026] In addition to those shown in the accompanying drawings, this disclosure contemplates many other possible aspects and configurations. The disclosed fuel nozzle can be effectively used with a variety of fuels, such as liquid fuels (e.g., Jet-A) and gaseous fuels (e.g., hydrogen). Fuel can be discharged by the fuel nozzle at the same time or at different times. Compared to other designs, the disclosed fuel nozzle can provide better flame stability, lower flame temperature, reduced flashback, reduced flame sustaining, and lower NOx emissions. x Emissions. Distributed fuel injection from disclosed fuel nozzles (such as radial distributed fuel injection, axial distributed fuel injection, or both) can promote combustion stability and reduce NO. x Emissions and improved durability. Limiting flashback and flame hold can allow the use of more reactive fuels (such as hydrogen), promote the use of more reactive fuels by limiting wear on engine components, or both. Increasing mix time can provide a more uniform temperature distribution and lower peak temperatures, which can limit NO. x emission.

[0027] During certain phases of flight (such as approach), using hydrogen fuel alone can limit coking by removing unburned liquid fuel from the combustion zone. During certain phases of flight (such as cruise and approach), using hydrogen fuel alone can achieve zero carbon emissions (e.g., zero CO2). Using hydrogen fuel can shorten burner length because mixing time can be reduced. Using hydrogen fuel alone at low power levels can limit or prevent smog. During at least some phases of flight (such as takeoff and climb), using liquid fuel can limit temperature to improve durability and limit NO. xemission.

[0028] For illustrative purposes, this disclosure will be described in relation to turbine engines. However, it will be understood that the aspects of the disclosure described herein are not limited thereto. The combustors described herein can be implemented in a variety of engines, including but not limited to turbojet engines, turboprop engines, turboshaft engines, and turbofan engines. The aspects of the disclosure discussed herein are generally applicable to non-aircraft engines with combustors, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0029] For the burner and fuel nozzle assemblies described herein, gaseous hydrogen fuel can be used without the need for a diluent. In some embodiments, no diluent is added to the combustion chamber, and the fuel is substantially entirely diatomic hydrogen without diluent. As used herein, the term "substantially entirely" to describe the amount of a particular element or molecule (e.g., diatomic hydrogen) means at least 99% (by mass) of the described portion of the element or molecule, such as at least 97.5%, at least 95%, at least 92.5%, at least 90%, at least 85%, or at least 75% (by mass) of the described portion of the element or molecule. In some examples, the fuel is entirely (e.g., 100%) hydrogen (by mass).

[0030] The term "exemplary" as used herein means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior to or advantageous to other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0031] As used herein, the terms “first,” “second,” “third,” etc., are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components.

[0032] The terms "front" and "rear" refer to relative positions within a gas turbine engine or carrier, and specifically to the normal operating posture of the gas turbine engine or carrier. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine exhaust outlet.

[0033] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "forward" or "front" indicate what is in front of something, and "backward" or "rear" indicate what is behind something. For example, when used in relation to fluid flow, forward / front can indicate upstream, and backward / rear can indicate downstream.

[0034] The term "fluid" can refer to either a gas or a liquid. The term "fluid connection" means that fluids can establish a connection between specified areas.

[0035] In the context of gas turbine engines, the term "nozzle" is used in various ways. In this application, "nozzle" refers to a component having a portion fluidly connected to a fuel supply section and having at least one portion fluidly connected to a burner section, burner bushing, combustion chamber, or a combination thereof.

[0036] Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction along a ray extending between the engine's central longitudinal axis and the engine's outer perimeter.

[0037] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are for identification purposes only to aid the reader in understanding this disclosure and do not impose limitations, particularly regarding the location, orientation, or use of the aspects of the disclosure described herein. Connecting references (e.g., attachment, connection, joint, and engagement) are to be interpreted broadly and may include intermediate structural elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, a connecting reference does not necessarily mean that two elements are directly connected and fixed relative to each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary.

[0038] The singular forms “a,” “an,” and “the” include plural references unless the context clearly indicates otherwise. Furthermore, as used herein, the term “group” or “set” of elements can be any number of elements, including only one.

[0039] The use of “and” and “or” will be interpreted broadly. For example, but not limited to, the use of “and” does not necessarily require all the elements or features listed, and the use of “or” is inclusive unless the structure is illogical.

[0040] As used herein and throughout the specification and claims, approximate language is applied to modify any quantitative representation that may allow for variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” “substantially,” and “basically” are not limited to the specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture parts and systems. For example, approximate language may refer to a margin of 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the endpoints of a single value, a range of values, or a range of defined values. Scope limitations are combined and interchanged herein and throughout the specification and claims; such scope is identified and includes all subscopes contained herein, unless otherwise indicated by context or language. For example, all scopes disclosed herein include endpoints, and endpoints can be combined independently of each other.

[0041] As used herein, “proximity” is a descriptor used to locate the parts described herein. Furthermore, the term “proximity” means that the part is closer to or closer to the referenced part than the following part. For example, “first orifice is close to the wall” or “first orifice is upstream of second orifice” means that the first orifice is closer to the wall than the second orifice.

[0042] Additionally, as used herein, "controller" can include components configured or adapted to provide instructions, control, operation, or any form of communication to an operable component to achieve its operation. A controller can include any known processor, microcontroller, or logic device, including but not limited to: field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), full-authority digital engine control (FADECs), proportional controllers (P), proportional-integral controllers (PI), proportional-derivative controllers (PD), proportional-integral-derivative controllers (PID controllers), proportional-resonant controllers (PR), hardware-accelerated logic controllers (e.g., for encoding, decoding, transcoding, etc.), and combinations thereof. Non-limiting examples of controllers can be configured or adapted to run, operate, or otherwise execute program code to affect operational or functional outcomes, including performing various methods, functions, processing tasks, calculations, comparisons, sensing, or measurement values, etc., to enable or implement the technical operations or actions described herein. Operational or functional outcomes can be based on one or more inputs, stored data values, sensed or measured values, true or false indications, etc. While “program code” is described, non-limiting examples of operable or executable instruction sets may include routines, programs, objects, components, data structures, algorithms, etc., that have the technical effect of performing a specific task or implementing a specific abstract data type. In another non-limiting example, the controller may also include data storage components accessible by the processor, including memory, whether transient, volatile, or non-transient or non-volatile.

[0043] Additional non-limiting examples of memory may include random access memory (RAM), read-only memory (ROM), flash memory, or one or more different types of portable electronic memory, such as discs, DVDs, CD-ROMs, flash drives, universal serial bus (USB) drives, etc., or any suitable combination of these types of memory. In one example, program code may be stored in memory in a machine-readable format accessible to a processor. Furthermore, memory may store various types of data, sensed or measured data values, input, generated or processed data, etc., accessible to a processor when providing instructions, control, or operations to achieve a function or operable result, as described herein. In another non-limiting example, a controller may be configured to compare a first value with a second value and operate and control the operation of additional components based on the satisfaction of that comparison. For example, when a sensed, measured, or provided value is compared with another value (including a stored or predetermined value), the satisfaction of that comparison may result in an action, function, or operation that can be controlled by the controller.

[0044] Figure 1This is a schematic diagram of a gas turbine engine 10. As a non-limiting example, the gas turbine engine 10 can be used within an aircraft. The gas turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16 arranged in a series flow configuration. A drive shaft 18 rotatably connects the compressor section 12 and the turbine section 16 such that rotation of one affects rotation of the other, and defines the rotation axis 20 of the gas turbine engine 10.

[0045] Compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 that are fluidly connected in series with each other. Turbine section 16 may include an HP turbine 26 and an LP turbine 28 that are fluidly connected in series with each other. Drive shaft 18 can operatively connect the LP compressor 22, HP compressor 24, HP turbine 26, and LP turbine 28 together. Alternatively, drive shaft 18 may include an LP drive shaft and an HP drive shaft. The LP drive shaft can connect the LP compressor 22 to the LP turbine 28, and the HP drive shaft can connect the HP compressor 24 to the HP turbine 26. The LP spool may be defined as a combination of the LP compressor 22, LP turbine 28, and LP drive shaft, such that rotation of the LP turbine 28 can apply a driving force to the LP drive shaft, which in turn can rotate the LP compressor 22. The HP spool may be defined as a combination of the HP compressor 24, HP turbine 26, and HP drive shaft, such that rotation of the HP turbine 26 can apply a driving force to the HP drive shaft, which in turn can rotate the HP compressor 24.

[0046] Compressor section 12 may include multiple axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Compressor blades for a stage of compressor section 12 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of compressor section 12 may be mounted to a shroud or housing that may extend circumferentially around and shield one or more sections of gas turbine engine 10. It should be understood that the representation of compressor section 12 is merely illustrative and any number of blades, blades, and stages may be possible. Furthermore, it is conceivable that any number of other components may be present within compressor section 12.

[0047] Similar to compressor section 12, turbine section 16 may include multiple axially spaced stages, each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Turbine blades for one stage of turbine section 16 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of turbine section 16 may be circumferentially mounted to a shroud or housing. It should be noted that any number of blades, blades, and turbine stages are possible, as the illustrated turbine section 16 is merely schematic. Furthermore, it is conceivable that any number of other components may be present within turbine section 16.

[0048] Combustion section 14 may be arranged in series between compressor section 12 and turbine section 16. Combustion section 14 may be fluidly coupled to at least a portion of compressor section 12 and turbine section 16, such that combustion section 14 at least partially fluidly couples compressor section 12 to turbine section 16. As a non-limiting example, combustion section 14 may be fluidly coupled to HP compressor 24 at its upstream end and to HP turbine 26 at its downstream end. Combustion section 14 may include burner 30.

[0049] During operation of the gas turbine engine 10, ambient air or atmospheric air is drawn into the compressor section 12 via a fan (not shown) upstream of the compressor section 12, where it is compressed to define pressurized air. This pressurized air can then flow into the combustion section 14, where it mixes with fuel and is ignited to generate combustion gases. The HP turbine 26 extracts some work from these combustion gases, driving the HP compressor 24. The combustion gases are discharged into the LP turbine 28, which extracts additional work to drive the LP compressor 22, and the exhaust gas is ultimately discharged from the gas turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 28 drives the LP spool to rotate the fan (not shown) and the LP compressor 22. The pressurized airflow and combustion gases together define the working airflow flowing through the fan, compressor section 12, combustion section 14, and turbine section 16 of the gas turbine engine 10.

[0050] Figure 2 Depicting along Figure 1 A cross-sectional view of combustion section 14 along line II-II. Combustion section 14 may include a combustor 30, which has a surrounding structure around the gas turbine engine 10. Figure 1The combustor portions 31 are arranged in an annular arrangement with their centerline or axis of rotation 20 set (e.g., circumferentially spaced apart from each other in an annular configuration). In some configurations, the combustor portions 31 may include or be configured as a combustor cup, fuel cup, or nozzle cup. A fuel nozzle assembly 48 may be connected to each combustor portion 31. Depending on the type of engine in which the combustor 30 is located, the combustor 30 may have a canister-shaped, canister-annular, or annular arrangement. In a non-limiting example, the combustor 30 may have an arrangement similar to that of the gas turbine engine 10. Figure 1 The protective cover or housing 29 is positioned together with the protective cover or housing 29. The protective cover or housing 29 can shield or cover at least a portion of the combustion zone 14.

[0051] The burner 30 may be at least partially defined by a burner bushing 40. In some examples, the burner bushing 40 may include an outer bushing 41 and an inner bushing 42 arranged concentrically with respect to each other and in a ring-like manner around the engine centerline or axis of rotation 20. In some examples, the burner bushing 40 may have a ring-like structure around the burner 30. In some examples, the burner bushing 40 may include multiple segments or portions that together form the burner bushing 40. In some examples, the burner bushing 40 may have a ring-like structure around the burner 30. In some examples, the burner bushing 40 may include multiple segments or portions that together form the burner bushing 40. In some examples, the burner bushing 40 may include an outer bushing 41 radially spaced from the inner bushing 42. In some examples, the burner bushing 40 may include a single bushing.

[0052] The burner bushing 40 may at least partially define a combustion chamber 50 arranged annularly about the axis of rotation 20. For example, a wall 46 (e.g., a dome wall) may be substantially perpendicular to the axis of rotation 20 and may cooperate with an outer liner 41, an inner liner 42, or both to at least partially define the combustion chamber 50. The compressed air passage 32 may be at least partially defined by both the burner bushing 40 and the housing 29.

[0053] The burner 30 may include or be fluidly coupled to a first fuel supply section 34 (e.g., a first fuel manifold or conduit) supplying a first fuel F1, a second fuel supply section 36 (e.g., a second fuel manifold or circuit) supplying a second fuel F2, or both. A fuel nozzle assembly 48 fluidly connects the first fuel supply section 34 and the second fuel supply section 36 to one of the burner section 31 and the combustion chamber 50 to supply the combustion chamber 50 with the first fuel F1, the second fuel F2, or both. The fuel nozzle assembly 48 may include a fuel nozzle body 49 and may be coupled to a wall 46. The first fuel F1 and the second fuel F2 may include any suitable fuel, including liquid fuels (such as Jet-A) or gaseous fuels (such as hydrogen fuel). In a non-limiting example, the hydrogen fuel may include 100% H2 (e.g., without diluent). In some examples, the first fuel F1 may include a liquid fuel (e.g., an atomized liquid fuel such as Jet-A), and the second fuel may include a gaseous fuel such as hydrogen. For example, the fuel nozzle assembly 48 may be a multi-fuel nozzle assembly, a liquid and gaseous fuel nozzle assembly, or a liquid and gaseous hydrogen fuel nozzle assembly. Additionally or alternatively, the first fuel supply section 34 may be a liquid fuel supply section, and the second fuel supply section may be a hydrogen fuel supply section. The burner section 31 may be arranged in a ring configuration about the axis of rotation 20. The burner section 31 may be configured to be radially distanced from the axis of rotation 20, a radial distance greater than the radial distance of the inner liner 42 and less than the radial distance of the outer liner 41. The controller 60 may be connected to the first fuel supply section 34, the second fuel supply section 36, the fuel nozzle assembly 48, or a combination thereof, and at least partially control their operation. The controller 60 may include a processor 62 and a memory 64. The combustion section centerline 33 of the combustion section 14 may be concentric with the axis of rotation 20. The combustion section centerline 33 may define a radial direction R, an axial direction A, and a circumferential direction C.

[0054] Figure 3 , Figure 4 and Figure 5 This is a schematic cross-sectional view of an example of a burner section 31, which may include or be coupled to a fuel nozzle assembly 48, and may include portions of a burner bushing 40 and a wall 46. The fuel nozzle assembly 48 may include a fuel nozzle assembly centerline 35, which is parallel to and radially offset from the combustion zone centerline 33. The fuel nozzle assembly centerline 35 may be collinear with the centerline of the burner section 31 to which the fuel nozzle assembly 48 is connected or coupled. The fuel nozzle assembly centerline 35 may define a second axial direction A2, a second radial direction R2 orthogonal to the second axial direction A2, and a second circumferential direction C2 about the second axial direction A2.

[0055] Fuel nozzle assembly 48 includes fuel nozzle body 49, which may include a central body 100, a first inner wall 102 radially outward of the central body 100, and a body wall 104 radially outward of the first inner wall 102. Body wall 104 may include an outer surface 106, which is the outer surface of at least some portions of the fuel nozzle body 49. Fuel nozzle assembly 48 may include an outer wall 108 mechanically coupled to and radially spaced from the outer surface 106. For example, the outer wall 108 may be mechanically coupled to the outer surface 106 via a swirler (e.g., a third swirler 144) disposed at least partially around the body wall 104, via one or more mounting posts or combinations thereof extending radially outward from the body wall 104. The first inner wall 102, body wall 104, and outer wall 108 may be radially spaced annular walls and may be centrally arranged in a ring around a fuel nozzle assembly centerline 35. A first internal fluid channel 120 may be at least partially defined between the central body 100 and the first inner wall 102. A second internal fluid channel 122 may be at least partially defined between the first inner wall 102 and the body wall 104. A first external fluid channel 124 may be at least partially defined between the outer surface 106 and the outer wall 108. In some examples, the first inner wall 102 may act as a first diverter (e.g., a guide diverter), and the outer wall 108 may act as a second diverter. In some configurations, the first inner wall 102 may include a convergence-divergence configuration.

[0056] The fuel nozzle assembly 48 may include a mixer 130 coupled to an outer wall 108, wall 46, or both. The mixer 130 and the outer wall 108 may at least partially define a second external fluid passage 132. The second external fluid passage 132 may include a radial portion 134 extending in a second radial direction R2 and may include an axial portion 136 extending in a second axial direction A2. For example, the second external fluid passage 132 may be annular, and the cross-sectional shape of the second external fluid passage 132 may include an L-shaped configuration. The mixer 130 may include a mixer wall 138 extending in the second axial direction A2 radially outward of the outer wall 108 and radially inward of at least some portions of the wall 46. The second external fluid passage 132 may be at least partially defined between the mixer wall 138 and the outer wall 108, between the mixer wall 138 and the outer surface 106, or both, because the mixer wall 138 may extend rearward further than the outer wall 108. The mixer wall 138 may extend axially rearward beyond the trailing edge 109 of the outer wall 108.

[0057] The fuel nozzle assembly 48 may include a first swirler 140 in a first internal fluid passage 120, a second swirler 142 in a second internal fluid passage 122, a third swirler 144 in a first external fluid passage 124, and a fourth swirler 146 in a second external fluid passage 132. The first swirler 140, the second swirler 142, and the third swirler 144 may include an axial swirler that receives air 70 (such as from compressor section 12) moving rearward in a second axial direction A2. Figure 1 The fourth vortex generator 146 may include a radial vortex generator configured to receive air 70 moving radially inward in the second radial direction R2 and to output swirling air 70 radially inward, such that the output swirling air 70 may impinge on the outer wall 108 and change its radially inward flow to a rearward flow in the second axial direction A2. For example, the fourth vortex generator 146 may be disposed in the radial portion 134 and may output swirling air 70 radially inward toward the outer wall 108.

[0058] The fuel nozzle assembly 48 may include a plurality of fuel orifices 150 fluidly connected to one or both of the first fuel supply section 34 or the second fuel supply section 36. The plurality of fuel orifices 150 may include one or more central body fuel orifices 152 of the central body 100, one or more first inner wall fuel orifices 154 of the first inner wall 102, one or more body wall fuel orifices 156 of the body wall 104, one or more outer wall fuel orifices 158 of the outer wall 108, or combinations thereof. One or more central body fuel orifices 152 may be in front of some or all other fuel orifices 150 (e.g., closer than some or all other fuel orifices 150). Figure 1 (The front end of the gas turbine engine 10). One or more body wall fuel ports 156 may be located behind some or all other fuel ports 150 (e.g., closer than some or all other fuel ports 150). Figure 1 (The rear end of the gas turbine engine 10). One or more first inner wall fuel ports 154 and one or more outer wall fuel ports 158 can be axially offset and can be axially located between one or more central body fuel ports 152 and one or more body wall fuel ports 156. Axially offset fuel ports (such as fuel ports 150) can allow different mixing times between air 70 and fuel (such as first fuel F1 and second fuel F2), which can provide reduced emissions and increased flame stability. For example, fuel ports positioned further forward allow for increased mixing time, which can reduce NO. xDischarge, and fuel orifices positioned further rearward can reduce mixing time, which can increase flame stability. At least some of the plurality of fuel orifices 150 (such as one or more outer wall fuel orifices 158) can be fluidly coupled to both the first fuel supply section 34 and the second fuel supply section 36 to discharge at least one of the first fuel F1 or the second fuel F2. Fluidly coupling the fuel orifices (such as one or more outer wall fuel orifices 158) to both the first and second fuel supplies 34, 36 allows the fuel nozzle assembly 48 to operate in multiple modes to discharge the first fuel F1 or the second fuel F2 from different locations during different operating conditions (e.g., flight conditions). Radially outward fuel discharge can promote a more uniform distribution of fuel in the combustion chamber 50, which can limit NO x emission.

[0059] The fuel nozzle assembly 48 may include a first fuel conduit 170 that fluidly connects a first fuel supply portion 34 to at least some of the fuel orifices 150, and may include a second fuel conduit 172 that fluidly connects a second fuel supply portion 36 to at least some of the fuel orifices 150. In some examples, fuel conduits 170 and 172 are included together with fuel supplies 34 and 36, respectively. Among other configurations, the first fuel conduit 170 and the second fuel conduit 172 may include one or a combination of a pipe, tube, or channel formed in the fuel nozzle body 49. Although in Figure 3 The first fuel conduit 170 and the second fuel conduit 172 are shown separately in the fuel nozzle body 49, but in some examples, such as Figure 3A As generally shown, at least some portions of the first fuel conduit 170 and the second fuel conduit 172 may be arranged concentrically. For example, at least a portion of the first fuel conduit 170 may extend through the second fuel conduit 172 such that the second fuel F2 flows around the first fuel F1 flowing through the first fuel conduit 170 through the second fuel conduit 172 (e.g., a smaller diameter first conduit disposed within a larger diameter second conduit).

[0060] The fuel nozzle assembly 48 can discharge various combinations of first fuel F1 and second fuel F2 into the combustion chamber 50 through various combinations of fuel orifices 150. (Reference) Figure 3For example, the fuel nozzle assembly 48 may operate only with the second fuel F2, which may include discharging the second fuel F2 through one or more first inner wall fuel orifices 154 and through one or more outer wall fuel orifices 158. Discharging the second fuel F2 through one or more first inner wall fuel orifices 154 may include discharging the second fuel F2 radially inward and rearward (e.g., at an angle between the second axial direction A2 and the second radial direction R2). For example, at least a portion of the fuel passage 155 of the first inner wall 102 may be radially inward at an angle toward the fuel nozzle assembly centerline 35 to allow angled discharge of the first fuel F1, the second fuel F2, or both. Discharging the second fuel F2 through one or more outer wall fuel orifices 158 may include discharging the second fuel F2 rearward in the second axial direction A2 (e.g., without a radial component).

[0061] refer to Figure 4 The fuel nozzle assembly 48 may operate solely with the first fuel F1, which may include discharging the first fuel F1 through one or more central body fuel orifices 152 and through one or more body wall fuel orifices 156. Discharging the first fuel F1 through one or more central body fuel orifices 152 may include radially outward and rearward discharge of the first fuel F1. For example, at least a portion of the central body fuel passage 153 of the central body 104 may be radially outward at an angle relative to the fuel nozzle assembly centerline 35 to allow angled discharge of the first fuel F1, the second fuel F2, or both. Discharging the first fuel F1 through one or more body wall fuel orifices 156 may include radially outward (e.g., parallel to a second radial direction R2, without an axial component) discharge of the first fuel F1. For example, at least a portion of the body wall fuel passage 157 may be radially outward at an angle relative to (e.g., perpendicular to) the fuel nozzle assembly centerline 35 to allow angled (e.g., directly radial) discharge of the first fuel F1, the second fuel F2, or both. The radial outward discharge of first fuel F1 from one or more body wall fuel orifices 156 can cause the first fuel F1 to intersect with air 70 flowing through or out of the first external fluid passage 124, with air 70 flowing through or out of the second external fluid passage 132, contact the mixer wall 138, or a combination thereof, which can promote mixing. For example, the flow direction of the first fuel F1 discharged from one or more body wall fuel orifices 156 can be perpendicular to the flow direction of air 70 in or from the first external fluid passage 124 and the second external fluid passage 132 (e.g., the discharged first fuel F1 can flow across the air 70). For example, one or more body wall fuel orifices 156 can be located at or downstream of the outlet 159 of the first external fluid passage 124. The outlet 159 can be defined at the trailing edge of the outer wall 108.

[0062] refer to Figure 5The fuel nozzle assembly 48 can operate in conjunction with both the first fuel F1 and the second fuel F2, which may include discharging at least one of the first fuel F1 or the second fuel F2 through one or more central body fuel orifices 152, one or more first inner wall fuel orifices 154, one or more body wall fuel orifices 156, one or more outer wall fuel orifices 158, or a combination thereof. In some configurations, discharging the first fuel F1 and the second fuel F2 may include discharging the first fuel F1 (e.g., as a main fuel) through one or more body wall fuel orifices 156 and discharging the second fuel F2 (e.g., as an ignition fuel) through one or more central body fuel orifices 152.

[0063] In the first operating mode (e.g., dual-fuel mode), such as Figure 5 As generally shown, the fuel nozzle assembly 48 can discharge first fuel F1 and second fuel F2 into the combustion chamber 50. For example, the fuel nozzle assembly 48 can discharge first fuel F1 through one or more outer wall fuel orifices 158 of the outer wall 108, and can discharge one or both of first fuel F1 and second fuel F2 through one or more central body fuel orifices 152. In some examples, first fuel F1 and second fuel F2 can be discharged through the central body fuel orifice 152.

[0064] In the second operating mode, such as Figure 3 As generally shown, the fuel nozzle assembly 48 can discharge second fuel F2 through one or more first inner wall fuel orifices 154 of the first inner wall 102 and one or more outer wall fuel orifices 158 of the outer wall 108, such as not discharging first fuel F1 into the combustion chamber 50.

[0065] In the third operating mode, such as Figure 4 As generally shown, the fuel nozzle assembly 48 can discharge first fuel F1 through one or more central body fuel orifices 152 of the central body 100 and one or more outer wall fuel orifices 158 of the outer wall 108, such as not discharging second fuel F2 into the combustion chamber 50.

[0066] For aircraft applications, the fuel nozzle assembly 48 may discharge only the first fuel F1, only the second fuel F2, or both the first fuel F1 and the second fuel F2, depending on the aircraft operating conditions. For example, during ignition, taxiing, cruise, approach, and landing, the fuel nozzle assembly 48 may operate in a second operating mode and discharge only the second fuel F2 (e.g., hydrogen), and during climb and takeoff, the fuel nozzle assembly 48 may operate in a third mode and discharge only the first fuel F1 (e.g., liquid fuel). Discharging the second fuel F2 during approach and landing can limit coking because the combustion of the second fuel F2 can burn most or all of any unburned liquid fuel (e.g., the first fuel F1). At least when fuel (such as the first fuel F1) is not discharged from one or more body wall fuel orifices 156, the air 70 flowing through the second external fluid passage 132 can provide flame shaping in the combustion chamber 50. For example, flame shaping can limit the flow of fuel (such as the second fuel F2) toward the burner bushing 40, which can limit the temperature, flashback, and flame retention at the burner bushing 40. Additionally or alternatively, flame shaping can restrict fuel (such as second fuel F2) at or near wall 46, which can reduce the temperature at wall 46, thereby reducing the chance of flashback and flame persistence. In some examples, fuel nozzle assembly 48 can discharge at least some of both first fuel F1 and second fuel F2 during one or more of ignition, taxiing, cruise, climb, takeoff, approach, or landing.

[0067] refer to Figure 6 and Figure 7 The outer wall 108 of the fuel nozzle body 49 of the fuel nozzle assembly 48 can extend axially rearward, such that the trailing edge 109 of the outer wall 108 and the trailing edge 139 of the mixer wall 138 of the mixer 130 are axially aligned relative to the centerline 35 of the fuel nozzle assembly. With this configuration, one or more outer wall fuel orifices 158 can directly discharge fuel (such as first fuel F1 from the first fuel supply 34, second fuel F2 from the second fuel supply 36, or both) into the combustion chamber 50. Air 70 from the second external fluid passage 132 can flow along the outer surface of the outer wall 108 to enter the combustion chamber 50 before mixing with the fuel, which can provide flame shaping to confine the flame at or near the wall 46, burner liner 40, or both.

[0068] For some examples, the mixing length of the second fuel F2 discharged through one or more central body fuel orifices 152 is approximately 0 inches (e.g., at wall 46) to 1.5 inches or 0–38.1 mm. The mixing length can be measured from the rear surface of wall 46 to one or more central body fuel orifices 152.

[0069] In some examples of fuel nozzle assembly 48, such as Figure 8 As generally shown, the outer wall fuel orifices 158 may be circumferentially spaced from each other in an annular configuration at the trailing edge 109 of the outer wall 108. In some examples, the outer wall fuel orifices 158 may be arranged in an alternating pattern, with some of them fluidly connected to the first fuel supply 34 via a first fuel conduit 170, and adjacent outer wall fuel orifices 158 fluidly connected to the second fuel supply 36 via a second fuel conduit 172. The diameter of the outer wall fuel orifices 158 may vary in a second circumferential direction C2 relative to the centerline 35 of the fuel nozzle assembly. In some examples, outer wall fuel orifices 158 with smaller diameters (e.g., 0.015 inches to 0.024 inches or 0.38 mm to 0.61 mm) may be provided in the radially outer portion 174 and radially inner portion 175 of the outer wall 108 (e.g., relative to the centerline 33 of the combustion zone, facing towards...). Figure 8 The outer wall fuel orifice 158, having a large diameter (e.g., 0.020 inches to 0.045 inches or 0.50 mm to 1.14 mm), can be disposed on the circumferential sides 176, 177 of the outer wall 108 (e.g., relative to the centerline 33 of the combustion zone). Figure 8 (Left and right sides). This configuration allows for proximity to the burner bushing 40 ( Figure 7 It provides a relatively small amount of fuel (such as a second fuel F2) because the outer wall fuel orifice 158 with a larger diameter can be positioned further away from the burner bushing 40 than the outer wall fuel orifice 158 with a smaller diameter. Figure 7 Further afield, this limits the temperature, flashback, flame hold-up, or a combination thereof at 40°C of the burner bushing.

[0070] refer to Figure 9 For some examples, the fuel nozzle assembly 48 may include one or more bushing fuel conduits 180 fluidly connected to one or more bushing fuel orifices 182 of the burner bushing 40. The one or more bushing fuel conduits 180 may be fluidly connected to a second fuel supply section 36 to supply second fuel F2 to the one or more bushing fuel orifices 182. The one or more bushing fuel orifices 182 may be located behind the wall 46 and may be radially inwardly pointed (e.g., directly radially inward (e.g., perpendicular to the second axial direction A2)) to discharge the second fuel F2 into the combustion chamber 50 behind the wall 46. The one or more bushing fuel orifices 182 may include a plurality of circumferentially spaced fuel orifices arranged annularly around the burner bushing 40. Discharging fuel (such as second fuel F2) behind the wall 46 via one or more bushing fuel orifices 182 can reduce the residence time of fuel in the combustion chamber 50, which can reduce combustion time and NO. xEmissions. In some examples, at least 30% and less than or equal to 80% of the second fuel F2 supplied to the combustion chamber 50 via the fuel nozzle assembly 48 may be supplied via one or more bushing fuel orifices 182. The remainder of the total supply of the second fuel F2 supplied to the combustion chamber 50 via the fuel nozzle assembly 48 (e.g., 20%-70%) may be supplied via fuel orifice 150.

[0071] The fuel nozzle assembly 48 may also include one or more bushing air orifices 184 extending through the burner bushing 40. In a non-limiting example, each of the one or more bushing fuel orifices 182 may have a complementary bushing air orifice in the one or more bushing air orifices 184, such that there are the same number of one or more bushing fuel orifices 182 and one or more bushing air orifices 184. In some examples, the one or more bushing fuel orifices 182 may be disposed in or adjacent to the one or more bushing air orifices 184. When the one or more bushing fuel orifices 182 are disposed in the one or more bushing air orifices 184, each bushing air orifice in the one or more bushing air orifices 184 may be positioned in a circumferential arrangement around a corresponding bushing fuel orifice in the one or more bushing fuel orifices 182. One or more bushing air orifices 184, such as those for discharging air 70 into the combustion chamber 50 around a second fuel F2 discharged from one or more bushing fuel orifices 182, facilitate the movement of the second fuel F2 away from the burner bushing 40, which can limit the temperature at the burner bushing 40. One or more bushing swirlers 186 may be fluidly coupled to or disposed therein with one or more bushing air orifices 184 to apply a swirling or tangential component to the air 70. In a non-limiting example, the first fuel flow rate (such as the first fuel flow rate of the second fuel F2) to one or more bushing fuel orifices 182 at the outer liner 41 may differ from the second fuel flow rate (such as the second fuel F2) to one or more bushing fuel orifices 182 at the inner liner 42.

[0072] In some examples, the burner bushing 40 may include an axial portion 190 and a converging portion 192 rear of the axial portion 190. The converging portion 192 is configured such that the radial dimension of the combustion chamber 50 relative to the centerline 33 of the combustion zone decreases in the rearward direction. One or more bushing fuel orifices 182 may be provided at the axial portion 190, the converging portion 192, or both.

[0073] In some examples, the fuel nozzle assembly 48 may discharge fuel depending on engine operating conditions, such as first fuel F1 from the first fuel supply section 34 and second fuel F2 from the second fuel supply section 36. For example, during higher power operation, the fuel nozzle assembly 48 may discharge one or both of the first fuel F1 or the second fuel F2 through some or all of the fuel orifices 150, and discharge the second fuel F2 through one or more bushing fuel orifices 182. During lower power operation (such as during cruise), the fuel nozzle assembly 48 may not discharge the second fuel F2 through one or more bushing fuel orifices 182. In some cases, the fuel nozzle assembly 48 may supply fuel (e.g., to provide ignition) via fuel orifices 150 (such as one or more first inner wall fuel orifices 154) before discharging the second fuel F2 from one or more bushing fuel orifices 182, which may limit cold zones in the combustion chamber 50.

[0074] refer to Figure 10 and Figure 11 This shows that it can be used in burner 30 ( Figure 1 Fuel nozzle assembly 248 is used and connected to burner bushing 40, wall 46, or both. Fuel nozzle assembly 248 may include aspects similar to those of fuel nozzle assembly 48; therefore, similar portions will be described with similar figures increased by 200, and it should be understood that, unless otherwise stated, the description of similar portions of fuel nozzle assembly 48 may apply to fuel nozzle assembly 248. For example, fuel nozzle assembly 248 may include fuel nozzle body 249, which includes a central body 300, a first inner wall 302, a body wall 304 having an outer surface 306, an outer wall 308 connected to the outer surface 306, and a second inner wall 310. The central body 300 may be centered about the fuel nozzle assembly centerline 235 of fuel nozzle assembly 248. The first inner wall 302 may be radially spaced outward from the central body 300 to at least partially define a first internal fluid passage 320 that can supply air 70 to combustion chamber 50. The second inner wall 310 may be spaced radially outward from the first inner wall 302 to at least partially define a second internal fluid passage 322 for supplying air 70 to the combustion chamber 50. The body wall 304 may be spaced radially outward from the second inner wall 310 to at least partially define a third internal fluid passage 326 for supplying air 70 to the combustion chamber 50. The outer wall 308 may be spaced radially outward from the body wall 304 to at least partially define a first external fluid passage 324 for supplying air 70 to the combustion chamber 50. The outer surface of the second inner wall 310 may diverge from the fuel nozzle assembly centerline 235, and the inner surface of the second inner wall 310 may converge toward the fuel nozzle assembly centerline 235 and then diverge from the fuel nozzle assembly centerline 235.

[0075] The fuel nozzle assembly 248 can be fluidly connected to the first fuel supply unit 34 and the second fuel supply unit 36 ​​to supply first fuel F1 and second fuel F2 to the combustion chamber 50. A first swirler 340 can be disposed in the first inner fluid passage 320 to swirl the air 70 before it enters the combustion chamber 50. A second swirler 342 can be disposed in the second inner fluid passage 322 to swirl the air 70 before it enters the combustion chamber 50. A third swirler 344 can be disposed in the third inner fluid passage 326 to swirl the air 70 before it enters the combustion chamber 50. A fourth swirler 346 can be disposed in the first outer fluid passage 324 to swirl the air 70 before it enters the combustion chamber 50. The fuel nozzle assembly 248 may be configured to supply air 70 to the combustion chamber 50 via a first internal fluid passage 320, a second internal fluid passage 322, a first external fluid passage 324, a third internal fluid passage 326, or a combination thereof. This air 70 may include air 70 that moves through and is swirled by a first swirler 340, a second swirler 342, a third swirler 344, a fourth swirler 346, or a combination thereof. The first swirler 340, the second swirler 342, the third swirler 344, the fourth swirler 346, or a combination thereof may be configured as axial swirlers that apply swirl (e.g., a tangential velocity component) to the air 70 flowing in the second axial direction A2.

[0076] The fuel nozzle assembly 248 may include a plurality of fuel orifices 350 fluidly connected to one or both of the first fuel supply section 34 or the second fuel supply section 36. The plurality of fuel orifices 350 may include one or more central body fuel orifices 352 of the central body 300, one or more first inner wall fuel orifices 354 of the first inner wall 302, one or more body wall fuel orifices 356 of the body wall 304, one or more second inner wall fuel orifices 360 of the second inner wall 310, or combinations thereof. One or more central body fuel orifices 352 may be in front of some or all other fuel orifices 350 (e.g., closer than some or all other fuel orifices 350). Figure 1 (The front end of the gas turbine engine 10). One or more second inner wall fuel ports 360 may be disposed behind some or all other fuel ports 350 via the second inner wall 310 (e.g., closer than some or all other fuel ports 350). Figure 1(The rear end of the gas turbine engine 10). One or more first inner wall fuel ports 354 and one or more body wall fuel ports 356 can be axially offset and can be axially located between one or more central body fuel ports 352 and one or more second inner wall fuel ports 360. Axially offset fuel ports (such as fuel ports 350) can allow different mixing times between air 70 and fuel (such as first fuel F1 and second fuel F2), which can provide reduced emissions and increased flame stability. For example, fuel ports positioned further forward allow for increased mixing time, which can reduce NO. x Discharge, and fuel orifices set further back can reduce mixing time, which can increase flame stability.

[0077] In the first operating mode of the fuel nozzle assembly 248, such as Figure 10As generally shown, the fuel nozzle assembly 248 can discharge first fuel F1, second fuel F2, or both through one or more central body fuel orifices 352, discharge second fuel F2 through one or more first inner wall fuel orifices 354, discharge second fuel F2 through one or more body wall fuel orifices 356, discharge second fuel F2 through one or more second inner wall fuel orifices 360, or a combination thereof. Discharging second fuel F2 through one or more first inner wall fuel orifices 354 can include rearward and radially outward discharge of second fuel F2. For example, at least a portion of the fuel passage 355 of the first inner wall 302 can be radially outward at an angle away from the fuel nozzle assembly centerline 235 to allow angled discharge of first fuel F1, second fuel F2, or both. Discharging second fuel F2 through one or more body wall fuel orifices 356 can include rearward and radially outward discharge of second fuel F2, rearward and radially inward discharge of second fuel F2, or both. For example, at least one of one or more body wall fuel orifices 356 (e.g., a first fuel orifice) may be located on the outer surface 306 of the body wall 304, and at least a portion of the body wall fuel passage 357 of the body wall 304 may be radially outward, directly radially outward, or angled between directly radially outward and directly axially rearward away from the fuel nozzle assembly centerline 235, thereby allowing angled discharge of the first fuel F1, the second fuel F2, or both. Additionally or alternatively, at least one of one or more body wall fuel orifices 356 (e.g., a second fuel orifice) may be formed on the inner surface 307 of the body wall 304 and may be angled between directly radially outward and directly axially rearward. Discharging the second fuel F2 through one or more second inner wall fuel orifices 360 may include directly rearward discharge of the second fuel F2. For example, at least a portion of the fuel passage 357 in the body wall may be radially inward, directly radially inward, or angled between the centerline 235 of the fuel nozzle assembly, thereby allowing angled discharge of the first fuel F1, the second fuel F2, or both.

[0078] In the second operating mode of the fuel nozzle assembly 248, such as Figure 11As generally illustrated, the fuel nozzle assembly 248 may discharge second fuel F2 through one or more first inner wall fuel orifices 354, through one or more body wall fuel orifices 356, through one or more second inner wall fuel orifices 360, or a combination thereof. Discharging second fuel F2 through one or more first inner wall fuel orifices 354 may include discharging second fuel F2 rearward and radially outward (e.g., between directly radially outward and directly axially rearward). Additionally or alternatively, discharging second fuel F2 through one or more first inner wall fuel orifices 354 may include discharging second fuel F2 rearward and radially inward (e.g., between directly radially inward and directly axially rearward). Discharging second fuel F2 through one or more body wall fuel orifices 356 may include discharging at least some of the second fuel F2 rearward and radially outward, at least some of the second fuel F2 rearward and radially inward, or both. For example, at least one of one or more body wall fuel orifices 356 may be located on the outer surface 306 of the body wall 304 and angled directly radially outward or at an angle between directly radially outward and directly axially rearward. Additionally or alternatively, at least one of one or more body wall fuel orifices 356 may be formed on the inner surface 307 of the body wall 304 and may be angled between directly radially outward and directly axially rearward. Discharging the second fuel F2 through one or more second inner wall fuel orifices 360 may include discharging the second fuel F2 directly rearward. In a second operating mode, the fuel nozzle assembly 248 may discharge fuel without passing through the central body 300.

[0079] refer to Figure 12-14 This shows that it can be used in burner 30 ( Figure 1 Fuel nozzle assembly 448 is used and coupled to burner bushing 40, wall 46, or both. Fuel nozzle assembly 448 may include components that are connected to the burner bushing 40, wall 46, or both. Figure 3-9 ), 248 Figure 10 and Figure 11 The similar aspects; therefore, the similar parts will be used relative to Figure 10-11Further using similar figures like 200 to describe the components, it should be understood that, unless otherwise stated, the description of similar portions of fuel nozzle assemblies 48, 248 can be applied to fuel nozzle assembly 448. For example, fuel nozzle assembly 448 may include fuel nozzle body 449, which includes a central body 500, a first inner wall 502, a body wall 504 having an outer surface 506, an outer wall 508 coupled to the outer surface 506, and a second inner wall 510. The central body 500 may be centered on a centerline 435 of the fuel nozzle assembly 448. The first inner wall 502 may be radially spaced from the central body 500 to at least partially define a first internal fluid passage 520. The second inner wall 510 may be radially spaced from the outer side of the first inner wall 502 to at least partially define a second internal fluid passage 522. The body wall 504 may be radially spaced from the outer side of the second inner wall 510 to at least partially define a third internal fluid passage 526. The outer wall 508 may be spaced radially outward from the body wall 504 to at least partially define the first external fluid passage 524. The fuel nozzle assembly 448 may be fluidly connected to the first fuel supply section 34 and the second fuel supply section 36 to supply first fuel F1 and second fuel F2 to the combustion chamber 50. A first swirler 540 may be disposed in the first internal fluid passage 520. A second swirler 542 may be disposed in the second internal fluid passage 522. A third swirler 544 may be disposed in the third internal fluid passage 526. A fourth swirler 546 may be disposed in the first external fluid passage 524. The fuel nozzle assembly 448 may be configured to supply air 70 to the combustion chamber 50 via a first internal fluid passage 520, a second internal fluid passage 522, a first external fluid passage 524, a third internal fluid passage 526, or a combination thereof. This air 70 may include air 70 moving through and swirled by a first swirler 540, a second swirler 542, a third swirler 544, a fourth swirler 546, or a combination thereof. The first swirler 540, the second swirler 542, the third swirler 544, the fourth swirler 546, or a combination thereof may be configured as axial swirlers that apply swirl (e.g., a tangential velocity component) to the air 70 flowing in the second axial direction A2.

[0080] The fuel nozzle assembly 448 may include a plurality of fuel orifices 550 fluidly connected to one or both of the first fuel supply section 34 or the second fuel supply section 36. The plurality of fuel orifices 550 may include one or more central body fuel orifices 552 of the central body 500, one or more first inner wall fuel orifices 554 of the first inner wall 502, one or more body wall fuel orifices 556 of the body wall 504, or combinations thereof. One or more central body fuel orifices 552 may be in front of some or all other fuel orifices 550 (e.g., closer than some or all other fuel orifices 550). Figure 1(The front end of the gas turbine engine 10). One or more first inner wall fuel orifices 554 may be axially located between one or more central body fuel orifices 552 and one or more body wall fuel orifices 556. Axially offset fuel orifices (such as fuel orifice 550) can allow different mixing times between air 70 and fuel (such as first fuel F1 and second fuel F2), which can provide reduced emissions and increased flame stability. For example, fuel orifices positioned further forward allow for increased mixing time, which can reduce NO. x Discharge, and fuel orifices set further back can reduce mixing time, which can increase flame stability.

[0081] In some examples, the second inner wall 510 may include a rearwardly opening recess 570. The recess 570 may be located at the rear edge of the second inner wall 510 and may be bent to facilitate the circulation of air 70 within the recess 570 to cool the rear edge of the second inner wall 510. The second inner wall 510 may include a first air orifice 572 and a second air orifice 574, such as replacing a fuel orifice on the second inner wall (e.g., ...). Figure 10 One or more second inner wall fuel ports 360). A first air port 572 can discharge air into the combustion chamber 50. A second air port 574 can discharge air into a recess 570, which may be partially or completely located in the combustion chamber 50.

[0082] In the first operating mode of the fuel nozzle assembly 448, such as Figure 12As generally shown, the fuel nozzle assembly 448 can discharge first fuel F1, second fuel F2, or both through one or more central body fuel orifices 552, discharge second fuel F2 through one or more first inner wall fuel orifices 554, discharge second fuel F2 through one or more body wall fuel orifices 556, discharge air 70 through first air orifices 572 and second air orifices 574, or a combination thereof. Discharging second fuel F2 through one or more first inner wall fuel orifices 554 can include rearward and radially outward discharge of second fuel F2. For example, at least a portion of the fuel passage 555 of the first inner wall 502 can be radially outward at an angle away from the fuel nozzle assembly centerline 435 to allow angled discharge of first fuel F1, second fuel F2, or both. Discharging second fuel F2 through one or more body wall fuel orifices 556 can include rearward and radially outward discharge of second fuel F2, rearward and radially inward discharge of second fuel F2, or both. For example, at least a portion of the fuel passage 557 of the body wall 504 may be radially outward at an angle away from the fuel nozzle assembly centerline 435, at least a portion of the fuel passage 557 may be radially inward at an angle toward the fuel nozzle assembly centerline 435, or a combination thereof, to allow angled discharge of the first fuel F1, the second fuel F2, or both.

[0083] Discharging air 70 through the first air orifice 572 may include radially outward and rearward air discharge. For example, at least a portion of the air passage 573 of the second inner wall 510 may be radially outward at an angle away from the fuel nozzle assembly centerline 435 to allow angled discharge of air 70. Discharging air 70 through the second air orifice 574 may include discharging air 70 into the recess 570. The recess 570, the first air orifice 572, the second air orifice 574, or a combination thereof may be located behind some or all of the fuel orifices 550 (e.g., closer than some or all of the fuel orifices 550). Figure 1 (The rear end of the gas turbine engine 10).

[0084] In the second operating mode of the fuel nozzle assembly 448, such as Figure 13 and Figure 14 As generally shown, the fuel nozzle assembly 448 can discharge second fuel F2 from one or more first inner wall fuel orifices 554, discharge second fuel F2 through one or more body wall fuel orifices 556, discharge air 70 through first air orifices 572 and second air orifices 574, or a combination thereof. Discharging second fuel F2 through one or more first inner wall fuel orifices 554 can include radially outward and rearward discharge of second fuel F2. Figure 13 ), or may include radially inward and rearward emission of the second fuel F2 and radially outward and rearward emission of the second fuel F2 ( Figure 14 ).

[0085] refer to Figure 15-17 This shows that it can be used in burner 30 ( Figure 1 Fuel nozzle assembly 648 is used and coupled to burner bushing 40, wall 46, or both. Fuel nozzle assembly 648 may include components that are connected to fuel nozzle assembly 48 (…). Figure 3-9 ), 248 Figure 10-11 ), 448 Figure 12-14 The similar aspects; therefore, the similar parts will be used relative to Figure 12-14 Further using similar figures like 200, it should be understood that, unless otherwise stated, the description of similar portions of fuel nozzle assemblies 48, 248, 448 can be applied to fuel nozzle assembly 648. For example, fuel nozzle assembly 648 may include fuel nozzle body 649, which includes a central body 700, a first inner wall 702, a body wall 704 having an outer surface 706, an outer wall 708 coupled to the outer surface 706, a second inner wall 710, and a third inner wall 712. The central body 700 may be centered on a fuel nozzle assembly centerline 635 of the fuel nozzle assembly 648. The first inner wall 702 may be radially spaced outward from the central body 700 to at least partially define a first internal fluid passage 720. The third inner wall 712 may be radially spaced outward from the first inner wall 702 to at least partially define a second internal fluid passage 722. The second inner wall 710 may be radially spaced outward from the third inner wall 712 to at least partially define a third internal fluid passage 726. The body wall 704 may be spaced radially outward from the second inner wall 710 to at least partially define the fourth inner fluid passage 728. The outer wall 708 may be spaced radially outward from the body wall 704 to at least partially define the first outer fluid passage 724. The fuel nozzle assembly 648 may be fluidly coupled to the first fuel supply section 34 and the second fuel supply section 36 to supply the combustion chamber 50 with the first fuel F1 and the second fuel F2. The outer surface of the second inner wall 710 may diverge from the centerline 635 of the fuel nozzle assembly, and the inner surface of the second inner wall 710 may converge toward the centerline 635 of the fuel nozzle assembly and then diverge from the centerline 635 of the fuel nozzle assembly. The diverging inner surface of the second inner wall 710 may facilitate radially outward flow of air to mix with fuel (such as the second fuel F2) discharged from the fuel orifice 756 of the body wall.

[0086] A first swirler 740 may be disposed in a first internal fluid passage 720. A second swirler 742 may be disposed in a second internal fluid passage 722. A third swirler 744 may be disposed in a third internal fluid passage 726. A fourth swirler 746 may be disposed in a fourth internal fluid passage 728. A fifth swirler 748 may be disposed in a first external fluid passage 724. The fuel nozzle assembly 648 may be configured to supply air 70 to the combustion chamber 50 through the first internal fluid passage 720, the second internal fluid passage 722, the first external fluid passage 724, the third internal fluid passage 726, the fourth internal fluid passage 728, or a combination thereof, the air 70 comprising air 70 moving through the first swirler 740, the second swirler 742, the third swirler 744, the fourth swirler 746, the fifth swirler 748, or a combination thereof. The first swirler 740, the second swirler 742, the third swirler 744, the fourth swirler 746, the fifth swirler 748, or combinations thereof, can be configured as axial swirlers that apply swirling (e.g., tangential velocity components) to air 70 flowing in the second axial direction A2.

[0087] The fuel nozzle assembly 648 may include a plurality of fuel orifices 750 fluidly connected to one or both of the first fuel supply section 34 or the second fuel supply section 36. The plurality of fuel orifices 750 may include one or more central body fuel orifices 752 of the central body 700, one or more first inner wall fuel orifices 754 of the first inner wall 702, one or more body wall fuel orifices 756 of the body wall 704, or combinations thereof. One or more central body fuel orifices 752 may be in front of some or all other fuel orifices 750 (e.g., closer to some or all other fuel orifices 750). Figure 1 (The front end of the gas turbine engine 10). One or more first inner wall fuel orifices 754 may be axially located between one or more central body fuel orifices 752 and one or more body wall fuel orifices 756. Axially offset fuel orifices (such as fuel orifice 750) can allow different mixing times between air 70 and fuel (such as first fuel F1 and second fuel F2), which can provide reduced emissions and increased flame stability. For example, fuel orifices positioned further forward allow for increased mixing time, which can reduce NO. x Discharge, and fuel orifices set further back can reduce mixing time, which can increase flame stability.

[0088] In the first operating mode of the fuel nozzle assembly 648, such as Figure 15As generally shown, the fuel nozzle assembly 648 can discharge first fuel F1, second fuel F2, or both through one or more central body fuel orifices 752, discharge second fuel F2 through one or more first inner wall fuel orifices 754, discharge second fuel F2 through one or more body wall fuel orifices 756, or a combination thereof. Discharging second fuel F2 through one or more first inner wall fuel orifices 754 can include rearward and radially outward discharge of second fuel F2. For example, at least a portion of the fuel passage 755 of the first inner wall 702 can be radially outward at an angle away from the fuel nozzle assembly centerline 635 to allow angled discharge of first fuel F1, second fuel F2, or both. Discharging second fuel F2 through one or more body wall fuel orifices 756 can include rearward and radially outward discharge of second fuel F2, rearward and radially inward discharge of second fuel F2, or both. For example, at least a portion of the fuel passage 757 of the body wall 704 may be radially outward at an angle away from the fuel nozzle assembly centerline 635, at least a portion of the fuel passage 757 of the body wall 704 may be radially inward at an angle toward the fuel nozzle assembly centerline 635, or a combination thereof, to allow angled discharge of the first fuel F1, the second fuel F2, or both.

[0089] In the second operating mode of the fuel nozzle assembly 648, such as Figure 16 and Figure 17 As generally shown, the fuel nozzle assembly 648 can discharge second fuel F2 from one or more first inner wall fuel orifices 754, discharge second fuel F2 through one or more body wall fuel orifices 756, or a combination thereof (e.g., not discharging fuel through one or more central body fuel orifices 752). Discharging second fuel F2 through one or more first inner wall fuel orifices 754 can include radially inward and rearward discharge of second fuel F2. Figure 16 ), or may include radially inward and rearward emission of the second fuel F2 and radially outward and rearward emission of the second fuel F2 ( Figure 17 ).

[0090] refer to Figure 18 This illustrates a method 1000 for operating a gas turbine engine. Method 1000 can be used with, for example,... Figure 1-17 The gas turbine engine 10 and its components are generally shown in the diagram. Method 1000 may include supplying a first fuel F1 (box 1002) to fuel nozzle assemblies 48, 248, 448, 648, such as from a first fuel supply unit 34. Additionally or alternatively, method 1000 may include supplying a second fuel F2 (box 1004) to fuel nozzle assemblies 48, 248, 448, 648, such as from a second fuel supply unit 36.

[0091] Method 1000 may include discharging fuel (such as first fuel F1, second fuel F2, or both) from fuel nozzle assemblies 48, 248, 448, 648 into combustion chamber 50 (box 1006), such as via one or more fuel orifices 150, 350, 550, 750. Discharging the first fuel F1 (e.g., liquid fuel) into combustion chamber 50 may include discharging the first fuel F1 from central body fuel orifices 152, 352, 552, 752 in a second axial direction A2 of fuel nozzle assemblies 48, 248, 448, 648. Additionally or alternatively, discharging a second fuel F2 (e.g., hydrogen) into the combustion chamber 50 may include radially outward discharge of the second fuel F2 from the outer surfaces of the fuel nozzle assemblies 48, 248, 448, 648 (such as from a first body wall fuel orifice 156, 356, 556, 756 located at one or more body wall fuel orifices 106, 306, 506, 706 on the outer surfaces 106, 306, 506, 706 of the body walls 304, 504, 704). Radially outward discharge of the second fuel F2 may include direct radial outward discharge or radial outward and rearward discharge of the second fuel F2. Discharging the second fuel F2 into the combustion chamber 50 may additionally or alternatively include discharging the second fuel F2 from a second body wall fuel orifice 156, 356, 556, 756 located at one or more body wall fuel orifices 156, 356, 556, 756 on the inner surfaces 307, 507, 707 of the body walls 304, 504, 704. Discharging the second fuel F2 into the combustion chamber 50 may additionally or alternatively include radially outward discharge of the second fuel F2 from one or more of the first inner wall fuel orifices 154, 354, 554, 754 of the first inner walls 102, 302, 502, 702. Discharging fuel into the combustion chamber 50 may additionally or alternatively include discharging the first fuel F1 and the second fuel F2 into the combustion chamber 50 from one or more central body fuel orifices 152, 352, 552, 752.

[0092] In some examples, discharging fuel into combustion chamber 50 (box 1006) may include operating fuel nozzle assemblies 48, 248, 448, 648 in a first mode, a second mode, a third mode, or a combination thereof.

[0093] Operation in a first mode (e.g., dual-fuel mode) may include the fuel nozzle assembly 48 discharging a first fuel F1 and a second fuel F2 (e.g., simultaneously) into the combustion chamber 50. This may include discharging at least one of the first fuel F1 or the second fuel F2 radially outward from the outer surfaces (e.g., from outer surfaces 106, 306, 506, 706) of the fuel nozzle assemblies 48, 248, 448, 648. For example, the fuel nozzle assemblies 48, 248, 448, 648 may discharge the first fuel F1 via one or more fuel orifices 150, 350, 550, 750, and the second fuel F2 may be discharged through one or more bushing fuel orifices 182.

[0094] Operating in the second mode (e.g., gaseous fuel mode) may include fuel nozzle assemblies 48, 248, 448, 648 discharging a second fuel F2 (e.g., gaseous hydrogen fuel) into the combustion chamber 50, such as radially inward from the first inner walls 102, 302, 502, 702, axially from the outer walls 108, 308, 508, 708, or both. The second operating mode may also include fuel nozzle assemblies 48, 248, 448, 648 not discharging the first fuel F1 into the combustion chamber 50. Operating in the second mode may allow for reduced or zero carbon emissions.

[0095] Operation in the third mode (e.g., liquid fuel mode) may include fuel nozzle assemblies 48, 248, 448, 648 discharging a first fuel F1 (e.g., liquid fuel) radially outward into the combustion chamber 50, such as from one or more body wall fuel orifices 156, 356, 556, 756, which may crossflow with air 70 from the mixer 130. Additionally or alternatively, operation in the third mode may include fuel nozzle assemblies 48, 248, 448, 648 discharging the first fuel F1 radially outward (e.g., directly radial outward or radial outward and rearward) from the central bodies 100, 300, 500, 700 (e.g., toward the first inner walls 102, 302, 502, 702). The third operating mode may include fuel nozzle assemblies 48, 248, 448, 648 not discharging a second fuel F2 into the combustion chamber 50.

[0096] Method 1000 may include identifying changes in operating parameters of the gas turbine engine 10 or a vehicle (e.g., an aircraft) coupled thereto (box 1008). These changes may be identified via controller 60, one or more sensors communicating with controller 60, or a combination thereof. Operating parameters may include thrust demand, the amount of available first fuel F1, the amount of available second fuel F2, or one or more other parameters. In response to identifying changes in operating parameters, method 1000 may include utilizing different combinations of fuel orifices 150, 350, 550, 750, and using different amounts of first fuel F1 and second fuel F2, or combinations thereof (box 1010). For example, if the controller 60 determines that the amount of first fuel F1 (e.g., as main fuel) discharged through one or more body wall fuel orifices 156, 356, 556, 756 is insufficient, the controller 60 may control one or more of the first fuel supply unit 34, the second fuel supply unit 36, or the fuel nozzle assembly 48, 248, 448, 648 to supply first fuel F1 (e.g., as ignition fuel) only to one or more central body fuel orifices 152, 352, 552, 752, one or more first inner wall fuel orifices 154, 354, 554, 754, or combinations thereof, without supplying first fuel F1 to one or more body wall fuel orifices 156, 356, 556, 756. Additionally or alternatively, the controller 60 may control one or more of the second fuel supply unit 36 ​​or fuel nozzle assemblies 48, 248, 448, 648 to supply second fuel F2 (e.g., as main fuel) to one or more body wall fuel orifices 156, 356, 556, 756.

[0097] Burner 30 ( Figure 2 It may include various combinations of adjacent fuel nozzle assemblies 48, 248, 448, and 648. For example, burner 30 ( Figure 2 ) can include Figure 3-17 A combination of fuel nozzle assemblies, and may include having Figure 3-17 The fuel nozzle assemblies shown are combinations of aspects of a fuel nozzle assembly. The disclosed fuel nozzle assemblies are not mutually exclusive.

[0098] The fluid passages of the fuel nozzle assemblies 48, 248, 448, 648 (such as first internal fluid passages 120, 320, 520, 720, second internal fluid passages 122, 322, 522, 722, first external fluid passages 124, 324, 524, 724, third internal fluid passages 326, 526, 726, and fourth internal fluid passage 728) can be configured as separate tubes (e.g., annular tubes) formed in the channels (e.g., annular channels) or combinations thereof in the fuel nozzle bodies 49, 249, 449, 649 of the fuel nozzle assemblies 48, 248, 448, 648.

[0099] For some examples, fuel nozzle assemblies 48, 248, 448, and 648 can operate without the use of inert gases such as steam.

[0100] Although a turbine engine has been described, it should be understood that the combustor described herein can be used in any engine having a combustor. It should also be understood that the application of the disclosed aspects discussed herein also applies to engines having a propeller section or a fan and supercharger section, as well as turbojet engines and turbocharged engines.

[0101] Within the scope not described herein, different features and structures of various embodiments may be combined or substituted for each other as needed. The fact that a feature is not shown in all embodiments does not mean that it cannot be shown so, but rather that it is done for the sake of brevity. Therefore, various features of different embodiments may be mixed and matched as needed to form new embodiments, regardless of whether the new embodiments are explicitly described. All combinations or permutations of the features described herein are covered by this disclosure.

[0102] This written description uses examples to illustrate aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice aspects of this disclosure, including making and using any apparatus or system and methods of making any combinations. The patentable scope of aspects of this disclosure is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0103] Further details are provided by the following topics:

[0104] A gas turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in a tandem flow configuration, wherein the combustion section includes: a combustor bushing that at least partially defines a combustion chamber; and a fuel nozzle assembly including: a liquid fuel supply section that supplies liquid fuel; a hydrogen fuel supply section that supplies gaseous hydrogen fuel; and a fuel nozzle body that defines a centerline of the fuel nozzle assembly, the fuel nozzle body being fluidly coupled to the liquid fuel supply section and the hydrogen fuel supply section to supply the liquid fuel and the gaseous hydrogen fuel to the combustion chamber; wherein the fuel nozzle body includes a body wall including an outer surface having a first fuel orifice for radially outward discharge of the gaseous hydrogen fuel, and an inner surface having a second fuel orifice for radially inward discharge of at least one of the gaseous hydrogen fuel or the liquid fuel.

[0105] According to any of the preceding clauses, in a gas turbine engine, the fuel nozzle assembly includes an outer wall radially outward of the body wall, and the first fuel orifice is angled radially outward and rearward to discharge the gaseous hydrogen fuel toward the outer wall, into the combustion chamber, or both.

[0106] According to any of the preceding clauses, in a gas turbine engine, the second fuel orifice is radially inward and rearward at an angle to discharge at least one of the gaseous hydrogen fuel or the liquid fuel into the combustion chamber.

[0107] In any of the preceding clauses of the gas turbine engine, the first fuel orifice is located at the trailing edge of the body wall.

[0108] In a gas turbine engine according to any of the foregoing clauses, the fuel nozzle assembly includes an outer wall coupled to and radially spaced outward from the outer surface of the body wall, such that an external fluid passage is at least partially defined between the outer surface of the body wall and the outer wall.

[0109] According to any of the preceding clauses, in a gas turbine engine, the first fuel orifice is configured to discharge at least one of the liquid fuel or the gaseous hydrogen fuel into or from the air in the external fluid passage.

[0110] According to any of the preceding clauses, the gas turbine engine, wherein the fuel nozzle body comprises: a central body, a first inner wall radially outward of the central body, and a second inner wall radially outward of the first inner wall.

[0111] According to any of the preceding clauses of the gas turbine engine, wherein the first inner wall is radially outside the central body such that a first internal fluid passage is at least partially defined between the central body and the first inner wall; and wherein the second inner wall is radially outside the first inner wall such that a second internal fluid passage is at least partially defined between the first inner wall and the second inner wall, and a third internal fluid passage is at least partially defined between the second inner wall and the body wall.

[0112] The gas turbine engine according to any of the foregoing clauses, wherein the fuel nozzle assembly includes a first swirler disposed in the first internal fluid passage, a second swirler disposed in the second internal fluid passage, and a third swirler disposed in the third internal fluid passage.

[0113] The gas turbine engine according to any of the foregoing clauses, wherein the central body includes a central body fuel orifice fluidly connected to the liquid fuel supply and the hydrogen fuel supply.

[0114] According to any of the foregoing clauses, the gas turbine engine wherein the first inner wall includes a first inner wall fuel orifice that is fluidly connected to the hydrogen fuel supply section.

[0115] The gas turbine engine according to any of the foregoing clauses, wherein the second inner wall includes a second inner wall fuel orifice that is fluidly connected to the hydrogen fuel supply section.

[0116] In any of the preceding clauses of the gas turbine engine, the first fuel orifice is located behind the fuel orifice of the central body.

[0117] In any of the preceding clauses of the gas turbine engine, the first inner wall fuel orifice is located behind the central body fuel orifice and in front of the first fuel orifice.

[0118] According to any of the foregoing clauses, in a gas turbine engine, the first inner wall fuel orifice of the first inner wall is angled radially outward and rearward relative to the centerline of the fuel nozzle assembly.

[0119] According to any of the preceding clauses, the gas turbine engine includes a fuel nozzle body comprising a third inner wall spaced radially outward from the first inner wall and radially inward from the second inner wall, and the fuel nozzle assembly comprising an outer wall radially outward from the body wall; wherein the central body and the first inner wall at least partially define a first internal fluid passage, the first inner wall and the third inner wall at least partially define a second internal fluid passage, the third inner wall and the second inner wall at least partially define a third internal fluid passage, the second inner wall and the body wall at least partially define a fourth internal fluid passage, and the body wall and the outer wall at least partially define a first external fluid passage; and wherein a first vortex is disposed in the first internal fluid passage, a second vortex is disposed in the second internal fluid passage, a third vortex is disposed in the third internal fluid passage, a fourth vortex is disposed in the fourth internal fluid passage, and a fifth vortex is disposed in the first external fluid passage.

[0120] According to any of the preceding clauses, in a gas turbine engine, the outer wall extends axially rearward such that the trailing edge of the outer wall and the trailing edge of the mixer wall of the mixer are axially aligned with respect to the centerline of the fuel nozzle assembly.

[0121] According to any of the foregoing clauses, the gas turbine engine, wherein the fuel nozzle assembly includes a first fluid conduit fluidly connected to or included together with the first fuel supply unit, and a second fluid conduit fluidly connected to or included together with the second fuel supply unit.

[0122] In any of the foregoing clauses, the gas turbine engine wherein the first fuel conduit and the second fuel conduit are separate.

[0123] In any of the foregoing clauses, the gas turbine engine is wherein at least some portions of the first fuel conduit and the second fuel conduit are concentrically arranged.

[0124] According to any of the preceding clauses, in a gas turbine engine, at least a portion of the first fuel conduit extends through the second fuel conduit to allow the second fuel to flow around the first fuel flowing through the first fuel conduit.

[0125] A method of operating a gas turbine engine, the gas turbine engine including a compressor section, a combustion section and a turbine section arranged in a series flow configuration, wherein the combustion section includes a combustor bushing that at least partially defines a combustion chamber and a gaseous fuel nozzle assembly fluidly connected to the combustion chamber, the method comprising: radially discharging gaseous hydrogen fuel from a first fuel orifice on an outer surface of the gaseous fuel nozzle assembly; and discharging liquid fuel from a central body fuel orifice of the gaseous fuel nozzle assembly in an axial direction.

[0126] The method according to any of the foregoing clauses further includes discharging the gaseous hydrogen fuel from a second fuel orifice formed on the inner surface of the body wall of the gaseous fuel nozzle assembly, the body wall including the outer surface.

[0127] The method according to any of the foregoing clauses further includes radially outward discharge of the gaseous hydrogen fuel from a fuel orifice in the first inner wall of the first inner wall of the gaseous fuel nozzle assembly.

[0128] The method according to any of the foregoing clauses further includes discharging the gaseous hydrogen fuel from the central body fuel orifice after discharging the liquid fuel from the central body fuel orifice.

[0129] A fuel nozzle assembly for a gas turbine engine, the fuel nozzle assembly comprising: a liquid fuel supply section supplying liquid fuel; a hydrogen fuel supply section supplying gaseous hydrogen fuel; and a fuel nozzle body defining a centerline of the fuel nozzle assembly, the fuel nozzle body being fluidly connected to the liquid fuel supply section and the hydrogen fuel supply section to supply the liquid fuel and the gaseous hydrogen fuel to a combustion chamber; wherein the fuel nozzle body includes a body wall, the body wall including an outer surface having a first fuel orifice for radially outward discharge of the gaseous hydrogen fuel, and an inner surface including an inner surface having a second fuel orifice for radially inward discharge of at least one of the gaseous hydrogen fuel or the liquid fuel.

[0130] The fuel nozzle assembly according to any of the foregoing clauses further includes an outer wall radially outward of the body wall, and the first fuel orifice is radially outward and rearward at an angle to discharge the gaseous hydrogen fuel toward the outer wall, into the combustion chamber, or both.

[0131] According to any of the preceding clauses, the fuel nozzle assembly wherein the second fuel orifice is radially inward and rearward at an angle to discharge at least one of the gaseous hydrogen fuel or the liquid fuel into the combustion chamber.

[0132] According to any of the foregoing clauses, the fuel nozzle assembly wherein the first fuel orifice is disposed at the rear edge of the body wall.

[0133] A fuel nozzle assembly according to any of the foregoing clauses, wherein the fuel nozzle assembly includes an outer wall coupled to and radially spaced outward from the outer surface of the body wall, such that an external fluid passage is at least partially defined between the outer surface of the body wall and the outer wall.

[0134] According to any of the preceding clauses, the fuel nozzle assembly wherein the first fuel orifice is configured to discharge at least one of the liquid fuel or the gaseous hydrogen fuel into or from the air in the external fluid passage.

[0135] The fuel nozzle assembly according to any of the foregoing clauses, wherein the fuel nozzle body comprises: a central body, a first inner wall radially outward of the central body, and a second inner wall radially outward of the first inner wall.

[0136] According to any of the preceding clauses, the first inner wall is radially outside the central body such that a first internal fluid passage is at least partially defined between the central body and the first inner wall; and wherein the second inner wall is radially outside the first inner wall such that a second internal fluid passage is at least partially defined between the first inner wall and the second inner wall, and a third internal fluid passage is at least partially defined between the second inner wall and the body wall.

[0137] The fuel nozzle assembly according to any of the foregoing clauses further includes a first swirler disposed in the first internal fluid passage, a second swirler disposed in the second internal fluid passage, and a third swirler disposed in the third internal fluid passage.

[0138] The fuel nozzle assembly according to any of the foregoing clauses, wherein the central body includes a central body fuel orifice fluidly connected to the liquid fuel supply section and the hydrogen fuel supply section.

[0139] According to any of the foregoing clauses, the fuel nozzle assembly wherein the first inner wall includes a first inner wall fuel orifice that is fluidly connected to the hydrogen fuel supply section.

[0140] According to any of the foregoing clauses, the fuel nozzle assembly wherein the second inner wall includes a second inner wall fuel orifice that is fluidly connected to the hydrogen fuel supply section.

[0141] According to any of the foregoing clauses, the fuel nozzle assembly wherein the first fuel orifice is located behind the fuel orifice of the central body.

[0142] According to any of the foregoing clauses, the outer surface of the second inner wall radiates from the centerline of the fuel nozzle assembly.

[0143] According to any of the foregoing clauses, the fuel nozzle assembly wherein the second inner wall includes a rearwardly opening recess.

[0144] According to any of the foregoing clauses, the fuel nozzle assembly wherein the recess is curved to facilitate air circulation within the recess.

[0145] According to any of the foregoing clauses, the inner surface of the second inner wall converges toward the centerline of the fuel nozzle assembly and then diverges from the centerline of the fuel nozzle assembly.

[0146] According to any of the foregoing clauses, the inner surface of the second inner wall radiates from the centerline of the fuel nozzle assembly to promote radial outward flow of air, thereby mixing with fuel discharged from the fuel orifice of the body wall.

[0147] According to any of the foregoing clauses, the first inner wall fuel orifice is located behind the central body fuel orifice and in front of the first fuel orifice.

[0148] According to any of the foregoing clauses, the first inner wall fuel orifice of the first inner wall is angled radially outward and rearward relative to the centerline of the fuel nozzle assembly.

[0149] A gas turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in a series flow configuration, wherein the combustion section includes: a combustor bushing that at least partially defines a combustion chamber; and a fuel nozzle assembly including: a liquid fuel supply section that supplies liquid fuel; a hydrogen fuel supply section that supplies gaseous hydrogen fuel; and a fuel nozzle body fluidly connected to the liquid fuel supply section and the hydrogen fuel supply section to supply the liquid fuel and the gaseous hydrogen fuel to the combustion chamber; wherein the fuel nozzle body includes an outer surface having a fuel orifice fluidly connected to the liquid fuel supply section and the hydrogen fuel supply section to discharge at least one of the liquid fuel or the gaseous hydrogen fuel radially outward relative to a centerline of the fuel nozzle assembly.

[0150] In any of the preceding clauses of the gas turbine engine, the fuel orifice is arranged parallel to a radial direction relative to the centerline of the fuel nozzle assembly.

[0151] According to any of the preceding clauses, the gas turbine engine, wherein the fuel nozzle body comprises: a central body, a first inner wall radially outside the central body such that a first internal fluid passage is at least partially defined between the central body and the first inner wall, and a body wall radially outside the first inner wall such that a second internal fluid passage is at least partially defined between the first inner wall and the body wall, the body wall including the outer surface.

[0152] In a gas turbine engine according to any of the foregoing clauses, the fuel nozzle assembly includes an outer wall coupled to and radially spaced outward from the outer surface of the body wall to define an external fluid passage.

[0153] According to any of the preceding clauses, the gas turbine engine includes a plurality of outer wall fuel ports arranged in an annular configuration, wherein the outer wall fuel ports located on the circumferential side of the outer wall relative to the centerline of the combustor have a relatively large diameter, and the outer wall fuel ports located on the radially inner and radially outer portions of the outer wall relative to the centerline of the combustion section have relatively small diameters.

[0154] According to any of the foregoing clauses, in a gas turbine engine, the plurality of outer wall fuel orifices are arranged in an alternating pattern, wherein at least some of the plurality of outer wall fuel orifices are fluidly connected to the liquid fuel supply, and adjacent outer wall fuel orifices of the plurality of outer wall fuel orifices are fluidly connected to the hydrogen fuel supply.

[0155] In any of the preceding clauses, the gas turbine engine wherein the fuel orifice is located at or downstream of the outlet of the external fluid passage.

[0156] In a gas turbine engine according to any of the foregoing clauses, the fuel nozzle assembly includes a mixer coupled to the outer wall.

[0157] The gas turbine engine according to any of the foregoing clauses, wherein the mixer includes a radial vortex.

[0158] The gas turbine engine according to any of the foregoing clauses, wherein the fuel nozzle assembly includes a first axial vortex in the first internal fluid passage and a second axial vortex in the second internal fluid passage.

[0159] The gas turbine engine according to any of the foregoing clauses, wherein the fuel nozzle assembly includes a third axial vortex in the external fluid passage.

[0160] In any of the preceding clauses, the gas turbine engine includes a mixer wall extending in the axial direction of the fuel nozzle assembly; and the fuel orifice points toward the mixer wall.

[0161] In any of the preceding clauses of the gas turbine engine, the fuel nozzle assembly includes a bushing fuel conduit that is fluidly connected to a bushing fuel orifice of the burner bushing.

[0162] According to any of the preceding clauses, in a gas turbine engine, the burner bushing further includes a bushing air port, and the bushing fuel port is adjacent to or disposed in the bushing air port.

[0163] The gas turbine engine according to any of the foregoing clauses further includes a bushing cyclone that is fluidly connected to or disposed in the bushing air orifice.

[0164] The gas turbine engine according to any of the foregoing clauses, wherein the burner bushing includes an axial portion and a converging portion rear of the axial portion.

[0165] The gas turbine engine according to any of the foregoing clauses, wherein the axial portion includes the bushing fuel orifice.

[0166] A method of operating a gas turbine engine, the gas turbine engine including a compressor section, a combustion section, and a turbine section arranged in a series flow configuration, wherein the combustion section includes a combustor bushing that at least partially defines a combustion chamber and a fuel nozzle assembly fluidly connected to the combustion chamber, the method comprising: operating the fuel nozzle assembly in a first mode to discharge gaseous hydrogen fuel and a liquid fuel into the combustion chamber; operating the fuel nozzle assembly in a second mode to discharge gaseous hydrogen fuel into the combustion chamber; operating the fuel nozzle assembly in a third mode to discharge liquid fuel into the combustion chamber; and wherein operating the fuel nozzle assembly in the third mode includes discharging at least one of the gaseous hydrogen fuel or the liquid fuel radially outward from an outer surface of the fuel nozzle assembly.

[0167] According to any of the foregoing provisions, operating the fuel nozzle assembly in the first mode includes discharging the liquid fuel from one or more fuel orifices of the fuel nozzle assembly and discharging the gaseous hydrogen fuel from the bushing fuel orifice of the burner bushing.

[0168] According to any of the foregoing provisions, the fuel nozzle assembly includes a central body, a first inner wall, a body wall including the outer surface, an outer wall coupled to the outer surface, and a mixer coupled to the outer wall; and wherein operating the fuel nozzle assembly in the third mode includes radially outwardly discharging the liquid fuel from a fuel orifice on the outer surface of the body wall in a manner that cross-flows with air from the mixer.

[0169] According to any of the foregoing provisions of the method, operating the fuel nozzle assembly in the first mode includes discharging the liquid fuel radially outward from the central body.

[0170] According to any of the foregoing provisions, operating the fuel nozzle assembly in the second mode includes discharging the gaseous hydrogen fuel radially inward from the first inner wall and axially from the outer wall.

[0171] A fuel nozzle assembly for a gas turbine engine includes: a liquid fuel supply section supplying liquid fuel; a hydrogen fuel supply section supplying gaseous hydrogen fuel; and a fuel nozzle body fluidly connected to the liquid fuel supply section and the hydrogen fuel supply section to supply the liquid fuel and the gaseous hydrogen fuel to a combustion chamber; wherein the fuel nozzle body includes an outer surface having a fuel orifice fluidly connected to the liquid fuel supply section and the hydrogen fuel supply section to discharge at least one of the liquid fuel or the gaseous hydrogen fuel radially outward relative to the centerline of the fuel nozzle assembly.

[0172] According to any of the foregoing clauses, the fuel nozzle assembly is wherein the fuel orifice is arranged in a radial direction parallel to the centerline of the fuel nozzle assembly.

[0173] According to any of the preceding clauses, the fuel nozzle assembly, wherein the fuel nozzle body includes: a central body, a first inner wall radially outside the central body such that a first internal fluid passage is at least partially defined between the central body and the first inner wall, and a body wall radially outside the first inner wall such that a second internal fluid passage is at least partially defined between the first inner wall and the body wall, the body wall including the outer surface.

[0174] A fuel nozzle assembly according to any of the foregoing clauses, wherein the fuel nozzle assembly includes an outer wall coupled to and radially spaced outward from the outer surface of the body wall to define an external fluid passage.

[0175] According to any of the preceding clauses, the fuel nozzle assembly includes a plurality of outer wall fuel orifices arranged in an annular configuration, wherein the outer wall fuel orifices located on the circumferential side of the outer wall have a relatively large diameter, and the outer wall fuel orifices located at the radially inner and radially outer portions of the outer wall have relatively small diameters.

[0176] According to any of the preceding clauses, the plurality of outer wall fuel orifices are arranged in an alternating pattern, wherein at least some of the plurality of outer wall fuel orifices are fluidly connected to the liquid fuel supply section, and adjacent outer wall fuel orifices of the plurality of outer wall fuel orifices are fluidly connected to the hydrogen fuel supply section.

[0177] According to any of the preceding clauses, the fuel nozzle assembly wherein the fuel orifice is located at or downstream of the outlet of the external fluid passage.

[0178] The fuel nozzle assembly according to any of the foregoing clauses, wherein the fuel nozzle assembly includes a mixer coupled to the outer wall.

[0179] The fuel nozzle assembly according to any of the foregoing clauses, wherein the mixer includes a radial vortex.

[0180] The fuel nozzle assembly according to any of the foregoing clauses, wherein the fuel nozzle assembly includes a first axial vortex in the first internal fluid passage and a second axial vortex in the second internal fluid passage.

[0181] The fuel nozzle assembly according to any of the foregoing clauses, wherein the fuel nozzle assembly includes a third axial vortex in the external fluid passage.

[0182] According to any of the preceding clauses, the fuel nozzle assembly includes a mixer wall extending in the axial direction of the fuel nozzle assembly; and the fuel orifice points toward the mixer wall.

Claims

1. A gas turbine engine, characterized in that, include: A compressor section, a combustion section, and a turbine section arranged in a series flow configuration, wherein the combustion section includes: A burner bushing, the burner bushing at least partially defining a combustion chamber; and Fuel nozzle assembly, the fuel nozzle assembly comprising: Liquid fuel supply unit, which supplies liquid fuel; Hydrogen fuel supply unit, which supplies gaseous hydrogen fuel; and A fuel nozzle body, which is fluidly connected to the liquid fuel supply unit and the hydrogen fuel supply unit to supply the liquid fuel and the gaseous hydrogen fuel to the combustion chamber; The fuel nozzle body includes an outer surface having a fuel orifice, which is fluidly connected to the liquid fuel supply and the hydrogen fuel supply to discharge at least one of the liquid fuel or the gaseous hydrogen fuel radially outward relative to the centerline of the fuel nozzle assembly.

2. The gas turbine engine according to claim 1, characterized in that, in, The fuel orifice is arranged in a radial direction parallel to the centerline of the fuel nozzle assembly.

3. The gas turbine engine according to claim 1, characterized in that, in, The fuel nozzle body includes: Central body, A first inner wall, radially outer of the central body, such that a first internal fluid channel is at least partially defined between the central body and the first inner wall. A body wall, located radially outside the first inner wall, such that a second internal fluid passage is at least partially defined between the first inner wall and the body wall, the body wall including the outer surface.

4. The gas turbine engine according to claim 3, characterized in that, in, The fuel nozzle assembly includes an outer wall that is coupled to and radially spaced outward from the outer surface of the body wall to define an external fluid passage.

5. The gas turbine engine according to claim 4, characterized in that, in, The outer wall includes a plurality of outer wall fuel orifices arranged in a ring structure, wherein the outer wall fuel orifices located on the circumferential side of the outer wall relative to the centerline of the combustion section have a relatively large diameter, and the outer wall fuel orifices located on the radially inner and radially outer portions of the outer wall relative to the centerline of the combustion section have relatively small diameters.

6. The gas turbine engine according to claim 5, characterized in that, in, The plurality of outer wall fuel orifices are arranged in an alternating pattern, wherein at least some of the plurality of outer wall fuel orifices are fluidly connected to the liquid fuel supply section, and adjacent outer wall fuel orifices of the plurality of outer wall fuel orifices are fluidly connected to the hydrogen fuel supply section.

7. The gas turbine engine according to claim 4, characterized in that, in, The fuel orifice is located at the outlet or downstream of the external fluid channel.

8. The gas turbine engine according to claim 7, characterized in that, in, The fuel nozzle assembly includes a mixer coupled to the outer wall.

9. The gas turbine engine according to claim 8, characterized in that, in, The mixer includes a radial vortex.

10. The gas turbine engine according to claim 9, characterized in that, in, The fuel nozzle assembly includes a first axial vortex in the first internal fluid channel and a second axial vortex in the second internal fluid channel.

Images