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

[0001] This application is a divisional application of patent application No. 202411777715.8 filed on December 5, 2024, entitled "Turbine Engine with Combustion Section with Fuel Nozzle Assembly". Technical Field

[0002] This topic generally relates to turbine engines, and more specifically, to turbine engines having a combustion section including a fuel nozzle assembly. Background Technology

[0003] A turbine engine is driven by a flow of combustion gases through the engine to rotate multiple turbine blades, which in turn rotates a compressor, thus supplying compressed air to the combustor for combustion. The combustor can be located within the turbine engine and fluidly connected to the turbine through which the combustion gases flow.

[0004] The use of hydrocarbon fuels in the combustors of turbine engines is known. Typically, air and fuel are fed into the combustion chamber, mixed, and then the fuel is burned in the presence of air to produce hot gases. These hot gases are then fed into the turbine, where they are cooled and expanded to generate power. Byproducts of fuel combustion often include environmentally undesirable byproducts such as nitrogen oxides and nitrogen dioxide (collectively known as NO). x Carbon monoxide (CO), unburned hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides including sulfur oxides (e.g., SO2 and SO3). Attached Figure Description

[0005] The complete and feasible disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, for those skilled in the art, wherein:

[0006] Figure 1 This is a schematic representation of a turbine engine, which includes a compression section, a combustion section, and a turbine section.

[0007] Figure 2 Depicting along Figure 1 The cross-sectional view of the combustion zone taken by line II-II further shows a set of fuel nozzle assemblies.

[0008] Figure 3 It is along Figure 2 A schematic diagram of a side cross-sectional view taken by line III-III further illustrates the fuel nozzle assembly that supplies fuel into the combustion chamber.

[0009] Figure 4 It is suitable for use as Figure 1A schematic side cross-sectional view of a portion of the combustion zone, which includes a fuel nozzle assembly having fuel nozzles terminating at a set of gaseous fuel orifices, a set of compressed air pipes, and a set of vortex generators.

[0010] Figure 5 From Figure 4 A schematic diagram of the fuel nozzle assembly as observed from line of sight VV further illustrates the set of vortex generators, including a set of first vortex generators and a set of second vortex generators.

[0011] Figure 6 It is along Figure 5 The schematic side cross-sectional view of the compressed air pipe in this group of compressed air pipes, taken by section line VI-VI, further shows a portion of the compressed air pipe without the group of vortex generators.

[0012] Figure 7 It is along Figure 5 The schematic side cross-sectional view of the compressed air pipe in this group of compressed air pipes, taken by section line VII-VII, further shows a portion of the compressed air pipe including the first vortex generator of this group.

[0013] Figure 8 Is Figure 5 A schematic diagram of the fuel nozzle assembly seen in section VIII further illustrates the vortex pair generator produced by each of the vortex generators in this group.

[0014] Figure 9 It is along Figure 5 The schematic side cross-sectional view of the compressed air pipe in this group of compressed air pipes, taken by section line IX-IX, further shows a portion of the compressed air pipe including the group of second vortex generators.

[0015] Figure 10 yes Figure 4 A schematic perspective view of the vortex generator in this group of vortex generators further shows the foot, apex, a pair of opposite sidewalls, and the trailing edge formed as a triangular wall.

[0016] Figure 11 Is it suitable for Figure 4 A schematic perspective view of an exemplary vortex generator used within this set of vortex generators, further showing the foot, apex, a pair of opposing sidewalls, and trailing edge formed as a rectangular wall.

[0017] Figure 12 Is it suitable for Figure 4 A schematic front view of an exemplary vortex generator used within this set of vortex generators further illustrates the sweeping segment terminating at the apex.

[0018] Figure 13 It is suitable for use as Figure 4 A schematic diagram of an exemplary fuel nozzle assembly further illustrates a set of polygonal compressed air pipes and a set of gaseous fuel orifices including a cluster of gaseous fuel orifices.

[0019] Figure 14 It is along Figure 13 The schematic cross-sectional view of the fuel orifice cluster in the group of gas fuel orifice clusters, taken by section line XIV-XIV, further shows the main branch, the first leg and the second leg.

[0020] Figure 15 It is suitable for use as Figure 4 A schematic diagram of an exemplary fuel nozzle assembly further illustrates a set of symmetrical polygonal compressed air pipes and a set of gaseous fuel orifices.

[0021] Figure 16 It is suitable for use as Figure 4 A schematic diagram of an exemplary fuel nozzle assembly further illustrates a set of asymmetric polygonal compressed air pipes and a set of gaseous fuel orifices. Detailed Implementation

[0022] The disclosed aspects described herein relate to a turbine engine including a combustion section, the combustion section including a fuel nozzle assembly. The fuel nozzle assembly includes fuel nozzles terminating at a set of gaseous fuel orifices. The fuel nozzle assembly includes a set of compressed air lines. A set of vortex generators is disposed within at least one of the compressed air lines in the set of compressed air lines.

[0023] Fuel nozzle assemblies are particularly well-suited for using hydrogen fuel (hereinafter referred to as "H2 fuel"). Specifically, fuel nozzle assemblies are particularly well-suited for supplying a stream of gaseous H2 fuel to the combustion chamber. Compared to conventional fuels (e.g., carbon fuels, petroleum fuels, etc.), H2 fuel has a higher combustion temperature and velocity. Furthermore, flashback can occur when using H2 fuel. As used herein, flashback refers to the unintended propagation of the flame during the combustion of H2 fuel. H2 fuel is more volatile, meaning that once H2 fuel is burned or ignited, the flame generated by igniting H2 fuel can expand in an undesirable location; in other words, flashback can occur. For example, the flame can expand into the fuel nozzle assembly or the igniter. As described herein, fuel nozzle assemblies ensure that flashback does not occur with H2 fuel. If H2 fuel is overheated, it may spontaneously combust. Spontaneous combustibility of H2 fuel can be undesirable at certain points in the combustion zone. Fuel nozzle assemblies, as described herein, ensure that the temperature of the H2 fuel is below its auto-ignition temperature, at least until it is desired to ignite the H2 fuel.

[0024] As used herein, the term "gaseous fuel" or its iterations refers to gaseous combustible fuel. It should be understood that gaseous fuel differs from atomized fuel. Atomized fuel utilizes impellers, orifices, etc., to obtain liquid fuel and atomize it into very small droplets.

[0025] In some cases, gaseous fuel exits the fuel nozzle at a given velocity and then mixes with air for combustion. As 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 fuel with an igniter.

[0026] For illustrative purposes, this disclosure will be described in relation to turbine engines (gas turbine engines). 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 are generally applicable to non-aircraft engines with combustors, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0027] The term "exemplary" as used herein means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior to or advantageous to other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0028] As used herein, the terms “first” and “second” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0029] The terms "front" and "rear" refer to relative positions within a turbine engine or carrier, and specifically to the normal operating posture of the turbine engine or carrier. For example, for a turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0030] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "forward" or "front" indicate what is in front of something, and "backward" or "rear" indicate what is behind something. For example, when used in relation to fluid flow, forward / front can indicate upstream, and backward / rear can indicate downstream.

[0031] The term "fluid" can refer to either a gas or a liquid. The term "fluid connectivity" means that fluids can establish connections between specified areas.

[0032] Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction along a ray extending between the engine's central longitudinal axis and the engine's outer perimeter.

[0033] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are used for identification purposes only to aid the reader in understanding this disclosure and do not impose limitations, particularly regarding the location, orientation, or use of the aspects of the disclosure described herein. Connective references (e.g., attachment, connection, joint, and engagement) are to be interpreted broadly and may include intermediate structural elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, a connective reference does not necessarily mean that two elements are directly connected and fixed relative to each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary.

[0034] The singular forms “a,” “an,” and “the” include plural references unless the context clearly indicates otherwise. Furthermore, as used herein, the term “group” or “set” of elements can be any number of elements, including only one.

[0035] Figure 1 This is a schematic diagram of a turbine engine 10. As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 may include at least a compression section 12, a combustion section 14, and a turbine section 16 arranged in series for flow. A drive shaft 18 rotatably connects the compression section 12 and the turbine section 16 such that rotation of one affects rotation of the other, and defines the axis of rotation or engine centerline 20 of the turbine engine 10.

[0036] Compression section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 fluidly connected in series with each other. Turbine section 16 may include an LP turbine 26 and an HP turbine 28 fluidly connected in series with each other. Drive shaft 18 may operatively connect the LP compressor 22, HP compressor 24, LP turbine 26, and HP turbine 28 together. Alternatively, drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may connect the LP compressor 22 to the LP turbine 26, and the HP drive shaft may connect the HP compressor 24 to the HP turbine 28. The LP spool may be defined as a combination of the LP compressor 22, LP turbine 26, and LP drive shaft, such that rotation of the LP turbine 26 may apply a driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool can be defined as a combination of an HP compressor 24, an HP turbine 28, and an HP drive shaft, such that the rotation of the HP turbine 28 can apply driving force to the HP drive shaft, which in turn can rotate the HP compressor 24.

[0037] Compression section 12 may include multiple axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. The compressor blades for a stage of compression section 12 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of compression section 12 may be mounted to a housing that may extend circumferentially around turbine engine 10. It should be understood that the representation of compression section 12 is merely illustrative and any number of stages may be present. Furthermore, it is contemplated that any other number of components may be present within compression section 12.

[0038] Similar to compression section 12, turbine section 16 may include multiple axially spaced stages, each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Turbine blades for one stage of turbine section 16 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of turbine section 16 may be circumferentially mounted to the housing. It should be noted that any number of blades, blades, and turbine stages can be present, as the illustrated turbine section is merely schematic. Furthermore, it is contemplated that any other number of components may be present within turbine section 16.

[0039] Combustion section 14 may be arranged in series between compression section 12 and turbine section 16. Combustion section 14 may be fluidly connected to at least a portion of compression section 12 and turbine section 16, such that combustion section 14 at least partially fluidly connects compression section 12 to turbine section 16. As a non-limiting example, combustion section 14 may be fluidly connected to HP compressor 24 at its upstream end and to HP turbine 28 at its downstream end.

[0040] 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, where it is compressed, defining compressed air. This compressed air can then flow into the combustion section 14, where it mixes with fuel and is ignited to generate combustion gases. The HP turbine 28 extracts some work from these combustion gases, driving the HP compressor 24. The combustion gases are discharged into the LP turbine 26, which extracts additional work to drive the LP compressor 22, and the exhaust gas is ultimately discharged from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 26 drives the LP spool, causing the fan (not shown) and the LP compressor 22 to rotate. The compressed airflow and combustion gases together define the working airflow flowing through the fan, compression section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

[0041] Figure 2 Depicting along Figure 1 A cross-sectional view of the combustion zone 14 along line II-II. For illustrative purposes, drive shaft 18 ( Figure 1 The combustion section 14 has been removed. Combustion section 14 includes a burner 34. The burner 34 includes a dome wall 44, which includes a set of fuel nozzle openings (not shown). The burner 34 includes a set of fuel nozzle assemblies 32 extending through the set of fuel nozzle openings. The set of fuel nozzle assemblies 32 is arranged annularly around a burner centerline 29. The burner centerline 29 may be a turbine engine 10 ( Figure 1 The engine centerline 20 ( Figure 1 Additionally or alternatively, the burner centerline 29 may be the centerline of the combustion section 14, a single burner, or a group of burners arranged around the burner centerline 29.

[0042] The fuel nozzle assembly 32 is arranged around the burner centerline 29. Each fuel nozzle in the fuel nozzle assembly 32 includes a fuel nozzle centerline 31. The fuel nozzle assembly 32 may include a fuel nozzle centerline 31 around the engine centerline 20. Figure 1The burner 34 can be annularly arranged with a rich cup, a lean cup, or a combination of both. The burner 34 is defined by a burner bushing 38. Depending on the type of engine in which the burner 34 is located, the burner 34 can have a canister-shaped, canister-annular, or annular arrangement. In a non-limiting example, the burner 34 can have a combined arrangement located within the engine housing 36 as further described herein. As shown by way of example, the burner bushing 38 can be annular. The burner bushing 38 can include an outer burner bushing 40 and an inner burner bushing 42 that are concentric with each other and annular about the engine centerline 20. The burner bushing 38 also defines the set of fuel nozzle assemblies 32. A dome wall 44, together with the burner bushing 38, can define a combustion chamber 46 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 defined at least partially by the burner bushing 38 and the housing 36. Each fuel nozzle in the fuel nozzle assembly 32 is defined by a discrete body that extends through a corresponding portion of the dome wall 44 and is configured to discharge gaseous fuel and compressed air into the combustion chamber 46.

[0043] Figure 3 Depicting along Figure 2 A cross-sectional view taken along line III-III shows combustion section 14. At least one flame-forming channel may fluidly connect compressed air and combustion chamber 46. As an example, at least one flame-forming channel is shown as a first set of flame-forming holes 50 or a second set of flame-forming holes 52. Burner 34 may include the first set of flame-forming holes 50, the second set of flame-forming holes 52, or both the first set of flame-forming holes 50 and the second set of flame-forming holes 52.

[0044] The first set of flame forming holes 50 can pass through the dome wall 44 to fluidly connect compressed air from the compression section 12 or the compressed air passage 48 to the combustion chamber 46.

[0045] The second set of flame forming holes 52 can pass through the burner bushing 38 to fluidly connect compressed air from the compressed air passage 48 to the combustion chamber 46.

[0046] Each fuel nozzle assembly in the group of fuel nozzle assemblies 32 is connectable to and disposed within the dome assembly 56. Each fuel nozzle assembly in the group of fuel nozzle assemblies 32 may include a flared cone 58 and a swirler 60. The flared cone 58 includes an outlet 62 directly fluidly connected to the corresponding fuel nozzle assembly in the combustion chamber 46. Each fuel nozzle assembly in the group of fuel nozzle assemblies 32 is fluidly connected to a fuel inlet 64 via a passage 66. Each fuel nozzle assembly in the group of fuel nozzle assemblies 32 includes a fuel nozzle centerline 31.

[0047] Both the inner burner bushing 42 and the outer burner bushing 40 can have an outer surface 68 and an inner surface 70 that at least partially define the combustion chamber 46. The burner bushing 38 can be made from a single continuous integral portion, or it can be multiple integral portions assembled together to define the inner burner bushing 42 and the outer burner bushing 40. As a non-limiting example, the outer surface 68 can define a first piece of the burner bushing 38, while the inner surface 70 can define a second piece of the burner bushing 38, which, when assembled together, form the burner bushing 38. As described herein, the burner bushing 38 includes a second first set of flame-forming orifices 52. Further contemplation suggests that the burner bushing 38 can be any type of burner bushing 38, including but not limited to single-walled or double-walled bushings or tile liner. The igniter 72 can be disposed at the burner bushing 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-forming orifices 52).

[0048] During operation, the compressed air supply (such as...) Figure 1 Compressed air (C) from the LP compressor 22 or 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 airflow (S) via the swirler 60 to each fuel nozzle assembly in the group of fuel nozzle assemblies 32. A fuel flow (F) is supplied to each fuel nozzle assembly in the group of fuel nozzle assemblies 32 via the fuel inlet 64 and the passage 66. The swirling airflow (S) and the fuel flow (F) mix at the flared cone 58 and are 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 from the outlet 62, it should be understood that the fuel / air mixture can be ignited at or near the outlet 62.

[0049] 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-forming gas flow (D1) to the first set of flame-forming orifices 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-forming orifices 50. An inlet 74 is defined by a portion of one or more flame-forming orifices in the first set of flame-forming orifices 50. The inlet 74 is fluidly connected to the compressed air (C). The first flame-forming gas flow (D1) enters at the inlet 74 and exits at the outlet 76 located on the dome wall 44.

[0050] Another portion of the compressed air (C) can flow through the compressed air passage 48 and can be supplied as a second flame-forming gas flow (D2) to the second first set of flame-forming orifices 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-forming orifices 52. That is, the compressed air (C) can flow through the burner bushing 38 and enter the combustion chamber 46 by passing through the second first set of flame-forming orifices 52.

[0051] The first flame-forming gas flow (D1) can be used to guide and shape the flame. The second flame-forming gas flow (D2) can be used to guide the combustion gases (G). In other words, air is guided into the combustion chamber 46 through the first set of flame-forming holes 50 or the second set of flame-forming holes 52 extending through the dome wall 44 or the burner bushing 38, wherein the guided air is used to control, shape, cool, or otherwise contribute to the combustion process in the combustion chamber 46.

[0052] Figure 3 The burner 34 shown is well-suited for use with hydrogen gas as fuel because it helps to accommodate the faster-moving flame front associated with hydrogen fuel compared to conventional hydrocarbon fuels. However, burner 34 can also be used with conventional hydrocarbon fuels.

[0053] Figure 4 It is suitable for use as Figure 1 A schematic side cross-sectional view of a portion of combustion section 200 of combustion section 14. Combustion section 200 is similar to combustion section 14; therefore, similar parts will be identified by similar names, and it should be understood that, unless otherwise stated, the description of combustion section 14 applies to combustion section 200.

[0054] Combustion section 200 includes a dome wall 214 that at least partially defines combustion chamber 216. (This is in contrast to combustion chamber 46.) Figure 3 Similarly, combustion chamber 216 is further composed of a combustion liner (not shown) (e.g., Figure 3 The combustion section 200 is defined by the inner burner bushing 42 and the outer burner bushing 40. The combustion section 200 includes a fuel nozzle assembly 202. Figure 2 Similar to the set of fuel nozzle assemblies 32, the fuel nozzle assembly 202 can be included within a set of fuel nozzle assemblies arranged circumferentially along the dome wall 214.

[0055] The fuel nozzle assembly 202 includes a fuel nozzle assembly 202 terminating at a set of gaseous fuel orifices 220 and a set of compressed air lines 222. The fuel nozzle assembly 202 includes a body 206 having a head 204 and defining a gaseous fuel channel 208 and a centerline axis 210. The fuel nozzle assembly 202 is attached to the dome wall 214 by any suitable method, such as, but not limited to, bonding, welding, joining, fastening, friction contact, etc.

[0056] The head 204 is defined as a portion of an extension of the fuel nozzle assembly 202 through a corresponding fuel nozzle assembly opening (not shown) disposed along the dome wall 214. The head 204 includes a periphery 212 facing the dome wall 214. At least a portion of the periphery 212 may be radially spaced from or in direct contact with the dome wall 214.

[0057] The set of compressed air pipes 222 is at least partially disposed within the head 204. Each compressed air pipe in the set of compressed air pipes 222 includes a compressed air inlet 224 and a compressed air outlet 226 discharging into the combustion chamber 216. The set of gaseous fuel orifices 220 is disposed along the head 204 and discharges into the combustion chamber 216. The gaseous fuel channel 208 may include a fuel manifold 218 disposed within the head 204, which distributes fluid flow within the gaseous fuel channel 208 to the set of gaseous 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 pipes 222. A portion of the gaseous fuel manifold 218 extending around the set of compressed air pipes 222 is shown in dashed lines.

[0058] The set of compressed air pipes 222 may be integrally or non-integrally formed with the head 204. As a non-limiting example, the set of compressed air pipes 222 may be defined by a channel cut out or otherwise formed within the body 206 of the fuel nozzle assembly 202. Alternatively, the set of compressed air pipes 222 may be defined by a discrete body or tube inserted into the fuel nozzle assembly 202. Each compressed air pipe 222 defines a corresponding pipe centerline axis 228. A compressed air inlet 224 is defined by a portion of the compressed air pipe 222 disposed within the head 204, which is axially furthest from the compressed air outlet 226 relative to the pipe centerline axis 228.

[0059] A set of vortex generators 230 are disposed within the set of compressed air pipes 222. Each of the set of vortex generators 230 is defined as a structure extending radially toward the pipe centerline axis 228 from the body of the fuel nozzle assembly 202 or otherwise from the outer boundary of the corresponding compressed air pipe in the set of compressed air pipes 222.

[0060] During operation, a gaseous fuel stream (Fg) is supplied to a gaseous fuel channel 208. The gaseous fuel stream (Fg) flows through the gaseous fuel channel 208 and is discharged into the combustion chamber 216 as an outlet gaseous fuel stream (Fgo) through the set of gaseous fuel orifices 220. The outlet gaseous fuel stream (Fgo) can be ignited within the combustion chamber 216 or the fuel nozzle assembly 202 by an igniter (not shown) or by auto-ignition. Ignition of the outlet gaseous fuel stream (Fgo) produces a flame within the combustion chamber 216. The gaseous fuel stream (Fg) may contain 100% hydrogen (“H2”) fuel, or a mixture of hydrogen fuel and another gaseous fuel (e.g., methane). Alternatively, the gaseous fuel stream (Fg) may be H2 fuel and fuel from, for example, the compression section (e.g., Figure 1 The mixture of compressed air in the compression section 12).

[0061] Compressed air flow (Fc) (e.g., Figure 3 Compressed air (C) is supplied to the compressed air line 222. The compressed air flow (Fc) exits from the compressed air outlet 226 as the outlet compressed air flow (Fco). The outlet compressed air flow (Fco) can be swirling or non-swirling. When the outlet compressed air flow (Fco) is swirling, it includes a helical or other swirling flow flowing into the combustion chamber 216. When swirling, the swirling amount of the outlet compressed air flow (Fco) can be quantified by the swirling number, which is defined as the integral of the tangential and axial momentum of the fluid flow downstream of the corresponding swirler. When swirling, the outlet compressed air flow (Fco) has a swirling 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 swirling number is zero.

[0062] Each of the compressed air pipes 222 in the group has a corresponding subgroup of gaseous fuel orifices 220 that output an outlet gaseous fuel flow (Fgo) near the corresponding compressed air pipe 222. An outlet compressed air flow (Fco) is used to capture or otherwise intercept at least a portion of the outlet gaseous fuel flow (Fgo) leaving the gaseous fuel orifice 220 closest to the corresponding compressed air pipe 222. The interception of the outlet gaseous fuel flow (Fgo) by the outlet compressed air flow (Fco) produces a mixed gaseous fuel and air flow (Fm). The mixed gaseous fuel and air flow (Fm) is then ignited within the combustion chamber 216 to define a flame within the combustion chamber 216. Since the group of compressed air pipes 222 may include multiple compressed air pipes, each fuel nozzle assembly 202 may include multiple discrete mixed gaseous fuel and air flows (Fm) supplied to the combustion chamber 216. Multiple discrete mixed gaseous fuel and air flows (Fm) are illustrated by multiple instances of mixed gaseous fuel and air flows (Fm). The introduction of multiple discrete fuel and air mixtures (Fm) means that each fuel nozzle assembly 202 can include multiple flames, rather than a single flame as in conventional fuel nozzle assemblies. It has been found that using multiple smaller flames per fuel nozzle assembly instead of a single larger flame reduces overall NOx emissions in the combustion zone 200.

[0063] The outlet compressed air flow (Fco) is used to shape the flame (e.g., to provide the desired footprint of the physical flame within combustion chamber 216) and to isolate the various portions of combustion section 200 from the flame. As a non-limiting example, the outlet compressed air flow (Fco) causes the outlet gas 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 gas 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 the various portions of combustion section 200 (e.g., dome wall 214, burner bushing 38) by providing an insulating layer between the flame and other sections of combustion section 200, cooling other sections of combustion section 200, or otherwise directing the flame away from other sections of combustion section 200. Figure 3 This provides thermal isolation between the combustion zone 200 and the flame. Furthermore, each fuel nozzle assembly 202 uses multiple discrete mixed gas fuel and air flows (Fm) to generate multiple smaller flames instead of a single larger flame, which contributes to the flame shaping and isolation capabilities of the outlet compressed air flow (Fco). Because the fuel nozzle assembly 202 includes multiple smaller flames, the amount of compressed air required to isolate the combustion zone 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.

[0064] Although not shown, combustion section 200 may include a controller module communicatively coupled to a set of valves to automatically control fluid flow to or within various portions of combustion section 200. As a non-limiting example, the controller module may automatically control the supply of gaseous fuel flow (Fg) to gaseous fuel channel 208. As a non-limiting example, the controller module may automatically control the supply of compressed air flow (Fc) to one or more compressed air lines in the set of compressed air lines 222. As a non-limiting example, the controller module may automatically control the supply of gaseous fuel flow (Fg) to any one or more gaseous fuel orifices in the set of gaseous fuel orifices 220. The gaseous fuel flow (Fg) and 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 compressed air lines in the set of compressed air lines 222, while the gaseous fuel flow (Fg) is supplied to one or more gaseous fuel orifices in the set of gaseous fuel orifices 220.

[0065] Compared to conventional fuels, flame shaping and isolation between the flame and other parts of the combustion section 200 are particularly important when using gaseous H2 fuel. Gaseous H2 fuel exhibits a higher combustion temperature and a greater tendency for flashback compared to conventional fuels. Therefore, the outlet compressed air flow (Fco) is used to push the flame away from the fuel nozzle assembly 202. Pushing the outlet gaseous fuel flow (Fgo) away from the fuel nozzle assembly 202 helps ensure that, once ignited, flashback to the fuel nozzle assembly 202 of the outlet gaseous fuel flow (Fgo) does not occur. The outlet compressed air flow (Fco) further ensures that the flame, with a higher combustion temperature than that produced by conventional fuels, does not overheat the section of combustion section 200. The outlet compressed air flow (Fco) can further be used to generate a uniform flame distribution at the combustor outlet. It is conceivable that a uniform flame distribution or temperature distribution at the combustor outlet will lead to higher efficiency in the turbine section.

[0066] Figure 5 From Figure 4 A schematic diagram of the combustion zone 200 as observed from the line of sight VV. For illustrative purposes, the fuel nozzle assembly 202 extends 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 the circle. As a non-limiting example, the head can be any suitable polygonal shape. The set of compressed air pipes 222 and the set of gas fuel orifices 220 are completely disposed within the boundaries of the perimeter 212.

[0067] The group of compressed air pipes 222 may contain any number of one or more compressed air pipes. The group of compressed air pipes 222 may be uniformly or non-uniformly spaced along the head 204. The fuel nozzle assembly 202 may be symmetrical or asymmetrical about a plane extending along the centerline axis 210 and intersecting the head 204. The placement of the group of compressed air pipes 222 may be symmetrical or asymmetrical about a plane extending along the centerline axis 210 and intersecting the head 204. Each compressed air pipe in the group of compressed air pipes 222 may be symmetrical or asymmetrical about a plane extending along the pipe centerline axis 228. The group of compressed air pipes 222 may include compressed air pipes aligned with the pipe centerline axis 228. In other words, the group of compressed air pipes 222 may include corresponding compressed air pipes having a pipe centerline axis 228 aligned with the pipe centerline axis 228, as shown. At least a portion of the dimensions of the group of compressed air pipes 222 may be equal or unequal to each other.

[0068] Each compressed air pipe in the group of compressed air pipes 222 is configured to be at a first distance (L1) from its corresponding adjacent compressed air pipe. The first distance (L1) is measured between the axis 228 of the pipe centerline of the adjacent compressed air pipes 222. The first distance (L1) between the first compressed air pipe and the second compressed air pipe adjacent to the first compressed air pipe may be equal to or unequal to the first distance (L1) between the first compressed air pipe and the third compressed air pipe adjacent to the first compressed air pipe, which is different from the second compressed air pipe.

[0069] The set of gaseous fuel orifices 220 are arranged circumferentially around the set of compressed air pipes 222 relative to the pipe centerline axis 228. As a non-limiting example, each compressed air pipe in the set of compressed air pipes 222 may include a corresponding set of gaseous fuel orifices 220 arranged in a circular or other polygonal shape around the compressed air pipe.

[0070] Each gas fuel orifice in the group of gas fuel orifices 220 can be circumferentially aligned with the corresponding vortex generator in the group of vortex generators 230 located in the nearest compressed air pipe in the group of compressed air pipes 222, relative to the pipe centerline axis 228.

[0071] Each of the vortex generators in the group 230 extends from a root 236 disposed along or otherwise facing the head 204, and radially extends to a apex 240 relative to the corresponding pipe centerline axis 228 of the corresponding compressed air pipe in which the vortex generator is disposed. Each of the vortex generators in the group 230 includes a pair of opposing sidewalls connecting the root 236 and the apex 240.

[0072] The set of eddy current generators 230 includes any suitable number of eddy current generators. At least a portion of the eddy current generators 230 may have different configurations. As a non-limiting example, the set of eddy current generators 230 may include a set of first eddy current generators 232 and a set of second eddy current generators 234, wherein the set of first eddy current generators 232 is different from the set of second eddy current generators 234. It should be understood that all eddy current generators in the set of eddy current generators 230 may have the same configuration, or any number of two or more sets of eddy current generators with different configurations may exist.

[0073] As a non-limiting example, the first vortex generator 232 may include a first polygonal shape, while the second vortex generator 234 may include a second polygonal shape different from the first polygonal shape. When viewed along a plane perpendicular to the pipe centerline axis 228 and intersecting the vortex generators, the set of vortex generators 230 can be formed into any suitable polygonal shape. The polygonal shape can be, but is not limited to, triangles, rectangles, rhombuses, hexagons, ellipses, semicircles, etc. As a non-limiting example, the set of gas fuel orifices 220 may be circumferentially aligned with the first vortex generator 232 but not with the second vortex generator 234, or vice versa.

[0074] Each compressed air pipe in the group of compressed air pipes 222 may include the group of first vortex generators 232 and the group of second vortex generators 234. The group of first vortex generators 232 and the group of second vortex generators 234 may be alternately or non-alternately spaced within the corresponding compressed air pipe. The group of vortex generators 230 within a single compressed air pipe 222 are circumferentially spaced uniformly or non-uniformly around the pipe centerline axis 228 within the compressed air pipe.

[0075] Figure 6 It is along Figure 5 The diagram shows a schematic side cross-sectional view of the compressed air pipe in the set of compressed air pipes 222, taken along section line VI-VI. The compressed air pipe 222 taken along section line VI-VI does not include the set of vortex generators 230. It should be understood that the vortex generator pair is formed between two vortex generators spaced apart on radially opposite sides of the compressed air pipe 222 relative to the pipe centerline axis 228. For the circular compressed air pipe 222, the vortex generators in the vortex generator pair are spaced 180 degrees apart from each other.

[0076] Compressed air conduit 222 may include a surface 252 terminating at compressed air outlet 226. At least a portion of surface 252 may extend radially outward relative to the conduit centerline axis 228 to define a flared surface, as shown. Alternatively, surface 252 may extend constantly (without flaring) or radially inward relative to the conduit centerline axis 228 to define a tapered surface. Surface 252 may extend relative to a protrusion 254 of the conduit centerline axis 228 at a surface angle 251. Surface angle 251 along surface 252 may be constant or non-constant. Surface angle 251 has a value greater than -60 degrees and less than or equal to 60 degrees.

[0077] 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 not located, and flows out of the compressed air outlet 226 as a first outlet compressed air flow (Fco1). The first outlet compressed air flow (Fco1) forms Figure 4 It is part of the outlet compressed air flow (Fco). The first outlet compressed air flow (Fco1) follows surface 252. Therefore, if surface 252 is radially flared outward, the first outlet compressed air flow (Fco1) will follow the flared surface and be guided radially outward from the pipe centerline axis 228 into the combustion chamber 216.

[0078] Compressed air pipe 222 extends a first axial distance (A1) relative to the pipe centerline axis 228 between compressed air inlet 224 and compressed air outlet 226. This excluding the set of vortex generators 230, extends along compressed air outlet 226. Figure 4 When viewed as part of the compressed air pipe 222, 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 between opposite portions of the compressed air pipe 222 along the compressed air outlet 226, regardless of the shape of the compressed air pipe 222.

[0079] Figure 7 It is along Figure 5 A schematic side cross-sectional view of the compressed air pipe 222 taken along section line VII-VII. The compressed air pipe 222 taken along section line VII-VII includes a portion of the set of vortex generators 230; in particular, the first vortex generator 232 of the set.

[0080] The set of eddy current generators 230 can be integrally formed with or attached to the head 204 at the root 236, as shown by the dashed line. The root 236 is defined as the set of eddy current generators 230 at surface 252 ( Figure 6The vortex generator 230 is aligned with the head 204. In other words, if the vortex generator 230 is formed as a separate body and subsequently attached 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 arranged axially furthest from the compressed air outlet 226 relative to the tube 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 may be aligned or offset axially with respect to the tube centerline axis 228 relative to the compressed air outlet 226.

[0081] The compressed air outlet 226 extends radially with respect to the pipe centerline axis 228 by a second radial height (H2). The second radial height (H2) is measured between the relative apexes 240 of the first vortex generators in the group 232. Each first vortex generator in the group 232 extends radially with respect to the pipe centerline axis 228 by a third radial height (H3). Each first vortex generator in the group 232 extends axially with respect to the pipe centerline axis 228 by a second axial distance (A2) between the foot 260 and the apex 240. The second radial height (H2) may be less than, equal to, or greater than the third radial height (H3). Reference Figure 6 and Figure 7 The second radial height (H2) is smaller than the first radial height (H1). In other words, the vortex generator 230 radially contracts the compressed air pipe 222 at the compressed air outlet 226.

[0082] Gas fuel channel 208 defines the channel centerline axis 250, and the channel centerline axis 250 is located at fuel manifold 218 ( Figure 4 The orifice branch extends into and extends to each gas fuel orifice in the group of gas fuel orifices 220. An orifice angle 258 is formed between the channel centerline axis 250 and the protrusion 254 of the pipe centerline axis 228 at the corresponding gas fuel orifice in the group of gas 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 group of gas fuel orifices 220 may be non-zero and oriented such that... Figure 4 The outlet gas fuel stream (Fgo) is radially directed away from the compressed air outlet 226. Figure 4 The outlet compressed air flow (Fco).

[0083] Each of the gas fuel orifices 220 in this group is positioned with a sixth radial height (H6) relative to the pipe centerline axis 228. The sixth radial height (H6) is measured between the point where the channel centerline axis 250 intersects with the gas fuel orifice and the point where the root 236 meets the trailing edge 266. Each gas fuel orifice 220 in this group includes a corresponding radial width (D) relative to the pipe centerline axis 228. The gas fuel orifice 220 can be formed as a circular orifice 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).

[0084] 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 first vortex generator 232 and exits as a second outlet compressed air flow (Fco2) from the compressed air outlet 226. The second outlet compressed air flow (Fco2) forms... Figure 4 It is part of the outlet compressed air flow (Fco). 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 within the combustion chamber 216.

[0085] Figure 8 Is Figure 5 A schematic diagram of the fuel nozzle assembly 202 as seen within section VIII. Although described with reference to the first vortex generator 232, it should be understood that aspects of the first vortex generator 232 can be applied to... Figure 5 Any of the eddy current generators in the group of eddy current generators 230.

[0086] For illustrative purposes, an exemplary vortex generator 231 in the set of vortex generators 230 is shown in dashed lines. A vortex generator centerline 242 extends from a midpoint along the base between opposing sidewalls 238 to a apex 240. Each vortex generator in the set of vortex generators 230 is angled by an angle 246 formed between the respective vortex generator centerline 242 and a radial line 244, which extends radially outward from the axis 228 of the corresponding compressed air pipe in which the vortex generator is disposed, and intersects the root 236 midway between opposing sidewalls 238. For illustrative purposes, the radial line 244 is not shown within the first vortex generator 232, as it corresponds to the vortex generator centerline 242 of the first vortex generator 232. The 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 eddy current generator may not be equal to 0 degrees. Exemplary eddy current generator 231 includes a non-zero included angle 246, while, as shown, the first eddy current generator 232 includes a zero included angle 246.

[0087] During operation, each vortex generator in the set of vortex generators 230 generates two vortices that define a pair of vortices disposed on opposite sides of opposite sidewalls 238. The two vortices generated by each vortex generator in the set of vortex generators 230 are defined as a pair of vortices. Therefore, each vortex generator in the set of vortex generators 230 is configured to generate a pair of vortices on opposite sides or circumferentially opposite sides of the vortex generator.

[0088] Eddy currents are used to increase the amount of gaseous fuel exiting the set of gaseous fuel orifices 220 (e.g., Figure 4 The outlet gas fuel stream (Fgo) is trapped. Specifically, the outlet gas fuel stream (Fgo) is captured by the outlet compressed air stream (Fco) using at least a second outlet compressed air stream (Fco2). Capturing the outlet gas fuel stream (Fgo) ensures that it is adequately mixed with the compressed air stream before ignition. As used herein, the terms "adequately mixed" or "effectively mixed" refer to the degree to which two or more fluids are mixed together, and it should be understood that the optimal mixture of two or more 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. With regard to fuel nozzle assembly 202, compared to a fuel nozzle assembly that does not include this vortex generator 230, Figure 4 The resulting mixed gas fuel and air stream (Fm) comprises 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).

[0089] It has been found that producing a more homogeneous mixture of gaseous fuel and compressed air reduces NOx emissions in combustion section 200. It is conceivable that if one section of the mixed gaseous fuel and air stream (Fm) is richer than another section (e.g., containing a higher concentration of gaseous fuel), the richer section will produce increased NOx emissions. This, in turn, means that an insufficiently mixed mixed gaseous fuel and air stream (Fm) will produce more NOx emissions during combustion compared to a fuel nozzle assembly 202 that includes a well-mixed mixed gaseous fuel and air stream (Fm) due to the use of the vortex generator 230.

[0090] At least a portion of the gaseous fuel orifices 220 in the set of gaseous fuel orifices is circumferentially aligned with at least a portion of the set of vortex generators 230. This alignment, in turn, ensures that the outlet gaseous fuel stream (Fgo) is directly injected into the opposing vortex (e.g., the second outlet compressed air stream (Fco2)). Directly injecting the outlet gaseous fuel stream (Fgo) into the vortex pair ensures thorough mixing of the outlet gaseous fuel stream (Fgo) with the outlet compressed air stream (Fco).

[0091] Figure 9 It is along Figure 5 A schematic side cross-sectional view of the compressed air pipe 222 taken along section line IX-IX. The compressed air pipe 222 taken along section line IX-IX includes a portion of the set of vortex generators 230; in particular, the set of second vortex generators 234. At least a portion of the set of gas fuel orifices 220, shown in dashed lines, can be circumferentially aligned with the set of second vortex generators 234.

[0092] The compressed air outlet 226 extends radially with respect to the pipe centerline axis 228 by a fourth radial height (H4). This fourth radial height (H4) is measured between the relative apexes 240 of the two second vortex generators in the group 234. Each second vortex generator in the group 234 extends radially with respect to the pipe centerline axis 228 by a fifth radial height (H5). Each second vortex generator in the group 234 extends axially with respect to the pipe centerline axis 228 by a third axial distance (A3) between the foot 260 and the apex 240. The fourth radial height (H4) may be less than, equal to, or greater than the fifth radial height (H5). Reference Figure 6 and Figure 9 The fourth radial height (H4) is smaller than the first radial height (H1). In other words, the vortex generator 230 radially contracts the compressed air pipe 222 at the compressed air outlet 226.

[0093] 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 second vortex generator 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 It is part of the outlet compressed air flow (Fco). The set of vortex generators 230 is configured to guide the compressed air flow (Fc) so 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 of the second vortex generators in this group of second vortex generators 234 generates a pair of vortices disposed on opposite sides of the vortex generator.

[0094] refer to Figure 5-7 and Figure 9 At least one of the second axial distance (A2) or the third radial height (H3) is greater than the third axial distance (A3) or the fifth radial height (H5), respectively. In other words, the group of second vortex generators 234 is smaller than the group of first vortex generators 232. The variation between the group of first vortex generators 232 and the group 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. Therefore, the group of first vortex generators 232 generates larger vortices compared to the vortices of the group of second vortex generators 234.

[0095] The group of eddy current generators 230 can be defined by various parameters related to each other. A first radial height (H1) is greater than the third radial height (H3) of the first eddy current generator 232 and the fifth radial height (H5) of the second eddy current generator 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).

[0096] The first axial distance (A1) is greater than the second axial distance (A2) of the first vortex generator 232 and the third axial distance (A3) of the second vortex generator 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).

[0097] The first distance (L1) between the compressed air pipe 222 and the adjacent pipe is greater than the first radial height (H1) of the compressed air pipe 222. As a non-limiting example, the first axial distance (A1) may 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) may 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).

[0098] The second radial height (H2) is less than the first radial height (H1). In other words, the set of vortex generators 230 radially contracts the compressed air pipe 222 at the compressed air outlet 226. A pair of opposing sidewalls 238 may cover the foot 260. Alternatively, the leading edge 264 may be formed similarly to the trailing edge 266 and include triangular walls.

[0099] Figure 10 yes Figure 4 A schematic perspective view of the eddy current generator 230 in this group of eddy current generators 230. The eddy current generator 230 can be the first eddy current generator 232 in this group (…). Figure 5 ) or the second eddy current generator 234 of the group ( Figure 5 Any one of the following. 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 inward from the root 236 and reach the leading edge 264 and the apex 240. Therefore, when along the axis 228 perpendicular to the tube centerline ( Figure 4 When viewed along a plane intersecting with the vortex generator 230, the vortex generator 230 comprises 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. Therefore, when viewed along a plane, the vortex generator 230 can comprise any suitable cross-section, such as, but not limited to, triangles, rectangles, trapezoids, etc.

[0100] Figure 11Is it suitable for Figure 4 A schematic perspective view of an exemplary eddy current generator 330 used within the set of eddy current generators 230. Eddy current generator 330 is similar to the set of eddy current generators 230; therefore, similar portions will be identified by similar numbers increasing to the 300 series. It should be understood that, unless otherwise stated, the description of the set of eddy current generators 230 applies to eddy current generator 330.

[0101] The vortex generator 330 includes a root 336, a 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.

[0102] Eddy generator 330 is similar to eddy generator 230 ( Figure 10 ), because the eddy current generator is formed in an inverted pyramid shape. However, the eddy current generator 330 includes a trailing edge 366. With trailing edge 266 ( Figure 10 Unlike other structures, 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. Therefore, when along an axis perpendicular to the tube centerline (e.g., ...), Figure 4 When viewed in a plane intersecting the centerline axis 228 of the tube and the vortex generator 330, the vortex generator 330 comprises 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 wall.

[0103] Figure 12 Is it suitable for Figure 4 A schematic perspective view of an exemplary eddy current generator 430 used within the set of eddy current generators 230. Eddy current generator 430 is similar to the set of eddy current generators 230, 330; therefore, similar portions will be identified by similar numbers increasing to the 400 series. It should be understood that, unless otherwise stated, the description of the set of eddy current generators 230, 330 applies to eddy current generator 430.

[0104] The vortex generator 430 includes a root 436, a apex 440, and a pair of opposing sidewalls 438. The vortex generator 430 includes a trailing edge 466 extending between the root 436 and the apex 440. The vortex generator 430 includes a vortex generator centerline axis 442 extending from the apex 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 pipe (not shown) defining a tube centerline axis 428.

[0105] Eddy generator 430 is similar to eddy generator 230 ( Figure 10 ), 330 Figure 11This is because it is used to apply swirl to the fluid flow passing through the vortex generator 430. However, the vortex generator 430 includes a swept body 470 originating from the 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 part of the vortex generator 430, and this part includes an edge swept circumferentially relative to the tube centerline axis 428 (e.g., swept circumferentially relative to the sidewalls).

[0106] The eddy current generator 430 as a whole extends from the root 436 to the apex 440 relative to the tube centerline axis 428 with a total radial height (Ht) (equal to Figure 7 and Figure 8 The third radial height (H3) or fifth radial height (H5) of the tube. The main body 471 extends radially (Hm) from the transition portion 472 to the root portion 436 relative to the tube centerline axis 428. The main 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 radially (Hs) from the transition portion 472 to the apex 440 relative to the tube centerline axis 428. The swept body radial height (Hs) is greater than, equal to, or less than the main body radial height (Hm).

[0107] The size, positioning, and formation of the swept body 470 are designed to direct the compressed air flow (e.g., through the vortex generator 430) Figure 4 The compressed air flow (Fc) is guided into a compressed air pipe (e.g., where a vortex generator 430 is installed) to a compressed air pipe. Figure 4 The desired location within the compressed air pipe 222. As a non-limiting example, the swept body 470 can apply tangential momentum to the compressed air flow. The tangential momentum can direct the compressed air flow towards the central region of the compressed air pipe (e.g., Figure 4 The centerline axis 228 of the pipe). The compressed air flow is guided toward the central region of the compressed air pipe, thereby carrying the gaseous fuel flow toward the central region of the compressed air pipe (e.g., Figure 4 The outlet gaseous fuel stream (Fgo) carries the gaseous fuel stream toward the central region, thereby increasing the penetration of the gaseous fuel stream into the compressed air stream, which ultimately improves the mixing efficiency of the gaseous fuel stream and compressed air.

[0108] Figure 13 It is suitable for use as Figure 4A schematic diagram of an exemplary fuel nozzle assembly 502 of fuel nozzle assembly 202. Fuel nozzle assembly 502 is similar to fuel nozzle assembly 202; therefore, similar portions will be identified by similar numbers increasing to the 500 series. It should be understood that, unless otherwise stated, the description of fuel nozzle assembly 202 applies to fuel nozzle assembly 502.

[0109] Fuel nozzle assembly 502 includes a head 504 and a body (e.g., Figure 4 The body 206). The body defines the gas fuel channel (e.g., Figure 4 The fuel nozzle assembly 502 includes a gaseous fuel channel 208 and a centerline axis 510. The head 504 includes a periphery 512. The gaseous fuel channel terminates at a set of gaseous fuel orifices 520. The fuel nozzle assembly 502 includes a set of compressed air pipes 522 terminating at a compressed air outlet 526. Each compressed air pipe in the set of compressed air pipes 522 includes a pipe centerline axis 528. The fuel nozzle assembly 502 includes a set of vortex generators 530, which may include any number of sets of vortex generators. As a non-limiting example, the set of vortex generators 530 may include a set of first vortex generators 532 and a set of second vortex generators 534.

[0110] Fuel nozzle assembly 502 is similar to fuel nozzle assembly 202 because the set of gaseous fuel orifices 520 surrounds the set of compressed air lines 522. The set of compressed air lines 522 is not like the set of compressed air lines 222 (…). Figure 5 That would be circular. Instead, the compressed air tubes 522 are non-circular polygons, such as, but not limited to, rectangles, triangles, hexagons, trapezoids, etc.

[0111] The group of gaseous fuel orifices 520 also includes a cluster of gaseous fuel orifices 572, which comprises a plurality of gaseous fuel orifices 520 discharging into individual but adjacent compressed air lines 522. As a non-limiting example, the cluster of gaseous fuel orifices 572 may include a total of three gaseous fuel orifices 520 at the location where three adjacent compressed air lines 522 converge. It should be understood that the cluster of gaseous fuel orifices 572 may be located at the location where adjacent compressed air lines 522 converge. Alternatively, it should be understood that a single gaseous fuel orifice 520 discharging into any one of the adjacent compressed air lines 522 or not discharging into any adjacent compressed air line 522 may be provided.

[0112] Figure 14 It is along Figure 12The diagram shows 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, which branches into a first leg 576 and a second leg 578, leading to a corresponding gas fuel orifice 520. The first leg 576 and the second leg 578 may each be oriented such that the outlet gas fuel flow (Fgo) flowing through the corresponding first leg 576 or second leg 578 is directed to an adjacent compressed air line 522.

[0113] Figure 15 It is suitable for use as Figure 4 A schematic diagram of an exemplary fuel nozzle assembly 602 of fuel nozzle assembly 202. Fuel nozzle assembly 602 is similar to fuel nozzle assemblies 202, 502; therefore, similar portions will be identified by similar numbers increasing to the 600 series, and it should be understood that, unless otherwise stated, the description of fuel nozzle assemblies 202, 502 applies to fuel nozzle assembly 602.

[0114] Fuel nozzle assembly 602 includes a head 604 and a body (e.g., Figure 4 The fuel nozzle assembly 602 (body 206) defines a gaseous fuel channel (e.g., Figure 4 The fuel nozzle assembly 602 includes a gaseous fuel channel 208 and a centerline axis 610. The head 604 includes a periphery 612. The gaseous fuel channel terminates at a set of gaseous fuel orifices 620. The fuel nozzle assembly 602 includes a set of compressed air pipes 622 terminating at a compressed air outlet 626. Each of the compressed air pipes 622 includes a pipe centerline axis 628. The fuel nozzle assembly 602 includes a set of vortex generators 630, which may include any number of sets 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.

[0115] Head 604 is similar to head 204 ( Figure 5 ), 504 Figure 13 ), because it is defined by perimeter 612. However, perimeter 612 is a non-circular polygon. A non-circular polygon can be any suitable polygon, such as, but not limited to, triangles, rectangles, rhombuses, trapezoids, hexagons, etc. Furthermore, with compressed air pipe 522 ( Figure 13 Similarly, the compressed air pipe 622 can be formed in a non-circular polygonal shape. The compressed air pipe 622 can be formed in any suitable pattern. As a non-limiting example, the compressed air pipe 622 can be formed in two or more rows, or two or more columns. Furthermore, the compressed air pipe 622 can be formed such that no pipe centerline axis 628 is aligned with the centerline axis 610.

[0116] Figure 16 It is suitable for use as Figure 4 A schematic diagram of an exemplary fuel nozzle assembly 702 of fuel nozzle assembly 202. Fuel nozzle assembly 702 is similar to fuel nozzle assemblies 202, 502, 602; therefore, similar portions will be identified by similar numbers increasing to the 700 series. It should be understood that, unless otherwise stated, the description of fuel nozzle assemblies 202, 502, 602 applies to fuel nozzle assembly 702.

[0117] Fuel nozzle assembly 702 includes a head 704 and a body (e.g., Figure 4 The body 206). The body defines the gas fuel channel (e.g., Figure 4 The fuel nozzle assembly 702 includes a gaseous fuel channel 208 and a centerline axis 710. The head 704 includes a periphery 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 pipes 722 terminating at a compressed air outlet 726. Each compressed air pipe in the set of compressed air pipes 722 includes a pipe centerline axis 728. The fuel nozzle assembly 702 includes a set of vortex generators 730, which may include any number of sets of vortex generators. As a non-limiting example, the set of vortex generators 730 may include a set of first vortex generators 732 and a set of second vortex generators 734.

[0118] Except that at least a portion of the compressed air pipes 722 can be formed as an asymmetric polygon or shape relative to a plane extending along the pipe centerline axis 728, the compressed air pipes 722 are similar to the compressed air pipes 222. Figure 5 ), 522 ( Figure 13 ), 622 ( Figure 15 Furthermore, at least a portion of the compressed air pipes in the group of compressed air pipes 722 may be configured 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 group of vortex generators 730 (e.g., no group of first vortex generators 732 and the group of second vortex generators 734).

[0119] The benefits of this disclosure include combustors suitable for use with gaseous H2 fuels. As previously stated, gaseous H2 fuels have higher flame temperatures, flashback potential, and auto-ignition potential than conventional fuels (e.g., non-hydrogen-containing fuels). That is, gaseous H2 fuels have a wider combustible range and faster combustion rate than conventional fuels (such as petroleum-based fuels, or mixtures of petroleum and synthetic fuels). These high combustion temperatures of gaseous H2 fuels mean that additional isolation is required between the ignited gaseous H2 fuel and the surrounding components of the turbine or gas turbine engine (e.g., dome walls, inner / outer liners, and other parts of the turbine engine). Furthermore, additional structures are required to mitigate flashback and prevent unwanted auto-ignition; combustors using conventional fuels do not face these problems. As described herein, the combustor includes a fuel nozzle assembly that provides an insulating layer between the flame and portions of the combustion zone, keeping the mixed fuel flow below the auto-ignition temperature and preventing flashback from occurring within the fuel nozzle. The fuel nozzle assembly further contributes to flame shaping, which helps ensure that the bushing wall temperature, dome wall temperature, burner outlet temperature profile, and the pattern of the flame / gas exiting 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 overheating, thereby increasing the turbine engine's lifespan. That is, as described herein, the fuel nozzle assembly ensures uniform, consistent, or otherwise desired flame propagation within the burner.

[0120] Furthermore, compared to conventional fuel nozzle assemblies that do not include this vortex generator, it has been found that using this vortex generator reduces NOx emissions in the combustion zone. As discussed herein, this vortex generator creates vortices in the combustion chamber that trap or otherwise capture the gaseous fuel flow exiting the combustion chamber. Trapping the gaseous fuel flow by vortices helps ensure adequate mixing of the gaseous fuel and compressed air. Using this vortex generator helps ensure that the compressed air and gaseous fuel mixture is more homogeneous (e.g., more effectively mixed) than the compressed air and gaseous fuel mixture in conventional fuel nozzle assemblies. Once the compressed air and gaseous fuel mixture is ignited, the more homogeneous mixture further reduces overall NOx emissions in the combustion zone.

[0121] Compared to conventional fuels, the benefits associated with using hydrogen fuel include more environmentally friendly engines because hydrogen fuel produces fewer carbon pollutants when burned than combustors using conventional fuels. For example, a combustor using 100% hydrogen fuel (e.g., 100% H2) would have zero carbon pollutants. As described in this article, combustors can be used in situations involving 100% hydrogen fuel.

[0122] Within the scope not described herein, different features and structures of the various embodiments may be combined or substituted for each other as needed. All combinations or arrangements of the features described herein are covered by this disclosure.

[0123] This written description uses examples to illustrate aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice aspects of this disclosure, including making and using any apparatus or system and methods of making any combinations. The patentable scope of aspects of this disclosure is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0124] Further details are provided by the following topics:

[0125] A turbine engine includes a compression section, a combustion section, and a turbine section arranged in a tandem flow configuration. The combustion section includes a dome wall and a burner bushing, the dome wall and the burner bushing together forming at least a portion of a combustion chamber; and a fuel nozzle assembly fluidly coupled to the combustion chamber, and including: a compressed air pipe 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 pipe defining a pipe centerline axis; and a body defining a gaseous fuel channel in a series of gas... A set of gaseous fuel orifices is discharged into the combustion chamber to supply a gaseous fuel flow to the combustion chamber, the set of gaseous fuel orifices surrounding at least a portion of the compressed air outlet; and a set of vortex generators located within the compressed air pipe, each of the set of vortex generators defining a corresponding portion of the compressed air outlet and configured to generate a pair of vortices defined by two vortices disposed on opposite sides of the vortex generators, the vortex pairs being used to capture the gaseous fuel flow from the set of gaseous fuel orifices to define a mixture of compressed air and gaseous fuel within the combustion chamber.

[0126] According to any of the preceding clauses, the set of gas fuel orifices are circumferentially spaced about the centerline axis of the tube and circumferentially aligned with at least a portion of the set of vortex generators.

[0127] According to any of the preceding clauses, the turbine engine comprises a set of first vortex generators and a set of second vortex generators different from the set of first vortex generators.

[0128] According to any of the preceding clauses, in a turbine engine, each of the first vortex generators in a set of first vortex generators generates a first vortex pair, and each of the second vortex generators in a set of second vortex generators generates a second vortex pair, wherein each second vortex in the second vortex pair is smaller than each first vortex in the first vortex pair.

[0129] According to any of the preceding clauses of the turbine engine, wherein the compressed air pipe extends a first axial length between a compressed air inlet and a compressed air outlet formed along the body, and a first vortex generator in the set of vortex generators extends a second axial length relative to the centerline axis of the pipe, 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.

[0130] According to any of the preceding clauses, in a turbine engine, the second vortex generator of the set of vortex generators extends a third axial length relative to the centerline axis of the tube, 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.

[0131] The turbine engine according to any of the foregoing clauses, wherein the second axial length is different from the third axial length.

[0132] According to any of the preceding clauses, in a turbine engine, when viewed along a plane extending along the centerline axis of the pipe and intersecting the compressed air pipe excluding a portion of the set of vortex generators, the compressed air outlet extends a first radial height relative to the centerline axis, and a first vortex generator of the set of vortex generators extends a second radial height along its leading edge 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.

[0133] According to any of the preceding clauses, in a turbine engine, a second vortex generator in a set of vortex generators extends a third radial height along the 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.

[0134] According to any of the foregoing clauses, the second radial height is not equal to the third radial height.

[0135] The turbine engine according to any of the foregoing clauses, wherein the compressed air pipe is included within 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, wherein 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.

[0136] According to any of the preceding clauses, in a turbine engine, when viewed along a plane extending along the centerline axis of the tube and intersecting a portion of the first compressed air tube excluding the set of vortex generators, the compressed air outlet of the first compressed air tube extends a first radial height relative to the centerline axis of the tube, the centerline axis of the tube at the compressed air outlet of the first compressed air tube being set at a distance from the centerline axis of the tube at the compressed air outlet of the second compressed air tube, wherein 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.

[0137] The turbine engine according to any of the foregoing clauses, wherein the fuel nozzle assembly is planar symmetrical about a plane extending along the centerline axis.

[0138] The turbine engine according to any of the foregoing clauses, wherein at least one of the compressed air pipes does not include the set of vortex generators.

[0139] According to any of the preceding clauses, the turbine engine comprises at least one gaseous fuel port cluster disposed between at least two adjacent compressed air pipes of the set of compressed air pipes, the at least one gaseous fuel port cluster having: a main leg; a first leg fluidly connecting the main leg to a first gaseous fuel port in the at least one gaseous fuel port cluster, the first gaseous fuel port discharging into a first compressed air pipe in the at least two adjacent compressed air pipes; and a second leg fluidly connecting the main leg to a second gaseous fuel port in the at least one gaseous fuel port cluster, the second gaseous fuel port discharging into a second compressed air pipe in the at least two adjacent compressed air pipes that is different from the first compressed air pipe.

[0140] According to any of the preceding clauses, in the turbine engine, one of the gas fuel orifices in the set extends radially with respect to the centerline axis of the pipe, and the gas fuel orifice is set radially at a distance from the compressed air outlet relative to the centerline axis of the pipe, the radial height being greater than or equal to 1.4 times the radial width and less than or equal to 20 times the radial width.

[0141] According to any of the preceding clauses, each of the set of vortex generators includes a root and a apex, and defines a vortex generator centerline extending from the apex 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 extending from the tube centerline axis and intersecting the vortex generator centerline at the root.

[0142] According to any of the preceding clauses, in a turbine engine, one of the set of vortex generators includes a trailing edge, a body, and a swept body extending from the body. The vortex generator extends a total radial height along the trailing edge relative to the tube centerline axis and extends a radial height along the trailing edge of the body, the radial height of the body being greater than or equal to 0.1 times and less than or equal to 0.7 times the total radial height.

[0143] According to any of the preceding clauses, the turbine engine wherein, when viewed along a plane perpendicular to the axis of the pipe centerline and intersecting the compressed air outlet, the compressed air pipe comprises a non-circular polygonal shape.

[0144] A method of operating a combustion section according to any of the preceding clauses, the method comprising: supplying a stream of gaseous hydrogen fuel to the gaseous fuel channel; and supplying a stream of compressed air to the set of compressed air pipes.

[0145] A combustion section includes: a dome wall and a burner bushing, the dome wall and the burner bushing together forming at least a portion of a combustion chamber; and a fuel nozzle assembly fluidly coupled to the combustion chamber, and including: a compressed air pipe having a compressed air outlet that discharges into the combustion chamber to supply a compressed air flow to the combustion chamber, the compressed air pipe defining a pipe centerline axis; and a body defining a gaseous fuel channel that discharges into the combustion chamber at a set of gaseous fuel orifices, thereby... A gaseous fuel flow is supplied to the combustion chamber, the set of gaseous fuel orifices surrounding at least a portion of the compressed air outlet; and a set of vortex generators located within the compressed air pipe, each of the vortex generators defining a corresponding portion of the compressed air outlet and configured to generate a pair of vortices defined by two vortices disposed on opposite sides of the vortex generators, the vortex pairs being used to capture the gaseous fuel flow from the set of gaseous fuel orifices to define a mixture of compressed air and gaseous fuel within the combustion chamber.

[0146] According to any of the preceding clauses, the set of gas fuel orifices are circumferentially spaced around the centerline axis of the tube and circumferentially aligned with at least a portion of the set of vortex generators.

[0147] According to any of the preceding clauses, the combustion zone includes a set of first vortex generators and a set of second vortex generators that are different from the set of first vortex generators.

[0148] According to any of the preceding clauses, each of the first vortex generators in the set of first vortex generators generates a first vortex pair, and each of the second vortex generators in the set of second vortex generators generates a second vortex pair, wherein each second vortex in the second vortex pair is smaller than each first vortex in the first vortex pair.

[0149] According to any of the preceding clauses, the combustion section wherein the compressed air pipe extends a first axial length between a compressed air inlet and a compressed air outlet formed along the body, and a first vortex generator in the set of vortex generators extends a second axial length relative to the centerline axis of the pipe, 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.

[0150] According to any of the preceding clauses, in the combustion section, the second vortex generator in the set of vortex generators extends a third axial length relative to the centerline axis of the tube, 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.

[0151] According to any of the preceding clauses, the combustion section, wherein the second axial length is different from the third axial length.

[0152] According to any of the preceding clauses, the combustion section wherein, when viewed along a plane extending along the centerline axis of the pipe and intersecting the compressed air pipe excluding a portion of the set of vortex generators, the compressed air outlet extends a first radial height relative to the centerline axis, and a first vortex generator of the set of vortex generators extends a second radial height along its leading edge 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.

[0153] According to any of the preceding clauses, in the combustion zone, the second vortex generator of the set of vortex generators extends a third radial height along the 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.

[0154] According to any of the preceding clauses, the combustion zone, wherein the second radial height is not equal to the third radial height.

[0155] According to any of the preceding clauses, the combustion section, wherein the compressed air pipe is included within 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, wherein 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.

[0156] According to any of the preceding clauses, the combustion section wherein, when viewed along a plane extending along the centerline axis of the pipe and intersecting a portion of the first compressed air pipe excluding the set of vortex generators, the compressed air outlet of the first compressed air pipe extends a first radial height relative to the centerline axis of the pipe, the centerline axis of the pipe at the compressed air outlet of the first compressed air pipe being set at a distance from the centerline axis of the pipe at the compressed air outlet of the second compressed air pipe, wherein 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.

[0157] According to any of the foregoing clauses, the combustion section wherein the fuel nozzle assembly is planar symmetrical about a plane extending along the central axis.

[0158] According to any of the preceding clauses, the combustion section wherein at least one of the compressed air pipes does not include the set of vortex generators.

[0159] According to any of the preceding clauses, the combustion section, wherein the set of gaseous fuel orifices comprises at least one cluster of gaseous fuel orifices disposed between at least two adjacent compressed air pipes of the set of compressed air pipes, the at least one cluster of gaseous fuel orifices having: a main leg; a first leg fluidly connecting the main leg to a first gaseous fuel orifice in the at least one cluster of gaseous fuel orifices, the first gaseous fuel orifice discharging into a first compressed air pipe in the at least two adjacent compressed air pipes; and a second leg fluidly connecting the main leg to a second gaseous fuel orifice in the at least one cluster of gaseous fuel orifices, the second gaseous fuel orifice discharging into a second compressed air pipe in the at least two adjacent compressed air pipes that is different from the first compressed air pipe.

[0160] According to any of the preceding clauses, in the combustion section, the gas fuel orifice of the set of gas fuel orifices extends radially with respect to the centerline axis of the pipe, and the gas fuel orifice is set radially at a distance from the compressed air outlet relative to the centerline axis of the pipe, the radial height being greater than or equal to 1.4 times the radial width and less than or equal to 20 times the radial width.

[0161] According to any of the preceding clauses, each of the set of vortex generators includes a root and a apex, and defines a vortex generator centerline extending from the apex 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 extending from the tube centerline axis and intersecting the vortex generator centerline at the root.

[0162] According to any of the preceding clauses, in the combustion section, the vortex generator in the set of vortex generators includes 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 extending a radial height of the body along the trailing edge, the radial height of the body being greater than or equal to 0.1 times and less than or equal to 0.7 times the total radial height.

[0163] According to any of the preceding clauses, the combustion section, wherein, when viewed along a plane perpendicular to the axis of the pipe centerline and intersecting the compressed air outlet, the compressed air pipe comprises a non-circular polygonal shape.

[0164] A method of operating a combustion section according to any of the preceding clauses, the method comprising: supplying a stream of gaseous hydrogen fuel to the gaseous fuel channel; and supplying a stream of compressed air to the set of compressed air pipes.

Claims

1. A combustion section for a turbine engine, the turbine engine comprising a compression section, the combustion section, and a turbine section arranged in a series flow configuration, characterized in that, The combustion zone includes: A dome wall and a burner bushing, the dome wall and the burner bushing together forming at least a portion of the combustion chamber; and Fuel nozzle assembly, fluidly coupled to the combustion chamber, the fuel nozzle assembly comprising: A set of compressed air pipes, each of the set of compressed air pipes having a compressed air outlet, the compressed air outlet being discharged into the combustion chamber, thereby supplying a flow of compressed air to the combustion chamber, each compressed air pipe defining a pipe centerline axis; The body defines a centerline axis and a gas fuel channel that discharges into the combustion chamber at a set of gas fuel orifices, thereby supplying a gas fuel flow to the combustion chamber, the set of gas fuel orifices surrounding at least a portion of the compressed air outlet; A head, which is connected to the body and defines a periphery, the periphery being a non-circular polygon; and A set of vortex generators, located within at least one of the set of compressed air pipes, the set of vortex generators being configured to guide the compressed air flow such that at least a portion of the compressed air flow forms a set of vortices, the set of vortices being used to capture or trap at least a portion of the gaseous fuel flow from the set of gaseous fuel orifices to form a mixed flow of compressed air and gaseous fuel in the combustion chamber.

2. The combustion zone according to claim 1, characterized in that, in, The non-circular polygon includes at least one of triangle, rectangle, rhombus, trapezoid or hexagon.

3. The combustion zone according to claim 1, characterized in that, in, At least one of the compressed air pipes in the set is formed in a non-circular polygonal shape.

4. The combustion zone according to claim 3, characterized in that, in, Each of the compressed air pipes in the set is formed in a non-circular polygonal shape.

5. The combustion zone according to claim 1, characterized in that, in, The set of compressed air pipes is formed in a pattern comprising two or more rows and / or two or more columns.

6. The combustion zone according to claim 5, characterized in that, in, The set of compressed air pipes is formed in two or more rows.

7. The combustion zone according to claim 5, characterized in that, in, The set of compressed air pipes is formed in two or more rows.

8. The combustion zone according to claim 1, characterized in that, in, None of the compressed air pipes in the group are aligned with the centerline of the main body.

9. The combustion zone according to claim 1, characterized in that, in, The set of eddy current generators includes a set of first eddy current generators and a set of second eddy current generators that are different from the set of first eddy current generators.

10. The combustion zone according to claim 9, characterized in that, in, The first set of eddy current generators has a first radial height, and the second set of eddy current generators has a second radial height different from the first radial height.

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