Turbine engine with combustion section

Abstract

A turbine engine has a compression section, a combustion section, and a turbine section in a serial flow arrangement and defining a working airflow path. The combustion section has a circumferential housing, a combustor, and a fuel nozzle. The circumferential housing defines an interior. The turbine engine includes a de-swirler assembly. A de-swirler assembly couples a working airflow path of the compression section to the interior. The turbine engine includes a fuel supply system.

Description

TECHNICAL FIELD

[0001] The present subject matter relates generally to a combustion section for a turbine engine. BACKGROUND

[0002] Turbine engines are 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 can be disposed within the turbine engine and fluidly coupled to a turbine through which the combustion gases flow.

[0003] Historically, hydrocarbon fuels have been used in combustors of turbine engines. Typically, air and fuel are fed into a combustion chamber, the air and fuel are mixed, and then the fuel is combusted in the presence of the air to produce hot gases. The hot gases are then fed into a turbine where the hot gases cool and expand to produce power. Byproducts of fuel combustion typically include environmentally undesirable byproducts such as nitrogen oxides and nitrogen dioxide (collectively, NOx), carbon monoxide (CO), unburned hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to atmospheric ozone), and other oxides including oxides of sulfur (e.g., SO2and SO3). x

[0004] To reduce environmentally undesirable byproducts, other fuels such as hydrogen are being explored. Hydrogen or hydrogen mixed fuels have higher flame temperatures than traditional hydrocarbon fuels. That is, hydrogen or hydrogen mixed fuels generally have a wider flammability range and faster burn rates than traditional hydrocarbon-based fuels. BRIEF DESCRIPTION OF DRAWINGS

[0005] A complete and enabling disclosure of the present disclosure, directed to one of ordinary skill in the art, is set forth in the specification, which works together with the drawings, in which:

[0006] Figure 1 is a schematic cross-sectional view of a turbine engine having a compressor section, a combustion section, and a turbine section, in accordance with various aspects described herein.

[0007] Figure 2 is a combustion section of Figure 1 is a schematic view of a combustor of

[0008] Figure 3 is a schematic cross-sectional view of a portion of an exemplary turbine engine suitable for use as Figure 1 the turbine engine of

[0009] ​Figure 4 is in accordance with various aspects described herein Figure 3 is a schematic cross-sectional view of a de-swirler assembly of

[0010] Figure 5 is in accordance with various aspects described herein Figure 1 is a schematic cross-sectional view of an exemplary turbine engine of a turbine engine of DETAILED DESCRIPTION

[0011] Aspects of the disclosure described herein relate to turbine engines having a working airflow path, a de-swirler assembly, a combustion section, and a fuel supply system. The combustion section includes a circumferential casing, a combustor, and a set of fuel nozzles. The circumferential casing defines an interior. The combustor is located within the interior. The de-swirler assembly opens into the interior and fluidly couples the working airflow path to a respective portion of the interior. The de-swirler assembly includes a de-swirler and a diffuser. The de-swirler and the diffuser include a set of de-swirler walls and a set of diffuser walls, respectively, thereby defining a set of de-swirler channels and a set of diffuser channels, respectively, therebetween. The fuel supply system includes a set of fuel channels extending through at least one wall of the set of diffuser walls or the set of de-swirler walls. The fuel supply system includes a set of fuel line branches extending within the interior and fluidly coupled to at least a portion of the set of fuel nozzles.

[0012] The set of fuel channels and the set of fuel line branches formed within the de-swirler assembly are formed as a single body. A joint is formed between the set of fuel line branches and the set of fuel nozzles. The joint forms a gas-tight seal. As used herein, a joint of a fuel supply system is a coupling or structure between the fuel supply system and a corresponding anchor point of the combustion chamber (e.g., at least a portion of the set of fuel nozzles).

[0013] The fuel supply system is particularly advantageous for use when supplying a combustion chamber with a hydrogen-containing fuel stream (hereinafter referred to as "H2 fuel") via the fuel supply system. The H2 fuel can include a gaseous H2 fuel, a liquid H2 fuel, or a combination thereof. The H2 fuel stream can also be mixed with other fuels or fluids such as, but not limited to, natural gas, coke oven gas, diesel, Jet-A, etc. H2 fuel has lower carbon emissions compared to conventional fuels (e.g., carbon fuels, petroleum fuels, etc.). However, H2 fuel has a higher combustion temperature and is relatively more unstable compared to conventional fuels. For example, H2 fuel diffuses faster and has a tendency to leak through joints formed within the fuel supply system. In other words, H2 fuel is highly prone to leaking into undesirable locations within the combustion section of a conventional fuel supply system that utilizes two or more elements coupled to one another. The disclosed fuel supply system, including the set of fuel channels and the set of fuel line branches formed as a single body, minimizes the total number of joints within the fuel supply system and between the fuel supply system and other portions of the combustion section. The minimization of joints, in turn, minimizes the likelihood of H2 fuel leaking from the fuel supply system and into undesirable portions of the combustion section associated with utilizing conventional fuel supply systems and H2 fuel.

[0014] For purposes of illustration, the present disclosure will be described with respect to a turbine engine. It will be understood, however, that the disclosed aspects described herein are not so limited, and that the combustion section described herein can be implemented in engines including, but not limited to, turbojet engines, turboprop engines, turboshaft engines, and turbofan engines. The disclosed aspects discussed herein can have universal applicability within non-aircraft engines having combustors, such as within other mobile applications and non-mobile industrial, commercial, and residential applications.

[0015] The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Furthermore, unless otherwise explicitly provided, none of the examples described herein are intended to be exclusive of other examples described herein. In addition, unless otherwise indicated, each of the examples described herein is to be considered exemplary in nature.

[0016] As can be used herein, the terms "first" and "second" can be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

[0017] The terms "forward" and "aft" refer to relative positions within a gas turbine engine or vehicle and refer to the normal operating attitude of the gas turbine engine or vehicle. For example, with respect to a gas turbine engine, forward refers to a position closer to the engine inlet and aft refers to a position closer to the engine exhaust.

[0018] As used herein, the term "upstream" refers to a direction opposite to the direction of fluid flow, while the term "downstream" refers to a direction the same as the direction of fluid flow. The terms "forward" or "front" mean in front of something, and "rearward" or "rear" mean behind something. For example, when used in the context of fluid flow, forward / front can mean upstream, and rearward / rear can mean downstream.

[0019] The term "fluid" can be a gas or a liquid, or a combination thereof. The term "fluidly coupled" means that a fluid is able to establish a connection between designated areas. The term "fluidly exposed" means that one or more portions of an object are in contact with a fluid.

[0020] Further, 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 a direction along a ray extending between a central longitudinal axis of the engine and an outer periphery of the engine.

[0021] In the context of a gas turbine engine, the term "nozzle" is used in various ways. In the present application, "nozzle" refers to a component having a portion fluidly coupled to a fuel supply and having at least one portion fluidly coupled to a combustion chamber.

[0022] All directional references (e.g., radial, axial, upper, lower, right, left, front, rear, top, bottom, above, below, vertical, horizontal, upstream, downstream, forward, rearward, etc.) are used only for identification purposes to aid the reader's understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of the disclosure described herein. Connection references (e.g., attached, coupled, and connected) are to be construed broadly and can be understood as referring to an element collection having at least one intermediate structure attached between the elements, as well as directly connecting elements to one another. As such, connection references do not necessarily mean the two elements are directly connected to each other without intervening structure. The exemplary drawings are for illustrative purposes only. The dimensions, positions, order and relative sizes reflected in the attached drawings can vary.

[0023] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise. Also, as used herein, the term "set" or "subset" or "a set" of elements or "subset" of elements can be any number of elements, including only one.

[0024] The use of "and" and "or" will be construed to mean "and / or" unless such a construction is not consistent with the context. Further, when "comprising" is used, it is not meant to be limiting, but rather to encompass the claimed device, such alternatives, modifications, additions or equivalents as fall within the scope of the claims.

[0025] Figure 1is a schematic illustration of a turbine engine 10. As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 includes at least a compression section 12, a combustion section 14, and a turbine section 16 in a serial flow arrangement. A drive shaft 18 rotationally couples the compression section 12 and the turbine section 16 such that rotation of one affects rotation of the other and defines a rotational axis or engine centerline 20 of the turbine engine 10.

[0026] The compression section 12 can include a low pressure (LP) compressor 22 and a high pressure (HP) compressor 24 fluidly coupled to one another in series. The turbine section 16 can include an LP turbine 28 and a HP turbine 26 fluidly coupled to one another in series. The drive shaft 18 operably couples the LP compressor 22, the HP compressor 24, the LP turbine 28, and the HP turbine 26 together. Alternatively, the drive shaft 18 can include an LP drive shaft (not shown) and a HP drive shaft (not shown). The LP drive shaft couples the LP compressor 22 to the LP turbine 28, and the HP drive shaft couples the HP compressor 24 to the HP turbine 26. An LP train is defined as the combination of the LP compressor 22, the LP turbine 28, and the LP drive shaft such that rotation of the LP turbine 28 applies a driving force to the LP drive shaft, which in turn rotates the LP compressor 22. A HP train is defined as the combination of the HP compressor 24, the HP turbine 26, and the HP drive shaft such that rotation of the HP turbine 26 applies a driving force to the HP drive shaft, which in turn rotates the HP compressor 24.

[0027] The compression section 12 includes 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, which 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 casing, which can extend circumferentially around the turbine engine 10. It should be understood that the representation of the compression section 12 is merely schematic and there can be any number of stages. Further, it is contemplated that there can be any other number of components within the compression section 12.

[0028] Similar to the compression section 12, the turbine section 16 includes a plurality of axially spaced stages, with each stage having 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, which 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 to a casing in a circumferential manner. It is 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.

[0029] The combustion section 14 is serially disposed between the compression section 12 and the turbine section 16. The combustion section 14 is fluidly coupled to at least a portion of the compression section 12 and the turbine section 16 such that the combustion section 14 at least partially fluidly couples the compression section 12 to the turbine section 16. As a non-limiting example, the combustion section 14 can be fluidly coupled to the HP compressor 24 at an upstream end of the combustion section 14 and fluidly coupled to the HP turbine 26 at a downstream end of the combustion section 14.

[0030] 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, the air is compressed at the compression section 12, defining compressed air. The compressed air then flows into the combustion section 14, where the compressed air is mixed with fuel and ignited, generating combustion gases. The HP turbine 26 extracts some work from these combustion gases, the HP turbine 26 driving the HP compressor 24. The combustion gases are exhausted into the LP turbine 28, the LP turbine 28 extracting additional work to drive the LP compressor 22, and the exhaust is ultimately exhausted from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The driving of the LP turbine 28 drives the 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 flows through the fan, the compression section 12, the combustion section 14, and the turbine section 16 of the turbine engine 10.

[0031] Figure 2 A cross-sectional view of the combustion section 14 along line II-II of Figure 1 has been removed for illustrative purposes. The combustion section 14 includes a circumferential housing 36 and a combustor 34. The circumferential housing 36 includes a centerline 30. The centerline 30 can be coincident with an engine centerline 20 Figure 1 of the turbine engine 10 Figure 1 of the turbine engine 10 Figure 1) aligned or offset. The circumferential housing 36 defines an interior 37. The combustor 34 is located within the interior 37. The combustor 34 includes an annular liner 38 and a dome wall 44. The annular liner 38 can include an outer liner 40 and an inner liner 42. The dome wall 44 interconnects the inner liner 42 and the outer liner 40. The dome wall 44 and the annular liner 38 collectively form a combustion chamber 46. The combustor 34 can have a can, can-annular, or annular arrangement depending on the type of engine in which the combustor 34 is located. In a non-limiting example, the combustor 34 can have a combined arrangement located within a circumferential housing 36 of a turbine engine 10 as described further herein. As shown by way of example, the annular liner 38 can be annular. A compressed air passage 48 can be at least partially defined by both the annular liner 38 and the circumferential housing 36. The compressed air passage 48 is located within the interior 37.

[0032] The dome wall 44 includes a set of fuel nozzle openings 78. The combustion section 14 includes a set of fuel nozzles 32 extending through the set of fuel nozzle openings 78. The set of fuel nozzles 32 is annularly arranged about the centerline 30. The set of fuel nozzles 32 is fluidly coupled to the combustion chamber 46. Each fuel nozzle of the set of fuel nozzles 32 includes a fuel nozzle centerline 31.

[0033] Figure 3 is a schematic cross-sectional view of an exemplary turbine engine 100 suitable for use as Figure 1 the turbine engine 10. The turbine engine 100 is similar to the turbine engine 10; therefore, like parts will be identified with like names and it will be understood that the description of the turbine engine 10 applies to the turbine engine 100 unless otherwise stated.

[0034] The turbine engine 100 includes an engine centerline 101 and a combustion section 102. The combustion section 102 includes a circumferential housing 104, a fuel supply system 140, and a combustor 106. The combustion section 102 includes a centerline 110. As shown, the centerline 110 is aligned with the engine centerline 101. However, it will be understood that at least a portion of the centerline 110 can be offset from the engine centerline 101. The circumferential housing 104 defines an interior 108.

[0035] The circumferential housing 104 can include an inner circumferential housing 176 and an outer circumferential housing 178. The interior 108 is radially formed therebetween.

[0036] The combustor 106 can include an annular liner 116 and a dome wall 122. The annular liner 116 and the dome wall 122 collectively form a combustion chamber 124. The annular liner 116 includes an inner liner 118 and an outer liner 120. The dome wall 122 interconnects the inner liner 118 and the outer liner 120. It will be understood that the combustor 106 can have various configurations. As a non-limiting example, the dome wall 122 can be excluded and the inner liner 118 can extend from the outer liner 120.

[0037] The combustion section 102 includes a set of fuel nozzles 130. Each fuel nozzle of the set of fuel nozzles 130 opens at a fuel nozzle outlet 132 to a respective portion of the combustion chamber 124. Each fuel nozzle of the set of fuel nozzles 130 can include a compressed air inlet 131 adapted to feed a flow of compressed air through the respective portion of the fuel nozzle 130. For example, the compressed air inlet 131 can be a swirler adapted to impart a swirl to a fluid flow that flows through the compressed air inlet 131. The amount of swirl of the fluid flow that flows through or past the compressed air inlet 131 is quantified by a swirl number. The swirl number is defined as an integral of the tangential momentum to the axial momentum of the fluid flow downstream of the respective compressed air inlet 131. The compressed air inlet 131 can produce a swirled air flow having a swirl number greater than 0.2 and less than or equal to 1.5.

[0038] While only a single fuel nozzle is shown, the set of fuel nozzles 130 includes any number of two or more fuel nozzles. The set of fuel nozzles 130 can extend through various portions of the combustor 106. As a non-limiting example, at least one fuel nozzle of the set of fuel nozzles 130 can extend through a portion of the annular liner 116, the dome wall 122, or a combination thereof.

[0039] The combustor 106 is located within the interior 108. At least a portion of the inner liner 118 can be radially inward from the inner peripheral shell 176 relative to the centerline 110. At least a portion of the outer liner 120 can be radially inward from the outer peripheral shell 178 relative to the centerline 110. The compressed air passage 128 is formed between the peripheral shell 104 and the combustor 106.

[0040] The combustor 106 is coupled to the circumferential housing 104 such that the combustor 106 is suspended within the interior 108. The combustor 106 is coupled to the circumferential housing 104 by any suitable method. As a non-limiting example, the combustion section 102 includes a first flange 158 and a combustor arm 156. The first flange 158 extends from a respective portion of the annular liner 116. The combustor arm 156 includes a second flange 157 in contact with the first flange 158. At least one of the first flange 158 and the combustor arm 156 are in frictional contact with one another or otherwise coupled to one another by any suitable coupling method such as, but not limited to, welding, bolting, bonding, fastening, etc. The combustor arm 156 extends from the combustor 106 (e.g., radially outward and forward) and to a respective portion of the circumferential housing 104 (e.g., the inner circumferential housing 176, the outer circumferential housing 178, or a combination thereof). The combustor arm 156 can be coupled to at least one of a respective portion of the combustor 106, a respective portion of the circumferential housing 104, or a combination thereof by any suitable method such as, but not limited to, welding, bolting, bonding, fastening, frictional contact, bonding, etc. Alternatively, the combustor arm 156 can be integrally formed with at least one of a respective portion of the combustor 106, a respective portion of the circumferential housing 104, or a combination thereof.

[0041] The turbine engine 100 includes an engine housing 180. The engine housing 180 defines a working airflow path 182 of a compression section (e.g., the compression section 12 of Figure 1 the turbine engine 100) and a turbine section (e.g., the turbine section 16 of Figure 1 the turbine engine 100).

[0042] The turbine engine 100 includes a de-swirler assembly 134. The de-swirler assembly 134 includes a de-swirler 135 and a diffuser 136. The diffuser 136 is disposed upstream of the de-swirler 135. The de-swirler 135 and the diffuser 136 each include a set of walls and a set of channels. The de-swirler 135 includes a set of de-swirler walls 137 and a set of de-swirler channels 141. The set of de-swirler walls 137 are circumferentially spaced apart relative to the engine centerline 101. The set of de-swirler channels 141 are circumferentially formed between circumferentially opposite portions of the set of de-swirler walls 137. The diffuser 136 includes a set of diffuser walls 138 and a set of diffuser channels 139. The set of diffuser walls 138 are circumferentially spaced apart relative to the engine centerline 101. The set of diffuser channels 139 are circumferentially formed between circumferentially opposite portions of the set of diffuser walls 138. The set of diffuser channels 139 open to the set of de-swirler channels 141. The de-swirler assembly 134 includes a de-swirler assembly centerline 143 that extends through the set of diffuser channels 139 and the set of de-swirler channels 141.

[0043] The diffuser 136 can be coupled to the deswirler 135. As a non-limiting example, the diffuser 136 and the deswirler 135 can be defined by separate bodies connected to each other via any suitable coupling method (such as, but not limited to, adhesive, welding, fastening, threaded connection, bolted connection, etc.). Alternatively, the diffuser 136 and the deswirler 135 can be integrally formed, such that the deswirler assembly 134 is formed as a single, single body.

[0044] Fuel supply system 140 is fluidly connected to fuel source 166 via fuel supply section 144 (shown in dashed lines). Fuel supply section 144 may include a single conduit or multiple conduits extending from fuel source 166. Fuel source 166 is any suitable container or vessel configured to hold a quantity of fuel in liquid, solid, or gaseous form. Fuel source 166 may be located within or outside of turbine engine 100. As a non-limiting example, turbine engine 100 may be coupled to the wing of an aircraft, and fuel source 166 may be located within the wing.

[0045] Fuel supply system 140 includes a body 145. Body 145 is defined as a series of continuous walls, conduits, or pipes defining fluid passages within fuel supply system 140. Fuel supply system 140 includes a set of fuel channels 142 and a set of fuel line branches 146. Body 145 defines the set of fuel channels 142 and the set of fuel line branches 146. Fuel supply system 140 may also include one or more distribution manifolds or chambers, such as an external chamber 150 located outside interior 108 and an internal chamber 152 located within interior 108. Body 145 may define at least one of the internal chamber 152 or the external chamber 150.

[0046] The set of fuel channels 142 is located within a corresponding portion of the decyclone assembly 134. The set of fuel channels 142 may include any number of one or more fuel channels. As a non-limiting example, the set of fuel channels 142 may include multiple fuel channels. An external gas chamber 150 (if included) may be used to distribute fluid received from the fuel supply section 144 to one or more fuel channels in the set of fuel channels 142. As shown, the set of fuel channels 142 is formed as straight channels extending through a corresponding portion of the decyclone assembly 134. As a non-limiting example, the set of fuel channels 142 extends through a corresponding wall in the set of walls of the decyclone assembly 134. As a non-limiting example, the set of fuel channels 142 extends through a corresponding portion of the set of diffuser walls 138. However, it will be understood that the set of fuel channels 142 may extend through a portion of at least one of the set of diffuser walls 138, the set of decyclone walls 137, or combinations thereof. However, it will be understood that the set of fuel channels 142 can have various structures. As a non-limiting example, the set of fuel channels 142 may include curved or S-shaped channels.

[0047] The outer chamber 150 may extend circumferentially around the engine centerline 101. The inner chamber 152 may extend circumferentially around the centerline 110. As a non-limiting example, the outer chamber 150 and the inner chamber 152 may extend approximately greater than or equal to 25% and less than or equal to 100% of the circumferential range of the centerline 110. The outer chamber 150 and the inner chamber 152 may each be formed as a duct or pipe extending approximately less than the entire circumferential range of the engine centerline 101 or the centerline 110. Alternatively, the outer chamber 150 and the inner chamber 152 may each be formed as a duct or pipe extending approximately less than the entire circumferential range of the engine centerline 101 or the centerline 110. The outer chamber 150 and the inner chamber 152 may be formed as a continuous duct or pipe. Alternatively, the outer chamber 150 and the inner chamber 152 may each consist of a plurality of segments circumferentially spaced apart from each other relative to the engine centerline 101 or centerline 110.

[0048] Each fuel line branch in the group of fuel line branches 146 extends from one of the group of fuel channels 142 or internal air chambers 152 (if included) to a corresponding fuel nozzle in the group of fuel nozzles 130. Any number of two or more fuel line branches in the group of fuel line branches 146 may be present. As a non-limiting example, each fuel nozzle in the group of fuel nozzles 130 may be fluidly coupled to a corresponding fuel line branch in the group of fuel line branches 146. Therefore, the total number of fuel line branches in the group of fuel line branches 146 may be equal to the total number of fuel nozzles in the group of fuel nozzles 130. Internal air chambers 152 (if included) may be used to distribute fluid flow within internal air chambers 152 from the group of fuel channels 142 to one or more fuel line branches in the group of fuel line branches 146.

[0049] Each fuel line branch in the group of fuel line branches 146 includes a first leg 184, a second leg 186, and a bend 188. The first leg 184 extends between the internal gas chamber 152 and the bend 188. The bend 188 interconnects the first leg 184 and the second leg 186. The bend 188 is generally defined as any transition between the first leg 184 and the second leg 186.

[0050] For illustrative purposes, a first transition 195 is shown in dashed lines between the first leg 184 and the internal air chamber 152, a second transition 196 is shown in dashed lines between the first leg 184 and the bend 188, and a third transition 198 is shown in dashed lines between the bend 188 and the second leg 186. Each leg of the plurality of fuel line branches includes a branch centerline 192. A leg angle 194 is formed between the branch centerline 192 at the second transition 196 and the branch centerline 192 at the third transition 198. The leg angle 194 is greater than or equal to 30 degrees and less than or equal to 150 degrees. However, the first leg 184 and the second leg 189 may extend in any suitable direction. In some cases, it is conceivable that at least a portion of the branch centerline 192 within the first leg 184 and at least a portion of the branch centerline 192 within the second leg 186 are positioned along two or more planes that extend along the centerline 110 and intersect the branch centerline 192 at the respective portions.

[0051] Although described with respect to the set of fuel line branches 146 extending between the internal gas chamber 152 and the set of fuel nozzles 130, it will be understood that at least one of the fuel line branches 146 may extend between a corresponding fuel channel in the set of fuel channels 142 and a corresponding portion of the set of fuel nozzles 130. As a non-limiting example, the internal gas chamber 152 may be omitted from the fuel supply system 140.

[0052] Fuel supply system 140 extends into combustion section 102. In other words, a first portion of fuel supply system 140 is located within combustion section 102, while a second portion is located outside combustion section 102. An internal gas chamber 152 and the set of fuel line branches 146 are located within combustion section 102. The set of fuel channels 142 and the optional external gas chamber 150 can be integrally formed with combustion section 102 (described in further detail below) and thus can be formed as part of combustion section 102.

[0053] At least a portion of the fuel supply system 140 is formed as a single, unified body. Specifically, body 145 (a combination of the set of fuel channels 142 and the set of fuel line branches 146, as well as the internal gas chamber 152 and the external gas chamber 150 (when included)) is formed as a single body. For example, the set of fuel channels 142, the internal gas chamber 152 (when included), the external gas chamber 150 (when included), and the set of fuel line branches 146 are formed as a single body, hereinafter referred to as the "single body of fuel supply system 140". Fuel supply system 140 can be manufactured by any suitable method (such as, but not limited to, 3D printing, casting, etc.). Although not shown, it will be understood that body 145 may include two or more components connected to each other in a fluid-impermeable manner. As a non-limiting example, the set of fuel channels 142 may be formed as a body separate from the set of fuel line branches 146. The set of fuel channels 142 and the set of fuel line branches 146 can then be joined together, for example, by welding, brazing, or a combination thereof, to form a body 145. When the set of fuel channels 142 and the set of fuel line branches 146, as well as the inner gas chamber 152 and the outer gas chamber 150 (when included), are formed by joining, additive manufacturing, casting, etc., they are referred to as being formed as a single body, wherein fluid within the body 145 cannot flow out of the body 145 along the transitions between the various components of the body 145.

[0054] A set of connectors 154 is formed between each fuel line branch in the set of fuel line branches 146 and a corresponding fuel nozzle in the set of fuel nozzles 130. The set of connectors 154 defines a physical connection between the single body of the fuel supply system 140 and the combustion section 102. This physical connection can be made by any suitable connection method, such as, but not limited to, welding, bolting, bonding, bonding, fastening, etc. Although described with respect to a corresponding fuel nozzle directly connected to the set of fuel nozzles 130, it will be understood that the corresponding fuel nozzle may be omitted, and at least one fuel line branch in the plurality of fuel line branches 146 may be connected to and extend through a corresponding portion of the liner 118, liner 120, dome wall 122, or a combination thereof.

[0055] It should be understood that the set of connectors 154 is located at a position where the internal conduit or passage of the body 145 of the fuel supply system 140 is fluidly connected to a fluid conduit or passage located outside the fuel supply system 140. For example, the set of connectors 154 is formed at a position where the set of fuel line branches 146 leads to a corresponding portion of the combustion chamber 124 (e.g., through at least a portion of the set of fuel nozzles 130, dome wall 122, inner liner 118, or outer liner 120).

[0056] The deswirler assembly 134 defines a fluid connection between the working airflow path 182 and the compressed air passage 128 of the combustion section 102. In other words, the working airflow path 182 of the upstream portion of the turbine engine 100 (e.g., the compression section) leads to the diffuser channel 139, which in turn leads to the deswirler channel 141. The deswirler channel 141 leads to the compressed air passage 128 of the combustion section 102.

[0057] At least a portion of the deswirl assembly 134 is formed by the engine housing 180. As a non-limiting example, the entire deswirl assembly 134 is integrally formed with the circumferential housing 104 as a single body. It is also contemplated that at least a portion of the fuel supply system 140 may be integrally formed with the circumferential housing 104 and the deswirl assembly 134. For example, the single body of the fuel supply system 140, the circumferential housing 104, and the deswirl assembly 134 may be formed as a single body.

[0058] During operation, the working airflow (Fw) originates from the compression section (e.g., Figure 1 The gas is extracted from the compression section 12) and supplied to the diffuser channel 139 via the working gas path 182. The diffuser channel 139 is formed to reduce the velocity of the working gas (Fw). [The remaining text appears to be incomplete and requires further context.] Figure 4 The formation of the diffuser channel 139 is described in more detail. The working airflow (Fw) within the diffuser 136 is then supplied to the decyclone channel 141. The decyclone wall 137 is oriented such that the working airflow (Fw) supplied through the decyclone channel 141 enters the compressed air passage 128 as a decyclone airflow (Fc) with zero tangential momentum. Further details regarding... Figure 4 The orientation of the set of decyclone walls 137 that enables the working airflow (Fw) to deswirl is described in more detail.

[0059] Further reference Figure 3At least a portion of the deswirl airflow (Fc) is supplied to the downstream portion (e.g., the turbine section) of the turbine engine 100 via compressed air passage 128. At least a portion of the deswirl airflow (Fc) is supplied to the combustion chamber 124 through at least one of the compressed air inlets 131 of the set of fuel nozzles 130, a series of holes or passages (not shown) formed in a portion of the combustor 106 (e.g., at least one of the annular bushing 116 or the dome wall 122), or a combination thereof.

[0060] Fuel flow (Ff) is drawn from fuel source 166 and supplied to fuel supply section 144. Fuel flow (Ff) within fuel supply section 144 is supplied to the set of fuel channels 142. Fuel flow (Ff) flows through outer chamber 150 (if included) as a first circumferential fuel flow (Ffc1) supplied to two or more circumferentially spaced fuel channels in the set of fuel channels 142. Fuel flow (Ff) from the set of fuel channels 142 is supplied to the set of fuel line branches 146. Fuel flow (Ff) flows through inner chamber 152 (if included) as a second circumferential fuel flow (Ffc2) supplied to two or more circumferentially spaced fuel line branches in the set of fuel line branches 146. Fuel flow (Ff) within the set of fuel line branches 146 is supplied to at least a portion of the set of fuel nozzles 130. The fuel stream (Ff) is then supplied to the combustion chamber 124, where it is ignited to generate a flame within the combustion chamber 124. It will be understood that the fuel stream (Ff) may be mixed with a corresponding portion of the deswirl gas stream (Fc) prior to ignition.

[0061] The assembly 154 is configured to be hermetically sealed. In other words, the assembly 154 is configured to restrict or otherwise prevent the flow of fuel (Ff) out of the assembly 154 and into the compressed air passage 128.

[0062] Some fuel tends to flow through joints formed within the corresponding fuel supply system. Specifically, H2 fuel tends to leak through or otherwise flow through joints within the corresponding fuel supply system. In other words, even if the joint is formed to be hermetically sealed, at least a portion of the H2 fuel can still flow through the joint and into the compressed air passage 128. It is desirable to limit the total number of physical joints or connectors between the fuel supply system 140 and the combustion section 102, as well as within the fuel supply system 140 itself. It will be understood that the single body of the fuel supply system 140 limits the total number of joints 154 in this set within the combustion section 102, which limits the location from which H2 fuel can leak from the fuel supply system 140 and enter the compressed air passage 128. In other words, the single body of the fuel supply system 140 makes the fuel supply system 140 particularly suitable for use when H2 fuel is used in the fuel flow (Ff).

[0063] Limiting the amount of fuel flow (Ff) leaking from the fuel supply system 140 into the compressed air passage 128 can be achieved by limiting the total number of joints between the body 145 and the combustion section 102. Limiting the leakage of fuel flow (Ff) increases the ratio between the fuel supplied to the combustion chamber 124 and the fuel leaking into the compressed air passage 128. Increasing the ratio between the fuel supplied to the combustion chamber 124 and the fuel leaking into the compressed air passage 128 reduces fuel waste because a higher ratio results in a higher percentage of fuel being burned to generate combustion gases supplied to the downstream portion of the turbine engine 100. Therefore, a higher ratio between the fuel supplied to the combustion chamber 124 and the fuel leaking into the compressed air passage 128 leads to higher overall efficiency of the turbine engine 100.

[0064] It is conceivable that the temperature of the working airflow (Fw) supplied to the compressed air passage 128 as a deswirl airflow (Fc) can be approximately 1000°F. The relatively high heat of the deswirl airflow (Fc) causes the portion of the fuel supply system 140 in contact with the deswirl airflow (Fc) (e.g., the set of fuel line branches 146) to undergo thermal expansion. The set of fuel line branches 146 is formed to ensure an airtight seal is maintained at the set of joints 154.

[0065] Furthermore, each of the plurality of fuel line branches 146 is designed such that the attenuation distance of the fuel line branch is greater than the axial distance (Ad) extending circumferentially into the housing 176. The total distance that each of the plurality of fuel line branches 146 extends axially along the corresponding branch centerline 192 is defined as the attenuation distance. The structure in which the axial distance (Ad) is less than the attenuation distance preloads the plurality of fuel line branches 146 onto the corresponding portions of the combustion section 102. This, in turn, helps to maintain contact between the plurality of fuel line branches 146 and the corresponding portions of the combustion section 102 (and to achieve an hermetically sealed relationship with the corresponding portions of the combustion section 102).

[0066] The temperature of the fuel flow (Ff) within the set of fuel channels 142 is lower than the temperature of the working gas flow (Fw) within the decyclone assembly 134. At least one of the set of decyclone walls 137, the set of diffuser walls 138, or combinations thereof may be made of a thermally conductive material. Therefore, heat from the working gas flow (Fw) within the decyclone assembly 134 can be transferred through at least one of the set of decyclone walls 137, the set of diffuser walls 138, or combinations thereof to the fuel flow (Ff) within the set of fuel channels 142. In other words, at least one of the set of decyclone walls 137, the set of diffuser walls 138, or combinations thereof may serve as a heat exchanger that transfers heat from the working gas flow (Fw) within the decyclone assembly 134 to the fuel flow (Ff) before the fuel flow (Ff) is supplied to the set of fuel line branches 146, the internal gas chamber 152, or both. It is conceivable that the working gas flow (Fw) within the decyclone assembly 134 can heat the fuel flow (Ff) within the set of fuel channels 142 to a certain extent, causing a phase change in the fuel flow (Ff). As a non-limiting example, a liquid fuel flow can be supplied as a fuel flow (Ff) through the fuel supply section 144, flowing through the set of fuel channels 142, and being heated to a degree that causes the liquid fuel to phase change into gaseous fuel. The gaseous fuel can then be supplied as a fuel flow (Ff) to the set of fuel line branches 146. Ensuring a phase change allows the fuel source 166 to supply liquid fuel and allows the fuel flow (Ff) within the combustion chamber 124 to be gaseous fuel. It is conceivable that the density of liquid fuel is higher than that of gaseous fuel. Therefore, a larger mass of liquid fuel can be stored within the fuel source 166 compared to a given volume of gaseous fuel. However, gaseous fuel is easier to shape and diffuse than liquid fuel to produce the desired flame profile within the combustion chamber 124.

[0067] The structure of the set of fuel channels 142 can be based on the desired amount of heat transfer between the working airflow (Fw) within the decyclone assembly 134 and the fuel flow (Ff) within the set of fuel channels 142. For example, the set of fuel channels 142 can take a serpentine route (e.g., have an S-shaped pattern) within the decyclone assembly 134, thereby increasing the total time of thermal contact between the fuel flow (Ff) within the set of fuel channels 142 and the working airflow (Fw) within the decyclone assembly 134; thus increasing the overall heating of the fuel flow (Ff) within the set of fuel channels 142.

[0068] Body 145 can be relatively easily removed from the rest of the turbine engine 100. As a non-limiting example, during continuous use of the turbine engine 100, thermal deformation of the fuel supply system 140 within the compressed air passage 128 can cause thermal stress or other thermal fatigue along portions of the fuel supply system 140. It is conceivable that the areas experiencing the greatest thermal stress are those in thermal contact with the working airflow (Fw) (e.g., the set of fuel channels 142) and the deswirl airflow (Fc) (e.g., the internal air chamber 152 and the set of fuel line branches 146). Therefore, the ability to remove at least body 145 from the turbine engine 100 allows for the replacement of at least body 145, rather than a larger section of the turbine engine 100 (e.g., combustion section 102).

[0069] It is conceivable that using a body 145 that can be relatively easily removed from the combustion section 102 is particularly advantageous for use with H2 fuel. H2 fuel has been found to adversely affect materials in contact with it compared to conventional fuels. Specifically, H2 fuel causes hydrogen embrittlement, which causes materials in contact with H2 fuel to degrade at a faster rate than when using conventional fuels. Therefore, when using H2 fuel, the fuel supply system 140 may degrade faster due to hydrogen embrittlement than other parts of the combustion section 102. This faster degradation of the fuel supply system 140, in turn, means that the lifespan of the fuel supply system 140 may be shorter than that of other parts of the combustion section 102. Forming a fuel supply system 140 with a body 145 allows for relatively easy removal of the body 145 from the combustion section 102, thus enabling replacement of the body 145.

[0070] Figure 4 This was observed along the centerline 143 of the decyclone assembly. Figure 3 A schematic cross-sectional view of the deswirl diffuser assembly 134. The diffuser channel set 139 expands circumferentially as it travels radially outward from the engine centerline 101. In other words, the more radially the diffuser channel set 139 moves away from the engine centerline 101, the more it tapers outward. The diffuser wall set 138 can take any suitable structure. As a non-limiting example, the diffuser wall set 138 can be formed as a set of airfoils having a leading edge 168, a trailing edge 170, a pressure side 172, and a suction side 174. Alternatively, the diffuser wall set 138 can be formed as a continuous ring or annulus having a series of channels more similar to the diffuser wall set 138.

[0071] The group of fuel channels 142 is formed within at least one of the group of diffuser walls 138, the group of decyclone walls 137, or combinations thereof. The group of fuel channels 142 is formed within at least one subgroup of at least one of the group of diffuser walls 138, the group of decyclone walls 137, or combinations thereof. As a non-limiting example, the group of fuel channels 142 is formed within a half of at least one of the group of diffuser walls 138, the group of decyclone walls 137, or combinations thereof. Alternatively, the group of fuel channels 142 may be formed within any number or one or more walls of at least one of the group of diffuser walls 138, the group of decyclone walls 137, or combinations thereof. The group of fuel channels 142 is arranged in various patterns. As shown by the dashed lines, the group of fuel channels 142 is located in every other wall of the group of decyclone walls 137. Therefore, the group of fuel channels 142 can be uniformly circumferentially spaced. However, it will be understood that the set of fuel channels 142 may have various patterns associated with the set of diffuser walls 138 and the set of decyclone walls 137. For example, the set of fuel channels 142 may be provided in every other decyclone wall 137 or diffuser wall 138, every three decyclone walls 137 or diffuser walls 138, etc.

[0072] During operation, a working gas flow (Fw) is supplied to diffuser 136. As shown, the working gas flow (Fw) has a circumferential component before entering diffuser 136. The working gas flow (Fw) flows within the diffuser channel 139. As the working gas flow (Fw) flows through the diffuser channel 139, its velocity decreases and its static pressure increases due to the expansion characteristics (volume increase) of the diffuser channel 139. The working gas flow (Fw) from the diffuser channel 139 is then supplied to deswirler 135. The working gas flow (Fw) follows the curvature defined by pressure side 172 within the deswirler channel 141. The deswirler wall 137 is oriented such that the working gas flow (Fw) within the deswirler channel 141 is deswirled to form a deswirled gas flow (Fc).

[0073] Figure 5 It is suitable for use as Figure 1 A schematic cross-sectional view of an exemplary turbine engine 200 of turbine engine 10. Turbine engine 200 is similar to turbine engine 10. Figure 1 ), 100 Figure 3 Therefore, similar parts will be used in turbine engine 10 ( Figure 1 Related similar names and additions to the 200 series with turbocharged engine 100 ( Figure 3 The turbine engine 10 (related similar numbers are used for identification, and it should be understood that, unless otherwise stated, the turbine engine 10) Figure 1 ), 100 Figure 3 The description applies to the turbine engine 200.

[0074] The turbine engine 200 includes an engine centerline 201, an engine housing 280, a deswirl assembly 234, and a combustion section 202. The engine housing 280 at least partially defines a working airflow path 282. The deswirl assembly 234 includes a deswirl 235 and a diffuser 236. The diffuser 236 has a set of diffuser walls 238 and a set of diffuser channels 239. The deswirl 235 has a set of deswirl walls 237 and a set of deswirl channels 241. The deswirl assembly 234 includes a deswirl assembly centerline 243. The combustion section 202 includes a circumferential housing 204 and a combustor 206. The combustion section 202 includes a centerline 210. The circumferential housing 204 defines an interior 208. The circumferential housing 204 includes an inner circumferential housing 276 and an outer circumferential housing 278. The combustor 206 has an annular bushing 216 and a set of fuel nozzles 230. Each of the fuel nozzles 230 leads to the combustion chamber 224 at a fuel nozzle outlet 232. The annular bushing 216 includes an inner liner 218 and an outer liner 220. The burner 206 may include a dome wall 222. The dome wall 222 and the annular bushing 216 may together form the combustion chamber 224. The burner 206 is located within an interior 208. A compressed air passage 228 is formed between the burner 206 and the circumferential housing 204.

[0075] The turbine engine 200 includes a fuel supply system 240. The fuel supply system 240 has a body 245. The fuel supply system 240 includes a set of fuel channels 242 and a set of fuel line branches 246. The fuel supply system 240 may also include an outer chamber 250 and an inner chamber 252. The set of fuel line branches 246 are coupled to at least a portion of the set of fuel nozzles 230 at a set of joints 254, or otherwise encounter at least a portion of the set of fuel nozzles 230. Each fuel line branch in the set of fuel line branches 246 includes a first leg 284, a second leg 286, a branch centerline 292, and a bend 288. The first leg 284 extends between a first transition 295 and a second transition 296. The second leg 286 extends between a third transition 298 and a corresponding fuel nozzle in the set of fuel nozzles 230. The fuel supply system 240 is fluidly coupled to a fuel source 266 via the fuel supply section 244.

[0076] With fuel supply system 140 ( Figure 3 Similarly, the fuel supply system 240 is partially formed as a single body. However, the difference is that the set of fuel line branches 246, the set of fuel channels 242, and the internal gas chamber 252 (when included) are formed as a single body (hereinafter referred to as "the single body of the fuel supply system 240"), and the external gas chamber 250 (if any) is excluded from the single body of the fuel supply system 240.

[0077] The turbine engine 200 is similar to the turbine engine 100 in that the decyclone assembly 234 is at least partially formed as a single body with the circumferential housing 204 and the fuel supply system 240. However, the decyclone assembly 234 is formed by a first body 212 coupled to a second body 214. The first body 212 is formed as a single body with the circumferential housing 204 and the fuel supply system 240. The set of decyclone walls 237 and the set of diffuser walls 238, and therefore the set of fuel channels 242, are formed as a single body with the first body 212. Alternatively, the set of fuel channels 242, the set of decyclone walls 237, and the set of diffuser walls 238 may be formed together with the second body 214. Alternatively, a first subset of the set of fuel channels 242 and a first subset of at least one of the set of decyclone walls 237, the set of diffuser walls 238, or combinations thereof may be formed together with the first body 212, while a second subset of the set of fuel channels 242 and a second subset of at least one of the set of decyclone walls 237, the set of diffuser walls 238, or combinations thereof may be formed together with the second body 214. An external gas chamber 250 (when included) is formed in the second body 214.

[0078] The first body 212 is coupled to the second body 214 at a connector 264. This connector defines the area where the first body 212 meets and is coupled to the second body 214. The connector 264 can be made by any suitable coupling method (such as, but not limited to, fastening, bolting, bonding, welding, joining, etc.). The connector 264 is reversible, allowing the first body 212 to be removably coupled to the second body 214. Therefore, a single body of the fuel supply system 240 is removably coupled to the second body 214. Figure 3 Compared to the fuel supply system 140, the removable connection between the single body of the fuel supply system 240 and the second body 214 allows for the replacement of fewer fuel supply systems 240 during maintenance. Furthermore, the ability to remove the fuel supply system 240 from the second body 214 allows access to the set of connectors 254 formed along the fuel supply system 240. It is conceivable that the set of connectors 254 may be, for example, a set of screws, bolts (as shown), or fasteners that require manual removal. Removing the fuel supply system 240 from the second body 214 allows access to the set of connectors 254, thereby reducing the burden of removing the set of connectors 254.

[0079] With burner 106 ( Figure 3 Similarly, burner 206 is connected to the inner circumferential housing 276 via burner arm 256. However, burner arm 256 extends from the axially forward portion of the annular bushing 216 and / or the dome wall 222. Burner arm 256 may be integrally formed with burner 206.

[0080] During operation, it is conceivable that the burner 206 may be affected by the flame and deswirl airflow within the combustion chamber 224 (e.g., Figure 3 The burner arm 256 expands or contracts due to thermal expansion caused by the deswirl airflow (Fc) or a combination thereof. The burner arm 256 is oriented to stabilize the burner 206 during thermal expansion, while still allowing the burner 206 to move with thermal expansion. The movement of the burner 206 with thermal expansion reduces the likelihood or magnitude of stress formation along the stable portion of the burner 206 (e.g., the burner arm 256).

[0081] As described herein, the combustion zone comprises a single unit of the fuel supply system that can be removed from the fuel supply section and fuel source. It is conceivable that at least a majority of this single unit of the fuel supply system represents the portion of the fuel supply system expected to experience thermal expansion and fatigue. In other words, this single unit of the fuel supply system is the part of the fuel supply system expected to require replacement first. Utilizing this single unit of the fuel supply system allows for the replacement of only these parts, rather than the entire fuel supply system, when necessary.

[0082] In some respects, the disclosed combustion zones and fuel nozzles can be used with gaseous fuels such as hydrogen. Gaseous fuels (including hydrogen) diffuse / disperse at a faster rate than atomized liquid fuels. The fuel supply system described herein is particularly well-suited for use with H2 fuels. H2 fuels have lower NO emissions when used compared to conventional fuels. x Emissions; thus allowing for reduced NO x Turbine engines that emit pollutants. Furthermore, H2 fuel has zero CO2 emissions compared to conventional fuels.

[0083] 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.

[0084] 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.

[0085] Further details are provided by the following topics:

[0086] A turbine engine includes: a compression section, a combustion section, and a turbine section, the compression section, the combustion section, and the turbine section being arranged in a series flow configuration and defining a working gas flow path, the combustion section having a centerline and including: a circumferential housing defining an interior; a combustor having an annular bushing located within the interior, the combustor having a combustion chamber; and a fuel nozzle opening into the combustion chamber; a deswirler assembly fluidly connecting the working gas flow path of the compression section to the interior, the deswirler assembly including a set of walls and a set of channels formed between adjacent walls in the set of walls, wherein at least one of the walls has a fuel channel; and a fuel supply system located within the combustion section, the fuel supply system including the fuel channels and a set of fuel line branches fluidly connected to the fuel channels and the fuel nozzle and extending within the interior between the fuel channels and the fuel nozzle.

[0087] The turbine engine according to any of the foregoing clauses, wherein the decyclone assembly includes a decyclone and a diffuser.

[0088] The turbine engine according to any of the foregoing clauses, wherein the diffuser includes a set of diffuser walls and a set of diffuser channels, wherein at least a portion of the set of walls is disposed within the set of diffuser walls.

[0089] According to any of the preceding clauses, the turbine engine includes a set of decyclone walls and a set of decyclone channels, wherein at least a portion of the set of walls is disposed within the set of decyclone walls.

[0090] The turbine engine according to any of the foregoing clauses, wherein the fuel channel extends through the interior of the at least one wall.

[0091] According to any of the preceding clauses, the turbine engine, wherein the fuel supply system includes an external chamber that extends circumferentially about the centerline and leads to the fuel channel, the external chamber being located outside the interior.

[0092] A turbine engine according to any of the foregoing clauses, wherein the external air chamber leads to two or more channels of the set of walls.

[0093] According to any of the foregoing clauses, the turbine engine wherein the outer chamber extends continuously for about 25% greater than or equal to the circumferential extent of the centerline and less than or equal to 100% of the circumferential extent of the centerline.

[0094] According to any of the foregoing clauses, the turbine engine, wherein the fuel supply system includes an internal chamber extending circumferentially about the centerline, and the fuel channel leads to the internal chamber.

[0095] The turbine engine according to any of the foregoing clauses, wherein the fuel nozzle is included in a plurality of fuel nozzles, and the fuel supply system includes a set of fuel line branches extending from the internal air chamber, wherein each of the set of fuel line branches extends between a corresponding portion of the internal air chamber and a corresponding fuel nozzle among the plurality of fuel nozzles.

[0096] According to any of the foregoing clauses, the internal air chamber extends continuously for about 25% of the circumferential extent of the centerline and less than or equal to 100% of the circumferential extent of the centerline.

[0097] The turbine engine according to any of the foregoing clauses, wherein the fuel nozzle is included in a plurality of fuel nozzles.

[0098] The turbine engine according to any of the foregoing clauses, wherein the fuel channels are included in a plurality of fuel channels, and every other wall of a set of arcuate walls includes at least one of the plurality of fuel channels.

[0099] According to any of the preceding clauses, in a turbine engine, the set of fuel line branches are connected to the fuel nozzle at a set of connectors, which are the only connectors between the fuel supply section and the combustion section within the interior.

[0100] In any of the foregoing clauses, the turbine engine wherein the decyclone assembly and the fuel supply unit are at least partially integrally formed.

[0101] In any of the preceding clauses, the turbine engine is wherein the at least one wall is a heat exchanger configured to transfer heat from the working gas flow passing through the at least one wall to the fuel flow within the fuel channel.

[0102] The turbine engine according to any of the foregoing clauses, wherein the combustion section includes a combustor arm extending between the combustor and the circumferential housing.

[0103] The turbine engine according to any of the foregoing clauses, wherein the circumferential housing, the fuel supply system and the decyclone assembly are integrally formed.

[0104] The turbine engine according to any of the foregoing clauses, wherein the combustion section includes a compressed air passage formed between the circumferential housing and the combustor, wherein the deswirl assembly leads to the compressed air passage.

[0105] The turbine engine according to any of the foregoing clauses, wherein the fuel supply system is configured to supply a stream of gaseous hydrogen-containing fuel to the combustion chamber.

[0106] The turbine engine according to any of the foregoing clauses, wherein the fuel line branch extends from the fuel channel to the fuel nozzle.

[0107] The turbine engine according to any of the foregoing clauses, wherein the fuel line branch has a decay distance, and the circumferential housing has an inner circumferential housing extending axially, wherein the decay distance is greater than the axial distance.

[0108] The turbine engine according to any of the foregoing clauses, wherein the circumferential housing includes a first body and a second body.

[0109] The turbine engine according to any of the foregoing clauses, wherein the first body is coupled to the second body.

[0110] The turbine engine according to any of the foregoing clauses, wherein the deswirl unit is integrally formed with one of the first body or the second body.

[0111] The turbine engine according to any of the foregoing clauses, wherein the burner is connected to the circumferential housing via a burner arm that engages with a first flange formed on the burner.

[0112] A combustion section for a turbine engine having a deswirl assembly including a set of walls and a set of channels formed between adjacent walls in the set of walls, wherein at least one of the walls has a fuel channel, the combustion section having a centerline and including: a circumferential housing defining an interior; a combustor having an annular bushing located within the interior, the combustor having a combustion chamber; and a fuel nozzle opening into the combustion chamber, wherein the turbine engine has a fuel supply system located within the combustion section, the fuel supply system including the fuel channels and a set of fuel line branches fluidly coupled to the fuel channels and the fuel nozzle and extending within the interior between the fuel channels and the fuel nozzle.

[0113] According to any of the preceding clauses, the combustion zone, wherein the deswirl assembly includes a deswirl and a diffuser.

[0114] According to any of the preceding clauses, the combustion zone, wherein the diffuser includes a set of diffuser walls and a set of diffuser channels, wherein at least a portion of the set of walls is disposed within the set of diffuser walls.

[0115] According to any of the preceding clauses, the combustion zone includes a set of deswirl walls and a set of deswirl channels, wherein at least a portion of the set of walls is disposed within the set of deswirl walls.

[0116] The combustion section according to any of the foregoing clauses, wherein the fuel channel extends through the interior of the at least one wall.

[0117] According to any of the preceding clauses, the combustion section, wherein the fuel supply system includes an external chamber that extends circumferentially around the centerline and leads to the fuel channel, the external chamber being located outside the interior.

[0118] According to any of the preceding clauses, the combustion section wherein the outer gas chamber leads to two or more channels of the set of walls.

[0119] According to any of the preceding clauses, the combustion zone wherein the outer chamber extends continuously for about 25% greater than or equal to the circumferential extent of the centerline and less than or equal to 100% of the circumferential extent of the centerline.

[0120] According to any of the preceding clauses, the combustion section, wherein the fuel supply system includes an internal chamber extending circumferentially around the centerline, and the fuel channel leads to the internal chamber.

[0121] According to any of the preceding clauses, the combustion section, wherein the fuel nozzle is included in a plurality of fuel nozzles, and the fuel supply system includes a set of fuel line branches extending from the internal gas chamber, wherein each of the set of fuel line branches extends between a corresponding portion of the internal gas chamber and a corresponding fuel nozzle among the plurality of fuel nozzles.

[0122] According to any of the preceding clauses, the combustion zone wherein the internal air chamber extends continuously for about 25% greater than or equal to the circumferential extent of the centerline and less than or equal to 100% of the circumferential extent of the centerline.

[0123] The combustion zone according to any of the foregoing clauses, wherein the fuel nozzle is included in a plurality of fuel nozzles.

[0124] The combustion section according to any of the foregoing clauses, wherein the fuel channel is included in a plurality of fuel channels, and every other wall in a set of arcuate walls includes at least one of the plurality of fuel channels.

[0125] According to any of the preceding clauses, the combustion section wherein the set of fuel line branches is connected to the fuel nozzle at a set of connectors, the set of connectors being the sole connector between the fuel supply unit and the combustion section within the interior.

[0126] According to any of the foregoing clauses, the combustion section wherein the deswirl assembly and the fuel supply section are at least partially integrally formed.

[0127] According to any of the preceding clauses, the combustion section wherein the at least one wall is a heat exchanger configured to transfer heat from the working gas flow passing through the at least one wall to the fuel flow within the fuel channel.

[0128] The combustion section according to any of the foregoing clauses, wherein the combustion section includes a burner arm extending between the burner and the circumferential housing.

[0129] According to any of the preceding clauses, the combustion section wherein the circumferential housing, the fuel supply system, and the deswirl assembly are integrally formed.

[0130] The combustion section according to any of the foregoing clauses, wherein the combustion section includes a compressed air passage formed between the circumferential housing and the burner, wherein the deswirl assembly leads to the compressed air passage.

[0131] According to any of the preceding clauses, the combustion section wherein the fuel supply system is configured to supply a stream of gaseous hydrogen-containing fuel to the combustion chamber.

[0132] According to any of the preceding clauses, the combustion section wherein the fuel line branch extends from the fuel channel to the fuel nozzle.

[0133] According to any of the preceding clauses, the combustion section, wherein the fuel line branch has a decay distance, and the circumferential housing has an inner circumferential housing extending axially, wherein the decay distance is greater than the axial distance.

[0134] The combustion zone according to any of the foregoing clauses, wherein the circumferential housing comprises a first body and a second body.

[0135] According to any of the foregoing clauses, the combustion section wherein the first body is connected to the second body.

[0136] According to any of the preceding clauses, the combustion section, wherein the deswirl diffuser is integrally formed with one of the first body or the second body.

[0137] According to any of the preceding clauses, the combustion section wherein the burner is connected to the circumferential housing via a burner arm that engages with a first flange formed on the burner.

Claims

1. A turbine engine characterized by, Comprising: a compression section, a combustion section, and a turbine section in serial flow arrangement and defining a working airflow path, the combustion section having a centerline and comprising: a circumferential shell defining an interior; a combustor having an annular liner within the interior, the combustor having a combustion chamber; and a fuel nozzle opening into the combustion chamber; a de-swirler assembly fluidically coupling the working airflow path of the compression section to the interior, the de-swirler assembly comprising a set of walls and a set of channels formed between adjacent walls of the set of walls, wherein at least one wall of the set of walls has a fuel channel; and a fuel supply system within the combustion section, the fuel supply system comprising the fuel channel and a set of fuel line branches fluidically coupled to and extending within the interior between the fuel channel and the fuel nozzle.

2. The turbine engine of claim 1, wherein, Wherein, the de-swirler assembly comprises a de-swirler and a diffuser.

3. The turbine engine of claim 2, wherein, Wherein, the diffuser comprises a set of diffuser walls and a set of diffuser channels, wherein at least a portion of the set of walls is disposed within the set of diffuser walls.

4. The turbine engine of claim 2, wherein, Wherein, the de-swirler comprises a set of de-swirler walls and a set of de-swirler channels, wherein at least a portion of the set of walls is disposed within the set of de-swirler walls.

5. The turbine engine of claim 1, wherein, Wherein, the fuel channel extends through the interior of the at least one wall.

6. The turbine engine of claim 1, wherein, Wherein, the fuel supply system comprises an outer plenum circumferentially extending about the centerline and opening into the fuel channel, the outer plenum being external to the interior.

7. The turbine engine of claim 6, wherein, Wherein, the outer plenum opens into two or more channels of the set of walls.

8. The turbine engine of claim 6, wherein, Wherein, the outer plenum extends continuously about greater than or equal to 25% and less than or equal to 100% of a circumferential extent of the centerline.

9. The turbine engine of claim 1, wherein, Wherein, the fuel supply system comprises an inner plenum circumferentially extending about the centerline, the fuel channel opening into the inner plenum.

10. The turbine engine of claim 9, wherein, Wherein: the fuel nozzle comprises in a plurality of fuel nozzles; and the fuel supply system comprises a set of fuel line branches extending from the inner plenum, wherein each fuel line branch of the set of fuel line branches extends between a respective portion of the inner plenum to a corresponding fuel nozzle of the plurality of fuel nozzles.

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