Gas turbine engine including fuel nozzle with vortex generator

Abstract

A gas turbine engine includes a compressor section, a combustion section, and a turbine section in a serial flow arrangement, where the combustion section has a fuel nozzle including a fuel nozzle body defining an axis and having an inner surface defining a gallery fluidly coupled to a combustion chamber, a support matrix within the gallery, the support matrix including a plurality of segments intersecting one another when viewed from aft, and a set of vortex generators on the support matrix.

Description

Technical Field

[0001] This topic generally concerns the combustion zone used in turbine engines. Background Technology

[0002] 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.

[0003] Historically, hydrocarbon fuels have been used in the combustors of turbine engines. 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).

[0004] To reduce unwanted environmental byproducts, other fuels, such as hydrogen, are being explored. Hydrogen, or hydrogen mixed with another element, has a higher flame temperature than conventional hydrocarbon fuels. In other words, hydrogen or hydrogen-blended fuels typically have a wider combustible range and a faster combustion rate than conventional hydrocarbon-based fuels. Attached Figure Description

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

[0006] Figure 1 This is a schematic diagram of a turbine engine having a compressor section, a combustion section and a turbine section, based on the various aspects described herein.

[0007] Figure 2 It is based on the various aspects described in this article along line II-II. Figure 1 A schematic diagram of the combustion zone.

[0008] Figure 3 Is it suitable for Figure 1 A schematic diagram of the combustion section used in the turbine is shown, further illustrating fuel nozzles with a support matrix and a set of vortex generators located on the support matrix, the support matrix having a first stage and a second stage.

[0009] Figure 4 It is along Figure 3The schematic cross-sectional front and rear views of line IV-IV depict the first-level segments and the second-level segments of the support matrix forming the mesh.

[0010] Figure 5 It is suitable for use as Figure 3 A schematic cross-sectional front and rear view of an exemplary fuel nozzle further illustrates a support matrix and a set of vortex generators, the support matrix having first-level non-intersecting segments and second-level non-intersecting segments.

[0011] Figure 6 It is suitable for use as Figure 3 A schematic cross-sectional front and rear view of an exemplary fuel nozzle further illustrates a support matrix and a set of vortex generators, the support matrix having segments forming a first stage of spoke wheel shape and segments forming a second stage of spoke wheel shape.

[0012] Figure 7 It is suitable for use as Figure 3 A schematic cross-sectional front and rear view of an exemplary fuel nozzle further illustrates a single stage of the support matrix and a set of vortex generators, wherein the segments of the single stage form a honeycomb shape.

[0013] Figure 8 Is it suitable for Figure 1 A schematic diagram of an exemplary combustion section used in a turbine engine, further showing a fuel nozzle with a support matrix and a set of vortex generators, the support matrix having a first flat stage, a second flat stage and a third radially converging stage, the third radially converging stage having a vertex located at the farthest downstream portion of the third stage.

[0014] Figure 9 Is it suitable for Figure 1 A schematic diagram of another combustion section used in the turbine engine further shows a fuel nozzle with a support matrix and a set of vortex generators. The support matrix has a first flat stage, a second flat stage and a third radial converging stage, with the third radial converging stage having a vertex located at the farthest upstream portion of the third stage. Detailed Implementation

[0015] The disclosed aspects described herein relate to a combustion section for a turbine engine. The combustion section has a combustor and a fuel nozzle. The combustor has a combustion chamber. The fuel nozzle has channels leading to the combustion chamber. The fuel nozzle has a support matrix and a set of vortex generators located on the support matrix.

[0016] During operation, compressed air is supplied to the channels of the fuel nozzle. The compressed air flows through the support matrix and the set of vortex generators. Fuel flow can optionally be supplied through part or all of the set of vortex generators. The generation of vortices increases the ability of the fuel flow to mix with the compressed air within the fuel nozzle.

[0017] When supplying a stream of hydrogen-containing fuel (hereinafter referred to as "H2 fuel") to the combustion chamber, fuel nozzles, including a support matrix and a set of vortex generators, are particularly advantageous. H2 fuel may include gaseous H2 fuel, liquid H2 fuel, or a combination thereof. The H2 fuel stream may also be mixed with other fuels or fluids, such as, but not limited to, natural gas, coke oven gas, diesel, Jet-A, etc.

[0018] H2 fuel has lower carbon emissions compared to conventional fuels (e.g., carbon fuels, petroleum fuels, etc.). However, H2 fuel has a higher combustion temperature and is relatively less stable than conventional fuels. For example, H2 fuel has a higher combustion rate and velocity than conventional fuels. Therefore, improper mixing of H2 fuel and compressed air can lead to flashback or the spread of the flame generated by igniting H2 fuel into unwanted areas of the turbine engine. For example, improper mixing of H2 fuel and compressed air can create H2 fuel pockets, which in some cases can ignite within the fuel nozzle (e.g., flashback). Fuel nozzles as described herein, including a support matrix with this set of vortex generators, are particularly suitable for combustion sections that utilize H2 fuel by generating turbulence.

[0019] For illustrative purposes, this disclosure will be described in relation to turbine engines. However, it will be understood that the aspects of the disclosure described herein are not limited thereto, and the combustion sections 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.

[0020] For the burner and fuel nozzle assemblies described herein, gaseous hydrogen fuel can be used without the need for a diluent. In some embodiments, no diluent is added to the combustion chamber, and the fuel is substantially entirely diatomic hydrogen without diluent. As used herein, the term "substantially entirely" to describe the amount of a particular element or molecule (e.g., diatomic hydrogen) means at least 99% (by mass) of the described portion of the element or molecule, such as at least 97.5%, at least 95%, at least 92.5%, at least 90%, at least 85%, or at least 75% (by mass). In some examples, the fuel is entirely (e.g., 100%) hydrogen (by mass).

[0021] As used herein, the term "swirling" fluid flow, or its iteration, refers to an axisymmetric fluid flow that has circumferential rotation or swirling about a central axis. The swirling quantity of a fluid flow is quantified by the swirling number. The swirling number is defined as the integral of the tangential momentum and axial momentum of the fluid flow relative to the central axis.

[0022] As used herein, the term "turbulent" fluid flow, or its iterations, refers to non-laminar, chaotic, and localized fluid flow. For example, turbulence can take the form of localized swirls, eddies, or vortices. Turbulence in a turbulent fluid flow is quantified using turbulent kinetic energy and the fluid's Reynolds number.

[0023] In relation to each other, swirling flow refers to large-scale, organized rotational movement of a fluid flow, while turbulent flow refers to localized, chaotic movement of a fluid flow. It will be understood that fluid flow can include both swirling and turbulent flow.

[0024] 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.

[0025] As used herein, the terms “first,” “second,” “third,” etc., are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components.

[0026] 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 exhaust outlet.

[0027] 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.

[0028] The term "fluid" can refer to either a gas or a liquid. The term "fluid connection" means that fluids can establish a connection between specified areas.

[0029] In the context of turbine engines, the term "nozzle" is used in various ways. In this application, "nozzle" refers to a component having a portion fluidly connected to a fuel supply section and having at least one portion fluidly connected to a burner section, burner bushing, combustion chamber, or a combination thereof.

[0030] 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.

[0031] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are for identification purposes only to 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.

[0032] 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.

[0033] The use of “and” and “or” will be interpreted broadly. For example, but not limited to, the use of “and” does not necessarily require all the elements or features listed, and the use of “or” is inclusive unless the structure is illogical.

[0034] As used herein and throughout the specification and claims, approximate language is applied to modify any quantitative representation that may allow for variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” “substantially,” and “basically” are not limited to the specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture parts and systems. For example, approximate language may refer to a margin of 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the endpoints of a single value, a range of values, or a range of defined values. Scope limitations are combined and interchanged herein and throughout the specification and claims; such scope is identified and includes all subscopes contained herein, unless otherwise indicated by context or language. For example, all scopes disclosed herein include endpoints, and endpoints can be combined independently of each other.

[0035] As used herein, “proximity” is a descriptor used to locate the parts described herein. Furthermore, the term “proximity” means that the part is closer to or closer to the referenced part than the following part. For example, “first orifice is close to the wall” or “first orifice is upstream of second orifice” means that the first orifice is closer to the wall than the second orifice.

[0036] Additionally, as used herein, "controller" can include components configured or adapted to provide instructions, control, operation, or any form of communication to an operable component to achieve its operation. A controller can include any known processor, microcontroller, or logic device, including but not limited to: field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), full-authority digital engine control (FADECs), proportional controllers (P), proportional-integral controllers (PI), proportional-derivative controllers (PD), proportional-integral-derivative controllers (PID controllers), proportional-resonant controllers (PR), hardware-accelerated logic controllers (e.g., for encoding, decoding, transcoding, etc.), and combinations thereof. Non-limiting examples of controllers can be configured or adapted to run, operate, or otherwise execute program code to affect operational or functional outcomes, including performing various methods, functions, processing tasks, calculations, comparisons, sensing, or measurement values, etc., to enable or implement the technical operations or actions described herein. Operational or functional outcomes can be based on one or more inputs, stored data values, sensed or measured values, true or false indications, etc. While “program code” is described, non-limiting examples of operable or executable instruction sets may include routines, programs, objects, components, data structures, algorithms, etc., that have the technical effect of performing a specific task or implementing a specific abstract data type. In another non-limiting example, the controller may also include data storage components accessible by the processor, including memory, whether transient, volatile, or non-transient or non-volatile.

[0037] Additional non-limiting examples of memory may include random access memory (RAM), read-only memory (ROM), flash memory, or one or more different types of portable electronic memory, such as discs, DVDs, CD-ROMs, flash drives, universal serial bus (USB) drives, etc., or any suitable combination of these types of memory. In one example, program code may be stored in memory in a machine-readable format accessible to a processor. Furthermore, memory may store various types of data, sensed or measured data values, input, generated or processed data, etc., accessible to a processor when providing instructions, control, or operations to achieve a function or operable result, as described herein. In another non-limiting example, a controller may be configured to compare a first value with a second value and operate and control the operation of additional components based on the satisfaction of that comparison. For example, when a sensed, measured, or provided value is compared with another value (including a stored or predetermined value), the satisfaction of that comparison may result in an action, function, or operation that can be controlled by the controller.

[0038] Figure 1 This is a schematic diagram of a turbine engine 10 (e.g., a gas turbine engine). As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16 arranged in a series flow configuration. A drive shaft 18 rotatably connects the compressor section 12 and the turbine section 16 such that rotation of one affects rotation of the other, and defines a rotation axis 20 for the turbine engine 10. The turbine engine 10 includes an engine housing 29. The engine housing 29 accommodates at least a portion of the compressor section 12, the combustion section 14, and the turbine section 16.

[0039] Compressor 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 HP turbine 26 and an LP turbine 28 fluidly connected in series with each other. Drive shaft 18 may operatively connect the LP compressor 22, HP compressor 24, HP turbine 26, and LP turbine 28 together. Alternatively, drive shaft 18 may include an LP drive shaft and an HP drive shaft. The LP drive shaft may connect the LP compressor 22 to the LP turbine 28, and the HP drive shaft may connect the HP compressor 24 to the HP turbine 26. The LP spool is defined as a combination of the LP compressor 22, LP turbine 28, and LP drive shaft, such that rotation of the LP turbine 28 may apply a driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool is defined as a combination of the HP compressor 24, HP turbine 26, and HP drive shaft, such that rotation of the HP turbine 26 may apply a driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

[0040] Compressor section 12 includes multiple axially spaced stages (not shown). Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Compressor blades for a stage of compressor 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 compressor section 12 may be mounted to a shroud or housing that may extend circumferentially around one or more sections of turbine engine 10 and shield one or more sections of turbine engine 10. It should be understood that the representation of compressor section 12 is merely illustrative and any number of blades, blades, and stages may be present. Furthermore, it is conceivable that any number of other components may be present within compressor section 12.

[0041] Similar to compressor section 12, turbine section 16 includes 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 can be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage can have its own disc. The blades of turbine section 16 can be circumferentially mounted to a shroud or housing. It should be noted that any number of blades, blades, and turbine stages are possible, as the illustrated turbine section 16 is merely schematic. Furthermore, it is conceivable that any number of other components may be present within turbine section 16.

[0042] Combustion section 14 is arranged in series between compressor section 12 and turbine section 16. Combustion section 14 is fluidly coupled to at least a portion of compressor section 12 and turbine section 16, such that combustion section 14 at least partially fluidly couples compressor section 12 to turbine section 16. As a non-limiting example, combustion section 14 may be fluidly coupled to HP compressor 24 at its upstream end and to HP turbine 26 at its downstream end. Combustion section 14 includes burner 30.

[0043] The turbine engine 10 includes a fuel source 34. The fuel source 34 is any suitable container or vessel suitable for storing a quantity of fuel. The fuel within the fuel source 34 can be in various states. As a non-limiting example, the fuel within the fuel source 34 can be solid, liquid, or gaseous. The fuel source 34 is disposed outside the engine housing 29. The fuel source 34 can be disposed outside the turbine engine 10. As a non-limiting example, the turbine engine 10 can be coupled to an aircraft with wings. The wings can include the fuel source 34. The fuel source 34 is configured to supply a fuel flow to the combustion section 14, particularly to the burner 30. Although only a single fuel source 34 is shown, it will be understood that the turbine engine 10 can include or otherwise coupled to any number of one or more fuel sources having any quantity of one or more types of fuel.

[0044] During operation of the turbine engine 10, ambient or atmospheric air is drawn into the compressor section 12 via a fan section (not shown) upstream of the compressor section 12, where it is compressed to define pressurized air. At least a portion of the pressurized air then flows into the combustion section 14, where it mixes with fuel from the fuel source 34 and is ignited to generate combustion gases. The turbine section 16 extracts some work from these combustion gases and, in turn, drives the compressor section 12 and the fan section via a drive shaft 18. The combustion gases are ultimately discharged from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The pressurized airflow and the combustion gases together define the working airflow flowing through the compressor section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

[0045] Figure 2 Depicting along Figure 1 A cross-sectional view of combustion section 14 along line II-II. Depending on the type of engine in which the burner 30 is located, the burner 30 may have a canister-shaped, canister-annular, or annular arrangement. In a non-limiting example, the burner 30 may have a combined arrangement positioned together with the engine housing 29. The engine housing 29 may shield or cover at least a portion of combustion section 14. Combustion section 14 includes a combustion section centerline 33. Combustion section 14 may be collinear with the axis of rotation 20, such that the combustion section centerline 33 extends along the axis of rotation 20. Alternatively, at least a portion of the combustion section centerline 33 may be offset from the axis of rotation 20. The combustion section centerline 33 defines a radial direction Rd, an axial direction Ad, and a circumferential direction Cd.

[0046] The burner 30 includes a burner bushing 40. The burner bushing 40 may include an outer burner bushing 41 and an inner burner bushing 42 arranged concentrically relative to each other and in a ring-like manner around the engine centerline or axis of rotation 20. The burner bushing 40 may have various configurations. As a non-limiting example, the burner bushing 40 may extend continuously in the circumferential direction Cd for approximately the entire circumferential extent of the combustion section centerline 33. As a non-limiting example, the burner bushing 40 may extend continuously in the circumferential direction Cd for approximately less than the entire circumferential extent of the combustion section centerline 33. As a non-limiting example, the burner bushing 40 may be segmented in the circumferential direction Cd, the axial direction Ad, the radial direction Rd, or combinations thereof (e.g., formed by two or more bodies connected to each other). As a non-limiting example, the burner bushing 40 may include two or more circumferential segments, each of which extends circumferentially in the circumferential direction Cd for approximately less than the entire circumferential extent of the combustion section centerline 33. When connected to each other, two or more circumferential segments will extend together in the circumferential direction Cd over the entire circumferential range of the combustion zone centerline 33.

[0047] The burner 30 may include a dome wall 46 that interconnects opposing portions of the burner bushing 40. As a non-limiting example, the dome wall 46 may extend radially between the outer burner bushing 41 and the inner burner bushing 42. The dome wall 46 may be formed substantially perpendicular to the combustion zone centerline 33. Similar to the burner bushing 40, the dome wall 46 may extend continuously in the circumferential direction Cd for approximately the entire circumferential extent of the combustion zone centerline 33. Alternatively, the dome wall 46 may be segmented in the circumferential direction Cd, the radial direction Rd, or a combination thereof.

[0048] At least one of the dome wall 46 or the burner bushing 40 includes a set of fuel nozzle openings 72. As shown, the dome wall 46 includes this set of fuel nozzle openings 72. However, it will be understood that at least one of the fuel nozzle openings 72 may be positioned along a corresponding portion of the burner bushing 40.

[0049] It will be understood that in some configurations, the dome wall 46 may be excluded from the burner 30. In such a configuration, the inner burner bushing 42 and the outer burner bushing 41 may meet at a common point. The dome wall 46 and the burner bushing 40 will be collectively referred to as the “wall” defining the combustion chamber 50.

[0050] The burner bushing 40 and the dome wall 46 (if included) together form the combustion chamber 50. The combustion chamber 50 is arranged in a ring around the centerline 33 of the combustion section in the circumferential direction Cd.

[0051] The compressed air passage 32 may be defined at least partially by both the burner bushing 40 and the engine housing 29. As a non-limiting example, the burner bushing 40 is spaced apart from the engine housing 29 to define the compressed air passage 32 therebetween. The compressed air passage 32 is fluidly connected to the compressor section 12. Figure 1 ).

[0052] Combustion section 14 may include an annular arrangement of combustor portions 31 disposed around the centerline or axis of rotation 20 of the turbine engine 10 in the circumferential direction Cd. It will be understood that one or more combustor portions in the annular arrangement of combustor portions 31 may be radially or axially offset, respectively, in the radial direction Rd or the axial direction Ad. In some configurations, combustor portions 31 may include or be configured as a combustor cup, fuel cup, or nozzle cup.

[0053] Each burner section in the annular arrangement of burner sections 31 includes a fuel nozzle 48. For illustrative purposes, only a single fuel nozzle 48 is shown; however, it will be understood that each burner section in the annular arrangement of burner sections 31 may include a corresponding fuel nozzle 48. Each fuel nozzle 48 includes a fuel nozzle body 38 extending through a corresponding fuel nozzle opening in the set of fuel nozzle openings 72.

[0054] During operation, fuel F is supplied from fuel source 34 to combustion chamber 50 through an annular array of burner sections 31. Specifically, fuel F is supplied to combustion chamber 50 through fuel nozzle bodies 38 of at least one burner section in the annular array of burner sections 31. Fuel F includes any suitable fuel, including gaseous fuels such as H2 fuel. As a non-limiting example, fuel F may include 100% H2 (e.g., without diluent). In some examples, fuel F may be a combination of fuel using other fuels and H2 fuel. For example, fuel F may include H2 fuel and methane, such as methane in the form of natural gas. Controller 60 may be connected to fuel source 34, fuel nozzle 48, or both, and at least partially controls the operation of fuel source 34, fuel nozzle 48, or both. Controller 60 may include processor 62 and memory 64.

[0055] Figure 3 Is it suitable for Figure 1 A schematic diagram of the combustor section 100 used in the turbine engine 10. The combustor section 100 is similar to the combustor section 31. Figure 2 Therefore, similar parts will be identified by similar names, and it should be understood that, unless otherwise stated, the description of burner part 31 applies to burner part 100.

[0056] Burner section 100 includes a burner 102 and a fuel nozzle 104. Burner 102 includes a burner wall 106. Burner wall 106 includes a fuel nozzle opening 110. Burner wall 106 at least partially defines a combustion chamber 108. Burner wall 106 can be various walls within burner 102, such as a dome wall at least partially defining the combustion chamber 108 (e.g., Figure 2 46) dome wall, burner bushing (e.g., Figure 2 Burner bushing 40 Figure 2 42. Internal burner bushing Figure 2 (External burner bushing 41 or a combination thereof) or a combination thereof.

[0057] Fuel nozzle 104 includes fuel nozzle body 112. Fuel nozzle body 112 defines fuel nozzle axis 114. Fuel nozzle axis 114 extends through the center of fuel nozzle body 112. Fuel nozzle body 112 may be symmetrical or asymmetrical about fuel nozzle axis 114. Fuel nozzle body 112 has a channel 116 defined by fuel nozzle inner surface 115. Channel 116 extends axially relative to fuel nozzle axis 114 between fuel nozzle inlet 118 and fuel nozzle outlet 120. Fuel nozzle inlet 118 is formed as at least one of a channel, groove, set of holes, or combination thereof extending through a corresponding portion of fuel nozzle body 112. Fuel nozzle body 112 opens into combustion chamber 108 at fuel nozzle outlet 120.

[0058] The channel 116 is divided into at least two sections: a compressed air flow passage 122 and a mixer 124. The compressed air flow passage 122 extends axially from the fuel nozzle inlet 118 to the mixer 124 relative to the fuel nozzle axis 114. The mixer 124 extends axially from the compressed air flow passage 122 to the fuel nozzle outlet 120 relative to the fuel nozzle axis 114. A further description of the fluid flow within the compressed air flow passage 122 and the mixer 124 will follow in more detail.

[0059] The fuel nozzle 104 includes a support matrix 126 within a channel 116. The support matrix 126 includes multiple stages, each stage including at least a first stage 128 and a second stage 130. The first stage 128 is located axially ahead of the second stage 130 relative to the fuel nozzle axis 114. The support matrix 126 may include a variety of numbers of stages, such as a single stage or any number of two or more stages.

[0060] The fuel nozzle 104 includes a set of vortex generators 132. Each of the vortex generators 132 is suspended within the channel 116 by a support matrix 126. That is, each of the vortex generators 132 is positioned along a corresponding portion of the support matrix 126.

[0061] A subgroup of the eddy current generators 132 is positioned along the first stage 128. This subgroup of the eddy current generators 132 positioned along the first stage 128 is referred to herein as a first-stage eddy current generator subgroup 134. The first-stage eddy current generator subgroup 134 may include any number of eddy current generators from the eddy current generators 132. For example, the first-stage eddy current generator subgroup 134 may include at least one eddy current generator from the eddy current generators 132. Another subgroup of the eddy current generators 132 is positioned along the second stage 130. This subgroup of the eddy current generators 132 positioned along the second stage 130 is referred to herein as a second-stage eddy current generator subgroup 136. The second-stage eddy current generator subgroup 136 may include any number of eddy current generators from the eddy current generators 132. For example, the second-stage eddy current generator subgroup 136 may include at least one eddy current generator from the eddy current generators 132. The first-stage vortex generator subgroup 134 is radially offset from the second-stage vortex generator subgroup 136 relative to the fuel nozzle axis 114. That is, the first-stage vortex generator subgroup 134 is located at a radial position different from that of the second-stage vortex generator subgroup 136.

[0062] In a non-limiting example, the set of vortex generators 132 may have a cross-section in the shape of a symmetrical airfoil. For example, vortex generator 135 in the set of vortex generators 132 has a symmetrical airfoil shape and includes a pressure side 137 and a suction side 139, each extending between a leading edge 141 and a trailing edge 143. A chord 145 extends through vortex generator 135 between the leading edge 141 and the trailing edge 143. The chord 145 forms a line of symmetry through vortex generator 135, which gives vortex generator 135 a symmetrical airfoil shape. However, other cross-sectional shapes of the set of vortex generators 132 are contemplated, including any shape that improves mixing, vorticity, or turbulent kinetic energy, such as (but not limited to) asymmetrical airfoils (e.g., vortex generator 147, which is asymmetrical about chord 149), triangular, deltaic, forked, circular, or combinations thereof. In the non-limiting example shown, each of the vortex generators 132 in the set has an airfoil-shaped cross-section that tapers towards the fuel nozzle outlet 120. The set of vortex generators 132 may be oriented parallel to the fuel nozzle axis 114 (e.g., vortex generator 136a), or may be angled relative to the fuel nozzle axis 114 (e.g., vortex generator 136b), or a combination thereof. That is, a portion of the set of vortex generators 132 may be oriented parallel to the fuel nozzle axis 114, and a portion of the set of vortex generators 132 may be angled inward or outward relative to the fuel nozzle axis 114.

[0063] When viewed along plane 133, perpendicular to the fuel nozzle axis 114 and at an axial position relative to the fuel nozzle axis 114 of the farthest downstream vortex generator in the group of vortex generators 132, the fuel nozzle 104 includes a flow area and a blocking area. The flow area is defined as the portion of the total cross-sectional area of ​​the channel 116 along plane 133 that remains open or otherwise unblocked by the support matrix 126 and the group of vortex generators 132. The blocking area is defined as the portion of the total cross-sectional area of ​​the channel 116 along plane 133 that is blocked by the support matrix 126 and the group of vortex generators 132. When viewed along plane 133, the sum of the flow area and the blocking area is the total cross-sectional area of ​​the channel 116 along plane 133. The flow area is greater than or equal to 40% and less than or equal to 80% of the total cross-sectional area of ​​the channel 116 along plane 133.

[0064] Fuel nozzle 104 includes at least one of a first fuel supply section 138, a second fuel supply section 148, or a combination thereof. The first fuel supply section 138 and the second fuel supply section 148 are each connected to a fuel source 131 (e.g., fuel source 34). Figure 1 Fluid connection. The fuel source 131 is located outside the fuel nozzle body 112. The first fuel supply unit 138 and the second fuel supply unit 148 are fluidly connected to the fuel source 131 through a series of pipes, conduits, passages, or combinations thereof shown by dashed lines.

[0065] The first fuel supply section 138 includes a first fuel chamber 140, a set of fuel inlet orifices 142, a first fuel passage 144, and a set of first fuel outlet orifices 146. The set of fuel inlet orifices 142 interconnects the first fuel chamber 140 and the first fuel passage 144. The first fuel passage 144 interconnects the set of fuel inlet orifices 142 with the set of first fuel outlet orifices 146. The first fuel passage 144 leads to a channel 116 at the set of first fuel outlet orifices 146.

[0066] The first fuel chamber 140 is defined as a distribution channel for dispensing fuel received from the fuel source 131. The first fuel chamber 140 is at least partially formed by the fuel nozzle body 112. As a non-limiting example, the first fuel chamber 140 may be integrally formed with the fuel nozzle body 112.

[0067] As shown, each of the set of fuel inlet orifices 142 is defined by a free passage, or alternatively by an orifice formed within and along a corresponding portion of the fuel nozzle body 112. Although only two fuel inlet orifices of the set 142 are shown, the set 142 may include any number of one or more fuel inlet orifices.

[0068] A first fuel passage 144 extends from a first fuel chamber 140 and into a corresponding portion of the support matrix 126 and a corresponding portion of the set of vortex generators 132. Specifically, the first fuel passage 144 extends through the first stage of the support matrix 126 closest to the combustion chamber 108 and through the vortex generators in the set of vortex generators 132 positioned along the first stage of the support matrix 126 closest to the combustion chamber 108. In a non-limiting example, the first fuel passage 144 extends through a second stage 130 of the support matrix 126 and a second-stage vortex generator subgroup 136. The first fuel passage 144 leads to a set of first fuel outlet orifices 146 disposed along at least a portion of the second-stage vortex generator subgroup 136. In some examples, the set of first fuel outlet orifices 146 is located only on a corresponding portion of the second-stage vortex generator subgroup 136. It is contemplated that in other non-limiting examples, the first fuel passage 144 may additionally or alternatively extend through another stage of the support matrix 126. That is, the first fuel passage 144 may optionally extend through the first stage 128 and the first stage eddy current generator sub-group 134. In this configuration, the first fuel outlet orifice 146 of this group is additionally or alternatively located on the first stage eddy current generator sub-group 134.

[0069] As shown in the figure, each of the first fuel outlet orifices 146 in the group is defined by a passage, or alternatively by an orifice formed within and along the corresponding portion of the group of vortex generators 132. The hydraulic diameter 151 of each of the first fuel outlet orifices 146 in the group can be greater than or equal to 6 millimeters (mils) and less than or equal to 100 mils.

[0070] The second fuel supply section 148 includes a second fuel chamber 150 and a set of second fuel outlet orifices 152. The second fuel supply section 148 leads to a channel 116 at the set of second fuel outlet orifices 152. As shown, each of the second fuel outlet orifices 152 is defined by a passage, or alternatively by an orifice formed within and along the corresponding portion of the fuel nozzle body 112 in the second fuel chamber 150.

[0071] The second fuel chamber 150 is defined as a distribution channel for distributing fuel received from the fuel source 131. The second fuel chamber 150 is at least partially formed by the fuel nozzle body 112. As a non-limiting example, the second fuel chamber 150 may be integrally formed with the fuel nozzle body 112 downstream of the support matrix 126 and the set of vortex generators 132.

[0072] During operation, a compressed air flow Fc is supplied to channel 116. Specifically, the compressed air flow Fc is supplied to compressed air flow passage 122 through fuel nozzle inlet 118. Therefore, it will be understood that compressed air flow passage 122 is defined as the area of ​​channel 116 without fuel flow but including compressed air flow Fc. The compressed air flow Fc originates from a turbine engine (e.g., Figure 1 The upstream section of the turbine engine 10 (such as from the compressor section, e.g., Figure 1 The compressed air flow in compressor section 12). The compressed air flow Fc has a first pressure.

[0073] The compressed air flow Fc flows within the flow area and passes through the support matrix 126 and the set of vortex generators 132. As the compressed air flow Fc passes through the set of vortex generators 132, it forms a turbulent air flow Ft in the form of vortices or eddies. For illustrative purposes, the turbulent air flow Ft is shown directly downstream of the first stage 128. However, it will be understood that each stage of the support matrix 126 and its corresponding vortex generator in the set of vortex generators 132 generates a corresponding turbulent air flow Ft. The turbulent air flow Ft forms vortex pairs within the channel 116 by radial and axial rotation relative to the fuel nozzle axis 114.

[0074] Furthermore, if at least one subgroup of the vortex generator 132 is angled inward or outward relative to the fuel nozzle axis 114, the corresponding turbulent airflow Ft can swirl together downstream of the support matrix 126 and the vortex generator 132, forming a swirling airflow Fs. The swirl number of the swirling airflow Fs is greater than or equal to 0.2 and less than or equal to 1.2.

[0075] A first fuel flow F1 can be supplied to the channel 116 via a first fuel supply section 138. Specifically, the first fuel flow F1 is discharged from a set of first fuel outlet orifices 146, which are at least included on the second-stage vortex generator sub-group 136 and optionally on the first-stage vortex generator sub-group 134. In a non-limiting example, the first fuel flow F1 is injected in a direction parallel to the fuel nozzle axis 114 (e.g., axially relative to the fuel nozzle axis 114). That is, the vector of the first fuel flow F1 is parallel to the fuel nozzle axis 114. Additionally or alternatively, the first fuel flow F1 is injected at an angle relative to the fuel nozzle axis 114. That is, the vector of the first fuel flow F1 is not parallel to the fuel nozzle axis 114. The first fuel flow F1 has a second pressure, wherein the second pressure is greater than or equal to 1.01 times and less than or equal to 1.5 times the first pressure of the compressed air flow Fc. A second fuel flow F2 can be supplied to the channel 116 via a second fuel supply section 148. It will be understood that fuel nozzle 104 may include at least one of a first fuel stream F1, a second fuel stream F2, or a combination thereof. The fuel supplied to channel 116 (e.g., the first fuel stream F1 and the second fuel stream F2) will be collectively referred to below as fuel streams. Fuel streams may contain any suitable fuel. As a non-limiting example, fuel streams may include H2 fuel streams (e.g., 100% gaseous H2 fuel, 100% liquid H2 fuel, or H2 fuel mixed with another fuel or fluid) or natural gas fuel streams.

[0076] Fuel is supplied from fuel source 131 to channel 116. Specifically, the fuel flow exits from a set of first fuel outlet orifices 146, a set of second fuel outlet orifices 152, or a combination thereof, into mixer 124 of channel 116. Therefore, mixer 124 is defined as a region of channel 116 comprising both a fuel flow and a compressed air flow Fc (e.g., in the form of a turbulent air flow Ft, a swirling air flow Fs, or a combination thereof). The plurality of first fuel outlet orifices 146 may be oriented such that a first fuel flow F1 is injected into mixer 124 axially or parallel to fuel nozzle axis 114 (e.g., from vortex generator 136a), injected into mixer 124 at an angle relative to fuel nozzle axis 114 (e.g., from vortex generator 136b), or a combination thereof. The fuel flow is mixed with a corresponding portion of the compressed air flow Fc, particularly with the turbulent air flow Ft, the swirling air flow Fs, or a combination thereof, to define a fuel-air mixture Fm. The fuel-air mixture Fm is supplied to the combustion chamber 108 and ignited to define a flame (not shown) within the combustion chamber 108.

[0077] By distributing this set of vortex generators 132 within the channel 116, turbulence is generated in the channel 116 near the fuel nozzle axis 114. This results in a reduced flame velocity and flashback risk compared to fuel nozzles that generate turbulence near the periphery of the fuel nozzle (e.g., near the inner surface 115 of the fuel nozzle). The set of vortex generators 132 can be specifically oriented relative to the fuel nozzle axis 114 to control the mixing degree of the fuel flow and compressed air flow Fc. In particular, a uniform mixing distribution can be achieved by oriented the set of vortex generators 132 away from the inner surface 115 of the fuel nozzle.

[0078] Fuel nozzle 104 is particularly suitable for use in situations where the fuel stream contains H2 fuel. As discussed herein, the turbulent airflow Ft ensures uniform mixing of fuel and air in the fuel-air mixture Fm, thereby reducing the likelihood of fuel pockets or fuel pooling forming within the fuel-air mixture Fm. As discussed herein, H2 fuel has a higher combustion rate and a greater chance of flashback. Eliminating or reducing high fuel pooling within the fuel-air mixture Fm reduces the likelihood of flashback by decreasing the areas where flames may spread.

[0079] Figure 4 From Figure 3 The image shows a cross-sectional view of the burner section 100 viewed along line IV-IV. The fuel nozzle 104 includes a support matrix 126 having a first stage 128 and a second stage 130. For illustrative purposes, the first stage 128 and the second stage 130 are shown with different line thicknesses. The first stage 128 includes multiple segments shown in thick lines. The second stage 130 includes multiple segments shown in thin lines. Both the first stage 128 and the second stage 130 have a spiderweb shape, simply referred to herein as a web shape, which will be described in more detail below.

[0080] The first stage 128 comprises a set of first radial segments 154 and a set of first viscous segments 156. The set of first radial segments 154 extends radially relative to the fuel nozzle axis 114. Each first viscous segment in the set of first viscous segments 156 interconnects two radial segments in the set of first radial segments 154. The set of first radial segments 154 meets the set of first viscous segments 156 at a set of first partial joints 158. Each first radial segment in the set of first radial segments 154 and each first viscous segment in the set of first viscous segments 156 is shown as linear. However, it is conceivable that the set of first radial segments 154 and the set of first viscous segments 156 may be linear, curved, or a combination thereof. For example, the set of first viscous segments 156 may each be curved, collectively forming a circular or elliptical shape.

[0081] At least a majority of the eddy current generators included in the first-stage eddy current generator subgroup 134 are located along the first stage 128 at the first partial joint 158 ​​of the group. That is, at least half of the total number of first partial joints in the group of first partial joints 158 includes a first-stage eddy current generator in the first-stage eddy current generator subgroup 134 located thereon. In a non-limiting example, a corresponding first-stage eddy current generator in the first-stage eddy current generator subgroup 134 is located at each of the first partial joints in the group of first partial joints 158. Additionally or alternatively, some or all of the first-stage eddy current generator subgroup 134 may be positioned along the group's first radial segment 154, the group's first viscous segment 156, or a combination thereof.

[0082] The second stage 130 has a similar shape to the first stage 128. That is, the second stage 130 includes a plurality of segments, shown in fine lines, comprising a set of second radial segments 160 and a set of second viscous segments 162. The set of second radial segments 160 extends radially relative to the fuel nozzle axis 114. Each second viscous segment in the set of second viscous segments 162 interconnects two radial segments in the set of second radial segments 160. The set of second radial segments 160 meets the set of second viscous segments 162 at a set of second partial joints 164. Each second radial segment in the set of second radial segments 160 and each second viscous segment in the set of second viscous segments 162 is shown as linear. However, it is contemplated that the set of second radial segments 160 and the set of second viscous segments 162 may be linear, curved, or a combination thereof. For example, the set of second viscous segments 162 may each be curved, collectively forming a circular or elliptical shape.

[0083] At least a majority of the eddy current generators included in the second-stage eddy current generator subgroup 136 are located along the second stage 130 at the second partial joint 164 of the group. That is, at least half of the total number of second partial joints in the group of second partial joints 164 includes a second-stage eddy current generator in the second-stage eddy current generator subgroup 136 located thereon. In a non-limiting example, the second-stage eddy current generators in the second-stage eddy current generator subgroup 136 are located at each of the second partial joints in the group of second partial joints 164. Additionally or alternatively, some or all of the second-stage eddy current generators in the second-stage eddy current generator subgroup 136 may be positioned along the second radial segment 160 of the group, the second viscous segment 162 of the group, or a combination thereof.

[0084] When along plane 133 ( Figure 3When observed, the first radial segment 154 intersects with the second radial segment 160, the second viscous segment 162, or a combination thereof. Additionally, the second radial segment 160 intersects with the first radial segment 154, the first viscous segment 156, or a combination thereof. Since the first stage 128 is axially separated from the second stage 130 relative to the fuel nozzle axis 114, the multiple segments of the first stage 128, including the first radial segment 154 and the first viscous segment 156, do not physically contact the multiple segments of the second stage 130, including the second radial segment 160 and the second viscous segment 162. However, as used in the above context, "when along plane 133 ( Figure 3 "Intersection during observation" does not require that the two components (e.g., any one of the multiple segments of the first stage 128 and any one of the multiple segments of the second stage 130) be in physical contact with each other; rather, "intersection" as used in the above context requires that they be in physical contact along a plane perpendicular to the fuel nozzle axis 114 (e.g., Figure 3 When viewed from a plane (133), the two components appear to overlap axially.

[0085] The first stage 128 and the second stage 130 are oriented such that the first partial joint 158 ​​and the second partial joint 164 are circumferentially offset. That is, the first partial joint 158 ​​does not axially overlap with the second partial joint 164 relative to the fuel nozzle axis 114. Therefore, since the first-stage vortex generator subgroup 134 and the second-stage vortex generator subgroup 136 are located on the first partial joint 158 ​​and the second partial joint 164 respectively, the first-stage vortex generator subgroup 134 is axially and radially spaced from the second-stage vortex generator subgroup 136 relative to the fuel nozzle axis 114.

[0086] Fuel nozzle 104 defines a radial distance 165 from fuel nozzle axis 114 to fuel nozzle inner surface 115. Each vortex generator in the set of vortex generators 132 is located in a region of channel 116 extending to less than or equal to 80% of the radial distance 165, where 0% of the radial distance 165 is the fuel nozzle axis 114 and 100% of the radial distance 165 is the fuel nozzle inner surface 115. For example, each vortex generator in the set of vortex generators 132 is located in a region of channel 116 extending from greater than or equal to 10% and less than or equal to 80% of the radial distance 165.

[0087] By positioning the vortex generator 132 in a region of the channel 116 away from the inner surface 115 of the fuel nozzle, a first fuel flow F1 is generated near the fuel nozzle axis 114. Figure 3 ) and compressed air flow Fc ( Figure 3 The mixing of fuel-air mixture Fm ( ) was thus achieved. Figure 3 The uniform mixing distribution of fuel and air reduces the risk of flashback and flame retention compared to conventional fuel nozzles where fuel and air mix near the inner surface of the fuel nozzle.

[0088] Figure 5 It is suitable for use as Figure 3 A schematic cross-sectional front and rear view of an exemplary fuel nozzle 204, which is similar to fuel nozzle 104. Figure 3-4 Therefore, similar parts will be identified by similar numbers increasing to the 200 series. It should be understood that, unless otherwise stated, the description of fuel nozzle 104 applies to fuel nozzle 204.

[0089] Fuel nozzle 204 includes a fuel nozzle body 212. The fuel nozzle body 212 defines a fuel nozzle axis 214. The fuel nozzle body 212 has a channel 216 defined by an inner surface 215 of the fuel nozzle. Fuel nozzle 204 includes a support matrix 226 within the channel 216. The support matrix 226 includes multiple stages, each stage including at least a first stage 228 and a second stage 230. The first stage 228 is located axially ahead of the second stage 230 relative to the fuel nozzle axis 214. For illustrative purposes, the first stage 228 and the second stage 230 are shown with different line thicknesses. Fuel nozzle 204 includes a set of vortex generators 232. Each of the vortex generators 232 is suspended within the channel 216 by the support matrix 226.

[0090] Fuel nozzle 204 and fuel nozzle 104 ( Figure 3 The similarity lies in the fact that when along a plane perpendicular to the fuel nozzle axis 214 at an axial position relative to the fuel nozzle axis 214 of the farthest downstream vortex generator in the group of vortex generators 232 (e.g., Figure 3 When viewed from plane 133, the first level 228 and the second level 230 form an overlapping pattern. However, with Figure 4 The mesh pattern formed by the support matrix 126 is opposite to the overlapping pattern, which is formed into a rectangular grid pattern.

[0091] Level 228 comprises a set of first segments 266. In the non-limiting example shown, the set of first segments 266 comprises three first segments 266a, 266b, and 266c. However, it is contemplated that the set of first segments 266 may include any number of segments, including a single segment. Each first segment in the set of first segments 266 is shown as linear. However, it is contemplated that the set of first segments 266 may be linear, curved, or a combination thereof. First segments 266a, 266b, and 266c are shown as parallel to each other. However, it is contemplated that the set of first segments 266 may include segments or portions of segments that are parallel or non-parallel to each other, as long as they do not intersect each other.

[0092] The second level 230 includes a set of second segments 268. In the non-limiting example shown, the set of second segments 268 includes three second segments 268a, 268b, and 268c. However, it is contemplated that the set of second segments 268 may include any number of segments, including a single segment. Each second segment in the set of second segments 268 is shown as linear. However, it is contemplated that the set of second segments 268 may be linear, curved, or a combination thereof. Second segments 268a, 268b, and 268c are shown as parallel to each other. However, it is contemplated that in all examples, the set of second segments 268 does not intersect with each other. That is, no segment in the set of second segments 268 intersects with another segment in the set of second segments 268. However, it is contemplated that the set of second segments 268 may include segments or portions of segments that are parallel or non-parallel to each other, as long as they do not intersect with each other.

[0093] When along a plane perpendicular to the fuel nozzle axis 214 at an axial position relative to the fuel nozzle axis 214 of the farthest downstream vortex generator in the group of vortex generators 232 (e.g., Figure 3 When viewed from plane 133, the first segment 266 of this group intersects with the second segment 268 of the same group. That is, when viewed along a plane perpendicular to the fuel nozzle axis 214 at an axial position relative to the fuel nozzle axis 214 of the downstreammost vortex generator in this group of vortex generators 232 (e.g., plane 133), the first segment 266 intersects with the second segment 268 of the same group. Figure 3 When viewed from plane 133, segments of the first stage 228 intersect segments of the second stage 230, thus forming a support matrix 226. In some examples, the first segment 266 is perpendicular to the second segment 268. Because the first stage 228 is axially separated from the second stage 230 relative to the fuel nozzle axis 214, the first segment 266 does not physically contact the second segment 268. However, as used in the above context, "when viewed from plane 133," the first segment 228 intersects segments of the second stage 230, thus forming a support matrix 226. Figure 3 When viewed along a plane perpendicular to the fuel nozzle axis 214, “intersection” does not require that the two components (e.g., the first segment 266 and the second segment 268 of the group) be in physical contact with each other; rather, “intersection” as used in the above context requires that when viewed along a plane perpendicular to the fuel nozzle axis 214 (e.g., ... Figure 3 When viewed from a plane (133), the two components appear to overlap axially.

[0094] The subgroup of this set of vortex generators 232, positioned along the first stage 228, is referred to herein as the first-stage vortex generator subgroup 234. Another subgroup of this set of vortex generators 232, positioned along the second stage 230, is referred herein as the second-stage vortex generator subgroup 236. The first-stage vortex generator subgroup 234 is located on the first stage 228 such that when along a plane perpendicular to the fuel nozzle axis 214 at an axial position relative to the fuel nozzle axis 214 of the farthest downstream vortex generator in this set of vortex generators 232 (e.g., ... Figure 3 When viewed along plane 133, they do not intersect with the segment of the second stage 230. The second-stage vortex generator subgroup 236 is located on the second stage 230 such that when viewed along a plane perpendicular to the fuel nozzle axis 214 and intersecting with the downstreammost vortex generator in the group of vortex generators 232 (e.g., plane 133), they do not intersect with the segment of the second stage 230. Figure 3 When viewed from plane 133, they do not intersect with the segments of the first level 228.

[0095] Figure 6 It is suitable for use as Figure 3 A schematic cross-sectional front and rear view of an exemplary fuel nozzle 304, which is similar to fuel nozzle 104. Figure 3-4 ), 204 Figure 5 Therefore, similar parts will be identified by similar numbers in the 300 series. It should be understood that, unless otherwise stated, the description of fuel nozzles 104 and 204 applies to fuel nozzle 304.

[0096] Fuel nozzle 304 includes fuel nozzle body 312. Fuel nozzle body 312 defines fuel nozzle axis 314. Fuel nozzle body 312 has a channel 316 defined by fuel nozzle inner surface 315. Fuel nozzle 304 includes a support matrix 326 within the channel 316. Support matrix 326 includes multiple stages, each stage including at least a first stage 328 and a second stage 330. The first stage 328 is located axially ahead of the second stage 330 relative to the fuel nozzle axis 314. For illustrative purposes, the first stage 328 and the second stage 330 are shown with different line thicknesses. Fuel nozzle 304 includes a set of vortex generators 332. Each of the vortex generators 332 is suspended within the channel 316 by the support matrix 326.

[0097] Fuel nozzle 304 and fuel nozzle 104 ( Figure 3 The similarity lies in the fact that when along a plane perpendicular to the fuel nozzle axis 314 at an axial position relative to the fuel nozzle axis 314 of the farthest downstream vortex generator in the group of vortex generators 332 (e.g., Figure 3When viewed from plane 133, the first stage 328 and the second stage 330 form an overlapping pattern. However, the overlapping pattern is formed at the fuel nozzle axis 314, and the support matrix 326 forms a spoke wheel pattern, which is consistent with the pattern formed by the fuel nozzle axis 314. Figure 4 The mesh pattern formed by the support matrix 126 is relative.

[0098] The first stage 328 includes a set of first segments 370. In the non-limiting example shown, the set of first segments 370 includes three first segments 370a, 370b, and 370c, each of which is linear and extends through the fuel nozzle axis 314 across the entire diameter of the groove 316 defined by the inner surface 315 of the fuel nozzle. Although three first segments 370a, 370b, and 370c of the set of first segments 370 are shown, it is contemplated that the set of first segments 370 may include any number of segments, including a single segment. Additionally or alternatively, the set of first segments 370 may include segments extending radially outward from the fuel nozzle axis 314, but not extending across the entire diameter of the inner surface 315 of the fuel nozzle (e.g., extending from the fuel nozzle axis 314 across the radius of the groove 316 defined by the inner surface 315 of the fuel nozzle). Still additionally or alternatively, the set of first segments 370 may be linear, curved, or a combination thereof.

[0099] The second stage 330 includes a set of second segments 372. In the non-limiting example shown, the set of second segments 372 includes three second segments 372a, 372b, and 372c, each of which is linear and extends through the fuel nozzle axis 314 across the entire diameter of the groove 316 defined by the inner surface 315 of the fuel nozzle. Although three second segments 372a, 372b, and 372c of the set of second segments 372 are shown, it is contemplated that the set of second segments 372 may include any number of segments, including a single segment. Additionally or alternatively, the set of second segments 372 may include segments extending radially outward from the fuel nozzle axis 314, but not extending across the entire diameter of the inner surface 315 of the fuel nozzle (e.g., extending from the fuel nozzle axis 314 across the radius of the groove 316 defined by the inner surface 315 of the fuel nozzle). Still additionally or alternatively, the set of second segments 372 may be linear, curved, or a combination thereof.

[0100] When along a plane perpendicular to the fuel nozzle axis 314 at an axial position relative to the fuel nozzle axis 314 of the farthest downstream vortex generator in the group of vortex generators 332 (e.g., Figure 3When viewed from plane 133, the first segment 370 and the second segment 372 of the group intersect at the fuel nozzle axis 314. That is, when viewed along a plane perpendicular to the fuel nozzle axis 314 at an axial position relative to the fuel nozzle axis 314 of the farthest downstream vortex generator in the group of vortex generators 332 (e.g., plane 133), the first segment 370 and the second segment 372 of the group intersect at the fuel nozzle axis 314. Figure 3 When viewed from plane 133, segments of the first stage 328 and the second stage 330 intersect at least at the fuel nozzle axis 314, thus forming a support matrix 326. Since the first stage 328 is axially separated from the second stage 330 relative to the fuel nozzle axis 314, the first segment 370 of this group does not physically contact the second segment 372 of this group. However, as used in the above context, "when viewed along a plane (e.g., Figure 3 When viewed along a plane perpendicular to the fuel nozzle axis 314, “intersection” does not require that the two components (e.g., the first segment 370 and the second segment 372 of the group) be in physical contact with each other; rather, “intersection” as used in the above context requires that when viewed along a plane perpendicular to the fuel nozzle axis 314 (e.g., ... Figure 3 When viewed from a plane (133), the two components appear to overlap axially.

[0101] The subgroup of this set of vortex generators 332 positioned along the first stage 328 is referred to herein as the first-stage vortex generator subgroup 334. Another subgroup of this set of vortex generators 332 positioned along the second stage 330 is referred to herein as the second-stage vortex generator subgroup 336. The first-stage vortex generator subgroup 334 is located on the first stage 328 such that when along a plane perpendicular to the fuel nozzle axis 314 at an axial position relative to the fuel nozzle axis 314 of the farthest downstream vortex generator in this set of vortex generators 332 (e.g., ... Figure 3 When viewed from plane 133, they do not intersect with the segments of the second stage 330. The second-stage vortex generator subgroup 336 is located on the second stage 330 such that when viewed along a plane perpendicular to the fuel nozzle axis 314 at an axial position relative to the fuel nozzle axis 314 of the farthest downstream vortex generator in this group of vortex generators (e.g., plane 133), the vortex generators are positioned to the right of the fuel nozzle axis 314. Figure 3 When viewed from plane 133, they do not intersect with the segments of the first level 328.

[0102] The spoked wheel shape of the support matrix 326 increases the turbulence intensity downstream of the support matrix 326 and the set of vortex generators 332. Furthermore, the segments of the support matrix 326 create alternating zones of high and low static pressure, which helps to achieve a uniform mixture of fuel and air downstream of the support matrix 326 and the set of vortex generators 332.

[0103] Figure 7 It is suitable for use as Figure 3A schematic cross-sectional front and rear view of an exemplary fuel nozzle 404, which is similar to fuel nozzle 104. Figure 3-4 ), 204 Figure 5 ), 304 Figure 6 Therefore, similar parts will be identified by similar numbers increasing to the 400 series. It should be understood that, unless otherwise stated, the description of fuel nozzle 104 applies to fuel nozzle 404.

[0104] Fuel nozzle 404 includes a fuel nozzle body 412. The fuel nozzle body 412 defines a fuel nozzle axis 414. The fuel nozzle body 412 has a channel 416 defined by an inner surface 415 of the fuel nozzle. Fuel nozzle 404 includes a support matrix 426 within the channel 416. The support matrix 426 includes stages 473. Stages 473 are suitable for use as at least one of first stages 128, 228, 328, second stages 130, 230, 330, or combinations thereof. Fuel nozzle 404 includes a set of vortex generators 432. Each vortex generator in the set 432 is suspended within the channel 416 by the support matrix 426.

[0105] Fuel nozzle 404 and fuel nozzle 104 ( Figure 3 Similar to ), the segments of level 473 form a repeating pattern. However, unlike those formed by... Figure 4 The mesh pattern formed by the first level 128 and the second level 130 of the support matrix 126 is opposite to each other, and the repeating pattern is formed into a hexagonal grid.

[0106] about Figure 4-7 , Figure 4 The mesh pattern is 128 for the first level and 130 for the second level. Figure 5 The square grid shape, first level 228 and second level 230, Figure 6 The spoked wheel shape, first stage 328 and second stage 330, and Figure 7 Each of the hexagonal grid-shaped stages 473 contributes to achieving a uniform fuel-air mixture Fm ( Figure 3 As discussed in this article, it will be understood that each level of shape (e.g., Figure 4-7 Those shown produce the corresponding turbulence distribution. It will be further understood that a specific stage shape is selected based on the desired turbulence distribution of a given fuel nozzle.

[0107] Figure 8 Is it suitable for Figure 1 A schematic diagram of the burner section 500 used in the turbine engine 10. The burner section 500 is similar to the burner section 31. Figure 2 ), 100 ( Figure 3Therefore, similar parts will be identified by similar names, and it should be understood that, unless otherwise stated, the description of burner parts 31 and 100 applies to burner part 500.

[0108] The burner section 500 includes a burner 502 and a fuel nozzle 504. The burner 502 includes a burner wall 506. The burner wall 506 at least partially defines a combustion chamber 508. The fuel nozzle 504 includes a fuel nozzle body 512. The fuel nozzle body 512 defines a fuel nozzle axis 514. The fuel nozzle axis 514 extends through the center of the fuel nozzle body 512. The fuel nozzle body 512 has a channel 516 defined by an inner surface 515 of the fuel nozzle. The fuel nozzle 504 includes a support matrix 526 within the channel 516. The fuel nozzle 504 includes a set of vortex generators 532. Each of the vortex generators 532 is suspended within the channel 516 by the support matrix 526. The fuel nozzle 504 includes a fuel supply section 538. The fuel supply section 538 is fluidly connected to a fuel source 531 via a series of pipes, conduits, passages, or combinations thereof, shown in dashed lines. The fuel supply section 538 includes a fuel chamber 540, a set of fuel inlet orifices 542, a fuel passage 544, and a set of fuel outlet orifices 546.

[0109] Fuel nozzle 504 and fuel nozzle 104 ( Figure 3 Similar to the support matrix 526, the support matrix 526 includes a first stage 528 and a second stage 530, each of which is flat. However, the fuel nozzle 504, and in particular the support matrix 526, includes an additional third stage 574, which has an arched or conical shape that converges to a vertex 577 located at the furthest downstream portion of the third stage 574.

[0110] The first stage 528 is located axially ahead of the second stage 530 relative to the fuel nozzle axis 514. The second stage 530 is located axially ahead of the third stage 574 relative to the fuel nozzle axis 514. The first stage 528 and the second stage 530 are each flat and extend perpendicular to the fuel nozzle axis 514. That is, the axial distance 578 from the combustion chamber 508 to the first stage 528 relative to the fuel nozzle axis 514 is consistent throughout the first stage 528. Similarly, the axial distance 580 from the combustion chamber 508 to the second stage 530 relative to the fuel nozzle axis 514 is consistent throughout the second stage 530. The third stage 574 has an arched or conical shape pointing towards the combustion chamber 508. That is, the third stage 574 converges radially to a apex 577, which is defined as the farthest downstream portion of the third stage 574, such that an open region 579 is formed between the radially opposite portions of the third stage 574. The axial distance 582 from the combustion chamber 508 to the third stage 574 relative to the fuel nozzle axis 514 is the shortest at the fuel nozzle axis 514 and increases as it moves radially outward from the fuel nozzle axis 514 toward the inner surface 515 of the fuel nozzle.

[0111] The subgroup of eddy current generators 532 located along the first stage 528 is referred to herein as the first-stage eddy current generator subgroup 534. Another subgroup of eddy current generators 532 located along the second stage 530 is referred to herein as the second-stage eddy current generator subgroup 536. Yet another subgroup of eddy current generators 532 located along the third stage 574 is referred to herein as the third-stage eddy current generator subgroup 576.

[0112] Fuel passage 544 extends from fuel chamber 540 and into a corresponding portion of support matrix 526 and a corresponding portion of the set of eddy current generators 532. Specifically, fuel passage 544 extends through the third stage 574 of support matrix 526 and the third-stage eddy current generator subgroup 576. Fuel passage 544 leads to a set of fuel outlet orifices 546 disposed along at least a portion of the third-stage eddy current generator subgroup 576. In some examples, the set of fuel outlet orifices 546 is located only on the corresponding portion of the third-stage eddy current generator subgroup 576. It is contemplated that in other non-limiting examples, fuel passage 544 may additionally or alternatively extend through another stage of support matrix 526.

[0113] By including a third stage 574 having an arched or conical shape pointing towards the combustion chamber 508, in operation, the portion downstream of the support matrix 526 of the channel 516, near the inner surface 515 of the fuel nozzle, has an increased mixing length compared to the portion downstream of the support matrix 526 of the channel 516, located in the central region near the fuel nozzle axis 514. Therefore, peak mixing occurs near the support matrix 526 and the fuel nozzle axis 514 downstream of the set of vortex generators 532, compared to the peripheral region near the inner surface 515 of the fuel nozzle. The flame velocity in the portion downstream of the support matrix 526 near the fuel nozzle axis 514 is lower than the flame velocity in the portion downstream of the support matrix 526. This configuration of the fuel nozzle 504 results in a low flashback risk and low NO. x Emissions. Therefore, fuel nozzle 504 is well-suited for high-power operation of burner section 500.

[0114] Figure 9 Is it suitable for Figure 1 A schematic diagram of the combustor section 600 used in the turbine engine 10. The combustor section 600 is similar to the combustor section 31. Figure 2 ), 100 ( Figure 3 ), 500 ( Figure 8 Therefore, similar parts will be identified by similar names. It should be understood that, unless otherwise stated, the descriptions of burner parts 31, 100, and 500 apply to burner part 600.

[0115] The burner section 600 includes a burner 602 and a fuel nozzle 604. The burner 602 includes a burner wall 606. The burner wall 606 at least partially defines a combustion chamber 608. The fuel nozzle 604 includes a fuel nozzle body 612. The fuel nozzle body 612 defines a fuel nozzle axis 614. The fuel nozzle axis 614 extends through the center of the fuel nozzle body 612. The fuel nozzle body 612 has a channel 616 defined by an inner surface 615 of the fuel nozzle. The fuel nozzle 604 includes a support matrix 626 within the channel 616. The fuel nozzle 604 includes a set of vortex generators 632. Each of the vortex generators 632 is suspended within the channel 616 by the support matrix 626. The fuel nozzle 604 includes a fuel supply section 638. The fuel supply section 638 is fluidly connected to a fuel source 631 via a series of pipes, conduits, passages, or combinations thereof, shown in dashed lines. The fuel supply section 638 includes a fuel chamber 640, a set of fuel inlet orifices 642, a fuel passage 644, and a set of fuel outlet orifices 646.

[0116] Fuel nozzle 604 and fuel nozzle 104 ( Figure 3Similar to the support matrix 626, the support matrix 626 includes a first stage 628 and a second stage 630, each of which is flat. However, the fuel nozzle 604, and in particular the support matrix 626, includes a third stage 684, which has an arched or conical shape that converges to a vertex 685 located at the farthest upstream portion of the third stage 684.

[0117] The first stage 628 is located axially ahead of the second stage 630 relative to the fuel nozzle axis 614. The second stage 630 is located axially ahead of the third stage 684 relative to the fuel nozzle axis 614.

[0118] The third stage 684 has an arched or conical shape pointing away from the combustion chamber 608. That is, the third stage 684 converges radially to a apex 685, which is defined as the farthest upstream portion of the third stage 684, such that an open region 687 is formed between the radially opposite portions of the third stage 684. The axial distance 686 from the combustion chamber 608 to the third stage 684 relative to the fuel nozzle axis 614 is longest at the fuel nozzle axis 614 and decreases as it moves radially outward from the fuel nozzle axis 614 toward the inner surface 615 of the fuel nozzle.

[0119] The subgroup of eddy current generators 632 located along the first stage 628 is referred to herein as the first-stage eddy current generator subgroup 634. Another subgroup of eddy current generators 632 located along the second stage 630 is referred to herein as the second-stage eddy current generator subgroup 636. Yet another subgroup of eddy current generators 632 located along the third stage 684 is referred to herein as the third-stage eddy current generator subgroup 688.

[0120] Fuel passage 644 extends from fuel chamber 640 and into a corresponding portion of support matrix 626 and a corresponding portion of the set of eddy current generators 632. Specifically, fuel passage 644 extends through the third stage 684 of support matrix 626 and the third-stage eddy current generator subgroup 688. Fuel passage 644 leads to a set of fuel outlet orifices 646 disposed along at least a portion of the third-stage eddy current generator subgroup 688. In some examples, the set of fuel outlet orifices 646 is located only on the corresponding portion of the third-stage eddy current generator subgroup 688. It is contemplated that, in other non-limiting examples, fuel passage 644 may additionally or alternatively extend through another stage of support matrix 626.

[0121] By including a third stage 684 with an arched or conical shape pointing away from the combustion chamber 608, during operation, the portion downstream of the support matrix 626 of the channel 616, near the fuel nozzle axis 614, has an increased mixing length compared to the portion downstream of the support matrix 626 of the channel 616 in the peripheral region near the inner surface 615 of the fuel nozzle. Therefore, peak mixing occurs near the inner surface 615 of the fuel nozzle downstream of the support matrix 626 and the set of vortex generators 632, compared to the central region near the fuel nozzle axis 614 of the channel 616. This configuration of the fuel nozzle 604 results in better flame stability, which is ideal for low-power operation of the burner section 600.

[0122] The benefits of this disclosure compared to conventional fuel nozzles include a fuel nozzle with increased mixing capability. For example, a conventional fuel nozzle may include a vortex generator formed as impellers that generates a swirling airflow within the fuel nozzle. However, this disclosure includes a set of vortex generators located within the fuel nozzle wall remote from the nozzle itself. It has been found that using turbulent airflow is particularly suitable for mixing fuel within a compressed airflow to produce a homogeneous or near-homogeneous mixture of air and fuel. Therefore, as described herein, the use of a support matrix and this set of vortex generators improves the mixing efficiency of the fuel nozzle compared to conventional fuel nozzles. This improved mixing efficiency reduces the risk of flashback within the fuel nozzle.

[0123] Although a turbine engine has been described, it should be understood that the combustor described herein can be used in any engine having a combustor. It should also be understood that the application of the disclosed aspects discussed herein also applies to engines having a propeller section or a fan and supercharger section, as well as turbojet engines and turbocharged engines.

[0124] Within the scope not yet described, different features and structures of various embodiments may be combined or substituted for each other as needed. The fact that a feature is not shown in all embodiments does not mean that it cannot be shown so, but rather that it is done for the sake of brevity. Therefore, various features of different embodiments may be mixed and matched as needed to form new embodiments, regardless of whether the new embodiments are explicitly described. All combinations or permutations of the features described herein are covered by this disclosure. For example, the levels of a support matrix may have different shapes, including such as Figure 4 The depicted net shape, such as Figure 5 The depicted square or rectangular grid shape, such as Figure 6 The shape of the spoked wheel depicted, or as Figure 7 The depicted hexagonal grid. Additionally or alternatively, Figure 2 The burner section may include Figure 3 , Figure 8 and Figure 9The combination of combustion components allows for the use of the most efficient specific combustor section during different operating modes of the turbine engine. Still additionally or alternatively, Figure 8 and Figure 9 The burner section may include Figure 3 The Second Fuel Supply Department.

[0125] 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.

[0126] Further details are provided by the following topics:

[0127] A gas turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in a series flow configuration, wherein the combustion section has a fuel nozzle, the fuel nozzle including: a fuel nozzle body defining an axis and having an inner surface defining a channel fluidly connected to a combustion chamber; a support matrix located within the channel, the support matrix including a plurality of segments intersecting each other when viewed from the rear; and a set of vortex generators located on the support matrix.

[0128] According to any of the preceding clauses, in a gas turbine engine, the inner surface is positioned radially away from the axis, and the set of vortex generators are located in a region of the channel extending to less than or equal to 80% of the radial distance, wherein 100% of the radial distance is the inner surface.

[0129] According to any of the preceding clauses, in a gas turbine engine, the set of vortex generators is located in a region of the channel extending from 10% of the radial distance, wherein 100% of the radial distance is the inner surface.

[0130] According to any of the preceding clauses, in a gas turbine engine, at least a portion of a set of fuel outlet orifices is arranged along at least a portion of the set of vortex generators.

[0131] According to any of the preceding clauses, the gas turbine engine wherein the set of fuel outlet orifices includes angled fuel outlet orifices that inject fuel flow at an angle relative to the axis.

[0132] A gas turbine engine according to any of the foregoing clauses, wherein the support matrix includes a plurality of local joints, segments of the support matrix meeting each other at the plurality of local joints, wherein a set of vortex generators is located at most of the plurality of local joints.

[0133] According to any of the preceding clauses, the gas turbine engine, wherein the fuel nozzle further comprises: a fuel passage extending through a corresponding portion of the support matrix and a corresponding portion of the set of vortex generators, the fuel passage opening to the channel at the set of fuel outlet orifices; and a fuel chamber surrounding at least a portion of the channel and fluidly connected to the fuel passage.

[0134] According to any of the preceding clauses, the gas turbine engine wherein the channel is defined by the cross-sectional area of ​​a plane perpendicular to the axis and intersecting the downstream portion of the set of vortex generators, and the flow area of ​​the channel not blocked by the support matrix or the set of vortex generators is greater than or equal to 40% and less than or equal to 80% of the cross-sectional area.

[0135] According to any of the preceding clauses, in a gas turbine engine, each of the set of fuel outlet orifices includes a corresponding hydraulic diameter of 6 millimeters or less than or equal to 100 millimeters.

[0136] According to any of the preceding clauses, a gas turbine engine wherein a compressed air stream from the compressor section is supplied to the channel, the compressed air stream having a first pressure, and fuel is discharged from the set of fuel outlet orifices into the channel, the fuel having a second pressure, wherein the second pressure is greater than or equal to 1.01 times and less than or equal to 1.5 times the first pressure.

[0137] In any of the preceding clauses, at least a portion of the set of fuel outlet orifices is disposed along the fuel nozzle body.

[0138] According to any of the preceding clauses, in a gas turbine engine, the set of fuel outlet orifices is configured to discharge fuel into the channel such that the vector of the fuel is not parallel to the axis.

[0139] According to any of the foregoing clauses, the gas turbine engine, wherein the support matrix includes a first stage and a second stage, the first stage being upstream of and spaced apart from the second stage.

[0140] According to any of the preceding clauses, the gas turbine engine comprises a first-stage vortex generator subgroup positioned along the first stage and a second-stage vortex generator subgroup positioned along the second stage.

[0141] According to any of the preceding clauses, the gas turbine engine, wherein the fuel nozzle includes a set of fuel outlet orifices that discharge into the channel and are positioned only along the corresponding portions of the second-stage vortex generator sub-assembly.

[0142] According to any of the preceding clauses, in a gas turbine engine, the support matrix extends from the inner surface, and at least one level of the support matrix converges radially to a vertex, the vertex being defined as the farthest downstream portion of the at least one level, such that an open region is formed between the radially opposite portions of the at least one level upstream of the vertex.

[0143] According to any of the preceding clauses, in a gas turbine engine, the support matrix extends from the inner surface, and at least one level of the support matrix converges radially to a vertex, the vertex being defined as the farthest upstream portion of the at least one level, such that an open region is formed between the radially opposite portions of the at least one level downstream of the vertex.

[0144] The gas turbine engine according to any of the foregoing clauses, wherein the shape of the support matrix is ​​one of a mesh, a hexagonal grille, a rectangular grille, or a spoked wheel.

[0145] According to any of the preceding clauses, the gas turbine engine wherein the set of vortex generators has a triangular cross-sectional shape, an airfoil cross-sectional shape, a delta wing cross-sectional shape, a fork cross-sectional shape, a circular cross-sectional shape, or a combination thereof.

[0146] According to any of the preceding clauses, in a gas turbine engine, at least one subgroup of the set of vortex generators has the airfoil cross-sectional shape.

[0147] According to any of the preceding clauses, in a gas turbine engine, a compressed air flow from the compressor section is supplied to the channel, and the support matrix and the set of vortex generators are configured to swirl the compressed air flow such that the compressed air flow downstream of the support matrix and the set of vortex generators has a swirl number greater than or equal to 0.2 and less than or equal to 1.2.

[0148] In any of the preceding clauses of the gas turbine engine, the fuel nozzle is configured to discharge a fuel-air mixture having hydrogen-containing fuel through a fuel nozzle outlet.

[0149] A combustion section having a fuel nozzle, the fuel nozzle comprising: a fuel nozzle body defining an axis and having an inner surface defining a channel fluidly connected to a combustion chamber; a support matrix located within the channel, the support matrix comprising a plurality of segments intersecting each other when viewed from the rear; and a set of vortex generators located on the support matrix.

[0150] According to any of the preceding clauses, the combustion section, wherein the inner surface is positioned radially away from the axis, and the set of vortex generators is located in a region of the channel extending to less than or equal to 80% of the radial distance, wherein 100% of the radial distance is the inner surface.

[0151] According to any of the preceding clauses, the combustion section wherein the set of vortex generators is located in a region of the channel extending from 10% of the radial distance, wherein 100% of the radial distance is the inner surface.

[0152] According to any of the preceding clauses, the combustion section wherein at least a portion of a set of fuel outlet orifices is arranged along at least a portion of the set of vortex generators.

[0153] According to any of the preceding clauses, the combustion zone wherein the set of fuel outlet orifices includes angled fuel outlet orifices that inject fuel flow at an angle relative to the axis.

[0154] According to any of the preceding clauses, the combustion section, wherein the support matrix includes a plurality of local joints, the segments of the support matrix meeting each other at the plurality of local joints, wherein a set of vortex generators is located at most of the plurality of local joints.

[0155] According to any of the preceding clauses, the combustion section, wherein the fuel nozzle further comprises: a fuel passage extending through a corresponding portion of the support matrix and a corresponding portion of the set of vortex generators, the fuel passage opening to the channel at the set of fuel outlet orifices; and a fuel chamber surrounding at least a portion of the channel and fluidly connected to the fuel passage.

[0156] According to any of the preceding clauses, the combustion section, wherein the channel is defined by the cross-sectional area of ​​a plane perpendicular to the axis and intersecting the downstream portion of the set of vortex generators, and the flow area of ​​the channel not blocked by the support matrix or the set of vortex generators is greater than or equal to 40% and less than or equal to 80% of the cross-sectional area.

[0157] According to any of the preceding clauses, the combustion section, wherein each of the set of fuel outlet orifices comprises a corresponding hydraulic diameter greater than or equal to 6 millimeters and less than or equal to 100 millimeters.

[0158] According to any of the preceding clauses, a combustion section wherein a compressed air stream from the compressor section is supplied to the channel, the compressed air stream having a first pressure, and fuel is discharged from the set of fuel outlet orifices into the channel, the fuel having a second pressure, wherein the second pressure is greater than or equal to 1.01 times and less than or equal to 1.5 times the first pressure.

[0159] According to any of the preceding clauses, the combustion zone wherein at least a portion of the set of fuel outlet orifices is disposed along the fuel nozzle body.

[0160] According to any of the preceding clauses, the combustion section wherein the set of fuel outlet orifices is configured to discharge fuel into the channel such that the fuel vector is not parallel to the axis.

[0161] According to any of the preceding clauses, the combustion zone, wherein the support matrix includes a first stage and a second stage, the first stage being upstream of and spaced apart from the second stage.

[0162] According to any of the preceding clauses, the combustion section, wherein the set of vortex generators includes a first-stage vortex generator subgroup positioned along the first stage and a second-stage vortex generator subgroup positioned along the second stage.

[0163] According to any of the preceding clauses, the combustion section, wherein the fuel nozzle includes a set of fuel outlet orifices that discharge into the channel and are positioned only along the corresponding portions of the second-stage vortex generator sub-assembly.

[0164] According to any of the preceding clauses, the combustion section wherein the support matrix extends from the inner surface and at least one level of the support matrix converges radially to a vertex, the vertex being defined as the farthest downstream portion of the at least one level, such that an open area is formed between the radially opposite portions of the at least one level upstream of the vertex.

[0165] According to any of the preceding clauses, the combustion section wherein the support matrix extends from the inner surface and at least one level of the support matrix converges radially to a vertex, the vertex being defined as the farthest upstream portion of the at least one level, such that an open region is formed between the radially opposite portions of the at least one level downstream of the vertex.

[0166] According to any of the preceding clauses, the combustion zone is wherein the shape of the support matrix is ​​one of a mesh, a hexagonal grid, a rectangular grid, or a spoked wheel.

[0167] According to any of the preceding clauses, the combustion section wherein the set of vortex generators has a triangular cross-sectional shape, an airfoil cross-sectional shape, a delta wing cross-sectional shape, a fork cross-sectional shape, a circular cross-sectional shape, or a combination thereof.

[0168] According to any of the preceding clauses, the combustion section wherein at least one subgroup of the set of vortex generators has the airfoil cross-sectional shape.

[0169] According to any of the preceding clauses, the combustion section wherein a compressed air flow from the compressor section is supplied to the channel, and the support matrix and the set of vortex generators are configured to cause the compressed air flow to swirl, such that the compressed air flow downstream of the support matrix and the set of vortex generators has a swirl number greater than or equal to 0.2 and less than or equal to 1.2.

[0170] According to any of the preceding clauses, the combustion section wherein the fuel nozzle is configured to discharge a fuel-air mixture having hydrogen-containing fuel through a fuel nozzle outlet.

[0171] A fuel nozzle includes: a fuel nozzle body defining an axis and having an inner surface defining a channel; a support matrix located within the channel, the support matrix including a plurality of segments that intersect each other when viewed from the rear; and a set of vortex generators located on the support matrix.

[0172] According to any of the preceding clauses, the fuel nozzle, wherein the inner surface is positioned radially away from the axis, and the set of vortex generators is located in a region of the channel extending to less than or equal to 80% of the radial distance, wherein 100% of the radial distance is the inner surface.

[0173] According to any of the preceding clauses, the fuel nozzle wherein the set of vortex generators is located in a region of the channel extending from 10% of the radial distance, wherein 100% of the radial distance is the inner surface.

[0174] A fuel nozzle according to any of the foregoing clauses, wherein at least a portion of a set of fuel outlet orifices is disposed along at least a portion of the set of vortex generators.

[0175] According to any of the preceding clauses, the fuel nozzle includes an angled fuel outlet orifice that injects fuel flow at an angle relative to the axis.

[0176] The fuel nozzle according to any of the foregoing clauses, wherein the support matrix includes a plurality of local joints, segments of the support matrix meeting each other at the plurality of local joints, wherein a set of vortex generators is located at most of the plurality of local joints.

[0177] The fuel nozzle according to any of the foregoing clauses, wherein the fuel nozzle further comprises: a fuel passage extending through a corresponding portion of the support matrix and a corresponding portion of the set of vortex generators, the fuel passage opening to the channel at the set of fuel outlet orifices; and a fuel chamber surrounding at least a portion of the channel and fluidly connected to the fuel passage.

[0178] According to any of the preceding clauses, the fuel nozzle, wherein the channel is defined by the cross-sectional area of ​​a plane perpendicular to the axis and intersecting the downstream portion of the set of vortex generators, and the flow area of ​​the channel not blocked by the support matrix or the set of vortex generators is greater than or equal to 40% and less than or equal to 80% of the cross-sectional area.

[0179] According to any of the preceding clauses, each of the set of fuel outlet orifices has a corresponding hydraulic diameter of 6 millimeters or less than or equal to 100 millimeters.

[0180] According to any of the preceding clauses, a compressed air flow is supplied to the channel, the compressed air flow having a first pressure, and fuel is discharged from the set of fuel outlet orifices into the channel, the fuel having a second pressure, wherein the second pressure is greater than or equal to 1.01 times and less than or equal to 1.5 times the first pressure.

[0181] A fuel nozzle according to any of the foregoing clauses, wherein at least a portion of the set of fuel outlet orifices is disposed along the fuel nozzle body.

[0182] According to any of the preceding clauses, the fuel nozzle, wherein the set of fuel outlet orifices is configured to discharge fuel into the channel such that the vector of the fuel is not parallel to the axis.

[0183] The fuel nozzle according to any of the foregoing clauses, wherein the support matrix includes a first stage and a second stage, the first stage being upstream of and spaced apart from the second stage.

[0184] According to any of the preceding clauses, the fuel nozzle comprises a first-stage vortex generator subgroup positioned along the first stage and a second-stage vortex generator subgroup positioned along the second stage.

[0185] The fuel nozzle according to any of the foregoing clauses, wherein the fuel nozzle includes a set of fuel outlet orifices that discharge into the channel and are positioned only along the corresponding portions of the second-stage vortex generator subgroup.

[0186] According to any of the preceding clauses, the fuel nozzle wherein the support matrix extends from the inner surface and at least one level of the support matrix converges radially to a vertex, the vertex being defined as the farthest downstream portion of the at least one level, such that an open area is formed between the radially opposite portions of the at least one level upstream of the vertex.

[0187] According to any of the preceding clauses, the fuel nozzle wherein the support matrix extends from the inner surface and at least one level of the support matrix converges radially to a vertex, the vertex being defined as the farthest upstream portion of the at least one level, such that an open area is formed between the radially opposite portions of the at least one level downstream of the vertex.

[0188] The fuel nozzle according to any of the foregoing clauses, wherein the shape of the support matrix is ​​one of a mesh, a hexagonal grid, a rectangular grid, or a spoke wheel.

[0189] The fuel nozzle according to any of the foregoing clauses, wherein the set of vortex generators has a triangular cross-sectional shape, an airfoil cross-sectional shape, a delta wing cross-sectional shape, a forked cross-sectional shape, a circular cross-sectional shape, or a combination thereof.

[0190] The fuel nozzle according to any of the foregoing clauses, wherein at least one subgroup of the set of vortex generators has the airfoil cross-sectional shape.

[0191] According to any of the preceding clauses, the fuel nozzle wherein a compressed air flow from the compressor section is supplied to the channel, and the support matrix and the set of vortex generators are configured to swirl the compressed air flow such that the compressed air flow downstream of the support matrix and the set of vortex generators has a swirl number greater than or equal to 0.2 and less than or equal to 1.2.

[0192] A fuel nozzle according to any of the foregoing clauses, wherein the fuel nozzle is configured to discharge a fuel-air mixture having hydrogen-containing fuel through a fuel nozzle outlet.

Claims

1. A gas turbine engine, characterized in that, include: A compressor section, a combustion section, and a turbine section arranged in a series flow configuration, wherein the combustion section has a fuel nozzle, the fuel nozzle comprising: A fuel nozzle body that defines an axis and has an inner surface that defines a channel for fluid connection to a combustion chamber; A support matrix, located within the channel, comprising a plurality of intersecting segments when viewed from the rear; and A set of eddy current generators, the set of eddy current generators being located on the support matrix.

2. The gas turbine engine according to claim 1, characterized in that, in, The inner surface is positioned radially away from the axis, and the set of eddy current generators are located in the region of the channel extending to less than or equal to 80% of the radial distance, wherein 100% of the radial distance is the inner surface.

3. The gas turbine engine according to claim 1, characterized in that, in, At least a portion of a set of fuel outlet orifices is arranged along at least a portion of the set of eddy current generators.

4. The gas turbine engine according to claim 3, characterized in that, in, The set of fuel outlet orifices includes angled fuel outlet orifices that inject fuel flow at an angle relative to the axis.

5. The gas turbine engine according to claim 3, characterized in that, in, The support matrix includes multiple local joints, where segments of the support matrix meet each other, and wherein a set of eddy current generators are located at most of the local joints.

6. The gas turbine engine according to claim 3, characterized in that, in, The fuel nozzle further includes: A fuel passage extending through a corresponding portion of the support matrix and a corresponding portion of the set of eddy current generators, the fuel passage leading to the channel at the set of fuel outlet orifices; and A fuel chamber that surrounds at least a portion of the channel and is fluidly connected to the fuel passage.

7. The gas turbine engine according to claim 3, characterized in that, in: The channel is defined by the cross-sectional area of ​​a plane perpendicular to the axis and intersecting the downstream portion of the set of vortex generators; and The flow area of ​​the channel that is not blocked by the support matrix or the set of vortex generators is greater than or equal to 40% and less than or equal to 80% of the cross-sectional area.

8. The gas turbine engine according to claim 3, characterized in that, in, Each of the set of fuel outlet orifices has a corresponding hydraulic diameter of 6 millimeters or less than or equal to 100 millimeters.

9. The gas turbine engine according to claim 3, characterized in that, in: A stream of compressed air from the compressor section is supplied to the channel, the compressed air stream having a first pressure; and Fuel is discharged from the set of fuel outlet orifices into the channel, the fuel having a second pressure, wherein the second pressure is greater than or equal to 1.01 times the first pressure and less than or equal to 1.5 times the first pressure.

10. The gas turbine engine according to claim 3, characterized in that, in, The set of fuel outlet orifices is configured to discharge fuel into the channel such that the fuel vector is not parallel to the axis.

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