Turbine engine having combustion section with fuel nozzle

Abstract

A turbine engine has a compression section, a combustion section, and a turbine section in a serial flow arrangement. The combustion section has a combustor liner and a domed wall that collectively form at least a portion of the combustion chamber. The domed wall has a fuel nozzle opening. The combustion section has a fuel nozzle extending through a fuel nozzle opening. The fuel nozzle has a gaseous fuel supply channel and a compressed air channel. The combustion section includes a gaseous fuel channel fluidly coupled to a gaseous fuel supply channel.

Description

TECHNICAL FIELD

[0001] The present subject matter generally relates to turbine engines and, more particularly, to turbine engines having a combustion section that includes fuel nozzles. BACKGROUND OF THE INVENTION

[0002] A turbine engine is driven by a flow of combustion gases through the engine to rotate a plurality of turbine blades, which in turn rotate a compressor to provide compressed air to a combustor for combustion. The combustor may be disposed within the turbine engine and is fluidly coupled to the turbine into which the combustion gases flow.

[0003] The use of hydrocarbon fuels in the combustors of turbine engines is known. Generally, air and fuel are fed into a combustion chamber, the air and fuel are mixed, and then the fuel is burned in the presence of air to produce hot gases. The hot gases are then fed into a turbine, where the hot gases are cooled and expanded to produce power. By-products of fuel combustion typically include environmentally undesirable by-products such as nitrogen oxides and nitrogen dioxide (collectively referred to as NO x 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 oxides of sulfur (e.g., SO2 and SO3). BRIEF DESCRIPTION OF THE DRAWINGS

[0004] A complete and enabling disclosure of the present disclosure, including the best mode thereof, to one of ordinary skill in the art, is set forth in the specification, which makes reference to the accompanying drawings, in which:

[0005] Figure 1 is a schematic representation of a turbine engine that includes a compression section, a combustion section, and a turbine section.

[0006] Figure 2 depicts a cross-sectional view of the combustion section taken along line II-II of Figure 1 further showing a set of fuel nozzles.

[0007] Figure 3 is a schematic of a side cross-sectional view taken along line III-III of Figure 2 further showing a fuel nozzle, a housing, a dome wall, a burner liner, a fuel port, and a gaseous fuel supply within the set of fuel nozzles, the gaseous fuel supply having a first circumferential gaseous fuel manifold.

[0008] Figure 4 is a schematic cross-sectional view of a section of the combustion section taken along line IV-IV of Figure 3 further showing a second circumferential gaseous fuel manifold and a third circumferential gaseous fuel manifold of the gaseous fuel supply.

[0009] Figure 5 is Figure 2 A schematic perspective view of a combustion section of

[0010] Figure 6 is Figure 2 A schematic view of a combustion section of

[0011] Figure 7 is a schematic perspective view of a combustion section suitable for use in a Figure 1 turbine engine, further showing circumferential dome wall dividing portions.

[0012] Figure 8 is a schematic view of a side cross-sectional view of an exemplary combustion section suitable for use in a Figure 1 turbine engine, further showing a housing, a dome wall, a burner liner, and a gaseous fuel supply, the gaseous fuel supply being separated from the dome wall. DETAILED DESCRIPTION

[0013] The disclosed aspects described herein relate to a turbine engine including a combustion section that includes a housing, a fuel nozzle, a dome wall, a burner liner, and a gaseous fuel supply. The gaseous fuel supply and the fuel nozzle are integrally formed to define a single body. As used herein, the term "single body" or its iterations refers to a combination of integrally formed parts. The combination of parts forming the single body does not include physical couplings such as welding, gluing, or fastening between the combinations of parts. The housing includes a fuel port. The gaseous fuel supply extends through the fuel port.

[0014] The fuel nozzle is particularly suitable for using hydrogen fuel (hereinafter referred to as "H2 fuel"). Specifically, the fuel nozzle is particularly suitable for supplying a gaseous H2 fuel stream to a combustion chamber. Compared with conventional fuels (e.g., carbon fuels, petroleum fuels, etc.), H2 fuel has a higher combustion temperature and speed. In addition, flashback may occur when using H2 fuel. As used herein, flashback refers to an unexpected flame propagation when H2 fuel burns. H2 fuel has a higher volatility, which means that once H2 fuel is burned or ignited, the flame generated by igniting H2 fuel will expand at an undesired location; in other words, flashback may occur. For example, the flame can expand into the fuel nozzle or the igniter. As described herein, the fuel nozzle ensures that flashback does not occur with H2 fuel. If H2 fuel overheats, H2 fuel may autoignite. Autoignition of H2 fuel may be undesired at certain locations in the combustion section. The fuel nozzle as described herein ensures that the temperature of H2 fuel is below the autoignition temperature, at least until it is desired to ignite H2 fuel.

[0015] As used herein, the term "gaseous fuel" or its iterations refers to a combustible fuel in a gaseous state. It should be understood that gaseous fuel is different from atomized fuel. Atomized fuel utilizes impellers, orifices, etc. to obtain liquid fuel and atomize the liquid fuel into very small droplets.

[0016] In some aspects, the gaseous fuel exits the fuel nozzle at a given velocity and then mixes with air for combustion. When the fuel / air mixture burns, the flame propagates upstream. It may be desirable to control or maintain a constant flame in the burner to ignite subsequent fuel rather than continuously ignite the fuel with an igniter.

[0017] For purposes of illustration, the present disclosure will be described with respect to a turbine engine (gas turbine engine). However, it will be understood that the aspects of the disclosure described herein are not limited thereto, and the fuel nozzles described herein can be implemented in engines (including but not limited to turbojet engines, turboprop engines, turboshaft engines, and turbofan engines). The aspects of the disclosure discussed herein can have general applicability within non-aircraft engines having burners, such as within other mobile applications and non-mobile industrial, commercial, and residential applications.

[0018] As used herein, the word "exemplary" means "serving as an example, instance, or illustration". Any embodiment described herein as "exemplary" is not necessarily to be construed as superior or advantageous to other embodiments. Additionally, unless otherwise expressly stated, all examples described herein should be considered exemplary.

[0019] As used herein, the terms "first" and "second" may be used interchangeably to distinguish one component from another and are not intended to denote the position or importance of the respective components.

[0020] The terms "front" and "rear" refer to relative positions within the turbine engine or vehicle and refer to the normal operating attitude of the turbine engine or vehicle. For example, for a turbine engine, front refers to a position closer to the engine inlet, and rear refers to a position closer to the engine nozzle or exhaust.

[0021] As used herein, the term "upstream" refers to the direction opposite to the fluid flow direction, while the term "downstream" refers to the direction the same as the fluid flow direction. The terms "forward" or "front" indicate in front of something, and "backward" or "rear" indicate behind something. For example, when used with fluid flow, forward / front can indicate upstream, and backward / rear can indicate downstream.

[0022] The term "fluid" can be a gas or a liquid. The term "fluidly connected" means that fluid can establish a connection between specified regions.

[0023] In addition, as used herein, the terms "radial" or "radially" refer 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 central longitudinal axis of the engine and the outer periphery of the engine.

[0024] 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 assist the reader in understanding the disclosure and do not create a limitation, particularly as to the position, orientation, or use of aspects of the disclosure described herein. Connecting references (e.g., attached, coupled, connected, and joined) will be construed broadly and may include intermediate structural elements between assemblies of elements and relative movement between the elements, unless otherwise indicated. Thus, a connecting reference does not necessarily imply that two elements are directly connected and fixed relative to each other. Exemplary drawings are for illustrative purposes only, and the dimensions, positions, sequences, and relative sizes reflected in the attached drawings may vary.

[0025] The singular forms "a", "an", and "the" include plural references unless the context clearly dictates otherwise. In addition, as used herein, the term "group" or "a group of" elements can be any number of elements, including only one.

[0026] Figure 1 is a schematic view of a turbine engine 10. As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 can at least include a compression section 12, a combustion section 100, and a turbine section 16 in a serial flow arrangement. A drive shaft 18 is rotationally coupled to the compression section 12 and the turbine section 16 such that the rotation of one affects the rotation of the other and defines a rotational axis or engine centerline 20 of the turbine engine 10.

[0027] The compression section 12 can include a low pressure (LP) compressor 22 and a high pressure (HP) compressor 24 that are fluidly coupled in series with each other. The turbine section 16 can include an LP turbine 26 and an HP turbine 28 that are fluidly coupled in series with each other. A drive shaft 18 can operably couple the LP compressor 22, the HP compressor 24, the LP turbine 26, and the HP turbine 28 together. Alternatively, the drive shaft 18 can include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft can couple the LP compressor 22 to the LP turbine 26, and the HP drive shaft can couple the HP compressor 24 to the HP turbine 28. An LP spool can be defined as the combination of the LP compressor 22, the LP turbine 26, and the LP drive shaft such that rotation of the LP turbine 26 can apply a driving force to the LP drive shaft, which in turn can cause the LP compressor 22 to rotate. An HP spool can be defined as the combination of the HP compressor 24, the HP turbine 28, and the HP drive shaft such that rotation of the HP turbine 28 can apply a driving force to the HP drive shaft, which in turn can cause the HP compressor 24 to rotate.

[0028] The compression section 12 can include a plurality of axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. Compressor blades for a stage of the compression section 12 can be mounted to a disk that is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the compression section 12 can be mounted to a housing that can extend circumferentially around the turbine engine 10. It should be understood that the representation of the compression section 12 is merely schematic and can have any number of stages. Further, it is contemplated that there can be any other number of components within the compression section 12.

[0029] Similar to the compression section 12, the turbine section 16 can include a plurality of axially spaced stages, where each stage has a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. Turbine blades for a stage of the turbine section 16 can be mounted to a disk that is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the turbine section 16 can be mounted circumferentially to the housing. It should be noted that there can be any number of blades, vanes, and turbine stages as the illustrated turbine section is merely a schematic representation. Further, it is contemplated that there can be any other number of components within the turbine section 16.

[0030] The combustion section 100 can be serially disposed between the compression section 12 and the turbine section 16. The combustion section 100 can be fluidly coupled to at least a portion of the compression section 12 and the turbine section 16 such that the combustion section 100 at least partially fluidly couples the compression section 12 to the turbine section 16. As a non-limiting example, the combustion section 100 can be fluidly coupled to the HP compressor 24 at an upstream end of the combustion section 100 and to the HP turbine 28 at a downstream end of the combustion section 100.

[0031] During operation of the turbine engine 10, ambient or atmospheric air is drawn into the compression section 12 via a fan (not shown) upstream of the compression section 12, and the air is compressed at the compression section 12 to define compressed air. The compressed air can then flow into the combustion section 100, where the compressed air is mixed with fuel and ignited at the combustion section 14 to generate combustion gases. The HP turbine 28 extracts some work from these combustion gases, and the HP turbine 28 drives the HP compressor 24. The combustion gases are discharged into the LP turbine 26, where the LP turbine 26 extracts additional work to drive the LP compressor 22, and the exhaust is ultimately discharged from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The driving of the LP turbine 26 drives an LP spool to rotate the fan (not shown) and the LP compressor 22. The compressed air flow and the combustion gases can together define a working air flow that passes through the fan, the compression section 12, the combustion section 100, and the turbine section 16 of the turbine engine 10.

[0032] Figure 2 Depicted is a cross-sectional view of the combustion section 100 along Figure 1 line II-II. For illustrative purposes, the drive shaft 18 ( Figure 1 ) has been removed. The combustion section 100 includes a burner 34. The burner 34 includes a dome wall 144 that includes a set of fuel nozzle openings (not shown). The burner 34 includes a set of fuel nozzles 148 disposed within the set of fuel nozzle openings. The set of fuel nozzles 148 is arranged annularly about a burner centerline 180. The burner centerline 180 can be the engine centerline 20 ( Figure 1 ) of the turbine engine 10 ( Figure 1 ). Additionally or alternatively, the burner centerline 180 can be the centerline of the combustion section 100, a single burner, or a set of burners arranged about the burner centerline 180.

[0033] The set of fuel nozzles 148 is arranged around the burner centerline 180. Each fuel nozzle in the set of fuel nozzles 148 includes a respective centerline axis 150. The set of fuel nozzles 148 can include rich cups, lean cups, or a combination of rich cups and lean cups arranged annularly around the engine centerline. The burner 34 is defined by a burner liner 139. Depending on the type of engine in which the burner 34 is located, the burner 34 can have a can-shaped, can-annular, or annular arrangement. In a non-limiting example, the burner 34 can have a combined arrangement located within the housing 135 of the engine as further described herein. As shown by way of example, the burner liner 139 can be annular. The burner liner 139 can include an outer burner liner 140 and an inner burner liner 142 that are concentric with each other and annularly disposed around the engine centerline 20. A dome wall 144 extends between the outer burner liner 140 and the inner burner liner 142. The burner liner 139 also defines the set of fuel nozzles 148. The dome wall 144 and the burner liner 139 together can define a combustion chamber 146 that is annularly disposed around the engine centerline 20. The set of fuel nozzles 148 can be fluidly coupled to the combustion chamber 146. The compressed air passage 133 can be at least partially defined by the burner liner 139 and the housing 135. Each fuel nozzle in the set of fuel nozzles 148 is defined by a discrete body that extends through a respective portion of the dome wall 144 and is configured to discharge a gaseous fuel and a compressed air stream into the combustion chamber 146.

[0034] Figure 3 is from Figure 2 FIG. 6 is a schematic side cross-sectional view of the combustion section 100 as seen along section line III-III. The combustion section 100 includes a shroud 138. The shroud 138, the outer burner liner 140, and the inner burner liner 142 together form the burner liner 139. The shroud 138 is disposed axially forward of the outer burner liner 140 and the inner burner liner 142 relative to the burner centerline 180. Compressed air openings 136 are provided within the shroud 138. The shroud 138 can include any number of one or more compressed air openings 136. The compressed air openings 136 can be formed as a channel that circumferentially extends around the burner centerline 180, a series of holes that are circumferentially spaced apart around the burner centerline 180, or a combination thereof.

[0035] A set of flame shaping holes 110 is formed between the dome wall 144 and the fuel nozzles 148. The set of flame shaping holes 110 discharges into the combustion chamber 146 at the flame shaping outlet 116. The set of flame shaping holes 110 can be formed as a discontinuous or continuous channel or holes that continuously extend around the entire centerline axis 150 or less than the entire centerline axis 150. The set of flame shaping channels 110 can be formed as a set of circumferentially spaced apart segments.

[0036] The cavity 182 is defined between the shroud 138 and the dome wall 144. The cavity 182 is disposed on a side of the dome wall 144 opposite to the combustion chamber 146. The fuel nozzle 148 extends into the cavity 182. The fuel nozzle 148 terminates within the cavity 182. The fuel nozzle 148 does not extend through any part of the shroud 138, the outer burner liner 140, and the inner burner liner 142.

[0037] The fuel nozzle 148 includes a first body 102 and a second body 104. The first body 102 defines a gaseous fuel passage 106. The second body 104 defines a compressed air passage 108 that discharges into the combustion chamber 146 at a compressed air outlet 114. The second body 104 is disposed radially outward from the first body 102 relative to a centerline axis 150. The second body 104 surrounds the first body 102. The dome wall 144 is disposed radially outward from the second body 104 relative to the centerline axis 150.

[0038] The fuel nozzle 148 may include a gaseous fuel swirler 118 and an air swirler 120. The gaseous fuel swirler 118 is disposed within the gaseous fuel passage 106. The air swirler 120 is disposed within the compressed air passage 108. The air swirler 120 extends between the first body 102 and the second body 104. The gaseous fuel swirler 118 and the air swirler 120 are integrally formed with or coupled to the first body 102. The air swirler 120 is integrally formed with or coupled to the second body 104. The air swirler 120 defines a connection between the first body 102 and the second body 104. As a non-limiting example, the first body 102, the gaseous fuel swirler 118, the air swirler 120, and the second body 104 may be integrally formed such that the first body 102, the gaseous fuel swirler 118, the air swirler 120, and the second body 104 form a single body. In other words, the fuel nozzle 148 may be formed as a single body.

[0039] The gaseous fuel swirler 118 and the air swirler 120 are any suitable components configured to cause a fluid flow to swirl from an upstream edge of the respective swirler to a downstream edge of the respective swirler. As a non-limiting example, the gaseous fuel swirler 118, the air swirler 120, or a combination thereof may be an airfoil or a plurality of airfoils disposed within the gaseous fuel passage 106 or the compressed air passage 108, respectively. As a non-limiting example, the gaseous fuel swirler 118 may be an orifice plate including a plurality of orifices 123. The plurality of orifices 123 are oriented to provide a swirling effect of the swirler. It should be understood that either or both of the gaseous fuel swirler 118 or the air swirler 120 may be formed as an orifice plate or a plurality of airfoils.

[0040] The swirl amount of the fluid flow passing through or flowing over the gas fuel swirler 118 and the air swirler 120 is quantified by the swirl number, which is defined as the integral of the tangential momentum and the axial momentum of the fluid flow downstream of the corresponding swirler. The gas fuel swirler 118 and the air swirler 120 are defined as swirlers that generate a swirling air flow with a swirl number greater than or equal to 0.2 and less than or equal to 1.2.

[0041] The opening defining the fuel port 124 is formed within a portion of the housing 135. The fuel port 124 is disposed along any suitable portion of the housing 135. As a non-limiting example, the fuel port 124 is axially aligned relative to the burner centerline 180 with the position where the dome wall 144 and the outer burner liner 140 meet. The gas fuel supply channel 122 extends through the fuel port 124 and into the compressed air passage 133. The gas fuel supply channel 122 extends through the corresponding portions of the burner liner 139, the dome wall 144, or a combination thereof, and ultimately reaches the gas fuel channel 106. The size of the fuel port 124 can be designed to leave a space between the gas fuel supply channel 122 and the housing 135. Alternatively, the size of the fuel port 124 can be designed such that the gas fuel supply channel 122 contacts the corresponding portion of the housing 135.

[0042] The gas fuel supply channel 122 includes a dome wall inlet section 126, a first circumferential gas fuel manifold 128, a second circumferential gas fuel manifold 130, a swirler section 132, a third circumferential gas fuel manifold 134, and a dome wall distribution section 137. It should be understood that at least a portion of the gas fuel supply channel 122 (e.g., the dome wall inlet section 126) is formed with the dome wall 144. As used herein, the term "formed with the dome wall" means that a portion of the gas fuel supply channel 122 directly contacts the dome wall 144 or is formed within the dome wall 144 (e.g., integrally formed with the dome wall 144).

[0043] The dome wall inlet section 126 extends through the corresponding portion of the dome wall 144. The dome wall inlet section 126 is fluidly coupled to the first circumferential gas fuel manifold 128 formed within the dome wall 144. The second circumferential gas fuel manifold 130 is formed within the second body 104. The first circumferential gas fuel manifold 128 is fluidly coupled to the second circumferential gas fuel manifold 130. The third circumferential gas fuel manifold 134 is formed within the first body 102 and is directly fluidly coupled to the gas fuel channel 106. The third circumferential gas fuel manifold 134 is fluidly coupled to the second circumferential gas fuel manifold 130 through the swirler section 132. The swirler section 132 extends through the interior of the air swirler 120.

[0044] The gas fuel supply channel 122 extends between any suitable number of one or more of the fuel nozzles in the set of fuel nozzles 148. As a non-limiting example, the combustion section 100 may include a single continuous gas fuel supply channel 122 that supplies gas fuel to each of the fuel nozzles in the set of fuel nozzles 148. Alternatively, the combustion section 100 may include two or more separate fuel channels that supply gas fuel to corresponding sub-groups of the fuel nozzles in the set of fuel nozzles 148.

[0045] Each fuel nozzle in the set of fuel nozzles 148 may include a corresponding first circumferential gas fuel manifold 128, a second circumferential gas fuel manifold 130, and a third circumferential gas fuel manifold 134 that supply gas fuel to a corresponding gas fuel channel 106 of the corresponding fuel nozzle 148. In the case where two or more fuel nozzles 148 are fluidly coupled to a single gas fuel supply channel 122, a dome wall distribution section 137 interconnects the first circumferential gas fuel manifolds 128 of circumferentially adjacent fuel nozzles 148. The dome wall distribution section 137 may extend radially, circumferentially, or a combination thereof through the dome wall 144 between adjacent fuel nozzles 148. The dome wall distribution section 137 may extend from any suitable portion of the first circumferential gas fuel manifold 128.

[0046] The fuel nozzle 148 and the gas fuel supply channel 122 may be integrally formed with the dome wall 144, the burner bushing 139, or a combination thereof to define a corresponding single body. As a non-limiting example, the fuel nozzle 148, the gas fuel supply channel 122, and the dome wall 144 may be integrally formed to form a single body. The single body of the fuel nozzle 148, the gas fuel supply channel 122, and the dome wall 144 may then be coupled to the burner bushing 139 and the shroud 138 at a coupling joint 141, as shown by way of example in dashed lines. The single body of the fuel nozzle 148, the gas fuel supply channel 122, and the dome wall 144 may be coupled to the burner bushing 139 by any suitable coupling method (such as but not limited to bonding, welding, fastening, etc.).

[0047] During operation, a gaseous fuel stream (Fg) is supplied through a fuel port 124 to a gaseous fuel supply channel 122. The gaseous fuel stream (Fg) flows through a dome wall inlet section 126 to define an inlet gaseous fuel stream (Fgi). The inlet gaseous fuel stream (Fgi) is supplied to a first circumferential gaseous fuel manifold 128. The inlet gaseous fuel stream (Fgi) within the first circumferential gaseous fuel manifold 128 is supplied to at least one of a second circumferential gaseous fuel manifold 130 or a dome wall distribution section 137. When supplied to the dome wall distribution section 137, the inlet gaseous fuel stream (Fgi) may be supplied to other portions of the gaseous fuel supply channel 122 (e.g., to an adjacent fuel nozzle 148) to define a distributed gaseous fuel stream (Fgd). The gaseous fuel stream (Fg) may comprise 100% hydrogen (“H2”) fuel, or a mixture of hydrogen fuel and another gaseous fuel (e.g., methane). Alternatively, the gaseous fuel stream (Fg) may be a mixture of H2 fuel and compressed air from, for example, a compression section (e.g., Figure 1 the compression section 12).

[0048] At least a portion of the inlet gaseous fuel stream (Fgi) within the first circumferential gaseous fuel manifold 128 is supplied to the second circumferential gaseous fuel manifold 130. At least a portion of the fuel within the second circumferential gaseous fuel manifold 130 is supplied as a supply gaseous fuel stream (Fgs) through a swirler section 132 to a third circumferential gaseous fuel manifold 134. At least a portion of the supply gaseous fuel stream (Fgs) is supplied to a gaseous fuel channel 106, where at least this portion of the supply gaseous fuel stream (Fgs) is swirled by a gaseous fuel swirler 118 to define a swirling gaseous fuel stream (Fs). The swirling gaseous fuel stream (Fs) is supplied to a combustion chamber 146. The swirling gaseous fuel stream (Fs) is ignited downstream of the gaseous fuel swirler 118 via an igniter. The ignition of the swirling gaseous fuel stream (Fs) creates a flame within the combustion chamber 146.

[0049] A compressed air stream (C) is supplied from a compressed air passage 133 and through a compressed air opening 136 to a fuel nozzle 148. The compressed air stream (C) is drawn from a compressed air supply (such as Figure 1 the LP compressor 22 or the HP compressor 24). The compressed air stream (C) is supplied to a compressed air channel 108 and the set of flame shaping holes 110 to respectively define a first compressed air stream (Fc1) and a second compressed air stream (Fc2). The first compressed air stream (Fc1) and the second compressed air stream (Fc2) are supplied to the combustion chamber 146.

[0050] The first compressed air stream (Fc1) and the second compressed air stream (Fc2) are used to shape the flame (e.g., provide a desired footprint of the physical flame within the combustion chamber 146) and isolate various portions of the combustion section 100 from the flame generated by the ignition of the swirling gaseous fuel stream (Fs). Flame shaping is accomplished by forming an annular compressed air curtain around the flame. The annular compressed air curtain in turn guides the flame or other swirling gaseous fuel stream (Fs) in a desired direction and holds the flame within a desired boundary at least partially defined by the annular compressed air curtain. The annular compressed air curtain also isolates the various portions of the combustion section 100 (e.g., the dome wall 114, the burner liner 139, etc.) from the heat of the flame by providing a layer of insulation between the flame and other sections of the combustion section 100 or otherwise cooling the other sections of the combustion section 100.

[0051] When using gaseous H2 fuel, the shaping and isolation of the flame are particularly important compared to conventional fuels. Compared to conventional fuels, gaseous H2 fuel burns at a higher temperature and has a higher tendency to flash back. The first compressed air stream (Fc1) and the second compressed air stream (Fc2) are used to accommodate the higher combustion temperature and higher flash-back tendency. Pushing the swirling gaseous fuel stream (Fs) away from the fuel nozzle 148 helps ensure that once ignited, flash-back into the fuel nozzle 148 of the swirling fuel stream (Fs) does not occur. The first compressed air stream (Fc1) and the second compressed air stream (Fc2) further ensure that a flame with a combustion temperature higher than that generated by conventional fuels does not overheat the sections of the combustion section 100. The first compressed air stream (Fc1) and the second compressed air stream (Fc2) can further be used to produce a uniform flame distribution at the burner outlet. It is contemplated that a uniform flame distribution or temperature distribution at the burner outlet will result in higher efficiency of the turbine section 16 ( Figure 1 ).

[0052] The gaseous fuel stream (Fg) through the gaseous fuel supply channel 122, particularly the inlet gaseous fuel stream (Fgi), is further used to cool the dome wall 144. By using the gaseous fuel stream (Fg) to cool the dome wall 144, the life of the dome wall 144 is increased by reducing the thermal stress that the dome wall 144 experiences during operation of the combustion section 100. It should be understood that the size of the dome wall 144 is designed to keep the gaseous fuel stream (Fg) sufficiently isolated from the flame to ensure that the gaseous fuel stream (Fb) does not exceed a threshold temperature and undergo autoignition.

[0053] Although not shown, the combustion section 100 can include a controller module communicatively coupled to a set of valves to automatically control the fluid flow to various parts of the combustion section 100 or within various parts of the combustion section 100. As a non-limiting example, the controller module can automatically control the supply of gas fuel to the gas fuel supply channel 122 and the gas fuel flow (Fg) through the gas fuel supply channel 122. As a non-limiting example, the controller module can automatically control the supply of compressed air flow (C) to the compressed air channel 108, the set of flame shaping holes 110, or a combination thereof to define a first compressed air flow (Fc1) and a second compressed air flow (Fc2), respectively. The fluid flow to various parts of the combustion section 100 or within various parts of the combustion section 100 can be accomplished independently of each other. As a non-limiting example, the supply of compressed air flow (C) to the compressed air channel 108 can be accomplished independently of the supply of compressed air flow (C) to the set of flame shaping holes 110.

[0054] Figure 4 is a schematic cross-sectional view of a cross-section of the combustion section 100 taken along line IV-IV Figure 3 of. The first circumferential gas fuel manifold 128 ( Figure 3 ), the second circumferential gas fuel manifold 130, and the third circumferential gas fuel manifold 134 can each be formed as an annular channel that extends continuously or discontinuously around the entire or less than the entire circumferential extent about the centerline axis 150. The first circumferential gas fuel manifold 128 surrounds the second circumferential gas fuel manifold 130, the second circumferential gas fuel manifold 130 surrounds the third circumferential gas fuel manifold 134, and the third circumferential gas fuel manifold 134 surrounds the gas fuel channel 106. As a non-limiting example, at least one of the first circumferential gas fuel manifold 128, the second circumferential gas fuel manifold 130, the third circumferential gas fuel manifold 134, or a combination thereof can be defined by circumferentially discrete segments. The set of flame shaping holes 110 can include a plurality of flame shaping holes circumferentially spaced about the centerline axis 150. Alternatively, the flame shaping channel 110 can be defined by one or more channels that extend continuously or discontinuously around the entire or less than the entire circumferential extent about the centerline axis 150.

[0055] The gas fuel supply channel 122 includes a connection to the first circumferential gas fuel manifold 128 ( Figure 3) Each part of which is fluidly connected to a set of connecting channels of the second circumferential gas fuel manifold 130. There can be any number of one or more connecting channels. As a non-limiting example, the set of connecting channels can include an inlet connecting channel 158 and an outlet connecting channel 159. The inlet connecting channel 158 is defined as the channel of the gas fuel supply channel 122 that directly supplies the gas fuel flow to the second circumferential gas fuel manifold 130. The outlet connecting channel 159 is defined as the channel of the gas fuel supply channel 122 that directly supplies the gas fuel flow from the second circumferential gas fuel manifold 130.

[0056] At least one air swirler 120 includes a swirler section 132. It should be understood that any number of one or more air swirlers 120 can include the swirler section 132. As a non-limiting example, each air swirler 120 can include the swirler section 132.

[0057] During operation, the inlet gas fuel flow (Fgi) passes through the inlet connecting channel 158 from the first circumferential gas fuel manifold 128 ( Figure 3 ) is supplied. At least a portion of the inlet gas fuel flow (Fgi) is supplied to the second circumferential gas fuel manifold 130 to define a manifold gas fuel flow (Fgm). The manifold gas fuel flow (Fgm) is circumferentially supplied through at least a portion of the second circumferential gas fuel manifold 130. At least a portion of the manifold gas fuel flow (Fgm) is supplied as a supply gas fuel flow (Fgs) to the third circumferential gas fuel manifold 134 through the swirler section 132. At least a portion of the manifold gas fuel flow (Fgm) is supplied as a distributed gas fuel flow (Fgd) back to a portion of the first gas fuel manifold 128 through the outlet connecting channel 159, or directly supplied to the dome wall distribution section 137 ( Figure 3 ).

[0058] Figure 5 is Figure 2 is a schematic perspective view of the combustion section 100 of. The housing 135 can include a set of housing dividing portions 160 that define a set of housing segments 162. The set of housing dividing portions 160 can extend radially through at least a portion of the housing 135 and extend axially, circumferentially (shown in dashed lines), or a combination thereof along the at least a portion of the housing 135. It should be understood that the burner liner 139, the dome wall 144 ( Figure 3 ) or a combination thereof can include a set of dividing portions similar to the set of housing dividing portions 160.

[0059] The fuel ports 124 are provided along any suitable portion of the housing 135 and may have any suitable shape or size. As a non-limiting example, each housing segment 162 may include one or more fuel ports 124. As a non-limiting example, each housing segment 162 may include a single fuel port 124. A single gaseous fuel supply 122( Figure 3 ) extends through each fuel port 124. Each fuel port 124 may be formed in the shape of any suitable polygon (such as but not limited to circular, rectangular, triangular, etc.) cutout provided along the outer burner liner 140. Each fuel port 124 may be the same as or different from the other fuel ports 124.

[0060] Figure 6 is Figure 2 a schematic view of the combustion section 100. The dome wall 144 may include a set of dome wall dividing portions 186 that divide the dome wall 144 into a set of dome wall segments 192. The set of dome wall dividing portions 186 may extend radially or circumferentially about the burner centerline 180. Each segment of the set of dome wall segments 192 may include one or more fuel nozzles 148. Each segment of the set of dome wall segments 192 may include the same number or different numbers of fuel nozzles 148. Each fuel nozzle 148 may be entirely disposed within a particular segment of the set of dome wall segments 192. Alternatively, at least one fuel nozzle of the set of fuel nozzles 148 may be disposed along a corresponding dividing portion of the set of dome wall dividing portions 186 such that the at least one fuel nozzle 148 extends between two or more dome wall segments 192.

[0061] Reference Figure 5 and Figure 6 , each housing segment of the set of housing segments 162 and each dome wall segment of the set of dome wall segments 192 are joined to each other by any suitable joining method (such as but not limited to gluing, welding, fastening, etc.). It should be understood that adjacent housing segments 162 and adjacent dome wall segments 192 are fluid-tight with respect to each other such that fluid flow cannot directly pass through the set of housing dividing portions 160 and the set of dome wall dividing portions 186, respectively.

[0062] The use of the set of housing dividing portions 160 and the set of dome wall dividing portions 186 is for manufacturing purposes. As described herein, at least the fuel nozzle 148 and the gaseous fuel supply channel 122 are formed as a single body. Dividing the housing 135, the dome wall 144, or a combination thereof into individual segments allows for easy installation of at least the single body that defines the fuel nozzle 148 and the gaseous fuel supply channel 122.

[0063] Figure 7 is suitable for use in Figure 1Schematic perspective view of the combustion section 200 used in the turbine engine 10. The combustion section 200 is similar to the combustion section 100; thus, similar parts will be identified with similar numbers incremented to the 200 series. It should be understood that the description of the combustion section 100 applies to the combustion section 200 unless otherwise specified.

[0064] The combustion section 200 includes a burner liner 239. The burner liner 239 includes an outer burner liner 240 and an inner burner liner 242. A dome wall 244 interconnects the outer burner liner 240 and the inner burner liner 242. The combustion section 200 includes a set of fuel nozzles 248 arranged annularly along the dome wall 244 around the burner centerline 280.

[0065] Similar to the burner liner 139( Figure 3 ), the burner liner 239 can be divided along a set of dome wall dividing portions (e.g., Figure 5 the set of dome wall dividing portions 186 of Figure 5 ) to define a set of dome wall segments (e.g.,

[0066] the set of dome wall segments 192 of

[0067] ). However, the difference is that the set of dome wall dividing portions includes a circumferential dome wall dividing portion 284 and a set of radial dome wall dividing portions 286. The circumferential dome wall dividing portion 284 extends circumferentially around the burner centerline 280. The set of radial dome wall dividing portions 286 extends radially outward, radially inward, or a combination thereof from the circumferential dome wall dividing portion 284.

[0068] Figure 8 is suitable for use in Figure 1Schematic side cross-sectional view of a combustion section 300 used within a turbine engine 10. Combustion section 300 is similar to combustion sections 100, 200; thus, like parts will be identified with like numbers incremented to the 300 series, and it should be understood that the description of combustion sections 100, 200 applies to combustion section 300 unless otherwise noted.

[0069] Combustion section 300 includes a housing 335 and a burner liner 339. Burner liner 339 includes an inner burner liner 342, an outer burner liner 340, and a shroud 338. Burner liner 339 is at least partially surrounded by housing 335. A compressed air passage 333 is at least partially formed between housing 335 and burner liner 339. A dome wall 344 interconnects outer burner liner 340 and inner burner liner 342. Dome wall 344 may be formed non-integrally with burner liner 339. Dome wall 344 and burner liner 339 at least partially define a combustion chamber 346. Shroud 338 includes a compressed air opening 336. Shroud 338 and dome wall 344 at least partially define a cavity 382. Combustion section 300 includes a set of fuel nozzles 348 arranged annularly along dome wall 344 about a burner centerline 380. The set of fuel nozzles 348 axially terminates within cavity 382.

[0070] Each fuel nozzle of the set of fuel nozzles 348 includes a first body 302 and a second body 304. First body 302 includes a centerline axis 350 and defines a gaseous fuel channel 306. Gaseous fuel channel 306 discharges into combustion chamber 346 at a gaseous fuel outlet 312. Second body 304 defines a compressed air channel 308. Compressed air channel 308 discharges into combustion chamber 346 at a compressed air outlet 314. Fuel nozzle 348 also includes a set of flame shaping holes 310 at least partially defined by dome wall 344. The set of flame shaping holes 310 discharges into combustion chamber 346 at a flame shaping outlet 316. A gaseous fuel swirler 318 is disposed within gaseous fuel channel 306. An air swirler 320 is disposed within compressed air channel 308 and interconnects first body 302 and second body 304.

[0071] A gaseous fuel supply channel 322 extends through a fuel port 324 provided along housing 335. Gaseous fuel supply channel 322 includes a dome wall inlet section 326, a first circumferential gaseous fuel manifold 328, a second circumferential gaseous fuel manifold 330, a swirler section 332, and a third circumferential gaseous fuel manifold 334. At least a portion of dome wall inlet section 326 is formed with dome wall 344.

[0072] Combustion section 300 is similar to Figure 1-7Combustion zones 100, 200, because the fuel nozzle 348 is integrally formed with the gaseous fuel supply channel 322. However, the fuel nozzle 348 and the gaseous fuel supply channel 322 are at least non-integrally formed with the dome wall 344. The dome wall inlet section 326 extends along the dome wall 344 but does not pass through the dome wall 344, such as the dome wall inlet section 126( Figure 4 ). In addition, the shroud 338 may include a compressed air opening 336 that at least partially defines the fuel port 324. In other words, the gaseous fuel supply channel 322 may extend through the corresponding compressed air opening 336.

[0073] The locking portion 315 defines the connection between the fuel nozzle 348 and the dome wall 344. The locking portion 315 is any suitable part, structure, or assembly that holds the fuel nozzle 348 to the dome wall 344. As a non-limiting example, the locking portion 315 may be formed by a protrusion extending from the fuel nozzle 348 that mates with or otherwise fits within a groove or notch provided along the dome wall 344, or vice versa. The locking portion 315 may extend circumferentially along the entire or less than the entire circumferential extent of the centerline axis 350 of the dome wall 344, the fuel nozzle 348, or a combination thereof. The locking portion 315 may be provided along any suitable portion of the fuel nozzle 348 that faces a portion of the dome wall 344. Any number of one or more locking portions 315 may be formed between the dome wall 344 and the fuel nozzle 348.

[0074] Forming the fuel nozzle 348 and the gaseous fuel supply channel 322 separate from the dome wall 144 increases the life of the fuel nozzle 348 and the gaseous fuel supply channel 322. As discussed herein, the dome wall 344 experiences thermal stress during operation of the combustion zone 300. During maintenance, if the dome wall 344 has degraded too much, the dome wall 344 may be replaced. However, if the fuel nozzle 348, the gaseous fuel supply channel 322, and the dome wall 344 are integrally formed, this would mean that the fuel nozzle 348, the gaseous fuel supply channel 322, and the dome wall 344 would all need to be replaced. Even if some parts (such as the fuel nozzle 348 and the gaseous fuel supply channel 322) may not need to be replaced at that point in time, the replacement would still have to be completed. When the gaseous fuel supply channel 322 abuts the dome wall 344, the gaseous fuel flow within the gaseous fuel supply channel 322 still serves as a cooling fluid to reduce the temperature of the dome wall 344.

[0075] Advantages of the present disclosure include a burner suitable for use with gaseous H2 fuel. As previously mentioned, gaseous H2 fuel has a higher flame temperature, flashback potential, and autoignition potential than conventional fuels (e.g., fuels without hydrogen). That is, gaseous H2 fuel has a wider flammable range and a faster combustion rate than conventional fuels such as petroleum-based fuels or mixtures of petroleum and synthetic fuels. These high combustion temperatures of gaseous H2 fuel mean that additional insulation is required between the ignited gaseous H2 fuel and the surrounding components of a turbine engine or a gas turbine engine (e.g., the dome wall, inner / outer liners, and other parts of the turbine engine). In addition, additional structures are needed to mitigate flashback and prevent unwanted autoignition; problems not faced by burners using conventional fuels. As described herein, the burner includes a fuel nozzle that provides an isolation layer between the flame and a portion of the combustion zone, keeps the mixed fuel stream below the autoignition temperature, and prevents flashback from occurring within the fuel nozzle. The fuel nozzle further aids in flame shaping, which helps ensure that the liner wall temperature, dome wall temperature, burner exit temperature profile, and the pattern of the flame / gas leaving the burner can be controlled. This control or shaping can further ensure that the combustion zone or other hot zones of the turbine engine do not fail or otherwise become ineffective due to being overheated, thereby increasing the life of the turbine engine. That is, as described herein, the fuel nozzle ensures uniform, consistent, or otherwise desired flame propagation within the burner.

[0076] Compared to conventional fuels, benefits associated with using hydrogen-containing fuels include a more environmentally friendly engine because hydrogen-containing fuels produce fewer carbon pollutants when burned than burners using conventional fuels. For example, a burner including 100% hydrogen-containing fuel (e.g., the fuel is 100% H2) will have zero carbon pollutants. As described herein, the burner can be used in cases where 100% hydrogen-containing fuel is used.

[0077] Advantages of the present disclosure compared to conventional combustion zones include a less complex combustion zone. For example, a conventional combustion zone includes a fuel nozzle having a fuel supply channel that extends through a burner liner and reaches a fuel supply section. Each fuel nozzle in a conventional combustion zone can include a respective fuel supply channel fluidly connected to the fuel supply section. However, the combustion zone as described herein includes a gas fuel channel that fluidly connects one or more fuel nozzles to the fuel supply section without having to extend the gas fuel supply channels of the fuel nozzles through the burner liner, which in turn reduces the complexity of the combustion zone by eliminating the need for each fuel nozzle to include a fuel supply channel that extends through the burner liner and reaches the fuel supply section as included in a conventional combustion zone.

[0078] Within the scope not yet described, the different features and structures of the various embodiments can be used in combination as needed or substituted for each other. All combinations or permutations of the features described herein are covered by this disclosure.

[0079] This written description uses examples to describe aspects of the disclosure described herein, including the best mode, and also enables any person skilled in the art to practice aspects of the disclosure, including making and using any device or system and performing any combined method. The patentable scope of the aspects of the disclosure is defined by the claims and may include other examples that occur to those skilled in the art. If these other examples have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ substantially from the literal language of the claims, then these other examples are intended to fall within the scope of the claims.

[0080] A further aspect is provided by the subject matter of the following clauses:

[0081] A turbine engine, comprising a compression section, a combustion section, and a turbine section in a serial flow arrangement, the combustion section having a burner centerline, the combustion section including: a burner liner and a dome wall, the burner liner having an inner burner liner and an outer burner liner, the burner liner and the dome wall together defining a combustion chamber, the dome wall having a fuel nozzle opening; a housing that at least partially surrounds the burner liner, the housing having at least one opening that defines a fuel port extending therethrough; a fuel nozzle disposed within the fuel nozzle opening, the fuel nozzle having a first body and a second body, the first body defining a centerline axis and a gaseous fuel channel that includes a gaseous fuel outlet discharging into the combustion chamber, the second body being radially spaced from the first body to define a compressed air channel therebetween, the compressed air channel including a compressed air outlet discharging into the combustion chamber; and a gaseous fuel supply channel that extends through the fuel port and reaches the gaseous fuel channel, wherein at least a portion of the gaseous fuel supply channel is formed with the dome wall.

[0082] The turbine engine according to any of the preceding clauses, wherein the gaseous fuel supply channel and the fuel nozzle are integrally formed as a single body.

[0083] The turbine engine according to any of the preceding clauses, wherein the fuel nozzle and the gaseous fuel supply channel are integrally formed with the dome wall.

[0084] A turbine engine according to any of the preceding clauses, wherein the fuel nozzle further comprises an air swirler disposed within the compressed air passage and interconnecting the first body and the second body.

[0085] A turbine engine according to any of the preceding clauses, wherein the gaseous fuel supply passage comprises a swirler section extending through the interior of the air swirler.

[0086] A turbine engine according to any of the preceding clauses, wherein the gaseous fuel supply passage comprises a dome wall inlet section extending along or integrally formed within a respective portion of the dome wall.

[0087] A turbine engine according to any of the preceding clauses, wherein the combustion section comprises a shroud defining a cavity disposed on a side of the dome wall opposite the combustion chamber, wherein the fuel nozzle axially terminates within the cavity.

[0088] A turbine engine according to any of the preceding clauses, wherein the combustion section further comprises a set of flame shaping holes disposed between respective portions of the second body and the dome wall, each flame shaping hole of the set discharging into the combustion chamber at a flame shaping outlet.

[0089] A turbine engine according to any of the preceding clauses, wherein the set of flame shaping holes comprises a plurality of flame shaping holes circumferentially spaced about the centerline axis.

[0090] A turbine engine according to any of the preceding clauses, wherein the gaseous fuel supply passage comprises a first circumferential gaseous fuel manifold, a second circumferential gaseous fuel manifold formed within the second body, and a third circumferential gaseous fuel manifold formed within the first body, the third circumferential gaseous fuel manifold being radially inwardly disposed from the second circumferential gaseous fuel manifold, and the second circumferential gaseous fuel manifold being radially inwardly disposed from the first circumferential gaseous fuel manifold.

[0091] A turbine engine according to any of the preceding clauses, wherein the housing comprises a set of housing divisions defining two or more housing segments.

[0092] A turbine engine according to any of the preceding clauses, wherein the two or more housing segments are axially or circumferentially spaced relative to the burner centerline.

[0093] A turbine engine according to any of the preceding clauses, wherein the housing includes a plurality of openings defining a plurality of fuel ports, and each of the two or more housing segments includes at least one of the plurality of fuel ports.

[0094] A turbine engine according to any of the preceding clauses, wherein the dome wall includes a set of dome wall dividing portions defining two or more dome wall segments.

[0095] A turbine engine according to any of the preceding clauses, wherein at least one of the two or more dome wall segments is radially spaced apart from, circumferentially spaced apart from, or a combination thereof, from each other.

[0096] A turbine engine according to any of the preceding clauses, wherein the set of dome wall dividing portions includes circumferential dome wall dividing portions that divide the dome wall into at least one outer dome wall segment and at least one inner dome wall segment.

[0097] A turbine engine according to any of the preceding clauses, wherein at least one of the inner dome wall segment, the outer dome wall segment, or a combination thereof, includes a fuel nozzle seat that is disposed along the circumferential dome wall dividing portion and is adapted to receive the fuel nozzle.

[0098] A turbine engine according to any of the preceding clauses, wherein the fuel nozzle is included within a plurality of fuel nozzles arranged annularly along the dome wall, and two or more fuel nozzles are fluidly coupled to a single gaseous fuel supply channel.

[0099] A method of operating a combustion section according to any of the preceding clauses, the method including: supplying a gaseous hydrogen fuel stream to the gaseous fuel supply channel through the gaseous fuel channel; and supplying a compressed air stream to the compressed air channel.

[0100] A turbine engine according to any of the preceding clauses, wherein the dome wall and the fuel nozzle are not integrally formed.

[0101] A turbine engine according to any of the preceding clauses, wherein the combustion section further includes a locking portion defining the connection of the dome wall and the fuel nozzle.

[0102] A turbine engine according to any of the preceding clauses, wherein the locking portion includes a protrusion extending from the fuel nozzle and engaging a groove provided along the dome wall.

[0103] A combustion section having a burner centerline, the combustion section comprising: a burner liner and a dome wall, the burner liner having an inner burner liner and an outer burner liner, the burner liner and the dome wall together defining a combustion chamber, the dome wall having a fuel nozzle opening; a housing that at least partially surrounds the burner liner, the housing having at least one opening defining a fuel port extending therethrough; a fuel nozzle disposed within the fuel nozzle opening, the fuel nozzle having a first body and a second body, the first body defining a centerline axis and a gaseous fuel channel, the gaseous fuel channel including a gaseous fuel outlet discharging into the combustion chamber, the second body being radially spaced from the first body to define a compressed air channel therebetween, the compressed air channel including a compressed air outlet discharging into the combustion chamber; and a gaseous fuel supply channel extending through the fuel port and reaching the gaseous fuel channel, wherein at least a portion of the gaseous fuel supply channel is formed together with the dome wall.

[0104] The combustion section according to any of the preceding clauses, wherein the gaseous fuel supply channel and the fuel nozzle are integrally formed as a single body.

[0105] The combustion section according to any of the preceding clauses, wherein the fuel nozzle and the gaseous fuel supply channel are integrally formed with the dome wall.

[0106] The combustion section according to any of the preceding clauses, wherein the fuel nozzle further includes an air swirler disposed within the compressed air channel and interconnecting the first body and the second body.

[0107] The combustion section according to any of the preceding clauses, wherein the gaseous fuel supply channel includes a swirler section extending through the interior of the air swirler.

[0108] The combustion section according to any of the preceding clauses, wherein the gaseous fuel supply channel includes a dome wall inlet section that extends along a corresponding portion of the dome wall or is integrally formed within the corresponding portion of the dome wall.

[0109] The combustion section according to any of the preceding clauses, further comprising a shroud defining a cavity, the cavity being disposed on a side of the dome wall opposite the combustion chamber, wherein the fuel nozzle axially terminates within the cavity.

[0110] The combustion section according to any of the preceding clauses, further comprising a set of flame shaping holes disposed between the second body and a corresponding portion of the dome wall, each flame shaping hole of the set of flame shaping holes discharging into the combustion chamber at a flame shaping outlet.

[0111] A combustion zone according to any of the preceding clauses, wherein the set of flame-forming holes includes a plurality of flame-forming holes circumferentially spaced apart around the centerline axis.

[0112] A combustion zone according to any of the preceding clauses, wherein the gaseous fuel supply channel includes a first circumferential gaseous fuel manifold, a second circumferential gaseous fuel manifold formed in the second body, and a third circumferential gaseous fuel manifold formed in the first body, the third circumferential gaseous fuel manifold being radially inwardly disposed from the second circumferential gaseous fuel manifold, and the second circumferential gaseous fuel manifold being radially inwardly disposed from the first circumferential gaseous fuel manifold.

[0113] A combustion zone according to any of the preceding clauses, wherein the housing includes a set of housing dividing portions defining two or more housing segments.

[0114] A combustion zone according to any of the preceding clauses, wherein the two or more housing segments are axially or circumferentially spaced apart relative to the burner centerline.

[0115] A combustion zone according to any of the preceding clauses, wherein the housing includes a plurality of openings defining a plurality of fuel ports, and each of the two or more housing segments includes at least one of the plurality of fuel ports.

[0116] A combustion zone according to any of the preceding clauses, wherein the dome wall includes a set of dome wall dividing portions defining two or more dome wall segments.

[0117] A combustion zone according to any of the preceding clauses, wherein at least one of the two or more dome wall segments is radially spaced apart from each other, circumferentially spaced apart from each other, or a combination thereof.

[0118] A combustion zone according to any of the preceding clauses, wherein the set of dome wall dividing portions includes a circumferential dome wall dividing portion that divides the dome wall into at least one outer dome wall segment and at least one inner dome wall segment.

[0119] A combustion zone according to any of the preceding clauses, wherein at least one of the inner dome wall segment, the outer dome wall segment, or a combination thereof includes a fuel nozzle seat that is disposed along the circumferential dome wall dividing portion and is adapted to receive the fuel nozzle.

[0120] A combustion zone according to any of the preceding clauses, wherein the fuel nozzle is included within a plurality of fuel nozzles arranged annularly along the dome wall, and two or more fuel nozzles are fluidly coupled to a single gaseous fuel supply channel.

[0121] A method of operating a combustion zone according to any of the preceding clauses, the method comprising: supplying a gaseous hydrogen fuel stream to the gaseous fuel supply channel through the gaseous fuel channel; and supplying a compressed air stream to the compressed air channel.

[0122] A combustion zone according to any of the preceding clauses, wherein the dome wall and the fuel nozzle are not integrally formed.

[0123] A combustion zone according to any of the preceding clauses, further comprising locking portions defining the connection of the dome wall and the fuel nozzle.

[0124] A combustion zone according to any of the preceding clauses, wherein the locking portion includes a protrusion extending from the fuel nozzle and engaging a groove provided along the dome wall.

Claims

1. A turbine engine, characterized in that: include: A compression section, a combustion section, and a turbine section in a series flow arrangement, the combustion section having a combustor centerline, the combustion section comprising: a combustor liner and a dome wall, the combustor liner having an inner combustor liner and an outer combustor liner, the combustor liner and the dome wall together defining a combustion chamber, the dome wall having a fuel nozzle opening; a casing at least partially surrounding the combustor liner, the casing having at least one opening defining a fuel port extending therethrough; A fuel nozzle disposed in the fuel nozzle opening, the fuel nozzle having: a first body defining a centerline axis and a gas fuel gallery including a gas fuel outlet that discharges into the combustion chamber; and a second body radially spaced from the first body to define a compressed air channel therebetween, the compressed air channel including a compressed air outlet that discharges into the combustion chamber; and A gaseous fuel supply channel extends through the fuel port and to the gaseous fuel channel, wherein at least a portion of the gaseous fuel supply channel is formed with the dome wall.

2. The turbine engine according to claim 1, characterized in that in, The gas fuel supply channel and the fuel nozzle are integrally formed as a single body.

3. The turbine engine according to claim 2, characterized in that: in, The fuel nozzle and the gas fuel supply channel are integrally formed with the dome wall.

4. The turbine engine according to claim 1, characterized in that: in, The fuel nozzle further includes an air swirler disposed within the compressed air channel and interconnecting the first body and the second body.

5. The turbine engine according to claim 4, characterized in that in, The gas fuel supply channel includes a swirler section extending through an interior of the air swirler.

6. The turbine engine according to claim 1, characterized in that in, The gas fuel supply channel includes a dome wall inlet section extending along or integrally formed within a corresponding portion of the dome wall.

7. The turbine engine according to claim 1, characterized in that in, The combustion section includes a shroud defining a cavity disposed on a side of the dome wall opposite the combustion chamber, wherein the fuel nozzle terminates axially within the cavity.

8. The turbine engine according to claim 1, characterized in that in, The combustion section further includes a set of flame-shaping holes disposed between the second body and corresponding portions of the dome wall, each flame-shaping hole in the set of flame-shaping holes discharging into the combustion chamber at a flame-shaping outlet.

9. The turbine engine according to claim 8, characterized in that in, The set of flame-shaping holes includes a plurality of flame-shaping holes that are circumferentially spaced about the centerline axis.

10. The turbine engine according to claim 1, characterized in that in, The gas fuel supply channel includes a first circumferential gas fuel manifold, a second circumferential gas fuel manifold formed in the second body, and a third circumferential gas fuel manifold formed in the first body, wherein the third circumferential gas fuel manifold is arranged radially inward from the second circumferential gas fuel manifold, and the second circumferential gas fuel manifold is arranged radially inward from the first circumferential gas fuel manifold.

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