Turbine engine having combustion section with fuel nozzle assembly

Abstract

A turbine engine has a compression section, a combustion section, and a turbine section in a serial flow arrangement. The combustion section has a combustion liner and a domed wall that collectively form at least a portion of the combustion chamber. The combustion section has a fuel nozzle assembly. The fuel nozzle assembly has a compressed air tube and a body. The body defines a gaseous fuel channel into the combustion chamber.

Description

Technical Field

[0001] The present subject matter generally relates to turbine engines, and more particularly, to turbine engines having a combustion section that includes a fuel nozzle assembly. 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, thereby providing compressed air to a combustor for combustion. The combustor may be disposed within the turbine engine and is fluidly coupled to the turbine into which the combustion gases flow.

[0003] The use of hydrocarbon fuels in the combustors of turbine engines is known. Generally, air and fuel are fed into a combustion chamber, the air and fuel are mixed, and then the fuel is burned in the presence of air to produce hot gases. The hot gases are then fed into a turbine, where the hot gases are cooled and expanded to produce power. By-products of fuel combustion typically include environmentally undesirable by-products such as nitrogen oxides and nitrogen dioxide (collectively referred to as NO x x), carbon monoxide (CO), unburned hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides including oxides of sulfur (e.g., SO2 and SO3). Brief Description of the Drawings

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

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

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

[0007] Figure 3 is a schematic of a side cross-sectional view taken along line III-III of Figure 2 further showing the fuel nozzle assemblies discharging into the combustion chamber.

[0008] Figure 4 is a schematic side cross-sectional view of a portion of a combustion section suitable for use as Figure 1 of the combustion section that includes a fuel nozzle assembly having a fuel nozzle terminating in a set of gaseous fuel orifices, a set of compressed air tubes, and a set of swirl generators.

[0009] Figure 5 is fromFigure 4 Schematic view of a fuel nozzle assembly observed along the line of sight V-V, further showing the set of vortex generators including a set of first vortex generators and a set of second vortex generators.

[0010] Figure 6 along Figure 5 Schematic side cross-sectional view of a compressed air pipe in the set of compressed air pipes taken along the section line VI-VI, further showing a part of the compressed air pipe without the set of vortex generators.

[0011] Figure 7 along Figure 5 Schematic side cross-sectional view of a compressed air pipe in the set of compressed air pipes taken along the section line VII-VII, further showing a part of the compressed air pipe including the set of first vortex generators.

[0012] Figure 8 in Figure 5 Schematic view of a fuel nozzle assembly seen in section VIII, further showing the vortex pair generators generated by each vortex generator in the set of vortex generators.

[0013] Figure 9 along Figure 5 Schematic side cross-sectional view of a compressed air pipe in the set of compressed air pipes taken along the section line IX-IX, further showing a part of the compressed air pipe including the set of second vortex generators.

[0014] Figure 10 is Figure 4 Schematic perspective view of a vortex generator in the set of vortex generators, further showing the foot, apex, a pair of opposite side walls, and the trailing edge formed as a triangular wall.

[0015] Figure 11 suitable for use in Figure 4 Schematic perspective view of an exemplary vortex generator suitable for use within the set of vortex generators, further showing the foot, apex, a pair of opposite side walls, and the trailing edge formed as a rectangular wall.

[0016] Figure 12 suitable for use in Figure 4 Schematic front view of an exemplary vortex generator suitable for use within the set of vortex generators, further showing the swept section terminating at the apex.

[0017] Figure 13 suitable for use as Figure 4 Schematic view of an exemplary fuel nozzle assembly suitable for use as a fuel nozzle assembly of , further showing a set of polygonal compressed air pipes and a set of gas fuel orifices including a cluster of gas fuel orifices.

[0018] Figure 14 is a schematic cross-sectional view of a fuel orifice cluster of the set of gas fuel orifice clusters taken along the Figure 13 section line XIV-XIV, further showing the main branch, the first leg, and the second leg.

[0019] Figure 15 is a schematic view of an exemplary fuel nozzle assembly suitable for use as a Figure 4 fuel nozzle assembly, further showing a set of symmetric polygon compressed air tubes and a set of gas fuel orifices.

[0020] Figure 16 is a schematic view of an exemplary fuel nozzle assembly suitable for use as a Figure 4 fuel nozzle assembly, further showing a set of asymmetric polygon compressed air tubes and a set of gas fuel orifices. DETAILED DESCRIPTION

[0021] 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 that terminates in a set of gas fuel orifices. The fuel nozzle assembly includes a set of compressed air tubes. A set of vortex generators is disposed within at least one of the set of compressed air tubes.

[0022] 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 an unexpected flame propagation 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 expands at an undesired location; in other words, flashback may occur. For example, the flame can expand into the fuel nozzle assembly or the 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 H2 fuel may be undesirable 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.

[0023] As used herein, the term "gas fuel" or its iterations refers to a gaseous combustible fuel. It should be understood that gas 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.

[0024] In some aspects, a gaseous fuel exits a 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.

[0025] For purposes of illustration, the present disclosure will be described with respect to a turbine engine (gas turbine engine). However, it will be understood that the aspects of the disclosure described herein are not limited thereto, and the fuel nozzle assemblies described herein can be implemented in engines (including but not limited to turbojet engines, turboprop engines, turboshaft engines, and turbofan engines). The aspects of the disclosure discussed herein have general applicability within non-aircraft engines having burners, such as within other mobile applications and non-mobile industrial, commercial, and residential applications.

[0026] As used herein, the word "exemplary" means "serving as an example, instance, or illustration". Any embodiment described herein as "exemplary" is not necessarily to be construed as superior or advantageous to other embodiments. Additionally, unless otherwise expressly stated, all embodiments described herein should be considered exemplary.

[0027] 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.

[0028] The terms "front" and "rear" refer to relative positions within a turbine engine or vehicle and refer to the normal operating attitude of the turbine engine or vehicle. For example, for a turbine engine, front refers to a position closer to the engine inlet, and rear refers to a position closer to the engine nozzle or exhaust.

[0029] As used herein, the term "upstream" refers to a direction opposite to the fluid flow direction, while the term "downstream" refers to a direction the same as the fluid flow direction. The terms "forward" or "front" indicate in front of something, and "backward" or "rear" indicate behind something. For example, when used with fluid flow, forward / front may indicate upstream, and backward / rear may indicate downstream.

[0030] 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.

[0031] Furthermore, as used herein, the terms "radial" or "radially" refer to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to a direction along a ray extending between the central longitudinal axis of the engine and the outer periphery of the engine.

[0032] All directional references (e.g., radial, axial, proximal, distal, upper, lower, 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 as to the position, orientation, or use of aspects of the disclosure described herein. Connecting references (e.g., attached, coupled, connected, and joined) will be construed broadly and may include intermediate structural elements between assemblies of elements and relative movement between the elements, unless otherwise indicated. Thus, a connecting reference does not necessarily imply that two elements are directly connected and fixed relative to each other. Exemplary drawings are for illustrative purposes only, and the dimensions, positions, sequences, and relative sizes reflected in the accompanying drawings may vary.

[0033] 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.

[0034] Figure 1 is a schematic view of a turbine engine 10. As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 can at least include a compression section 12, a combustion section 14, and a turbine section 16 arranged in a series flow configuration. A drive shaft 18 is rotationally coupled to the compression section 12 and the turbine section 16 such that the rotation of one affects the rotation of the other and defines a rotational axis or engine centerline 20 of the turbine engine 10.

[0035] The compression 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.

[0036] The compression section 12 may 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 compression section 12 may be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The vanes of the compression section 12 may be mounted to a housing, which may extend circumferentially around the turbine engine 10. It should be understood that the representation of the compression section 12 is merely schematic and may have any number of stages. Further, it is contemplated that there may be any other number of components within the compression section 12.

[0037] Similar to the compression section 12, the turbine section 16 may 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 may be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The vanes of the turbine section 16 may be mounted circumferentially to a housing. It should be noted that there may 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 may be any other number of components within the turbine section 16.

[0038] The combustion section 14 may be serially disposed between the compression section 12 and the turbine section 16. The combustion section 14 may be fluidly coupled to at least a portion of the compression section 12 and the turbine section 16 such that the combustion section 14 fluidly couples the compression section 12 to the turbine section 16 at least in part. As a non-limiting example, the combustion section 14 may 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.

[0039] During operation of the turbine engine 10, ambient air or atmospheric air is drawn into the compression section 12 via a fan (not shown) upstream of the compression section 12, and the air is compressed at the compression section 12, defining compressed air. Then, the compressed air may flow into the combustion section 14, where the compressed air is mixed with fuel and ignited, 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, where 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 may together define a working air flow that passes through the fan, the compression section 12, the combustion section 14, and the turbine section 16 of the turbine engine 10.

[0040] Figure 2 depicts a cross-sectional view of the combustion section 14 along line II-II Figure 1 . 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, and the dome wall 44 includes a set of fuel nozzle openings (not shown). The burner 34 includes a set of fuel nozzle assemblies 32 that extend through the set of fuel nozzle openings. The set of fuel nozzle assemblies 32 is arranged annularly about a burner centerline 29. The burner centerline 29 can be the engine centerline 20 ( Figure 1 ) of the turbine engine 10 ( Figure 1 ). 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.

[0041] The set of fuel nozzle assemblies 32 is arranged about the burner centerline 29. Each fuel nozzle in the set of fuel nozzle assemblies 32 includes a fuel nozzle centerline 31. The set of fuel nozzle assemblies 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 nozzle assemblies 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 nozzle assemblies 32 can be fluidly coupled to the combustion chamber 46. The 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 nozzle assemblies 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.

[0042] Figure 3 depicts a cross-sectional view along Figure 2Cross-sectional view taken along line III-III, showing the combustion section 14. At least one flame shaping passage may 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 may include the first set of flame shaping holes 50, the 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.

[0043] The first set of flame shaping holes 50 may pass through the dome wall 44 to fluidly couple compressed air from the compression section 12 or the compressed air passage 48 to the combustion chamber 46.

[0044] The second first set of flame shaping holes 52 may pass through the burner liner 38 to fluidly couple compressed air from the compressed air passage 48 to the combustion chamber 46.

[0045] Each fuel nozzle assembly in the set of fuel nozzle assemblies 32 may be coupled to and disposed within the dome assembly 56. Each fuel nozzle assembly in the set of fuel nozzle assemblies 32 may include a flare cone 58 and a swirler 60. The flare cone 58 includes an outlet 62 that is directly fluidly coupled to the corresponding fuel nozzle assembly of the combustion chamber 46. Each fuel nozzle assembly in the set of fuel nozzle assemblies 32 is fluidly coupled to the fuel inlet 64 via a passage 66. Each fuel nozzle assembly in the set of fuel nozzle assemblies 32 includes a fuel nozzle centerline 31.

[0046] Both the inner burner liner 42 and the outer burner liner 40 may have outer surfaces 68 and inner surfaces 70 that at least partially define the combustion chamber 46. The burner liner 38 may be made of one continuous integral part or may 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 may define a first piece of the burner liner 38, while the inner surface 70 may 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. Further contemplated, the burner liner 38 may be any type of burner liner 38, including but not limited to single-wall or double-wall liners or tile liners. The igniter 72 may be disposed at the burner liner 38 and 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).

[0047] During operation, from a compressed air supply (such as Figure 1The compressed air (C) from the LP compressor 22 or the HP compressor 24 can flow from the compression section 12 to the burner 34. A portion of the compressed air (C) can flow through the dome assembly 56. The first portion of the compressed air (C) flowing through the dome assembly 56 can be supplied as a swirling air flow (S) to each fuel nozzle assembly in the set of fuel nozzle assemblies 32 via the swirler 60. The fuel flow (F) is supplied to each fuel nozzle assembly in the set of fuel nozzle assemblies 32 via the fuel inlet 64 and the passage 66. The swirling air flow (S) and the fuel flow (F) are mixed at the flared cone portion 58 and supplied as a fuel / air mixture to the combustion chamber 46. 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.

[0048] 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 air flow (D1) to the first set of flame shaping holes 50. That is, a portion of the compressed air (C) from the compression 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 air flow (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.

[0049] Another portion of the compressed air (C) can flow through the compressed air passage 48 and can be supplied as a second flame shaping air flow (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.

[0050] The first flame shaping air flow (D1) can be used to direct and shape the flame. The second flame shaping air flow (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.

[0051] Figure 3The burner 34 shown in is well-suited for using hydrogen-containing gas as fuel because, compared with traditional hydrocarbon fuels, it helps to accommodate the faster-moving flame front associated with hydrogen fuel. However, the burner 34 can be used with traditional hydrocarbon fuels.

[0052] Figure 4 is suitable for use as Figure 1 A schematic side cross-sectional view of a part of the 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, similar parts will be identified by similar names, and it should be understood that the description of the combustion section 14 applies to the combustion section 200 unless otherwise specified.

[0053] 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 ), the combustion chamber 216 is further defined by a combustion liner (not shown) (e.g., Figure 3 the inner burner liner 42 and the outer burner liner 40 of ). The combustion section 200 includes a fuel nozzle assembly 202. Similar to Figure 2 the set of fuel nozzle assemblies 32 of , the fuel nozzle assembly 202 can be included within a set of fuel nozzle assemblies arranged annularly along the dome wall 214.

[0054] The fuel nozzle assembly 202 includes a fuel nozzle assembly 202 terminating in a set of gas fuel orifices 220 and a set of compressed air tubes 222. The fuel nozzle assembly 202 includes a body 206 having a head 204 and defining a gas fuel channel 208 and a centerline axis 210. The fuel nozzle assembly 202 is coupled to the dome wall 214 by any suitable method (such as but not limited to adhesion, welding, bonding, fastening, frictional contact, etc.).

[0055] The head 204 is defined as a part of the fuel nozzle assembly 202 that extends through a corresponding fuel nozzle assembly opening (not shown) provided along the dome wall 214. The head 204 includes a perimeter 212 facing the dome wall 214. At least a part of the perimeter 212 can be radially spaced from the dome wall 214 or in direct contact with the dome wall 214.

[0056] The set of compressed air tubes 222 is at least partially disposed within the head 204. Each compressed air tube of the set of compressed air tubes 222 includes a compressed air inlet 224 and a compressed air outlet 226 that discharges into the combustion chamber 216. The set of gas fuel orifices 220 is disposed along the head 204 and discharges into the combustion chamber 216. The gas fuel channel 208 may include a fuel manifold 218 disposed within the head 204, and the fuel manifold 218 distributes the fluid flow within the gas fuel channel 208 to the set of gas fuel orifices 220. The fuel manifold 218 may be defined by a series of channels extending through the head 204. The fuel manifold 218 may extend around the set of compressed air tubes 222. A portion of the gas fuel manifold 218 that extends around the set of compressed air tubes 222 is shown in dashed lines.

[0057] The set of compressed air tubes 222 may be integrally or non-integrally formed with the head 204. As a non-limiting example, the set of compressed air tubes 222 may be defined by channels cut or otherwise formed within the body 206 of the fuel nozzle assembly 202. Alternatively, the set of compressed air tubes 222 may be defined by discrete bodies or tubes inserted into the fuel nozzle assembly 202. Each compressed air tube 222 defines a corresponding tube centerline axis 228. The compressed air inlet 224 is defined by a portion of the compressed air tube 222 disposed within the head 204 that is axially farthest from the compressed air outlet 226 relative to the tube centerline axis 228.

[0058] A set of swirl generators 230 is disposed within the set of compressed air tubes 222. Each of the set of swirl generators 230 is defined as a structure that extends radially from the body of the fuel nozzle assembly 202 or otherwise from the outer boundary of the corresponding compressed air tube of the set of compressed air tubes 222 toward the tube centerline axis 228.

[0059] During operation, a gas fuel flow (Fg) is supplied to the gas fuel channel 208. The gas fuel flow (Fg) flows through the gas fuel channel 208 and discharges into the combustion chamber 216 as an outlet gas fuel flow (Fgo) through the set of gas fuel orifices 220. The outlet gas fuel flow (Fgo) may be ignited within the combustion chamber 216 or within the fuel nozzle assembly 202 by an igniter (not shown) or by auto-ignition. Ignition of the outlet gas fuel flow (Fgo) produces a flame within the combustion chamber 216. The gas fuel flow (Fg) may comprise 100% hydrogen (“H2”) fuel, or a mixture of hydrogen fuel and another gas fuel (e.g., methane). Alternatively, the gas fuel flow (Fg) may be a mixture of H2 fuel and compressed air from, for example, a compression section (e.g., Figure 1 the compression section 12).

[0060] A compressed air flow (Fc) (e.g., Figure 3Compressed air (C) is supplied to the set of compressed air tubes 222. A compressed air flow (Fc) exits as an outlet compressed air flow (Fco) from the compressed air outlet 226. The outlet compressed air flow (Fco) can be swirling or non - swirling. In the case where the outlet compressed air flow (Fco) is swirling, the outlet compressed air flow (Fco) includes a helical flow or other swirling flow that flows into the combustion chamber 216. When swirling, the amount of swirl of the outlet compressed air flow (Fco) can be quantified by a swirl number, which is defined as the integral of the tangential momentum of the fluid flow downstream of the corresponding swirler and the axial momentum. When swirling, the outlet compressed air flow (Fco) has a swirl number greater than or equal to 0.2 and less than or equal to 1.2. Alternatively, the outlet compressed air flow (Fco) can be non - swirling, such that the swirl number is zero.

[0061] Each compressed air tube in the set of compressed air tubes 222 has a corresponding subgroup of the set of gas fuel orifices 220 that outputs an outlet gas fuel flow (Fgo) near the corresponding compressed air tube 222. The outlet compressed air flow (Fco) is used to capture or otherwise intercept at least a portion of the outlet gas fuel flow (Fgo) that exits the gas fuel orifice 220 closest to the corresponding compressed air tube 222. The interception of the outlet compressed air flow (Fco) on the outlet gas fuel flow (Fgo) produces a mixed gas fuel and air flow (Fm). The mixed gas fuel and air flow (Fm) is then ignited within the combustion chamber 216 to define a flame within the combustion chamber 216. Since the set of compressed air tubes 222 can include multiple compressed air tubes, each fuel nozzle assembly 202 can include multiple discrete mixed gas fuel and air flows (Fm) that are supplied to the combustion chamber 216. The multiple discrete mixed gas fuel and air flows (Fm) are illustrated by multiple instances of the mixed gas fuel and air flow (Fm). The introduction of the multiple discrete mixed gas fuel and air flows (Fm) in turn means that each fuel nozzle assembly 202 can include multiple flames, rather than just a single flame as in a conventional fuel nozzle assembly. It has been found that using multiple smaller flames instead of a single larger flame per fuel nozzle assembly reduces the overall NO x emissions.

[0062] The outlet compressed air flow (Fco) is used to shape the flame (e.g., provide a desired footprint of the physical flame within the combustion chamber 216) and isolate various portions of the combustion section 200 from the flame. As a non-limiting example, the outlet compressed air flow (Fco) causes the outlet gaseous fuel flow (Fgo) to follow the path followed by the outlet compressed air flow (Fco). This in turn means that the flame generated by the ignition of the outlet gaseous fuel flow (Fgo) follows the path followed by the outlet compressed air flow (Fco). In other words, the outlet compressed air flow (Fco) shapes and directs the flame in a desired manner. The outlet compressed air flow (Fco) further isolates various portions of the combustion section 200 (e.g., the dome wall 214, the burner liner 38( Figure 3 ) etc.) from the heat of the flame by providing a layer of isolation between the flame and other sections of the combustion section 200, cooling other sections of the combustion section 200, or otherwise directing the flame away from other sections of the combustion section 200. Additionally, each fuel nozzle assembly 202 using multiple discrete mixed gaseous fuel and air flows (Fm) to produce multiple smaller flames rather than a single larger flame contributes to the flame shaping and isolation capabilities of the outlet compressed air flow (Fco). Since the fuel nozzle assembly 202 includes multiple smaller flames, the amount of compressed air required to isolate the combustion section 200 from the flame and effectively shape the flame is reduced compared to the amount of compressed air required to isolate and shape a single larger flame.

[0063] 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 portions 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 compressed air flow (Fc) to one or more of the set of compressed air tubes 222. As a non-limiting example, the controller module may automatically control the supply of the gaseous fuel flow (Fg) to any one or more of the set of gaseous fuel orifices 220. The gaseous fuel flow (Fg) and the compressed air flow (Fc) may be controlled independently of each other. As a non-limiting example, the compressed air flow may be cut off to one or more of the set of compressed air tubes 222 while the gaseous fuel flow (Fg) is supplied to one or more of the set of gaseous fuel orifices 220.

[0064] When using gaseous H2 fuel, compared with traditional fuels, the shaping of the flame and the isolation between the flame and other parts of the combustion section 200 are particularly important. Compared with traditional fuels, gaseous H2 fuel has a higher combustion temperature and a tendency to flash back. Therefore, the outlet compressed air flow (Fco) is used to push the flame away from the fuel nozzle assembly 202. Pushing the outlet gas fuel flow (Fgo) away from the fuel nozzle assembly 202 helps ensure that once ignited, flashback into the fuel nozzle assembly 202 of the outlet gas fuel flow (Fgo) does not occur. The outlet compressed air flow (Fco) further ensures that a flame with a combustion temperature higher than that of a flame generated by traditional fuels does not overheat the section of the combustion section 200. The outlet compressed air flow (Fco) can further be used to produce a uniform flame distribution at the burner outlet. It is conceivable that a uniform flame distribution or temperature distribution at the burner outlet will result in higher efficiency of the turbine section.

[0065] Figure 5 is from Figure 4 a schematic view of the combustion section 200 observed along the line of sight V-V. For illustrative purposes, the fuel nozzle assembly 202 is removed from the dome wall 214 ( Figure 4 ). The head 204 can take any suitable form. As a non-limiting example, the head 204 can be circular, such that the perimeter 212 is defined by the circumference of a circle. As a non-limiting example, the head can be any suitable polygonal shape. The set of compressed air tubes 222 and the set of gas fuel orifices 220 are entirely disposed within the bounds of the perimeter 212.

[0066] Any number of one or more compressed air tubes are in the set of compressed air tubes 222. The set of compressed air tubes 222 can be spaced evenly or unevenly along the head 204. The fuel nozzle assembly 202 can be symmetric or asymmetric about a plane extending along the centerline axis 210 and intersecting the head 204. The placement of the set of compressed air tubes 222 can be symmetric or asymmetric about a plane extending along the centerline axis 210 and intersecting the head 204. Each compressed air tube in the set of compressed air tubes 222 can be symmetric or asymmetric about a plane extending along the tube centerline axis 228. The set of compressed air tubes 222 can include compressed air tubes aligned with the tube centerline axis 228. In other words, the set of compressed air tubes 222 can include corresponding compressed air tubes having a tube centerline axis 228 aligned with the tube centerline axis 228, as shown. The dimensions of at least a portion of the set of compressed air tubes 222 can be equal or unequal to each other.

[0067] Each compressed air tube in the set of compressed air tubes 222 is arranged to be at a first distance (L1) from an adjacent corresponding compressed air tube. The first distance (L1) is measured between the tube centerline axes 228 of adjacent compressed air tubes 222. The first distance (L1) between a first compressed air tube and a second compressed air tube adjacent to the first compressed air tube may be equal to or different from the first distance (L1) between the first compressed air tube and a third compressed air tube adjacent to the first compressed air tube, where the third compressed air tube is different from the second compressed air tube.

[0068] The set of gas fuel orifices 220 is circumferentially arranged around the set of compressed air tubes 222 with respect to the tube centerline axis 228. As a non-limiting example, each compressed air tube in the set of compressed air tubes 222 may include a corresponding set of gas fuel orifices from the set of gas fuel orifices 220 arranged around the compressed air tube in a circular or other polygonal shape.

[0069] Each gas fuel orifice in the set of gas fuel orifices 220 may be circumferentially aligned with a corresponding vortex generator from the set of vortex generators 230 disposed within the nearest compressed air tube in the set of compressed air tubes 222 with respect to the tube centerline axis 228.

[0070] Each vortex generator in the set of vortex generators 230 extends from a root 236 that is disposed along or otherwise faces the head 204 and extends radially with respect to the corresponding tube centerline axis 228 of the corresponding compressed air tube within which the vortex generator is disposed to a vertex 240. Each vortex generator in the set of vortex generators 230 includes a pair of opposing sidewalls connecting the root 236 and the vertex 240.

[0071] The set of vortex generators 230 includes any suitable number of vortex generators. At least a portion of the vortex generators 230 may have different configurations. As a non-limiting example, the set of vortex generators 230 may include a set of first vortex generators 232 and a set of second vortex generators 234, where the set of first vortex generators 232 is different from the set of second vortex generators 234. It should be understood that all the vortex generators in the set of vortex generators 230 may have the same configuration, or there may be any number of two or more sets of vortex generators with different structures.

[0072] As a non-limiting example, the set of first vortex generators 232 may include a first polygonal shape, while the set of second vortex generators 234 includes a second polygonal shape that is different from the first polygonal shape. When viewed along a plane perpendicular to the tube centerline axis 228 and intersecting the vortex generators, the set of vortex generators 230 may be formed into any suitable polygonal shape. The polygonal shape may be, but is not limited to, a triangle, a rectangle, a diamond, a hexagon, an ellipse, a semicircle, etc. As a non-limiting example, the set of gas fuel orifices 220 may be circumferentially aligned with the set of first vortex generators 232 but not the set of second vortex generators 234, or vice versa.

[0073] Each compressed air tube in the set of compressed air tubes 222 may include the set of first vortex generators 232 and the set of second vortex generators 234. The set of first vortex generators 232 and the set of second vortex generators 234 may be alternately or non-alternatingly spaced within the respective compressed air tubes. The set of vortex generators 230 within a single compressed air tube 222 may be uniformly or non-uniformly circumferentially spaced within the compressed air tube around the tube centerline axis 228.

[0074] Figure 6 It is along Figure 5 Schematic side cross-sectional view of a compressed air tube in the group of compressed air tubes 222 taken along section line VI-VI. The compressed air tube 222 taken along section line VI-VI does not include the group of vortex generators 230. It should be understood that a vortex generator pair is formed between two vortex generators in the group of vortex generators 230 that are spaced apart on radially opposite sides of the compressed air tube 222 relative to the tube centerline axis 228. In the case of a circular compressed air tube 222, the vortex generators in the vortex generator pair are spaced 180 degrees relative to each other.

[0075] The compressed air pipe 222 may include a surface 252 that terminates at the compressed air outlet 226. At least a portion of the surface 252 may extend radially outward relative to the tube centerline axis 228 to define a flared surface, as shown. Alternatively, the surface 252 may extend constant (no flaring) or radially inward relative to the tube centerline axis 228 to define a tapered surface. The surface 252 may extend at a surface angle 251 relative to the protrusion 254 of the tube centerline axis 228. The surface angle 251 may be constant or non-constant along the surface 252. The surface angle 251 has a value greater than -60 degrees and less than or equal to 60 degrees.

[0076] During operation, a compressed air flow (Fc) is supplied to the compressed air pipe 222. At least a portion of the compressed air flow (Fc) follows the surface 252 where the set of vortex generators 230 is absent and exits the compressed air outlet 226 as a first outlet compressed air flow (Fco1). The first outlet compressed air flow (Fco1) forms Figure 4 a part of the outlet compressed air flow (Fco). The first outlet compressed air flow (Fco1) follows the surface 252. Thus, if the surface 252 flares radially outward, the first outlet compressed air flow (Fco1) will follow the flared surface and be radially outwardly guided from the pipe centerline axis 228 into the combustion chamber 216.

[0077] The compressed air pipe 222 extends a first axial distance (A1) between the compressed air inlet 224 and the compressed air outlet 226 relative to the pipe centerline axis 228. When observed along a portion of the compressed air outlet 226 that does not include the set of vortex generators 230 ( Figure 4 ), the compressed air outlet 226 extends a first radial height (H1) relative to the pipe centerline axis 228. The first radial height (H1) is defined as the maximum radial distance along the compressed air outlet 226 between opposing portions of the compressed air pipe 222, regardless of the shape of the compressed air pipe 222.

[0078] Figure 7 is a schematic side cross-sectional view of the compressed air pipe 222 taken along section line VII-VII of Figure 5 . The compressed air pipe 222 taken along section line VII-VII includes a portion of the set of vortex generators 230; in particular, the set of first vortex generators 232.

[0079] The set of vortex generators 230 can be integrally formed with or coupled to the head 204 at the root 236, as shown by the dashed line. The root 236 is defined as the portion of the set of vortex generators 230 that is aligned with the surface 252 ( Figure 6 ). In other words, if the vortex generators 230 are formed as separate bodies and subsequently coupled to the head 204, the root 236 will extend along the surface 252. Each vortex generator in the set of vortex generators 230 includes a foot 260, which is defined as the portion of the vortex generator that is axially furthest from the compressed air outlet 226 relative to the pipe centerline axis 228. Each vortex generator in the set of vortex generators 230 includes a trailing edge 266 and a leading edge 264. At least a portion of the trailing edge 266 can be axially aligned with or offset from the compressed air outlet 226 relative to the pipe centerline axis 228.

[0080] The compressed air outlet 226 extends radially a second radial height (H2) relative to the tube centerline axis 228. The second radial height (H2) is measured between the opposing vertices 240 of the opposing first vortex generators in the set of first vortex generators 232. Each first vortex generator in the set of first vortex generators 232 extends radially a third radial height (H3) relative to the tube centerline axis 228. Each first vortex generator in the set of first vortex generators 232 extends axially a second axial distance (A2) between a foot 260 and a vertex 240 relative to the tube centerline axis 228. The second radial height (H2) can be less than, equal to, or greater than the third radial height (H3). Refer to Figure 6 and Figure 7 , the second radial height (H2) is less than the first radial height (H1). In other words, the set of vortex generators 230 radially constricts the compressed air tube 222 at the compressed air outlet 226.

[0081] The gaseous fuel channel 208 defines a channel centerline axis 250 that branches within the fuel manifold 218 ( Figure 4 ) and extends to each gaseous fuel orifice in the set of gaseous fuel orifices 220. An orifice angle 258 is formed between the channel centerline axis 250 and a projection 254 of the tube centerline axis 228 at a respective gaseous fuel orifice in the set of gaseous fuel orifices 220. The orifice angle 258 has a value greater than or equal to -60 degrees and less than or equal to 60 degrees. As a non-limiting example, the orifice angle 258 of at least a portion of the set of gaseous fuel orifices 220 can be non-zero and oriented such that Figure 4 the exiting gaseous fuel flow (Fgo) is radially directed away from the compressed air outlet 226 of Figure 4 the exiting compressed air flow (Fco).

[0082] Each gaseous fuel orifice in the set of gaseous fuel orifices 220 is disposed at a sixth radial height (H6) relative to the tube centerline axis 228, the sixth radial height (H6) being measured between the location where the channel centerline axis 250 intersects the gaseous fuel orifice and the location where a root 236 meets a trailing edge 266. Each gaseous fuel orifice in the set of gaseous fuel orifices 220 includes a respective radial width (D) relative to the tube centerline axis 228. The gaseous fuel orifices 220 can be formed as circular orifices or any other polygonal shape. When formed as a circular orifice, the radial width (D) is the diameter. The radial width (D) is less than the sixth radial height (H6). As a non-limiting example, the sixth radial height (H6) is greater than or equal to 1.5 times the radial width (D) and less than or equal to 20 times the radial width (D) (e.g., 1.5*D < H6 < 20*D).

[0083] During operation, a compressed air flow (Fc) is supplied to the compressed air pipe 222. At least a portion of the compressed air flow (Fc) flows through the set of first vortex generators 232 and flows out of the compressed air outlet 226 as a second outlet compressed air flow (Fco2). The second outlet compressed air flow (Fco2) forms Figure 4 The set of vortex generators 230 is configured to guide the compressed air flow (Fc) so that the second outlet compressed air flow (Fco2) forms a vortex in the combustion chamber 216.

[0084] Figure 8 is Figure 5 Schematic diagram of the fuel nozzle assembly 202 as seen in section VIII of FIG. Although described in terms of the first vortex generator 232, it should be understood that aspects of the first vortex generator 232 may be applied to Figure 5 Any vortex generator in the set of vortex generators 230.

[0085] For purposes of illustration, an exemplary vortex generator 231 in the set of vortex generators 230 is shown in phantom. A vortex generator centerline 242 extends from a midpoint disposed along the base midway between the opposing sidewalls 238 to an apex 240. Each vortex generator in the set of vortex generators 230 is angled at an included angle 246 formed between the corresponding vortex generator centerline 242 and a radial line 244 extending radially outward from the corresponding tube centerline axis 228 of the corresponding compressed air tube in which the vortex generator is disposed and intersecting the root 236 midway between the opposing sidewalls 238. For purposes of illustration, the radial line 244 is not shown within the first vortex generator 232 because the radial line 244 corresponds to the vortex generator centerline 242 of the first vortex generator 232. The included angle 246 has a value greater than or equal to -60 degrees and less than or equal to 60 degrees. As a non-limiting example, the included angle 246 of at least one vortex generator may be different than 0 degrees. The exemplary vortex generator 231 includes a non-zero included angle 246, while as shown, the first vortex generator 232 includes an included angle 246 of zero.

[0086] During operation, each vortex generator in the set of vortex generators 230 generates two vortices that define a vortex pair disposed on opposite sides of the opposite sidewalls 238. The two vortices generated by each vortex generator in the set of vortex generators 230 are defined as a vortex pair. Thus, each vortex generator in the set of vortex generators 230 is configured to generate a vortex pair on opposite or circumferentially opposite sides of the vortex generator.

[0087] The swirl pair is used to increase the gas fuel (eg, Figure 4Trapping of the outlet gas fuel stream (Fgo). Specifically, by using at least a second outlet compressed air stream (Fco2), the outlet gas fuel stream (Fgo) is captured by the outlet compressed air stream (Fco). Capturing the outlet gas fuel stream (Fgo) in turn ensures that the outlet gas fuel stream (Fgo) is sufficiently mixed with the compressed air stream before being ignited. As used herein, the terms "sufficiently mixed" or "effectively mixed" refer to the degree to which two or more fluids are mixed together. It should be understood that the optimal resulting mixture of two fluids will be a homogeneous mixture of the two or more fluids. In other words, one part of the mixture does not contain more of one fluid than another part of the mixture. In the case of the fuel nozzle assembly 202, compared to a fuel nozzle assembly that does not include the set of vortex generators 230, Figure 4 the resulting mixed gas fuel and air stream (Fm) includes a stream of a mixture of fuel and air, wherein the gaseous fuel is uniformly or more uniformly distributed in the mixed gas fuel and air stream (Fm).

[0088] It has been found that producing a more homogeneous mixture of gaseous fuel and compressed air reduces the NO x emissions in the combustion zone 200. It is contemplated that if one section of the mixed gas fuel and air stream (Fm) is richer than another section (e.g., contains a higher concentration of gaseous fuel), the richer section will produce increased NO x emissions. This in turn means that compared to the fuel nozzle assembly 202 that includes a mixed gas fuel and air stream (Fm) that is sufficiently mixed due to the use of the set of vortex generators 230, an insufficiently mixed mixed gas fuel and air stream (Fm) will produce more NOx emissions when combusted.

[0089] At least a portion of the gas fuel orifices in the set of gas fuel orifices 220 is circumferentially aligned with at least a portion of the set of vortex generators 230. This alignment in turn ensures that the outlet gas fuel stream (Fgo) is directly injected into the opposing vortex (e.g., the second outlet compressed air stream (Fco2)). Directly injecting the outlet gas fuel stream (Fgo) into the vortex pair ensures that the outlet gas fuel stream (Fgo) is sufficiently mixed with the outlet compressed air stream (Fco).

[0090] Figure 9 is a schematic side cross-sectional view of the compressed air tube 222 taken along Figure 5 section line IX-IX. The compressed air tube 222 taken along section line IX-IX includes a portion of the set of vortex generators 230; specifically, the set of second vortex generators 234. At least a portion of the set of gas fuel orifices 220 shown in dashed lines may be circumferentially aligned with the set of second vortex generators 234.

[0091] The compressed air outlet 226 extends radially a fourth radial height (H4) relative to the tube centerline axis 228. The fourth radial height (H4) is measured between the opposing vertices 240 of the opposing second vortex generators in the set of second vortex generators 234. Each second vortex generator in the set of second vortex generators 234 extends radially a fifth radial height (H5) relative to the tube centerline axis 228. Each second vortex generator in the set of second vortex generators 234 extends axially a third axial distance (A3) between a foot 260 and a vertex 240 relative to the tube centerline axis 228. The fourth radial height (H4) can be less than, equal to, or greater than the fifth radial height (H5). Refer to Figure 6 and Figure 9 , the fourth radial height (H4) is less than the first radial height (H1). In other words, the set of vortex generators 230 radially constricts the compressed air tube 222 at the compressed air outlet 226.

[0092] During operation, a compressed air flow (Fc) is supplied to the compressed air tube 222. At least a portion of the compressed air flow (Fc) flows through the set of second vortex generators 234 and exits the compressed air outlet 226 as a third outlet compressed air flow (Fco3). The third outlet compressed air flow (Fco3) forms Figure 4 a portion of the outlet compressed air flow (Fco). The set of vortex generators 230 is configured to direct the compressed air flow (Fc) such that the third outlet compressed air flow (Fco3) forms a vortex within the combustion chamber 216, similar to Figure 7 the second outlet compressed air flow (Fb2). Each second vortex generator in the set of second vortex generators 234 generates a pair of vortices disposed on opposing sides of the vortex generator.

[0093] Refer to Figure 5 - 7 and Figure 9 , at least one of the second axial distance (A2) or the third radial height (H3) is respectively greater than the third axial distance (A3) or the fifth radial height (H5). In other words, the set of second vortex generators 234 is smaller than the set of first vortex generators 232. The variation between the set of first vortex generators 232 and the set of second vortex generators 234 results in a variation in the size of the vortices generated by the respective vortex generators. The larger the vortex generator, the larger each vortex generated by the vortex generator will be. Accordingly, the set of first vortex generators 232 generates larger vortices compared to the vortices of the set of second vortex generators 234.

[0094] The set of vortex generators 230 can be defined by respective parameters that are related to each other. A first radial height (H1) is greater than a third radial height (H3) of the set of first vortex generators 232 and a fifth radial height (H5) of the set of second vortex generators 234. As a non-limiting example, the third radial height (H3) is greater than or equal to 0.01 times the first radial height (H1) and less than or equal to 0.4 times the first radial height (H1) (e.g., 0.01*H1 < H3 < 0.4*H1). As a non-limiting example, the fifth radial height (H5) is greater than or equal to 0.005 times the first radial height (H1) and less than or equal to 0.4 times the first radial height (H1) (e.g., 0.001*H1 < H5 < 0.4*H1).

[0095] A first axial distance (A1) is greater than a second axial distance (A2) of the set of first vortex generators 232 and a third axial distance (A3) of the set of second vortex generators 234. As a non-limiting example, the second axial distance (A2) is greater than or equal to 0.3 times the first axial distance (A1) and less than or equal to 1 times the first axial distance (A1) (e.g., 0.3*A1 < A2 < A1). As a non-limiting example, the third axial distance (A3) is greater than or equal to 0.1 times the first axial distance (A1) and less than or equal to 1 times the first axial distance (A1) (e.g., 0.1*A1 < A3 < A1).

[0096] A first distance (L1) between the compressed air tube 222 and an adjacent tube is greater than a first radial height (H1) of the compressed air tube 222. As a non-limiting example, the first axial distance (A1) can be greater than or equal to 1.1 times the first distance (L1) and less than or equal to 4 times the first distance (L1) (e.g., 1.1*L1 < A1 < 4*L1). The first distance (L1) can be greater than or equal to 1.1 times the first radial height (H1) and less than or equal to 4 times the first radial height (H1) (e.g., 1.1*H1 < L1 < 4*H1).

[0097] A second radial height (H2) is less than the first radial height (H1). In other words, the set of vortex generators 230 radially constricts the compressed air tube 222 at the compressed air outlet 226. A pair of opposing sidewalls 238 can cover the foot 260. Alternatively, the leading edge 264 can be formed to be similar to the trailing edge 266 and include a triangular wall.

[0098] Figure 10 Yes Figure 4 A schematic perspective view of the vortex generator 230 of the set of vortex generators 230. The vortex generator 230 can be any one of the set of first vortex generators 232 ( Figure 5 ) or the set of second vortex generators 234 ( Figure 5 ). The vortex generator 230 is formed as an inverted pyramid converging at the apex 240. The trailing edge 266 can be formed as a triangular wall. In other words, the pair of opposing sidewalls 238 converge inwardly from the root 236 and reach the leading edge 264 and the apex 240. Thus, when viewed in a plane perpendicular to the tube centerline axis 228 ( Figure 4 ) and intersecting the vortex generator 230, the vortex generator 230 includes a triangular cross-section. Although shown as an inverted pyramid, it should be understood that the vortex generator 230 can take any suitable three-dimensional polygonal shape. Thus, when viewed in a plane, the vortex generator 230 can include any suitable cross-section, such as but not limited to triangular, rectangular, trapezoidal, etc.

[0099] Figure 11 Is suitable for use within Figure 4 The set of vortex generators 230 is a schematic perspective view of an exemplary vortex generator 330. The vortex generator 330 is similar to the set of vortex generators 230; thus, similar parts will be identified with similar numbers increased to the 300 series, and it should be understood that the description of the set of vortex generators 230 applies to the vortex generator 330 unless otherwise stated.

[0100] The vortex generator 330 includes a root 336, an apex 340, a foot 360, and a pair of opposing sidewalls 338. The vortex generator 330 includes a leading edge 364 extending between the foot 360 and the apex 340.

[0101] The vortex generator 330 is similar to the vortex generator 230 ( Figure 10 ) because the vortex generator is formed as an inverted pyramid. However, the vortex generator 330 includes a trailing edge 366. Different from the trailing edge 266 ( Figure 10 ), the trailing edge 366 can be formed as a rectangular wall. In other words, the pair of opposing sidewalls 338 extend from the root 236 and reach the leading edge 364 and the apex 240 without intersecting. Thus, when viewed in a plane perpendicular to the tube centerline axis (e.g., Figure 4 The tube centerline axis 228) and intersecting the vortex generator 330, the vortex generator 330 includes a rectangular cross-section. It should be understood that the leading edge 364 and the trailing edge 366 can be formed as any suitable polygonal walls.

[0102] Figure 12 Is suitable for use withinFigure 4 Schematic perspective view of an exemplary vortex generator 430 used within the set of vortex generators 230. The vortex generator 430 is similar to the sets of vortex generators 230, 330; thus, like parts will be identified with like numerals incremented to the 400 series, and it should be understood that the description of the sets of vortex generators 230, 330 applies to the vortex generator 430 unless otherwise noted.

[0103] The vortex generator 430 includes a root 436, a vertex 440, and a pair of opposing sidewalls 438. The vortex generator 430 includes a trailing edge 466 extending between the root 436 and the vertex 440. The vortex generator 430 includes a vortex generator centerline axis 442 that extends from the vertex 440 to a point on the root 436 midway between the opposing sidewalls 438. The vortex generator 430 may be disposed within a compressed air tube (not shown) defining a tube centerline axis 428.

[0104] The vortex generator 430 is similar to the vortex generator 230 ( Figure 10 ), 330 ( Figure 11 ) in that it is used to impart swirl to a fluid flow passing through the vortex generator 430. However, the vortex generator 430 includes a swept body 470 that originates from a body 471 of the vortex generator 430. The transition 472 between the swept body 470 and the body 471 is shown in dashed lines. The swept body 470 is defined as a portion of the vortex generator 430 that includes an edge that is circumferentially swept relative to the tube centerline axis 428 (e.g., the opposing sidewalls are swept in the circumferential direction).

[0105] The vortex generator 430 as a whole extends a total radial height (Ht) from the root 436 to the vertex 440 relative to the tube centerline axis 428 (equal to the third radial height (H3) or the fifth radial height (H5) respectively of Figure 7 and Figure 8 ). The body 471 extends a body radial height (Hm) from the transition 472 to the root 436 relative to the tube centerline axis 428. The body radial height (Hm) may be greater than or equal to 0.1 times the total radial height (Ht) and less than or equal to 0.7 times the total radial height (Ht) (e.g., 0.1*Ht < Hm < 0.7*H5). The swept body 470 extends a swept body radial height (Hs) from the transition 472 to the vertex 440 relative to the tube centerline axis 428. The swept body radial height (Hs) is greater than, equal to, or less than the body radial height (Hm).

[0106] The size, positioning, and formation of the swept body 470 are for imparting swirl to a compressed air flow passing through the vortex generator 430 (e.g., Figure 4The compressed air flow (Fc)) is directed to a desired location within a compressed air tube (e.g., Figure 4 compressed air tube 222) in which a vortex generator 430 is provided. As a non-limiting example, the swept body 470 can impart tangential momentum to the compressed air flow. The tangential momentum can direct the compressed air flow towards the central region of the compressed air tube (e.g., Figure 4 the tube centerline axis 228) of the compressed air tube. The guiding of the compressed air flow towards the central region of the compressed air tube in turn carries the gaseous fuel flow (e.g., Figure 4 the outlet gaseous fuel flow (Fgo)) towards the central region of the compressed air tube. Carrying the gaseous fuel flow towards the central region in turn increases the penetration of the gaseous fuel flow into the compressed air flow, which ultimately improves the mixing efficiency of the gaseous fuel flow and the compressed air.

[0107] Figure 13 is suitable for use as Figure 4 FIG. is a schematic view of an exemplary fuel nozzle assembly 502 that is suitable as the fuel nozzle assembly 202 of

[0108] The fuel nozzle assembly 502 includes a head 504 and a body (e.g., Figure 4 body 206) of Figure 4 . The body defines a gaseous fuel channel (e.g.,

[0109] gaseous fuel channel 208) of Figure 5 and a centerline axis 510. The head 504 includes a perimeter 512. The gaseous fuel channel terminates in a set of gaseous fuel orifices 520. The fuel nozzle assembly 502 includes a set of compressed air tubes 522 that terminate in a compressed air outlet 526. Each compressed air tube in the set of compressed air tubes 522 includes a tube centerline axis 528. The fuel nozzle assembly 502 includes a set of vortex generators 530, which can include any number of one or more sets of vortex generators. As a non-limiting example, the set of vortex generators 530 can include a set of first vortex generators 532 and a set of second vortex generators 534.

[0110] The set of gas fuel orifices 520 further includes a gas fuel orifice cluster 572, which includes a plurality of gas fuel orifices 520 discharging into separate but adjacent compressed air tubes 522. As a non-limiting example, the gas fuel orifice cluster 572 may include a total of three gas fuel orifices 520 at a location where three adjacent compressed air tubes 522 converge. It should be understood that the gas fuel orifice cluster 572 may be provided at a location where adjacent compressed air tubes 522 converge. Alternatively, it should be understood that individual gas fuel orifices 520 may be provided that discharge into any one of the adjacent compressed air tubes 522 or do not discharge into the adjacent compressed air tubes 522.

[0111] Figure 14 is taken along Figure 12 a schematic cross-sectional view of an exemplary gas fuel orifice cluster 572 taken along section line XIV-XIV. The gas fuel orifice cluster 572 may include a main leg 574 that branches into a first leg 576 and a second leg 578 and leads to respective gas fuel orifices 520. The first leg 576 and the second leg 578 may each be oriented such that the exiting gas fuel flow (Fgo) flowing through the respective first leg 576 or second leg 578 is directed towards the adjacent compressed air tube 522.

[0112] Figure 15 is suitable for use as Figure 4 a schematic view of an exemplary fuel nozzle assembly 602 of a fuel nozzle assembly 202. The fuel nozzle assembly 602 is similar to the fuel nozzle assemblies 202, 502; thus, like parts will be identified with like numbers incremented to the 600 series, and it should be understood that the description of the fuel nozzle assemblies 202, 502 applies to the fuel nozzle assembly 602 unless otherwise noted.

[0113] The fuel nozzle assembly 602 includes a fuel nozzle assembly 602 having a head 604 and a body (e.g., Figure 4 the body 206). The body defines a gas fuel channel (e.g., Figure 4 the gas fuel channel 208) and a centerline axis 610. The head 604 includes a perimeter 612. The gas fuel channel terminates in a set of gas fuel orifices 620. The fuel nozzle assembly 602 includes a set of compressed air tubes 622 that terminate in a compressed air outlet 626. Each compressed air tube in the set of compressed air tubes 622 includes a tube centerline axis 628. The fuel nozzle assembly 602 includes a set of vortex generators 630, which may include any number of sets or groups of vortex generators. As a non-limiting example, the set of vortex generators 630 may include a set of first vortex generators 632 and a set of second vortex generators 634.

[0114] The head 604 is similar to the head 204 ( Figure 5)、504( Figure 13 ), because it is defined by the perimeter 612. However, the perimeter 612 is a non-circular polygon. The non-circular polygon can be any suitable polygon, such as but not limited to a triangle, rectangle, rhombus, trapezoid, hexagon, etc. In addition, similar to the compressed air tube 522( Figure 13 ), the compressed air tube 622 can be formed into a non-circular polygon shape. The compressed air tube 622 can be formed in any suitable pattern. As a non-limiting example, the compressed air tube 622 can be formed in two or more rows, or two or more columns. In addition, the compressed air tube 622 can be formed such that no tube centerline axis 628 is aligned with the centerline axis 610.

[0115] Figure 16 is suitable for use as Figure 4 FIG. is a schematic view of an exemplary fuel nozzle assembly 702 that is suitable for use as the fuel nozzle assembly 202 of. The fuel nozzle assembly 702 is similar to the fuel nozzle assemblies 202, 502, 602; therefore, similar parts will be identified with similar numbers increased to the 700 series. It should be understood that unless otherwise specified, the description of the fuel nozzle assemblies 202, 502, 602 applies to the fuel nozzle assembly 702.

[0116] The fuel nozzle assembly 702 includes a head 704 and a body (e.g., Figure 4 's body 206). The body defines a gaseous fuel channel (e.g., Figure 4 's gaseous fuel channel 208) and a centerline axis 710. The head 704 includes a perimeter 712. The gaseous fuel channel terminates at a set of gaseous fuel orifices 720. The fuel nozzle assembly 702 includes a set of compressed air tubes 722 that terminate at a compressed air outlet 726. Each compressed air tube in the set of compressed air tubes 722 includes a tube centerline axis 728. The fuel nozzle assembly 702 includes a set of swirl generators 730, and the set of swirl generators 730 can include any number of one or more sets of swirl generators. As a non-limiting example, the set of swirl generators 730 can include a set of first swirl generators 732 and a set of second swirl generators 734.

[0117] Except that at least a portion of the set of compressed air tubes 722 can be formed into an asymmetric polygon or shape relative to a plane extending along the tube centerline axis 728, the set of compressed air tubes 722 is similar to the set of compressed air tubes 222( Figure 5 ), 522( Figure 13 ), 622( Figure 15)。In addition, at least a portion of the compressed air pipes in the group of compressed air pipes 722 can be formed to have all groups of vortex generators 730 (e.g., both the group of first vortex generators 732 and the group of second vortex generators 734), a single group of vortex generators 730 (e.g., one of the group of first vortex generators 732 or the group of second vortex generators 734), or no groups of vortex generators 730 (e.g., without the group of first vortex generators 732 and the group of second vortex generators 734).

[0118] 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 gas turbine engine (e.g., dome walls, inner / outer liners, and other parts of the turbine engine). In addition, additional structures are needed to mitigate flashback and prevent unwanted autoignition; problems not faced by burners using conventional fuels. As described herein, the burner includes a fuel nozzle 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 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.

[0119] In addition, compared to conventional fuel nozzle assemblies that do not include the group of vortex generators, it has been found that using the group of vortex generators reduces NO x emissions in the combustion zone. As discussed herein, the group of vortex generators creates vortices in the combustion chamber that intercept or otherwise capture the gaseous fuel stream output into the combustion chamber. Intercepting the gaseous fuel stream by the vortices in turn helps ensure sufficient mixing of the gaseous fuel and compressed air. Using the group of vortex generators helps ensure that the mixture of compressed air and gaseous fuel is more homogeneous (e.g., more effectively mixed) than the mixture of compressed air and gaseous fuel of conventional fuel nozzle assemblies. Once the mixture of compressed air and gaseous fuel is ignited, the more homogeneous mixture of compressed air and gaseous fuel in turn reduces the overall NO xEmission

[0120] Compared with conventional fuels, the benefits associated with using hydrogen-containing fuels include a more environmentally friendly engine because hydrogen-containing fuels produce fewer carbon pollutants when burned than burners using conventional fuels. For example, a burner including 100% hydrogen-containing fuel (e.g., the fuel is 100% H2) will have zero carbon pollutants. As described herein, the burner can be used in cases where 100% hydrogen-containing fuel is used.

[0121] Within the scope not yet described, the different features and structures of the various embodiments can be combined or used interchangeably as needed. All combinations or permutations of the features described herein are covered by this disclosure.

[0122] This written description uses examples to describe aspects of the disclosure described herein, including the best mode, and also enables any person skilled in the art to practice aspects of the disclosure, including making and using any device or system and performing any combined method. The patentable scope of the aspects of the disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. If these other examples have structural elements that 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.

[0123] A further aspect is provided by the subject matter of the following clauses:

[0124] A turbine engine, comprising a compression section, a combustion section, and a turbine section in a serial flow arrangement, the combustion section including: a dome wall and a burner liner, the dome wall and the burner liner together forming at least a part of a combustion chamber; and a fuel nozzle assembly fluidly coupled to the combustion chamber and including: a compressed air tube having a compressed air outlet discharging into the combustion chamber to supply a compressed air stream to the combustion chamber, the compressed air tube defining a tube centerline axis; a body defining a gaseous fuel channel discharging into the combustion chamber at a set of gaseous fuel orifices to supply a gaseous fuel stream to the combustion chamber, the set of gaseous fuel orifices surrounding at least a part of the compressed air outlet; and a set of vortex generators located within the compressed air tube, each vortex generator of the set of vortex generators defining a respective part of the compressed air outlet and being configured to generate a pair of vortices defined by two vortices disposed on opposite sides of the vortex generator, the pair of vortices being for capturing the gaseous fuel stream from the set of gaseous fuel orifices to define a mixture of compressed air and gaseous fuel within the combustion chamber.

[0125] A turbine engine according to any of the preceding clauses, wherein the set of gaseous fuel orifices are circumferentially spaced about the tube centerline axis and are circumferentially aligned with at least a portion of the set of vortex generators.

[0126] A turbine engine according to any of the preceding clauses, wherein the set of vortex generators includes a set of first vortex generators and a set of second vortex generators different from the set of first vortex generators.

[0127] A turbine engine according to any of the preceding clauses, wherein each first vortex generator in the set of first vortex generators generates a first pair of vortices, and each second vortex generator in the set of second vortex generators generates a second pair of vortices, each second vortex in the second pair of vortices being smaller than each first vortex in the first pair of vortices.

[0128] A turbine engine according to any of the preceding clauses, wherein the compressed air tube extends a first axial length between a compressed air inlet formed along the body and the compressed air outlet, and a first vortex generator in the set of vortex generators extends a second axial length relative to the tube centerline axis, the second axial length being greater than or equal to 0.1 times and less than or equal to 1 times the first axial length.

[0129] A turbine engine according to any of the preceding clauses, wherein a second vortex generator in the set of vortex generators extends a third axial length relative to the tube centerline axis, the third axial length being greater than or equal to 0.3 times and less than or equal to 1 times the first axial length.

[0130] A turbine engine according to any of the preceding clauses, wherein the second axial length is different from the third axial length.

[0131] A turbine engine according to any of the preceding clauses, wherein when viewed along a plane extending along the tube centerline axis and intersecting a portion of the compressed air tube that does not include the set of vortex generators, the compressed air outlet extends a first radial height relative to the tube centerline axis, and a first vortex generator in the set of vortex generators extends a second radial height along the leading edge of the first vortex generator relative to the centerline axis, wherein the second radial height is greater than or equal to 0.01 times and less than or equal to 0.4 times the first radial height.

[0132] A turbomachine according to any of the preceding clauses, wherein a second vortex generator of the set of vortex generators extends a third radial height along a leading edge of the first vortex generator relative to the centerline axis, where the third radial height is greater than or equal to 0.005 times the first radial height and less than or equal to 0.4 times the first radial height.

[0133] A turbomachine according to any of the preceding clauses, wherein the second radial height is not equal to the third radial height.

[0134] A turbomachine according to any of the preceding clauses, wherein the compressed air pipe is included in a set of compressed air pipes having a first compressed air pipe and a second compressed air pipe adjacent to the first compressed air pipe, where each compressed air pipe has a corresponding subgroup of the set of gaseous fuel orifices surrounding at least a portion of the compressed air outlet.

[0135] A turbomachine according to any of the preceding clauses, wherein when viewed in a plane extending along the pipe centerline axis and intersecting a portion of the first compressed air pipe that does not include the set of vortex generators, the compressed air outlet of the first compressed air pipe extends a first radial height relative to the pipe centerline axis, and the pipe centerline axis at the compressed air outlet of the first compressed air pipe is set at a distance from the pipe centerline axis at the compressed air outlet of the second compressed air pipe, where the distance is greater than or equal to 1.1 times the first radial height and less than or equal to 4 times the first radial height.

[0136] A turbomachine according to any of the preceding clauses, wherein the fuel nozzle assembly is symmetric about a plane extending along the centerline axis.

[0137] A turbomachine according to any of the preceding clauses, wherein at least one of the compressed air pipes does not include the set of vortex generators.

[0138] A turbine engine according to any of the preceding clauses, wherein the set of gaseous fuel orifices includes at least one gaseous fuel orifice cluster disposed between at least two adjacent compressed air tubes of the set of compressed air tubes, the at least one gaseous fuel orifice cluster having: a main leg; a first leg that fluidly couples the main leg to a first gaseous fuel orifice in the at least one gaseous fuel orifice cluster, the first gaseous fuel orifice discharging into a first compressed air tube of the at least two adjacent compressed air tubes; and a second leg that fluidly couples the main leg to a second gaseous fuel orifice in the at least one gaseous fuel orifice cluster, the second gaseous fuel orifice discharging into a second compressed air tube of the at least two adjacent compressed air tubes that is different from the first compressed air tube.

[0139] A turbine engine according to any of the preceding clauses, wherein the gaseous fuel orifices in the set of gaseous fuel orifices extend a radial width relative to the tube centerline axis, the gaseous fuel orifices are disposed relative to the tube centerline axis at a radial height from the compressed air outlet, the radial height being greater than or equal to 1.4 times and less than or equal to 20 times the radial width.

[0140] A turbine engine according to any of the preceding clauses, wherein each vortex generator in the set of vortex generators includes a root and a vertex and defines a vortex generator centerline extending from the vertex to the root and an angle greater than or equal to -60 degrees and less than or equal to 60 degrees relative to a radial line that extends from the tube centerline axis and intersects the vortex generator centerline at the root.

[0141] A turbine engine according to any of the preceding clauses, wherein the vortex generators in the set of vortex generators include a trailing edge, a body, and a swept body extending from the body, the vortex generators extending a total radial height along the trailing edge relative to the tube centerline axis and a body radial height along the trailing edge, the body radial height being greater than or equal to 0.1 times and less than or equal to 0.7 times the total radial height.

[0142] A turbine engine according to any of the preceding clauses, wherein the compressed air tubes include a non-circular polygonal shape when viewed in a plane perpendicular to the tube centerline axis and intersecting the compressed air outlet.

[0143] A method of operating a combustion section according to any of the preceding clauses, the method including: supplying a gaseous hydrogen fuel stream to the gaseous fuel channel; and supplying a compressed air stream to the set of compressed air tubes.

[0144] A combustion zone includes: a dome wall and a burner liner, the dome wall and the burner liner together forming at least a part of a combustion chamber; and a fuel nozzle assembly fluidly coupled to the combustion chamber and including: a compressed air tube having a compressed air outlet discharging into the combustion chamber to supply a stream of compressed air to the combustion chamber, the compressed air tube defining a tube centerline axis; a body defining a gaseous fuel channel discharging into the combustion chamber at a set of gaseous fuel orifices to supply a stream of gaseous fuel to the combustion chamber, the set of gaseous fuel orifices surrounding at least a part of the compressed air outlet; and a set of vortex generators located within the compressed air tube, each vortex generator of the set of vortex generators defining a respective part of the compressed air outlet and configured to generate a pair of vortices defined by two vortices disposed on opposite sides of the vortex generator, the pair of vortices for capturing the stream of gaseous fuel from the set of gaseous fuel orifices to define a mixture of compressed air and gaseous fuel within the combustion chamber.

[0145] The combustion zone according to any of the preceding clauses, wherein the set of gaseous fuel orifices are circumferentially spaced about the tube centerline axis and are circumferentially aligned with at least a part of the set of vortex generators.

[0146] The combustion zone according to any of the preceding clauses, wherein the set of vortex generators includes a set of first vortex generators and a set of second vortex generators different from the set of first vortex generators.

[0147] The combustion zone according to any of the preceding clauses, wherein each first vortex generator of the set of first vortex generators generates a first pair of vortices and each second vortex generator of the set of second vortex generators generates a second pair of vortices, each second vortex of the second pair of vortices being smaller than each first vortex of the first pair of vortices.

[0148] The combustion zone according to any of the preceding clauses, wherein the compressed air tube extends a first axial length between a compressed air inlet formed along the body and the compressed air outlet, a first vortex generator of the set of vortex generators extends a second axial length relative to the tube centerline axis, the second axial length being greater than or equal to 0.1 times and less than or equal to 1 times the first axial length.

[0149] A combustion zone according to any of the preceding clauses, wherein a second vortex generator of the group of vortex generators extends a third axial length relative to the tube centerline axis, the third axial length being greater than or equal to 0.3 times and less than or equal to 1 time the first axial length.

[0150] A combustion zone according to any of the preceding clauses, wherein the second axial length is different from the third axial length.

[0151] A combustion zone according to any of the preceding clauses, wherein when viewed in a plane extending along the tube centerline axis and intersecting a portion of the compressed air tube that does not include the group of vortex generators, the compressed air outlet extends a first radial height relative to the tube centerline axis, and a first vortex generator of the group of vortex generators extends a second radial height along a leading edge of the first vortex generator relative to the centerline axis, wherein the second radial height is greater than or equal to 0.01 times and less than or equal to 0.4 times the first radial height.

[0152] A combustion zone according to any of the preceding clauses, wherein a second vortex generator of the group of vortex generators extends a third radial height along a leading edge of the first vortex generator relative to the centerline axis, wherein the third radial height is greater than or equal to 0.005 times and less than or equal to 0.4 times the first radial height.

[0153] A combustion zone according to any of the preceding clauses, wherein the second radial height is not equal to the third radial height.

[0154] A combustion zone according to any of the preceding clauses, wherein the compressed air tube is included within a group of compressed air tubes having a first compressed air tube and a second compressed air tube adjacent to the first compressed air tube, wherein each compressed air tube has a corresponding subgroup of the group of gas fuel orifices surrounding at least a portion of the compressed air outlet.

[0155] A combustion zone according to any of the preceding clauses, wherein when viewed in a plane extending along the tube centerline axis and intersecting a portion of the first compressed air tube that does not include the group of vortex generators, the compressed air outlet of the first compressed air tube extends a first radial height relative to the tube centerline axis, and the tube centerline axis at the compressed air outlet of the first compressed air tube is set at a distance from the tube centerline axis at the compressed air outlet of the second compressed air tube, wherein the distance is greater than or equal to 1.1 times and less than or equal to 4 times the first radial height.

[0156] The combustion zone according to any of the preceding clauses, wherein the fuel nozzle assembly is symmetric about a plane extending along the centerline axis.

[0157] The combustion zone according to any of the preceding clauses, wherein at least one of the compressed air tubes in the compressed air tubes does not include the set of vortex generators.

[0158] The combustion zone according to any of the preceding clauses, wherein the set of gas fuel orifices includes at least one gas fuel orifice cluster disposed between at least two adjacent compressed air tubes of the set of compressed air tubes, the at least one gas fuel orifice cluster having: a main leg; a first leg that fluidly couples the main leg to a first gas fuel orifice in the at least one gas fuel orifice cluster, the first gas fuel orifice discharging into a first compressed air tube of the at least two adjacent compressed air tubes; and a second leg that fluidly couples the main leg to a second gas fuel orifice in the at least one gas fuel orifice cluster, the second gas fuel orifice discharging into a second compressed air tube of the at least two adjacent compressed air tubes that is different from the first compressed air tube.

[0159] The combustion zone according to any of the preceding clauses, wherein the gas fuel orifices in the set of gas fuel orifices extend a radial width relative to the tube centerline axis, and the gas fuel orifices are disposed relative to the tube centerline axis at a radial height from the compressed air outlet, the radial height being greater than or equal to 1.4 times and less than or equal to 20 times the radial width.

[0160] The combustion zone according to any of the preceding clauses, wherein each vortex generator in the set of vortex generators includes a root and a vertex, and defines a vortex generator centerline extending from the vertex to the root, and an angle greater than or equal to -60 degrees and less than or equal to 60 degrees relative to a radial line that extends from the tube centerline axis and intersects the vortex generator centerline at the root.

[0161] The combustion zone according to any of the preceding clauses, wherein the vortex generators in the set of vortex generators include a trailing edge, a body, and a swept body extending from the body, the vortex generator extending a total radial height along the trailing edge relative to the tube centerline axis, and a body radial height along the trailing edge, the body radial height being greater than or equal to 0.1 times and less than or equal to 0.7 times the total radial height.

[0162] A combustion zone according to any of the foregoing clauses, wherein the compressed air tube has a non-circular polygon shape when viewed in a plane perpendicular to the tube centerline axis and intersecting the compressed air outlet.

[0163] A method of operating a combustion zone according to any of the foregoing clauses, the method comprising: supplying a gaseous hydrogen fuel stream to the gaseous fuel channel; and supplying a compressed air stream to the set of compressed air tubes.

Claims

1. A turbine engine, characterized in that: include: A compression section, a combustion section, and a turbine section in a series flow arrangement, the combustion section comprising: a dome wall and a combustor liner, the dome wall and the combustor liner together forming at least a portion of a combustion chamber; and A fuel nozzle assembly fluidly coupled to the combustion chamber and comprising: a compressed air tube having a compressed air outlet that discharges into the combustion chamber to supply a flow of compressed air to the combustion chamber, the compressed air tube defining a tube centerline axis; a body defining a gas fuel gallery that discharges into the combustion chamber at a set of gas fuel orifices to supply a flow of gas fuel to the combustion chamber, the set of gas fuel orifices surrounding at least a portion of the compressed air outlet; and a set of vortex generators, the set of vortex generators being located within the compressed air pipe, each vortex generator in the set of vortex generators defining a respective portion of the compressed air outlet and being configured to generate a vortex pair defined by two vortices disposed on opposite sides of the vortex generator, the vortex pair being used to capture the gas fuel flow from the set of gas fuel orifices to define a mixture of compressed air and gas fuel within the combustion chamber.

2. The turbine engine according to claim 1, characterized in that in, The set of gas fuel orifices are circumferentially spaced about the tube centerline axis and are circumferentially aligned with at least a portion of the set of vortex generators.

3. The turbine engine according to claim 1, characterized in that: in, The group of vortex generators includes a group of first vortex generators and a group of second vortex generators different from the group of first vortex generators.

4. The turbine engine according to claim 3, characterized in that in: Each first vortex generator in the set of first vortex generators generates a first vortex pair; and Each second vortex generator in the set of second vortex generators generates a second vortex pair, each second vortex in the second vortex pair is smaller than each first vortex in the first vortex pair.

5. The turbine engine according to claim 1, characterized in that in: The compressed air tube extends a first axial length between a compressed air inlet formed along the body and the compressed air outlet; and A first vortex generator in the set of vortex generators extends a second axial length relative to the tube centerline axis, the second axial length being greater than or equal to 0.1 times and less than or equal to 1 times the first axial length.

6. The turbine engine according to claim 5, characterized in that in, A second vortex generator in the set of vortex generators extends a third axial length relative to the tube centerline axis, the third axial length being greater than or equal to 0.3 times the first axial length and less than or equal to 1 times the first axial length.

7. The turbine engine according to claim 6, characterized in that in, The second axial length is different from the third axial length.

8. The turbine engine according to claim 1, characterized in that in: the compressed air outlet extends a first radial height relative to the tube centerline axis when viewed along a plane extending along the tube centerline axis and intersecting a portion of the compressed air tube that does not include the set of vortex generators; and A first vortex generator in the set of vortex generators extends a second radial height relative to the centerline axis along a leading edge of the first vortex generator, wherein the second radial height is greater than or equal to 0.01 times and less than or equal to 0.4 times the first radial height.

9. The turbine engine according to claim 8, characterized in that in, A second vortex generator in the set of vortex generators extends a third radial height relative to the centerline axis along a leading edge of the first vortex generator, wherein the third radial height is greater than or equal to 0.005 times and less than or equal to 0.4 times the first radial height.

10. The turbine engine according to claim 9, characterized in that in, The second radial height is not equal to the third radial height.

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