Turbine engine having combustion section with fuel nozzle

Abstract

A turbine engine has a compressor 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 assembly extending through a fuel nozzle opening. The fuel nozzle assembly has a first body, a second body, a first swirler, and a second swirler.

Description

Technical Field

[0001] The present subject matter generally relates to turbine engines and, more particularly, to a turbine engine having a combustor section that includes fuel nozzles. Background Art

[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 rotates 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 ), 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., SO 2 and SO 3 ). 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 compressor section, a combustor section, and a turbine section.

[0006] Figure 2 depicts a cross-sectional view of the combustor 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 the fuel nozzles discharging into the combustion chamber.

[0008] Figure 4 is a schematic side cross-sectional view of a portion of a combustor section suitable for use as Figure 1 of the combustor section that includes a fuel nozzle assembly having a fuel nozzle that includes a first body, and the fuel nozzle assembly further includes a second body and a third body.

[0009] Figure 5 is a schematic view of a combustion section observed from the line of sight V-V of Figure 4 , further showing the first body, the second body, and the third body.

[0010] Figure 6 is an exemplary side cross-sectional view of a combustion section suitable for use as Figure 1 a combustion section, the combustion section including a fuel nozzle assembly having a first body, a second body, a third body, a gaseous fuel channel defined by the first body, a first compressed air channel defined between the first body and the second body, and a second compressed air channel defined between the second body and the third body.

[0011] Figure 7 is a schematic view of the fuel nozzle assembly observed from the line of sight VII-VII of Figure 6 , further showing the second compressed air channel including a scalloped section.

[0012] Figure 8 is an exemplary side cross-sectional view of a combustion section suitable for use as Figure 1 a combustion section, the combustion section including a fuel nozzle assembly having a first body, a second body, and a third body, the first body defining a gaseous fuel channel, and an orifice plate being disposed within the gaseous fuel channel.

[0013] Figure 9 is an exemplary side cross-sectional view of a combustion section suitable for use as Figure 1 a combustion section, the combustion section including a fuel nozzle assembly having a first body, a second body, and a third body, the first body including a first angled section, and the second body including a second angled section opposite the first angled section.

[0014] Figure 10 is an exemplary side cross-sectional view of a combustion section suitable for use as Figure 1 a combustion section, the combustion section including a fuel nozzle assembly having a first body, a second body, and a third body, the first body including a first angled section, and the second body including a second angled section not opposite the first angled section. DETAILED DESCRIPTION

[0015] The disclosed aspects described herein relate to a turbine engine including a combustion section that includes a fuel nozzle assembly. The fuel nozzle assembly includes a fuel nozzle having a first body. The fuel nozzle assembly includes a second body and a third body. The first body defines a gaseous fuel passage. A first compressed air passage is defined between the first body and the second body. A second compressed air passage is defined between the third body and the second body.

[0016] The fuel nozzle assembly is particularly suitable for using hydrogen fuel (hereinafter referred to as "H2 fuel"). Specifically, the fuel nozzle assembly 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 the unexpected propagation of a flame when H2 fuel burns. H2 fuel has a higher volatility, which means that once the H2 fuel is burned or ignited, the flame generated by igniting the 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 igniter. As described herein, the fuel nozzle assembly ensures that flashback does not occur with H2 fuel. If the H2 fuel overheats, the H2 fuel may autoignite. Autoignition of the H2 fuel may be undesired at certain locations in the combustion section. The fuel nozzle assembly as described herein ensures that the temperature of the H2 fuel is below the autoignition temperature, at least until it is desired to ignite the H2 fuel.

[0017] As used herein, the term "gaseous fuel" or its iterations refers to a gaseous combustible fuel. It should be understood that gaseous fuel is different from atomized fuel. Atomized fuel uses impellers, orifices, etc. to obtain liquid fuel and atomize the liquid fuel into very small droplets.

[0018] 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 igniting the fuel with an igniter.

[0019] For illustrative purposes, the present disclosure will be described with respect to a turbine engine (a gas turbine engine). However, it will be understood that the disclosed aspects described herein are not limited thereto, and the fuel nozzle assembly 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 have general applicability within non-aircraft engines having burners, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0020] As used herein, the term "exemplary" means "serving as an example, instance, or illustration". Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Additionally, unless otherwise expressly stated, all examples described herein should be considered exemplary.

[0021] 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.

[0022] The terms "front" and "rear" refer to relative positions within a turbomachine or vehicle and refer to the normal operating attitude of the turbomachine or vehicle. For example, for a turbomachine, front refers to a position closer to the engine inlet, and rear refers to a position closer to the engine nozzle or exhaust.

[0023] As used herein, the term "upstream" refers to a direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction of fluid flow. The terms "forward" or "front" indicate in front of something, and "backward" or "rear" indicate behind something. For example, when used in the context of fluid flow, forward / front may indicate upstream, and backward / rear may indicate downstream.

[0024] The term "fluid" can be a gas or a liquid. The term "fluidly connected" means that a fluid can establish a connection between specified regions.

[0025] Additionally, 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 turbomachine, radial refers to the direction along a ray extending between the central longitudinal axis of the engine and the outer periphery of the engine.

[0026] 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 present disclosure and do not impose limitations, particularly with respect 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 accompanying drawings may vary.

[0027] The singular forms "a", "an" and "the" include plural references unless the context clearly dictates otherwise. Additionally, as used herein, the term "group" or "a group of" elements can be any number of elements, including only one.

[0028] As used herein, the term "radius of curvature" is equal to the radius of the arc of the circle that most closely approximates the curve at that point. The radius of curvature of a linear or flat surface is zero. Thus, a curved surface has a non-zero radius of curvature.

[0029] 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 compressor section 12, a combustion section 14, and a turbine section 16 arranged in a series flow configuration. A drive shaft 18 is rotationally coupled to the compressor 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.

[0030] The compressor section 12 can include a low pressure (LP) compressor 22 and a high pressure (HP) compressor 24 fluidly coupled in series with each other. The turbine section 16 can include an LP turbine 26 and an HP turbine 28 fluidly coupled in series with each other. The 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. The LP spool can be defined as the combination of the LP compressor 22, the LP turbine 26, and the LP drive shaft such that the 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. The HP spool can be defined as the combination of the HP compressor 24, the HP turbine 28, and the HP drive shaft such that the 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.

[0031] The compressor 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. The compressor blades for a stage of the compressor 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 compressor 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 compressor 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 compressor section 12.

[0032] Similar to the compressor 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. The turbine blades for a stage of the turbine section 16 can be mounted to a disk, and the disk 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 the housing in a circumferential manner. 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.

[0033] The combustion section 14 can be serially disposed between the compressor section 12 and the turbine section 16. The combustion section 14 can be fluidly coupled to at least a portion of the compressor section 12 and the turbine section 16 such that the combustion section 14 at least partially fluidly couples the compressor 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 the upstream end of the combustion section 14 and to the HP turbine 28 at the downstream end of the combustion section 14.

[0034] During operation of the turbine engine 10, ambient air or atmospheric air is drawn into the compressor section 12 via a fan (not shown) upstream of the compressor section 12, and the air is compressed at the compressor section 12, defining compressed air. Then, the compressed air can flow into the combustion section 14, where the compressed air is mixed with fuel and ignited at the combustion section 14, thereby generating 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, and the LP turbine 26 extracts additional work to drive the LP compressor 22, and the exhaust is finally 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 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, compressor section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

[0035] Figure 2 Depicted is a cross-sectional view of the combustion section 14 along Figure 1 line II-II. For illustrative purposes, the drive shaft 18 ( Figure 1)has been removed. The combustion section 14 includes a burner 34. The burner 34 includes a dome wall 44 that includes a set of fuel nozzle openings (not shown). The burner 34 includes a set of fuel nozzles 32 that extend through the set of fuel nozzle openings. The set of fuel nozzles 32 is arranged annularly about a burner centerline 29. The burner centerline 29 can be the engine centerline 20 of the turbine engine 10. Additionally or alternatively, the burner centerline 29 can be the centerline of the combustion section 14, a single burner, or a set of burners arranged about the burner centerline 29.

[0036] The set of fuel nozzles 32 is arranged about the burner centerline 29. Each fuel nozzle in the set of fuel nozzles 32 includes a fuel nozzle centerline 31. The set of fuel nozzles 32 can include a rich cup, a lean cup, or a combination of a rich cup and a lean cup arranged annularly about the engine centerline 20 ( Figure 1 )). The burner 34 is defined by a burner liner 38. 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 36 of the engine as further described herein. As shown by way of example, the burner liner 38 can be annular. The burner liner 38 can include an outer burner liner 40 and an inner burner liner 42 that are concentric with each other and annular about the engine centerline 20. The burner liner 38 also defines the set of fuel nozzles 32. The dome wall 44 and the burner liner 38 together can define a combustion chamber 46 that is annular about the engine centerline 20. The set of fuel nozzles 32 can be fluidly coupled to the combustion chamber 46. A compressed air passage 48 can be at least partially defined by the burner liner 38 and the housing 36. Each fuel nozzle in the set of fuel nozzles 32 is defined by a discrete body that extends through a corresponding portion of the dome wall 44 and is configured to discharge a gaseous fuel and a compressed air stream into the combustion chamber 46.

[0037] Figure 3 A cross-sectional view taken along line III-III of Figure 2 is depicted, showing the combustion section 14. At least one flame shaping passage can fluidly connect compressed air and the combustion chamber 46. As an example, at least one flame shaping passage is shown as a first set of flame shaping holes 50 or a second first set of flame shaping holes 52. The burner 34 can include a first set of flame shaping holes 50, a second first set of flame shaping holes 52, or both the first set of flame shaping holes 50 and the second first set of flame shaping holes 52.

[0038] The first set of flame shaping holes 50 can pass through the dome wall 44 to fluidly couple compressed air from the compressor section 12 or the compressed air passage 48 to the combustion chamber 46.

[0039] The second first set of flame shaping holes 52 can pass through the burner liner 38 to fluidly couple compressed air from the compressed air passage 48 to the combustion chamber 46.

[0040] The fuel nozzle 32 can be coupled to and disposed within the dome assembly 56. The fuel nozzle 32 can include a flared cone portion 58 and a swirler 60. The flared cone portion 58 includes an outlet 62 of the fuel nozzle 32 that is directly fluidly coupled to the combustion chamber 46. The fuel nozzle 32 is fluidly coupled to the fuel inlet 64 via a passage 66. The fuel nozzle centerline 31 can be defined by the fuel nozzle 32, the flared cone portion 58, or the outlet 62.

[0041] Both the inner burner liner 42 and the outer burner liner 40 can have an outer surface 68 and an inner surface 70 that at least partially define the combustion chamber 46. The burner liner 38 can be made of a single continuous integral part or can be a plurality of integral parts assembled together to define the inner burner liner 42 and the outer burner liner 40. As a non-limiting example, the outer surface 68 can define a first piece of the burner liner 38, while the inner surface 70 can define a second piece of the burner liner 38, which forms the burner liner 38 when assembled together. As described herein, the burner liner 38 includes the second first set of flame shaping holes 52. It is further contemplated that the burner liner 38 can be any type of burner liner 38, including but not limited to a single-wall or double-wall liner or a tile liner. The igniter 72 can be disposed at the burner liner 38 and is fluidly coupled to the combustion chamber 46 at any location (as a non-limiting example, upstream of the second first set of flame shaping holes 52).

[0042] During operation, compressed air (C) from a compressed air supply (such as Figure 1 the LP compressor 22 or the HP compressor 24) can flow from the compressor section 12 to the burner 34. A portion of the compressed air (C) can flow through the dome assembly 56. A first portion of the compressed air (C) that flows through the dome assembly 56 can be supplied to the fuel nozzle 32 as a swirling air stream (S) via the swirler 60. A fuel stream (F) is supplied to the fuel nozzle 32 via the fuel inlet 64 and the passage 66. The swirling air stream (S) and the fuel stream (F) are mixed at the flared cone portion 58 and are supplied to the combustion chamber 46 as a fuel / air mixture. The igniter 72 can ignite the fuel / air mixture to define a flame within the combustion chamber 46, which generates combustion gases (G). Although shown as starting axially downstream of the outlet 62, it should be understood that the fuel / air mixture can be ignited at or near the outlet 62.

[0043] A second portion of the compressed air (C) flowing through one or more portions of the dome assembly 56 can be supplied as a first flame shaping airflow (D1) to the first set of flame shaping holes 50. That is, a portion of the compressed air (C) from the compressor section 12 can flow through the dome wall 44 and enter the combustion chamber 46 by passing through the first set of flame shaping holes 50. The inlet 74 is defined by a portion of one or more of the flame shaping holes in the first set of flame shaping holes 50. The inlet 74 is fluidly coupled to the compressed air (C). The first flame shaping airflow (D1) enters one or more of the flame shaping holes in the first set of flame shaping holes 50 at the inlet 74 and exits one or more of the flame shaping holes in the first set of flame shaping holes 50 at the outlet 76 located in the dome wall 44.

[0044] Another portion of the compressed air (C) can flow through the compressed air passage 48 and can be supplied as a second flame shaping airflow (D2) to the second first set of flame shaping holes 52. In other words, another portion of the compressed air (C) can flow axially through the dome assembly 56 and enter the combustion chamber 46 by passing through the second first set of flame shaping holes 52. That is, the compressed air (C) can flow through the burner liner 38 and enter the combustion chamber 46 by passing through the second first set of flame shaping holes 52.

[0045] The first flame shaping airflow (D1) can be used to direct and shape the flame. The second flame shaping airflow (D2) can be used to direct the combustion gases (G). In other words, the first set of flame shaping holes 50 or the second first set of flame shaping holes 52 extending through the dome wall 44 or the burner liner 38 direct air into the combustion chamber 46, where the directed air is used to control, shape, cool, or otherwise contribute to the combustion process in the combustion chamber 46.

[0046] Figure 3 The burner 34 shown therein is well suited for using hydrogen-containing gas as fuel because it helps to accommodate the faster moving flame front associated with hydrogen fuel as compared to conventional hydrocarbon fuels. However, the burner 34 can be used with conventional hydrocarbon fuels.

[0047] Figure 4 is suitable for use as Figure 1 is a schematic side cross-sectional view of a portion of a combustion section 200 of the combustion section 14 that is suitable for use as. The combustion section 200 is similar to the combustion section 14; thus, like parts will be identified by like names, and it should be understood that the description of the combustion section 14 applies to the combustion section 200 unless otherwise stated.

[0048] The combustion section 200 includes a dome wall 214 that at least partially defines a combustion chamber 216. Similar to the combustion chamber 46 ( Figure 3) Similarly, the combustion chamber 216 is further defined by a burner liner (not shown) (e.g., Figure 3 the inner burner liner 42 and the outer burner liner 40). The combustion section 200 includes a fuel nozzle assembly 201. Similar to the set of fuel nozzles 32 ( Figure 2 ), the fuel nozzle assembly 201 is arranged to pass through a fuel nozzle opening provided along the dome wall 214. The fuel nozzle assembly 201 includes a fuel nozzle 202 having a first body 204, a second body 205, and a third body 206. The first body 204 and the second body 205 may be integrally formed.

[0049] The first body 204 defines a centerline axis 218. The first body 204 defines a gaseous fuel channel 208. The gaseous fuel channel 208 discharges into the combustion chamber 216 at a gaseous fuel outlet 220. At least a portion of the second body 205 is radially spaced from the first body 204 relative to the centerline axis 218 to define a first compressed air channel 210 provided therebetween. The first compressed air channel 210 discharges into the combustion chamber 216 at a first outlet 221. At least a portion of the third body 206 is radially spaced from the second body 205 relative to the centerline axis 218 to define a second compressed air channel 212 therebetween. The second compressed air channel 212 discharges into the combustion chamber 216 at a second outlet 223.

[0050] The first body 204 may further define a third compressed air channel 232. The third compressed air channel 232 discharges into the combustion chamber 216 at a third outlet 234. The third compressed air channel 232 may axially extend relative to a portion of the centerline axis 218. The third compressed air channel 232 may extend along a corresponding portion of the centerline axis 218. Although shown as integrally formed with the first body 204, it should be understood that the third compressed air channel 232 may be defined by a fourth body (not shown) extending through the gaseous fuel channel 208. The fuel nozzle assembly 201 may be separated from the dome wall 214. In other words, the fuel nozzle assembly 201 may be coupled to the dome wall 214 but not integrally formed with the dome wall 214. Alternatively, the fuel nozzle assembly 201 may be integrally formed within the dome wall 214.

[0051] When viewed along a plane extending along the centerline axis 218, the gaseous fuel channel 208, the first compressed air channel 210, the second compressed air channel 212, and the third compressed air channel 232 may extend any suitable distance or have any suitable cross-sectional area. As a non-limiting example, at least two of the gaseous fuel outlet 220, the first outlet 221, the second outlet 223, the third outlet 234, or a combination thereof may be axially aligned or offset from each other.

[0052] The first swirler 228 is disposed within the gaseous fuel passage 208. The second swirler 230 is disposed within the first compressed air passage 210. The first swirler 228 and the second swirler 230 are any suitable components configured to impart a swirling motion to a fluid flow from an upstream edge of the swirler to a downstream edge of the swirler such that the fluid flow downstream of the swirler includes a helical flow or other swirling flow. As a non-limiting example, the first swirler 228 and the second swirler 230 may each be formed as a plurality of airfoils circumferentially spaced within the gaseous fuel passage 208 and the first compressed air passage 210, respectively. The amount of swirl of the fluid flow passing through or flowing over the first swirler 228 and the second swirler 230 may be quantified by a swirl number, which is defined as the integral of the tangential momentum of the fluid flow downstream of the respective swirler to the axial momentum. The first swirler 228 and the second swirler 230 are defined as swirlers that produce a swirling gas flow having a swirl number greater than or equal to 0.2 and less than or equal to 1.2.

[0053] The second swirler 230 is operatively coupled to the first body 204 and the second body 205. The first swirler 228 and the second swirler 230 may be integrally formed with the first body 204 such that the first body 204 and the first swirler 228, the second swirler 230, or a combination thereof form a single body. The second swirler 230 may be integrally formed with the second body 205 such that the second body 205 and the second swirler 230 form a single body. The first swirler 228, the second swirler 230, the first body 204, and the second body 205 may be integrally formed such that the first swirler 228, the second swirler 230, the first body 204, and the second body 205 are formed as a single body.

[0054] The first set of flame forming holes 222 may be disposed within the second body 205. The first set of flame forming holes 222 exhaust into the combustion chamber 216. Each flame forming passage of the first set of flame forming holes 222 may extend from the left side of the page to the right side, radially toward, radially away from, or parallel to the centerline axis 218. The first set of flame forming holes 222 fluidly couple compressed air from a compressor (e.g., Figure 1 compressor 12) to the combustion chamber 216. The compressed air passing through the first set of flame forming holes 222 is used to shape the flame and / or provide additional air to assist in more complete combustion, as well as increase the mass flow rate in the working fluid flow.

[0055] The third body 206 is connected to the dome wall 214. The third body 206 may include an annular arm 224 that extends continuously around the entire centerline axis 218. Alternatively, the annular arm 224 may be segmented or otherwise extend for less than the entire centerline axis 218. The dome wall 214 may include an annular groove 226 that extends continuously around the entire centerline axis 218. Alternatively, the annular groove 226 may be segmented or otherwise extend for less than the entire centerline axis 218. As a non-limiting example, the annular arm 224 may be fitted within the annular groove 226 such that a lap joint is formed between the third body 206 and the dome wall 214. The dimensions of the annular arm 224 and the annular groove 226 are designed to allow the annular arm 224 to move radially within the annular groove 226. Accordingly, the third body 206 may move freely radially within the annular groove 226 such that the fuel nozzle assembly 201 may move radially relative to the centerline axis 218 during operation of the fuel nozzle assembly 201.

[0056] The third body 206 may be defined as a movable annular collar that seals the fuel nozzle assembly 201 to the dome wall 214. In other words, the third body 206 is sealingly connected to the dome wall 214 such that fluid cannot pass between the interfaces of the dome wall 214 and the third body 206. The third body 206 is also used to align the fuel nozzle assembly 201 along the dome wall 214 within the fuel nozzle opening. As a non-limiting example, during assembly, the third body 206 is connected to the dome wall 214 and then the fuel nozzle 202 is inserted into the fuel nozzle opening such that the fuel nozzle 202 is surrounded by the third body 206.

[0057] The dome wall 214 may include a second set of flame shaping holes 236. The second set of flame shaping holes 236 is disposed radially outward from the first set of flame shaping holes 222. The second set of flame shaping holes 236 vents to the combustion chamber 216. Each flame shaping hole in the second set of flame shaping holes 236 may extend from the left side to the right side of the page, radially toward, radially away from, or parallel to the centerline axis 218.

[0058] The combustion section 200 may include any number of one or more fuel nozzle assemblies 201. Each fuel nozzle assembly 201 is defined by a portion of the combustion section 200 that extends through a respective single portion (e.g., a respective fuel nozzle opening) of the dome wall 214 and has a single gaseous fuel supply.

[0059] During operation, a gaseous fuel stream (Fg) is supplied to the gaseous fuel passage 208. The gaseous fuel stream (Fg) flows through the gaseous fuel passage 208 and through the first swirler 228 to define a swirling gaseous fuel stream (Fs) discharged into the combustion chamber 216. The swirling gaseous fuel stream (Fs) can be ignited within the combustion chamber 216 by an igniter (not shown) or by auto-ignition. The gaseous fuel stream (Fg) can comprise 100% hydrogen (“H2”) fuel, or a mixture of hydrogen fuel and another gaseous fuel (e.g., methane). Alternatively, the gaseous fuel stream (Fg) can be a mixture of H2 fuel and compressed air from, for example, a compressor section (e.g., Figure 1 compressor section 12) of

[0060] A compressed air (e.g., Figure 3 compressed air (C)) stream is supplied to various parts of the fuel nozzle assembly 201. As a non-limiting example, a first compressed air stream (Fc1) is supplied to and through the first compressed air passage 210, a second compressed air stream (Fc2) is supplied to and through the second compressed air passage 212, a third compressed air stream (Fc3) is supplied to and through the first set of flame shaping holes 222, and a fourth compressed air stream (Fc4) is supplied to and through the third compressed air passage 232. Since the first set of flame shaping holes 222 can include the third compressed air stream (Fc3), the first set of flame shaping holes 222 can be defined as a third air passage. Since the third compressed air passage 232 can include the fourth compressed air stream (Fc4), the third compressed air passage 232 is defined as a fourth air passage.

[0061] The first compressed air stream (Fc1), the second compressed air stream (Fc2), the third compressed air stream (Fc3), the fourth compressed air stream (Fc4), or a combination thereof can be from the same or different compressed air sources. As a non-limiting example, the first compressed air stream (Fc1) can be from an HP compressor (e.g., Figure 1 HP compressor 24) of Figure 1 while the second compressed air stream (Fc2) can be from an LP compressor (e.g., Figure 1 LP compressor 22) of

[0062] by similar toFigure 3 The flame shaping air flow (D1) defined by the compressed air flow of the first flame shaping air flow (D1) can be supplied to the combustion chamber 216 through the second set of flame shaping holes 236. The flame shaping air flow (D1) can be radially outwardly disposed from the first compressed air flow (Fc1), the second compressed air flow (Fc2), the third compressed air flow (Fc3), and the fourth compressed air flow (Fc4). Similar to the first compressed air flow (Fc1), the second compressed air flow (Fc2), the third compressed air flow (Fc3), and the fourth compressed air flow (Fc4), the flame shaping air flow (D1) can be a compressed air flow from a part upstream of the combustion chamber 216 of the turbine engine 10.

[0063] The first compressed air flow (Fc1), the second compressed air flow (Fc2), the third compressed air flow (Fc3), the fourth compressed air flow (Fc4), the flame shaping air flow (D1), or a combination thereof is used to shape the flame (e.g., provide a desired footprint of the physical flame within the combustion chamber 216) and isolate various parts of the combustion section 200 from the flame. Flame shaping is accomplished by forming an annular compressed air curtain around the flame. As a non-limiting example, the first compressed air flow (Fc1), the second compressed air flow (Fc2), the third compressed air flow (Fc3), the flame shaping air flow (D1), or a combination thereof can form an annular air curtain that is used to shape the flame in a desired manner and provide a layer of isolation between the flame and various parts of the combustion section 200. The fourth compressed air flow (Fc4) is used to push the flame behind the fuel nozzle assembly 201 and the dome wall 214. Similar to the way the first swirler 228 and the second swirler 230 are used, at least one of the first compressed air flow (Fc1), the second compressed air flow (Fc2), the third compressed air flow (Fc3), the flame shaping air flow (D1), or a combination thereof can be used to swirl the flame.

[0064] It should be understood that the combustion section 200 can include any number of sets or groups of flame shaping holes or channels that are configured to provide a footprint of the flame generated by igniting the gas fuel flow (Fg) from the gas fuel channel 208. The combustion section 200 can include a set of flame shaping holes disposed along the dome wall (e.g., the second set of flame shaping holes 236), the second body 205 (e.g., the first set of flame shaping holes 222), the third body 206 (e.g., the second compressed air channel 212), or a combination thereof.

[0065] Although not shown, the combustion section 200 may include a controller module communicatively coupled to a set of valves to automatically control the fluid flow to or within various parts of the combustion section 200. As a non-limiting example, the controller module may automatically control the supply of the gaseous fuel flow (Fg) to the gaseous fuel channel 208. As a non-limiting example, the controller module may automatically control the supply of the first compressed air flow (Fc1) to the first compressed air channel 210. As a non-limiting example, the controller module may automatically control the supply of the second compressed air flow (Fc2) to the second compressed air channel 212. As a non-limiting example, the controller module may automatically control the supply of the third compressed air flow (Fc3) to the first set of flame shaping holes 222. As a non-limiting example, the controller module may automatically control the supply of the fourth compressed air flow (Fc4) to the third compressed air channel 232. As a non-limiting example, the controller module may automatically control the supply of the flame shaping air flow (D1) to at least a portion of the flame shaping holes in the second set of flame shaping holes 236. The gaseous fuel flow (Fg), the first compressed air flow (Fc1), the second compressed air flow (Fc2), the third compressed air flow (Fc3), and the fourth compressed air flow (Fc4) may be controlled independently of each other. As a non-limiting example, the compressed air flow may be cut off to the first set of flame shaping holes 222 but may be sent to the first compressed air channel 210.

[0066] When using gaseous H2 fuel, the shaping of the flame and the isolation of the flame from other parts of the combustion section 200 are particularly important compared to conventional fuels. Compared to conventional fuels, gaseous H2 fuel has a higher combustion temperature and a tendency to flashback. Accordingly, at least one of the first compressed air flow (Fc1), the second compressed air flow (Fc2), the third compressed air flow (Fc3), the fourth compressed air flow (Fc4), or a combination thereof is used to push the flame away from the fuel nozzle 202. Pushing the swirling fuel flow (Fs) away from the fuel nozzle assembly 201 helps ensure that once ignited, flashback into the fuel nozzle 202 of the swirling fuel flow (Fs) does not occur. At least one of the first compressed air flow (Fc1), the second compressed air flow (Fc2), the third compressed air flow (Fc3), the fourth compressed air flow (Fc4), or a combination thereof further ensures that a flame having a combustion temperature higher than that generated by conventional fuels does not overheat the section of the combustion section 200. At least one of the first compressed air flow (Fc1), the second compressed air flow (Fc2), the third compressed air flow (Fc3), the fourth compressed air flow (Fc4), or a combination thereof may further be used to create a uniform flame distribution at the burner outlet. It is contemplated that a uniform flame distribution or temperature distribution at the burner outlet would result in a more efficient turbine section.

[0067] Figure 5is a schematic view of the fuel nozzle 202 observed along the Figure 4 line of sight V-V. The gaseous fuel channel 208, the first compressed air channel 210, the second compressed air channel 212, and the third compressed air channel 232 are each formed as an annular groove. The second compressed air channel 212 surrounds the first compressed air channel 210. The first compressed air channel 210 surrounds the gaseous fuel channel 208. The gaseous fuel channel 208 surrounds the third compressed air channel 232.

[0068] The gaseous fuel channel 208, the first compressed air channel 210, the second compressed air channel 212, and the third compressed air channel 232 may each extend continuously around the entire centerline axis 218. Alternatively, the gaseous fuel channel 208, the first compressed air channel 210, the second compressed air channel 212, the third compressed air channel 232, or a combination thereof may be segmented, discontinuous, or otherwise extend for less than the entire centerline axis 218. As a non-limiting example, the second compressed air channel 212 may be segmented such that the second body 205 may be integrally formed with the third body 206.

[0069] The first set of flame shaping holes 222 and the second set of flame shaping holes 236 may be formed as discrete holes or channels disposed along the second body 205. The second set of flame shaping holes 236 may be disposed along any suitable portion of the dome wall 214. The second flame shaping holes in the second set of flame shaping holes 236 may be circumferentially spaced apart from each other, radially spaced apart from each other, or a combination thereof. The first set of flame shaping holes 222, the second set of flame shaping holes 236, or a combination thereof may be spaced apart evenly or unevenly around the centerline axis 218. It should be understood that the first set of flame shaping holes 222 may be used in place of the second set of flame shaping holes 236 or in combination with the second set of flame shaping holes 236, or vice versa.

[0070] It should be understood that each compressed air passage (e.g., the second compressed air channel 212, the first set of flame shaping holes 222, the second set of flame shaping holes 236, and the third compressed air channel 232) is defined by a percentage of the total volume of compressed air supplied to the combustion chamber 216. As a non-limiting example, greater than or equal to 10% and less than or equal to 30% of the total volume of compressed air supplied to the combustion chamber 216 may be supplied through the first compressed air channel 210 (e.g., Figure 4 the first compressed air flow (Fc1)). As a non-limiting example, greater than or equal to 5% and less than or equal to 25% of the total volume of compressed air supplied to the combustion chamber 216 may be supplied through the second compressed air channel 212 (e.g., Figure 4 the second compressed air flow (Fc2)), through the first set of flame shaping holes 222 (e.g., Figure 4The third compressed air stream (Fc3)) is supplied through an outer set of flame shaping holes 236 or a combination thereof. As a non-limiting example, greater than or equal to 0.1% and less than or equal to 2% of the total volume of compressed air supplied to the combustion chamber 216 can be supplied through the third compressed air channel 232 (e.g., Figure 4 the fourth compressed air stream (Fc4)) of

[0071] Figure 6 is suitable for use as Figure 1 FIG. 300 is a schematic side cross-sectional view of an exemplary combustion section 300 of the combustion section 200. The combustion section 300 is similar to the combustion section 200 ( Figure 4 ), and thus, like parts will be identified with like numbers increased to the 300 series. It should be understood that the description of the combustion section 200 applies to the combustion section 300 unless otherwise stated.

[0072] The combustion section 300 includes a fuel nozzle assembly 301, a dome wall 314, and a combustion chamber 316. The fuel nozzle assembly 301 includes a fuel nozzle 302 having a first body 304 that defines a centerline axis 318. The first body 304 defines a gaseous fuel channel 308. The gaseous fuel channel 308 discharges into the combustion chamber 316 at a gaseous fuel outlet 320. The fuel nozzle assembly 301 also includes a second body 305 and a third body 306. A first compressed air channel 310 that discharges into the combustion chamber 316 at a first outlet 321 is at least partially defined between the first body 304 and the second body 305. A second compressed air channel 312 that discharges into the combustion chamber 316 at a second outlet 323 is at least partially defined between the second body 305 and the third body 306. The third body 306 may include an annular arm 324. The dome wall 314 may include an annular groove 326. A first swirler 328 is disposed within the gaseous fuel channel 308. A second swirler 330 is disposed within the first compressed air channel 310. The first body 304, the second body 305, the third body 306, the first swirler 328, and the second swirler 330 may be integrally formed such that the first body 304, the second body 305, the third body 306, the first swirler 328, and the second swirler 330 form a single body. A first set of flame shaping holes (not shown) may be provided along the fuel nozzle assembly 301, the dome wall 314, or a combination thereof. Although not shown, the first set of flame shaping holes (e.g., Figure 4 the second set of flame shaping holes 236 in

[0073] Figure 4 ) may be provided along the dome wall 314. Figure 4 except that the fuel nozzle assembly 301 does not include the third compressed air channel 232 ()。The second compressed air channel 312 further includes a first leg 338 and a second leg 340. The second leg 340 is not parallel to the first leg 338, and they converge together at the second compressed air channel 312. The first leg 338 may be formed between the third body 306 and the second body 305. Alternatively, the first leg 338 may be formed within one of the third body 306 or the second body 305. The second leg 340 may be formed within the third body 306. The first leg 338 may extend axially, while the second leg 340 may extend radially. The second compressed air channel 312 is at least partially defined by a sector section 350 that terminates within the second compressed air channel 312 at an inner surface 356. Although only two legs are shown, it should be understood that the second compressed air channel 312 may include any number of legs. As a non-limiting example, a third leg and a fourth leg may branch off from the second compressed air channel 312 and discharge into the combustion chamber 316 at corresponding portions of the second outlet 323. It should also be understood that any of the channels described herein (e.g., the gaseous fuel channel 308, the first compressed air channel 310, etc.) may include any number of legs.

[0074] The first body 304 and the second body 305 may be integrally formed to define a single body, similar to Figure 4 the first body 204 and the second body 205. The third body 306 may be formed integrally or non-integrally with the single body of the first body 304 and the second body 305. As a non-limiting example, the single body of the first body 304 and the second body 305 may be formed non-integrally with the third body 306 such that the third body 306 is first coupled to the dome wall 314 or otherwise formed integrally with the dome wall 314, and then the single body of the first body 304 and the second body 305 is inserted into the third body 306.

[0075] During operation, a first third-body compressed air flow (Fc2a) may be supplied or selectively supplied (e.g., by using a controller module and a valve) to the first leg 338. A second third-body compressed air flow (Fc2b) may be supplied or selectively supplied (e.g., by using a controller module and a valve) to the second leg 340. The first third-body compressed air flow (Fc2a), the second third-body compressed air flow (Fc2b), or a combination thereof is supplied to the second compressed air channel 312 to define a third compressed air flow (e.g., Figure 4The third compressed air flow (Fc3)). The first and second body third compressed air flows (Fc2a and Fc2b) can be from the same or different compressed air sources. Including the first leg 338 and the second leg 340 rather than just a single leg (e.g., similar to the fuel nozzle assembly 201) ensures that the volume of compressed air supplied to the combustion chamber 316 is sufficient to provide the desired flame shaping and insulation characteristics described herein. It is contemplated that the first leg 338, the second leg 340, and the fan section 350 can be formed to ensure that the total volume of air supplied to the combustion chamber 316 through the second compressed air channel 312 is greater than or equal to 5% and less than or equal to 25% of the total volume of compressed air supplied to the combustion chamber 316. The volume of compressed air supplied through the compressed air channel 312 falling within the above range ensures that the volume of compressed air supplied through the compressed air channel 312 is sufficient to provide the desired flame shaping and insulation characteristics.

[0076] Figure 7 is from Figure 6 Schematic view of a portion of the fuel nozzle assembly 301 as seen along line of sight VII-VII. The fan section 350 of the second compressed air channel 312 is defined by a series of circumferentially spaced apart cuts within the third body 306. A gap 346 can be provided between the inner surface 356 of the fan section 350 and the second body 305.

[0077] During operation, the fuel nozzle assembly 301 (particularly the second body 305) can move radially inwards and outwards as shown by arrow 348. Accordingly, the size of the gap 346 can change as the second body 305 moves. In some cases, the second body 305 can contact the third body 306 such that the corresponding portion of the gap 346 is zero. The fan section 350 ensures that even when the gap 346 is zero, the compressed fluid flow ( Figure 6 the third compressed fluid flow (Fc3)) continues to flow through the second compressed air channel 312, particularly the fan section 350 of the second compressed air channel 312. This in turn ensures that even when the gap 346 is zero, an annular air curtain will always form around the flame.

[0078] It should be understood that the second compressed air channel 312 serves as a flame shaping channel, similar to the first set of flame shaping holes 222 ( Figure 4 ) and the second set of flame shaping holes 236 ( Figure 3 ). The fan section 350 ensures that a portion of the second compressed air channel 312 remains open at all times. In other words, the third compressed air flow (Fc3) can always flow through the fan section 350 such that the fan section 350 defines a series of flame shaping holes disposed along the fuel nozzle assembly 301 and formed within the third body 306.

[0079] Figure 8 is an exemplary side cross-sectional view of a combustion zone 400 suitable for use as Figure 1 the combustion zone 200. The combustion zone 400 is similar to the combustion zone 200 ( Figure 4 ), 300 ( Figure 6 ), and thus, like parts will be identified with like numbers incremented to the 400 series. It should be understood that the description of the combustion zones 200, 300 applies to the combustion zone 400 unless otherwise stated.

[0080] The combustion zone 400 includes a fuel nozzle assembly 401, a dome wall 414, and a combustion chamber 416. The fuel nozzle assembly 401 includes a fuel nozzle 402 having a first body 404 that defines a centerline axis 418. The first body 404 defines a gaseous fuel passage 408. The gaseous fuel passage 408 discharges into the combustion chamber 416 at a gaseous fuel outlet 420. The fuel nozzle assembly 401 also includes a second body 405 and a third body 406. A first compressed air passage 410 that discharges into the combustion chamber 416 at a first outlet 421 is at least partially defined between the first body 404 and the second body 405. A second compressed air passage 412 that discharges into the combustion chamber 416 at a second outlet 423 is at least partially defined between the second body 405 and the third body 406. The third body 406 may include an annular arm 424. The dome wall 414 may include an annular groove 426. A first swirler 428 is disposed within the gaseous fuel passage 408. A second swirler 430 is disposed within the first compressed air passage 410. The first body 404, the second body 405, the third body 406, the first swirler 428, and the second swirler 430 may be integrally formed such that the first body 404, the second body 405, the third body 406, the first swirler 428, and the second swirler 430 form a single body. A first set of flame shaping holes (not shown) may be provided along the fuel nozzle assembly 401, the dome wall 414, or a combination thereof. Although not shown, a first set of flame shaping holes (e.g., Figure 4 the second set of flame shaping holes 236) may be provided along the dome wall 414.

[0081] The fuel nozzle assembly 401 is similar to the fuel nozzle assembly 201 ( Figure 4 ), 301 ( Figure 6 ) in that it includes a first swirler 428 within the gaseous fuel passage 408. However, the first swirler 428 may alternatively be formed as an orifice plate including a plurality of orifices 458 rather than a set of circumferentially spaced airfoils. The plurality of orifices 458 may be oriented such that the plurality of orifices 458 provide a first swirler 228 ( Figure 4 ), 328 ( Figure 6)The swirling effect provided. The first swirler 428 is formed as a wall that extends radially and circumferentially through the entire corresponding portion of the gas fuel channel 408. It should be understood that either or both of the first swirler 428 and the second swirler 430 can be formed as an orifice plate.

[0082] Figure 9 is suitable for use as Figure 1 a schematic side cross-sectional view of an exemplary combustion section 500 of the combustion section 200. The combustion section 500 is similar to the combustion section 200( Figure 5 ), 300( Figure 6 ), 400( Figure 8 ), and thus, similar parts will be identified with similar numbers increased to the 500 series. It should be understood that the description of the combustion sections 200, 300, 400 applies to the combustion section 500 unless otherwise specified.

[0083] The combustion section 500 includes a fuel nozzle assembly 501, a dome wall 514, and a combustion chamber 516. The fuel nozzle assembly 501 includes a fuel nozzle 502 having a first body 504 that defines a centerline axis 518. The first body 504 defines a gas fuel channel 508. The gas fuel channel 508 discharges into the combustion chamber 516 at a gas fuel outlet 520. The fuel nozzle assembly 501 includes a second body 505 and a third body 506. A first compressed air channel 510 that discharges into the combustion chamber 516 at a first outlet 521 is at least partially defined between the first body 504 and the second body 505. A second compressed air channel 512 that discharges into the combustion chamber 516 at a second outlet 523 is at least partially defined between the second body 505 and the third body 506. The third body 506 may include an annular arm 524. The dome wall 514 may include an annular groove 526. A first swirler 528 is disposed within the gas fuel channel 508. A second swirler 530 is disposed within the first compressed air channel 510. The first body 504, the second body 505, the third body 506, the first swirler 528, and the second swirler 530 may be integrally formed such that the first body 504, the second body 505, the third body 506, the first swirler 528, and the second swirler 530 form a single body. A first set of flame shaping holes (not shown) may be disposed along the fuel nozzle assembly 501, the dome wall 514, or a combination thereof. Although not shown, a first set of flame shaping holes (e.g., Figure 4 the second set of flame shaping holes 236) may be disposed along the dome wall 514.

[0084] The fuel nozzle assembly 501 is similar to the fuel nozzle assembly 201( Figure 4 ), 301( Figure 6 ), 401( Figure 8), because it includes a gaseous fuel channel 508, a first compressed air channel 510, and a second compressed air channel 512. The gaseous fuel channel 508 and the first compressed air channel 510 respectively include a first angled section 552 and a second angled section 554. The first angled section 552 may be opposite the second angled section 554. As a non-limiting example, the first angled section 552 may expand radially outward, while the second angled section 554 may contract radially inward, or vice versa. The first angled section 552 extends to and terminates at the gaseous fuel outlet 520. The second angled section 554 extends to and terminates at the first outlet 521. Alternatively, at least one of the first angled section 552 or the second angled section 554 may extend respectively toward the gaseous fuel outlet 520 or the first outlet 521, but axially terminate before the gaseous fuel outlet 520 or the first outlet 521.

[0085] During operation, the first angled section 552 expands a fluid (e.g., Figure 4 a swirling gaseous fuel flow (Fs)), while the second angled section 554 contracts a fluid flow (e.g., Figure 4 a first compressed air flow (Fc1)). When compared to Figure 4 the fuel nozzle 202, the flame exiting the fuel nozzle 502 will have a smaller footprint than the flame exiting the fuel nozzle 202 because the second angled section 554 radially inwardly pushes the flame through the fluid flow passing through the first compressed air channel 510. The benefit of flaring the first angled section 552 radially outward and tapering the second angled section 554 radially inward is an increased flow interaction between the compressed air flowing through the first compressed air channel 510 and the gaseous fuel flowing through the gaseous fuel channel 508. The increased flow interaction in turn helps ensure that the hottest part of the flame (e.g., the central part of the flame) remains within the central part of the combustion chamber 516 and away from, for example, the burner liner, the dome wall 514, or a combination thereof.

[0086] Figure 10 is a schematic side cross-sectional view of an exemplary combustion section 600 suitable for use as Figure 1 the combustion section 200. The combustion section 600 is similar to the combustion sections 200 ( Figure 6 ), 300 ( Figure 6 ), 400 ( Figure 8 ), 500 ( Figure 8 ), and thus, like parts will be identified with like numerals incremented to the 600 series, and it should be understood that the description of the combustion sections 200, 300, 400, 500 applies to the combustion section 600 unless otherwise stated.

[0087] The combustion zone 600 includes a fuel nozzle assembly 601, a dome wall 614, and a combustion chamber 616. The fuel nozzle assembly 601 includes a fuel nozzle 602 having a first body 604 that defines a centerline axis 618. The first body 604 defines a gaseous fuel passage 608. The gaseous fuel passage 608 discharges into the combustion chamber at a gaseous fuel outlet 620. The fuel nozzle assembly 601 includes a second body 605 and a third body 606. A first compressed air passage 610 that discharges into the combustion chamber 616 at a first outlet 621 is at least partially defined between the first body 604 and the second body 605. A second compressed air passage 612 that discharges into the combustion chamber 616 at a second outlet 623 is at least partially defined between the second body 605 and the third body 606. The third body 606 may include an annular arm 624. The dome wall 614 may include an annular groove 626. A first swirler 628 is disposed within the gaseous fuel passage 608. A second swirler 630 is disposed within the first compressed air passage 610. The first body 604, the second body 605, the third body 606, the first swirler 628, and the second swirler 630 may be integrally formed such that the first body 604, the second body 605, the third body 606, the first swirler 628, and the second swirler 630 form a single body. A first set of flame shaping holes (not shown) may be provided along the fuel nozzle assembly 601, the dome wall 614, or a combination thereof. Although not shown, a first set of flame shaping holes (e.g., Figure 4 a second set of flame shaping holes 236) may be provided along the dome wall 614.

[0088] The fuel nozzle assembly 601 is similar to the fuel nozzle assembly 201( Figure 4 ), 301( Figure 6 ), 401( Figure 8 ), 501( Figure 9), as it includes a gaseous fuel passage 608, a first compressed air passage 610, and a second compressed air passage 612. The gaseous fuel passage 608 and the first compressed air passage 610 respectively include a first angled section 652 and a second angled section 654. The first angled section 652 may be in line with (e.g., in the same general direction as) the second angled section 654. As a non-limiting example, the first angled section 652 and the second angled section 654 may each extend radially inwardly. The first angled section 652 may be parallel or non-parallel to the second angled section 654. The first angled section 652 extends to and terminates at the gaseous fuel outlet 620. The second angled section 654 extends to and terminates at the first outlet 621. Alternatively, at least one of the first angled section 652 or the second angled section 654 may extend respectively towards the gaseous fuel outlet 620 or the first outlet 621, but axially terminate before the gaseous fuel outlet 620 or the first outlet 621. Both the first angled section 652 and the second angled section 654 may extend radially towards or radially away from the centerline axis 618.

[0089] During operation, the first angled section 652 contracts a fluid (e.g., Figure 4 a swirling gaseous fuel flow (Fs)). The second angled section 654 contracts a fluid flow (e.g., Figure 4 a first compressed air flow (Fc1)). When compared to Figure 9 the fuel nozzle 502, the flame exiting the fuel nozzle 602 will have a smaller footprint than the flame exiting the fuel nozzle 502 because both the first angled section 652 and the second angled section 654 contract the respective fluid flows. The benefit of having both the first angled section 652 and the second angled section 654 radially taper inwardly is that the flame is contracted such that the hottest part of the flame (e.g., the central part of the flame) remains within the central part of the combustion chamber 516 and away from, for example, the burner liner, the dome wall 614, or a combination thereof.

[0090] Benefits of the present disclosure include burners suitable for use with gaseous H2 fuel. As previously mentioned, gaseous H2 fuel has higher flame temperatures, flashback potential, and autoignition potential than conventional fuels (e.g., fuels without hydrogen). That is, gaseous H2 fuel has a wider flammable range and faster combustion speed 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 isolation is required between the ignited gaseous H2 fuel and the surrounding components of a turbine engine or a gas turbine engine (e.g., dome walls, inner / outer liners, and other parts of the turbine engine). Additionally, 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 assembly that provides an isolation layer between the flame and portions 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 assembly 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 assembly ensures uniform, consistent, or otherwise desired flame propagation within the burner.

[0091] 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% H 2 ) will have zero carbon pollutants. As described herein, the burner can be used in cases where 100% hydrogen-containing fuel is used.

[0092] Within the scope not yet described, the different features and structures of the various embodiments can be used in combination or substituted for each other as needed. That is, any flame-forming hole that connects compressed air to the combustion chamber can include one or more of the aspects described herein. As a non-limiting example, one or more flame-forming holes can include channels or a single rounded inlet fluidly connected to one or more channels. As a further non-limiting example, one or more flame-forming holes can include a chamber portion or at least one orifice. The fact that a feature is not shown in all embodiments does not mean that it cannot be so shown, but rather it is done for the sake of brevity of description. Thus, the various features of different embodiments can be mixed and matched as needed to form new embodiments, whether or not the new embodiments are explicitly described. Additionally, the rounded inlet connected to the passageway can be applied to any flow path that provides flow through one or more parts or components of a turbine engine. That is, the aspects of the present disclosure are shown in the context of the flame-forming holes of a burner, however, other channels within the turbine engine can be envisioned. All combinations or permutations of the features described herein are covered by the present disclosure.

[0093] This written description uses examples to describe the aspects of the disclosure described herein, including the best mode, and also enables any person skilled in the art to practice the 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 present 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 are indistinguishable from the literal language of the claims, or if they include equivalent structural elements that have no substantial difference from the literal language of the claims, then these other examples are intended to fall within the scope of the claims.

[0094] Further aspects are provided by the subject matter of the following clauses:

[0095] A turbine engine, comprising a compressor section, a combustion section, and a turbine section in a serial flow arrangement, the combustion section including: a burner liner and a dome wall, the burner liner and the dome wall together forming at least a part of a combustion chamber, wherein the dome wall has a fuel nozzle opening; and a fuel nozzle assembly extending through the fuel nozzle opening, the fuel nozzle assembly including: a first body having a centerline axis, the first body defining a gas fuel channel having a gas fuel outlet; a second body defining a first compressed air channel having a first outlet, the first compressed air channel surrounding at least a part of the gas fuel channel; a first swirler disposed within the gas fuel channel; and a second swirler disposed within the first compressed air channel, the second swirler extending between the first body and the second body.

[0096] A turbine engine according to any of the preceding clauses, wherein the fuel nozzle assembly further comprises a third body disposed at least partially radially outwardly from the second body.

[0097] A turbine engine according to any of the preceding clauses, wherein the third body is spaced from the second body to define a second compressed air channel therebetween.

[0098] A turbine engine according to any of the preceding clauses, wherein the second compressed air channel includes a fan-shaped section terminating in an inner surface, with a gap formed between the inner surface and the second body.

[0099] A turbine engine according to any of the preceding clauses, wherein the second body is free to move radially within the gap.

[0100] A turbine engine according to any of the preceding clauses, wherein the third body includes an annular arm, and the dome wall includes an annular groove, wherein the annular arm is received within the annular groove.

[0101] A turbine engine according to any of the preceding clauses, wherein the annular arm and the annular groove extend continuously around the entire centerline axis.

[0102] A turbine engine according to any of the preceding clauses, wherein the fuel nozzle assembly is free to move radially within the annular groove.

[0103] A turbine engine according to any of the preceding clauses, wherein the first body, the second body, the first swirler, and the second swirler are integrally formed and separated from the third body.

[0104] A turbine engine according to any of the preceding clauses, wherein the fuel nozzle assembly further comprises a third compressed air channel extending through the gaseous fuel channel and integrally formed with the first body.

[0105] A turbine engine according to any of the preceding clauses, wherein the fuel nozzle assembly further comprises a third body disposed at least partially radially outwardly from the second body; the combustion section includes a set of flame shaping holes configured to discharge a compressed air flow into the combustion chamber and provide a footprint of a flame generated by igniting a gaseous fuel flow from the gaseous fuel channel; and the set of flame shaping holes is disposed within the dome wall, the second body, the third body, or a combination thereof.

[0106] A turbine engine according to any of the preceding clauses, wherein the fuel nozzle assembly further comprises a first set of flame shaping holes disposed within the second body, and the dome wall comprises a second set of flame shaping holes disposed radially outwardly from the first set of flame shaping holes.

[0107] A turbine engine according to any of the preceding clauses, wherein the first body, the second body, the first swirler and the second swirler are integrally formed.

[0108] A turbine engine according to any of the preceding clauses, wherein the first body and the second body are separated from the dome wall.

[0109] A turbine engine according to any of the preceding clauses, wherein the first body comprises a first angled section and the second body comprises a second angled section.

[0110] A turbine engine according to any of the preceding clauses, wherein one of the first angled section or the second angled section extends radially towards the centreline axis while the other of the first angled section and the second angled section extends radially away from the centreline axis; or both the first angled section and the second angled section extend radially away from the centreline axis or radially towards the centreline axis.

[0111] A turbine engine according to any of the preceding clauses, wherein at least one of the first swirler or the second swirler is an orifice plate.

[0112] A method of operating a combustion section according to any of the preceding clauses, the method comprising: supplying a gaseous fuel stream to the gaseous fuel passageway; and supplying a first compressed air stream to the first compressed air passageway.

[0113] A method according to any of the preceding clauses, wherein the gaseous fuel stream comprises one of 100% hydrogen fuel, a mixture of hydrogen fuel and another gaseous fuel, or a mixture of hydrogen fuel and compressed air.

[0114] A method according to any of the preceding clauses, further comprising supplying a second compressed air stream to a second compressed air passageway formed between the second body and a third body disposed radially outwardly from the second body.

[0115] A turbine engine according to any of the preceding clauses, wherein the combustion section further includes a set of flame shaping holes configured to discharge a stream of compressed air into the combustion chamber and provide a footprint of a flame generated by igniting a stream of gaseous fuel from the gaseous fuel channel, and the set of flame shaping holes is disposed within the dome wall, the second body, the third body, or a combination thereof.

[0116] A turbine engine according to any of the preceding clauses, wherein the flame shaping holes are formed as a continuous channel extending circumferentially around the entire centerline axis.

[0117] A turbine engine according to any of the preceding clauses, wherein the flame shaping holes are formed as a segmented channel extending circumferentially around less than the entire centerline axis.

[0118] A turbine engine according to any of the preceding clauses, wherein the flame shaping holes extend circumferentially around less than the entire centerline axis.

[0119] A turbine engine according to any of the preceding clauses, wherein the flame shaping holes are formed as a plurality of circumferentially spaced-apart holes.

[0120] A turbine engine according to any of the preceding clauses, wherein the flame shaping holes are angled radially inwardly, radially outwardly, parallel to the centerline axis, or a combination thereof, with respect to the centerline axis.

[0121] A turbine engine according to any of the preceding clauses, wherein the fuel nozzle assembly further includes a third body disposed at least partially radially outward from the second body.

[0122] A turbine engine according to any of the preceding clauses, wherein the third body is spaced apart from the second body to define a second compressed air channel therebetween.

[0123] A turbine engine according to any of the preceding clauses, wherein the second compressed air channel includes a first leg and a second leg.

[0124] A turbine engine according to any of the preceding clauses, wherein the first leg and the second leg are not parallel.

[0125] A turbine engine according to any of the preceding clauses, wherein the second leg is formed within the third body and the first leg is formed between the third body and the second body.

[0126] A combustion section includes: a burner liner and a dome wall, the burner liner and the dome wall together forming at least a part of a combustion chamber, wherein the dome wall has a fuel nozzle opening; and a fuel nozzle assembly extending through the fuel nozzle opening, the fuel nozzle assembly including: a first body having a centerline axis, the first body defining a gas fuel channel having a gas fuel outlet; a second body defining a first compressed air channel having a first outlet, the first compressed air channel surrounding at least a part of the gas fuel channel; a first swirler disposed within the gas fuel channel; and a second swirler disposed within the first compressed air channel, the second swirler extending between the first body and the second body.

[0127] The combustion section according to any of the preceding clauses, wherein the fuel nozzle assembly further includes a third body disposed at least partially radially outward from the second body.

[0128] The combustion section according to any of the preceding clauses, wherein the third body is spaced apart from the second body to define a second compressed air channel therebetween.

[0129] The combustion section according to any of the preceding clauses, wherein the second compressed air channel includes a sector section terminating at an inner surface, wherein a gap is formed between the inner surface and the second body.

[0130] The combustion section according to any of the preceding clauses, wherein the second body is free to move radially within the gap.

[0131] The combustion section according to any of the preceding clauses, wherein the third body includes an annular arm, and the dome wall includes an annular groove, wherein the annular arm is received within the annular groove.

[0132] The combustion section according to any of the preceding clauses, wherein the annular arm and the annular groove extend continuously around the entire centerline axis.

[0133] The combustion section according to any of the preceding clauses, wherein the fuel nozzle assembly is free to move radially within the annular groove.

[0134] The combustion section according to any of the preceding clauses, wherein the first body, the second body, the first swirler, and the second swirler are integrally formed and separated from the third body.

[0135] A combustion zone according to any of the preceding clauses, wherein the fuel nozzle assembly further comprises a third compressed air channel extending through the gaseous fuel channel, the third compressed air channel being integrally formed with the first body.

[0136] A combustion zone according to any of the preceding clauses, wherein the fuel nozzle assembly further comprises a third body disposed at least partially radially outward from the second body; the combustion zone includes a set of flame shaping holes configured to discharge a compressed air flow into the combustion chamber and provide a footprint of a flame generated by igniting a gaseous fuel flow from the gaseous fuel channel; and the set of flame shaping holes is disposed within the dome wall, the second body, the third body, or a combination thereof.

[0137] A combustion zone according to any of the preceding clauses, wherein the fuel nozzle assembly further comprises a first set of flame shaping holes disposed within the second body, and the dome wall includes a second set of flame shaping holes disposed radially outward from the first set of flame shaping holes.

[0138] A combustion zone according to any of the preceding clauses, wherein the first body, the second body, the first swirler, and the second swirler are integrally formed.

[0139] A combustion zone according to any of the preceding clauses, wherein the first body and the second body are separated from the dome wall.

[0140] A combustion zone according to any of the preceding clauses, wherein the first body includes a first angled section, and the second body includes a second angled section.

[0141] A combustion zone according to any of the preceding clauses, wherein one of the first angled section or the second angled section extends radially towards the centerline axis, while the other of the first angled section and the second angled section extends radially away from the centerline axis; or both the first angled section and the second angled section extend radially away from the centerline axis or radially towards the centerline axis.

[0142] A combustion zone according to any of the preceding clauses, wherein at least one of the first swirler or the second swirler is an orifice plate.

[0143] A method of operating a combustion zone according to any of the preceding clauses, the method comprising: supplying a gaseous fuel flow to the gaseous fuel channel; and supplying a first compressed air flow to the first compressed air channel.

[0144] The method according to any of the preceding clauses, wherein the gaseous fuel stream comprises one of 100% hydrogen fuel, a mixture of hydrogen fuel and another gaseous fuel, or a mixture of hydrogen fuel and compressed air.

[0145] The method according to any of the preceding clauses further comprises supplying a second compressed air stream to a second compressed air channel formed between the second body and a third body disposed radially outward from the second body.

[0146] The combustion section according to any of the preceding clauses further comprises a set of flame shaping holes configured to discharge a compressed air stream into the combustion chamber and provide a footprint of a flame generated by igniting a gaseous fuel stream from the gaseous fuel channel, and the set of flame shaping holes is disposed within the dome wall, the second body, the third body, or a combination thereof.

[0147] The combustion section according to any of the preceding clauses, wherein the flame shaping holes are formed as a continuous channel extending circumferentially around the entire centerline axis.

[0148] The combustion section according to any of the preceding clauses, wherein the flame shaping holes are formed as a segmented channel extending circumferentially around less than the entire centerline axis.

[0149] The combustion section according to any of the preceding clauses, wherein the flame shaping holes extend circumferentially around less than the entire centerline axis.

[0150] The combustion section according to any of the preceding clauses, wherein the flame shaping holes are formed as a plurality of circumferentially spaced holes.

[0151] The combustion section according to any of the preceding clauses, wherein the flame shaping holes are angled radially inward, radially outward, parallel to the centerline axis, or a combination thereof with respect to the centerline axis.

[0152] The combustion section according to any of the preceding clauses, wherein the fuel nozzle assembly further comprises a third body disposed at least partially radially outward from the second body.

[0153] The combustion section according to any of the preceding clauses, wherein the third body is spaced apart from the second body to define a second compressed air channel therebetween.

[0154] The combustion section according to any of the preceding clauses, wherein the second compressed air channel comprises a first leg and a second leg.

[0155] The combustion section according to any of the preceding clauses, wherein the first leg is not parallel to the second leg.

[0156] A combustion zone according to any of the preceding clauses, wherein the second leg is formed within the third body and the first leg is formed between the third body and the second body.

Claims

1. A turbine engine, characterized in that: include: A compressor section, a combustion section, and a turbine section in a series flow arrangement, the combustion section comprising: a combustor liner and a dome wall, the combustor liner and the dome wall together forming at least a portion of a combustion chamber, wherein the dome wall has a fuel nozzle opening; and a fuel nozzle assembly extending through the fuel nozzle opening, the fuel nozzle assembly comprising: a first body having a centerline axis, the first body defining a gas fuel channel having a gas fuel outlet; a second body defining a first compressed air channel having a first outlet, the first compressed air channel surrounding at least a portion of the gas fuel channel; a first swirler disposed in the gas fuel channel; and A second swirler is disposed in the first compressed air channel and extends between the first body and the second body.

2. The turbine engine according to claim 1, characterized in that in, The fuel nozzle assembly further includes a third body disposed at least partially radially outward from the second body.

3. The turbine engine according to claim 2, characterized in that: in, The third body is spaced apart from the second body to define a second compressed air channel therebetween.

4. The turbine engine according to claim 3, characterized in that in, The second compressed air channel includes a sector-shaped section terminating at an inner surface, wherein a gap is formed between the inner surface and the second body.

5. The turbine engine according to claim 4, characterized in that in, The second body is free to move radially within the gap.

6. The turbine engine according to claim 2, characterized in that: in, The third body includes an annular arm and the dome wall includes an annular groove, wherein the annular arm is received within the annular groove.

7. The turbine engine according to claim 6, characterized in that in, The annular arm and the annular groove extend continuously around the entire centerline axis.

8. The turbine engine according to claim 6, characterized in that in, The fuel nozzle assembly is free to move radially within the annular groove.

9. The turbine engine according to claim 2, characterized in that: in, The first body, the second body, the first cyclone, and the second cyclone are integrally formed and separated from the third body.

10. The turbine engine according to claim 2, characterized in that in, The fuel nozzle assembly further includes a third compressed air channel extending through the gaseous fuel channel, the third compressed air channel being integrally formed with the first body.

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