Gas turbine engine including fluid diodes

Abstract

A gas turbine engine including a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section having a fuel nozzle. The fuel nozzle includes a fuel nozzle body defining a central channel including a compressed air passage and a mixing tube, the fuel nozzle body defining a fuel nozzle centerline. The fuel nozzle includes an inner air flow path supplying a first air flow to the mixing tube, an outer air flow path, circumscribing the inner air flow path, and supplying a second air flow to the mixing tube, a set of fluid diodes including a subset of the set of fluid diodes located within the outer air flow path and generating a set of vortices within the outer air flow path, and a fuel supply including a set of fuel orifices through which a fuel flow is supplied to the mixing tube.

Description

TECHNICAL FIELD

[0001] The present subject matter relates generally to a gas turbine engine including a fuel nozzle.BACKGROUND

[0002] Turbine engines are driven by a flow of combustion gases passing through the engine to rotate a multitude of turbine blades, which, in turn, rotate a compressor to provide compressed air to the combustor for combustion. A combustor can be provided within the turbine engine and is fluidly coupled with a turbine into which the combusted gases flow.

[0003] The use of hydrocarbon fuels in the combustor of a turbine engine is known. Generally, air and fuel are fed to a combustion chamber, the air and fuel are mixed, and then the fuel is burned in the presence of the air to produce hot gas. The hot gas is then fed to a turbine where it cools and expands to produce power. By-products of the fuel combustion typically include environmentally unwanted byproducts, such as nitrogen oxide and nitrogen dioxide (collectively called NOx), carbon monoxide (CO), unburned hydrocarbon (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides, including oxides of sulfur (e.g., SO2 and SO3).BRIEF DESCRIPTION OF DRAWINGS

[0004] A full and enabling disclosure of the present disclosure, including the best mode thereof, directed to one of ordinary skill in the art is set for in the specification, which makes reference to the appended figures, in which:

[0005] FIG. 1 is a schematic representation of a turbine engine, the turbine engine including a compression section, a combustion section, and a turbine section.

[0006] FIG. 2 is a schematic view of the combustion section of FIG. 1 along line II-II in accordance with various aspects described herein.

[0007] FIG. 3 is a schematic side cross-sectional view of an exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0008] FIG. 4 is a schematic cross-sectional view as seen from sight line IV-IV of FIG. 3 from forward looking aft, further illustrating the fuel nozzle, in accordance with various aspects described herein.

[0009] FIG. 5 is a schematic top view along line V-V of FIG. 4 of an exemplary set of fluid diodes having a wave shape suitable for use as the set of fluid diodes of FIGS. 4-5.

[0010] FIG. 6 is a schematic top view of another exemplary set of fluid diodes having a linear shape suitable for use as the set of fluid diodes of FIGS. 4-5.

[0011] FIG. 7 is a schematic side cross-sectional view of another exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0012] FIG. 8 is a schematic side cross-sectional view of another exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0013] FIG. 9 is a schematic cross-sectional view from forward looking aft of another exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0014] FIG. 10 is a schematic side cross-sectional view of another exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0015] FIG. 11 is a schematic side cross-sectional view of an exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.DETAILED DESCRIPTION

[0016] Aspects of the disclosure described herein are directed to a gas turbine engine including a combustion section. The combustion section includes a fuel nozzle. The fuel nozzle includes a fuel nozzle body defining an air supply opening to a mixing tube. The fuel nozzle also includes a fuel supply opening to the mixing tube. The mixing tube opens to a combustion chamber. A set of fluid diodes is located in one or both of the air supply and the fuel supply.

[0017] During operation, a flow of compressed air is fed to the air supply, and a flow of fuel (e.g. gaseous hydrogen fuel) is fed to the fuel supply, and the flows of compressed air and fuel are mixed in the mixing tube. The set of fluid diodes generates pressure waves within one or both of the air supply and the fuel supply. The pressure waves generated by the set of fluid diodes are used to offset or otherwise dampen the effect of acoustic oscillations or acoustic pressure waves that are generated by combustion of fuel within the combustion chamber.

[0018] The fuel nozzle is especially well adapted for the use of hydrogen fuel (hereinafter, “H2 fuel”). Specifically, the fuel nozzle is especially well adapted to feed a flow of H2 fuel to the combustion chamber. The flow of H2 fuel can include a gaseous H2 fuel, a liquid H2 fuel, or a combination thereof. The flow of H2 fuel can further be mixed with other fuels or fluids such as, but not limited to, natural gas, coke oven gas, diesel, Jet-A, or the like. H2 fuels, when compared to traditional fuels (e.g., carbon fuels, petroleum fuels, etc.), have a higher burn temperature and velocity. When ignited, H2 fuels generate relatively large acoustic pressure waves in comparison with traditional fuels. The use of fluid diodes in one or both of the flows of compressed air and fuel dampens the effects of the acoustic pressure waves associated with the ignition of H2 fuels in the combustion chamber.

[0019] For purposes of illustration, the present disclosure will be described with respect to a turbine engine. It will be understood, however, that aspects of the disclosure described herein are not so limited and that a combustion section as described herein can be implemented in engines, including but not limited to turbojet, turboprop, turboshaft, and turbofan engines. Aspects of the disclosure discussed herein may have general applicability within non-aircraft engines having a combustor, such as other mobile applications and non-mobile industrial, commercial, and residential applications.

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

[0021] As used herein, the term “swirled” fluid flow or iterations thereof refers to an axisymmetric fluid flow having a circumferential rotation, or swirl, about a central axis. The amount of swirl that fluid flow has is quantified by a swirl number. The swirl number is defined as an integral of the tangential momentum to the axial momentum of the flow of fluid with respect to the central axis.

[0022] As used herein, the term “turbulent” fluid flow or iterations thereof refers to a non-laminar, chaotic and localized fluid flow. Turbulence, for example, can be in the form of a localized swirls, vortices or eddies. The turbulence of a turbulent fluid flow is quantified through use of turbulent kinetic energy and the Reynolds number of the fluid.

[0023] In relation to one another, the swirl of a fluid flow refers to a large-scale organized rotational movement of the fluid flow, while the turbulence of a fluid flow refers to a localized chaotic movement of the fluid flow. It will be appreciated that a fluid flow can include both swirl and turbulence.

[0024] The word “exemplary” is used herein to mean “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other implementations. Additionally, unless specifically identified otherwise, all embodiments described herein should be considered exemplary.

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

[0026] The terms “forward” and “aft” refer to relative positions within a turbine engine or vehicle and refer to the normal operational attitude of the turbine engine or vehicle. For example, with regard to a turbine engine, forward refers to a position closer to an engine inlet and aft refers to a position closer to an engine exhaust.

[0027] As used herein, the term “upstream” refers to a direction that is opposite the fluid flow direction, and the term “downstream” refers to a direction that is in the same direction as the fluid flow. The term “fore” or “forward” means in front of something and “aft” or “rearward” means behind something. For example, when used in terms of fluid flow, fore / forward can mean upstream and aft / rearward can mean downstream.

[0028] The term “fluid” may be a gas or a liquid. The term “fluidly coupled” means that a fluid is capable of making the connection between the areas specified.

[0029] The term “nozzle” has been used in various ways in the context of turbine engines. In the instant application, “nozzle” refers to a component having a portion for fluid coupling to a fuel supply and having at least one portion for fluidly coupling with a combustor portion, a combustor liner, a combustion chamber, or combinations thereof.

[0030] Additionally, as used herein, the terms “radial” or “radially” refer to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to a direction along a ray extending between a center longitudinal axis of the engine and an outer engine circumference.

[0031] All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, aft, etc.) are only used for identification purposes to aid the reader's understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of aspects of the disclosure described herein. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and can include intermediate structural elements between a collection of elements and relative movement between elements unless otherwise indicated. As such, connection references do not necessarily infer that two elements are directly connected and in fixed relation to one another. The exemplary drawings are for purposes of illustration only, and the dimensions, positions, order, and relative sizes reflected in the drawings attached hereto can vary.

[0032] The singular forms “a”, “an”, and “the” include plural references unless the context clearly dictates otherwise. Furthermore, as used herein, the term “set” or a “set” of elements can be any number of elements, including only one.

[0033] Uses of “and” and “or” are to be construed broadly. For example, and without limitation, uses of “and” do not necessarily require all elements or features listed, and uses of “or” are inclusive unless such a construction would be illogical.

[0034] Approximating language, as used herein throughout the specification and claims, is applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about”, “approximately”, “generally”, and “substantially”, are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or machines for constructing or manufacturing the components and systems. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or machines for constructing or manufacturing the components and systems. For example, the approximating language may refer to being within a 1, 2, 4, 5, 10, 15, or 20 percent margin in either individual values, range(s) of values and endpoints defining range(s) of values. Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other.

[0035] “Proximate” as used herein is a descriptor for locating parts described herein. Further, the term “proximate” means nearer or closer to the part recited than the following part. For example, a first aperture proximate a wall, the first aperture located upstream from a second aperture means that the first aperture is closer to the wall than the first aperture is to the second aperture.

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

[0037] Additional non-limiting examples of the memory can 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, the like, or any suitable combination of these types of memory. In one example, the program code can be stored within the memory in a machine-readable format accessible by the processor. Additionally, the memory can store various data, data types, sensed or measured data values, inputs, generated or processed data, or the like, accessible by the processor in providing instruction, control, or operation to affect a functional or operable outcome, as described herein. In another non-limiting example, a controller can be configured for comparing a first value with a second value and operating and controlling operations of additional components based on the satisfying 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 can result in actions, functions, or operations controllable by the controller.

[0038] FIG. 1 is a schematic view of a turbine engine 10. As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 can include, at least, a compressor section 12, a combustion section 14, and a turbine section 16 in a serial flow arrangement. A drive shaft 18 rotationally couples the compressor section 12 and turbine section 16, such that rotation of one affects the rotation of the other and defines a rotational axis 20 for the turbine engine 10. The turbine engine 10 includes an engine casing 29. The engine casing 29 houses at least a portion of the compressor section 12, the combustion section 14, and the turbine section 16.

[0039] The compressor section 12 can include a low-pressure (LP) compressor 22, and a high-pressure (HP) compressor 24 serially fluidly coupled to one another. The turbine section 16 can include an HP turbine 26, and an LP turbine 28 serially fluidly coupled to one another. The drive shaft 18 can operatively couple the LP compressor 22, the HP compressor 24, the HP turbine 26 and the LP turbine 28 together. Alternatively, the drive shaft 18 can include an LP drive shaft and an HP drive shaft. The LP drive shaft can couple the LP compressor 22 to the LP turbine 28, and the HP drive shaft can couple the HP compressor 24 to the HP turbine 26. An LP spool is defined as the combination of the LP compressor 22, the LP turbine 28, and the LP drive shaft such that the rotation of the LP turbine 28 can apply a driving force to the LP drive shaft, which in turn can rotate the LP compressor 22. An HP spool is defined as the combination of the HP compressor 24, the HP turbine 26, and the HP drive shaft such that the rotation of the HP turbine 26 can apply a driving force to the HP drive shaft which in turn can rotate the HP compressor 24.

[0040] The compressor section 12 includes a plurality of axially spaced stages (not illustrated). Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The compressor blades for a stage of the compressor section 12 can be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the compressor section 12 can be mounted to a shroud or casing, which can extend circumferentially about and enshroud one or more sections of the turbine engine 10. It will be appreciated that the representation of the compressor section 12 is merely schematic and that there can be any number of blades, vanes and stages. Further, it is contemplated that there can be any number of other components within the compressor section 12.

[0041] Similar to the compressor section 12, the turbine section 16 includes a plurality of axially spaced stages, with each stage having a set of circumferentially-spaced, rotating blades and a set of circumferentially-spaced, stationary vanes. The turbine blades for a stage of the turbine section 16 can be mounted to a disk which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the turbine section 16 can be mounted to the shroud or casing in a circumferential manner. It is noted that there can be any number of blades, vanes and turbine stages as the illustrated turbine section 16 is merely a schematic representation. Further, it is contemplated that there can be any number of other components within the turbine section 16.

[0042] The combustion section 14 is provided serially between the compressor section 12 and the turbine section 16. The combustion section 14 is fluidly coupled to at least a portion of the compressor section 12 and the turbine section 16 such that the combustion section 14 at least partially fluidly couples the compressor section 12 to the turbine section 16. As a non-limiting example, the combustion section 14 can be fluidly coupled to the HP compressor 24 at an upstream end of the combustion section 14 and to the HP turbine 26 at a downstream end of the combustion section 14. The combustion section 14 includes a combustor 30.

[0043] The turbine engine 10 includes a fuel source 34. The fuel source 34 is any suitable container or vessel adapted to store a volume of fuel. The fuel within the fuel source 34 can have various states. As a non-limiting example, the fuel within the fuel source 34 can be a solid, a liquid, or a gas. The fuel source 34 is provided exterior the engine casing 29. The fuel source 34 can be provided exterior the turbine engine 10. As a non-limiting example, the turbine engine 10 can be coupled to an aircraft having a wing. The wing can include the fuel source 34. The fuel source 34 is configured to feed a flow of the fuel to the combustion section 14, specifically the combustor 30. While only a single fuel source 34 is illustrated, it will be appreciated that the turbine engine 10 can include or otherwise be coupled to any number of one or more fuel sources having any number 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 illustrated) upstream of the compressor section 12, where the air is compressed defining a pressurized air. At least a portion of the pressurized air then flows into the combustion section 14 where the pressurized air is mixed with fuel from the fuel source 34 and ignited, thereby generating combustion gases. Some work is extracted from these combustion gases by the turbine section 16, which in turn drives the compressor section 12 and the fan section through the drive shaft 18. The combustion gases are ultimately discharged from the turbine engine 10 via an exhaust section (not illustrated) downstream of the turbine section 16. The pressurized air flow and the combustion gases can together define a working air flow that flows through the compressor section 12, the combustion section 14, and the turbine section 16 of the turbine engine 10.

[0045] FIG. 2 depicts a cross-sectional view of the combustion section 14 along line II-II of FIG. 1. The combustor 30 can have a can, can-annular, or annular arrangement depending on the type of engine in which the combustor 30 is located. In a non-limiting example, the combustor 30 can have a combination arrangement located with the engine casing 29. The engine casing 29 can enshroud or cover at least a portion of the combustion section 14. The combustion section 14 includes a combustion section centerline 33. The combustion section 14 can be collinear with the rotational axis 20 such that the combustion section centerline 33 extends along the rotational axis 20. Alternatively, at least a portion of the combustion section centerline 33 can be offset from the rotational axis 20. The combustion section centerline 33 defines a radial direction Rd, an axial direction Ad and a circumferential direction Cd.

[0046] The combustor 30 includes a combustor liner 40. The combustor liner 40 can include an outer liner 41 and an inner liner 42 concentric with respect to each other and arranged in an annular fashion about the engine centerline or rotational axis 20. The combustor liner 40 can have various configurations. As a non-limiting example, the combustor liner 40 can extend continuously about an entirety of a circumferential extent the combustion section centerline 33 in the circumferential direction Cd. As a non-limiting example, the combustor liner 40 can extend continuously about less than the entirety of the circumferential extent the combustion section centerline 33 in the circumferential direction Cd. As a non-limiting example, the combustor liner 40 can be segmented (e.g., formed of two or more bodies coupled to one another) in the circumferential direction Cd, the axial direction Ad, the radial direction Rd, or a combination thereof. As a non-limiting example, the combustor liner 40 can include two or more circumferential segments, with each segment of the two or more circumferential segments extending circumferentially about less than the entirety of the circumferential extent the combustion section centerline 33 in the circumferential direction Cd. The two or more circumferential segments, when coupled to each other, will collectively extend about the entirety of the circumferential extent the combustion section centerline 33 in the circumferential direction Cd.

[0047] The combustor 30 can include a dome wall 46 interconnecting opposing portions of the combustor liner 40. As a non-limiting example, the dome wall 46 can extend radially between the outer liner 41 and the inner liner 42. The dome wall 46 can be formed substantially perpendicular to the combustion section centerline 33. The dome wall 46, like the combustor liner 40, can extend continuously about an entirety of the circumferential extent of the combustion section centerline 33 in the circumferential direction Cd. Alternatively, the dome wall 46 can 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 combustor liner 40 includes a set of fuel nozzle openings 72. As illustrated, the dome wall 46 includes the set of fuel nozzle openings 72. It will be appreciated, however, that at least one fuel nozzle opening of the set of fuel nozzle openings 72 can be located along a respective portion of the combustor liner 40.

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

[0050] The combustor liner 40 and the dome wall 46 (if included) collectively form the combustion chamber 50. The combustion chamber 50 is arranged annularly about the combustion section centerline 33 in the circumferential direction Cd.

[0051] A compressed air passage 32 can be defined at least in part by both the combustor liner 40 and the engine casing 29. As a non-limiting example, the combustor liner 40 is spaced from the engine casing 29 to define the compressed air passage 32 therebetween. The compressed air passage 32 is fluidly coupled to the compressor section 12 (FIG. 1).

[0052] The combustion section 14 can include an annular arrangement of combustor portions 31 disposed around the centerline or rotational axis 20 of the turbine engine 10 in the circumferential direction Cd. It will be appreciated that one or more combustor portions of the annular arrangement of combustor portions 31 can be radially or axially offset in the radial direction Rd or axial direction Ad, respectively. The combustor portions 31 can, in some configurations, include or be configured as combustor cups, fuel cups, or nozzle cups.

[0053] Each combustor portion of the annular arrangement of combustor portions 31 includes a fuel nozzle assembly 48. For purposes of illustration, only a singular fuel nozzle assembly 48 is shown, however, it will be appreciated that each combustor portion of the annular arrangement of combustor portions 31 can include a respective fuel nozzle assembly 48. Each fuel nozzle assembly 48 includes a fuel nozzle 38 that extends through a respective one fuel nozzle opening of the set of fuel nozzle openings 72.

[0054] During operation, a fuel (F) is fed from the fuel source 34 and to the combustion chamber 50 through the annular array of combustor portions 31. Specifically, the fuel (F) is fed to the combustion chamber 50 through the fuel nozzle 38 of at least one combustor portion of the annular array of combustor portions 31. The fuel (F) includes any suitable fuel, including gaseous fuel, such as H2 fuel. As a non-limiting example, the fuel (F) can include 100% H2 (e.g., without diluents). In some examples, the fuel (F) can be a combination of fuels using other fuels with H2 fuels. For example, the fuel (F) can comprise H2 fuel and methane, such as in the form of natural gas. A controller 60 can be connected to and at least partially control operation of the fuel source 34, the fuel nozzle assembly 48, or both. The controller 60 can include a processor 62 and a memory 64.

[0055] FIG. 3 is a schematic cross-sectional side view of a combustor portion 100 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 100 is similar to the combustor portion 31 (FIG. 2); therefore, like parts will be identified with like names with it being understood that the description of the combustor portion 31 applies to the combustor portion 100 unless noted otherwise.

[0056] The combustor portion 100 includes a fuel nozzle 101 with a set of fluid diodes 140 and a combustor 103. The combustor 103 includes a combustor wall 105. The combustor wall 105 includes a fuel nozzle opening 107. The combustor wall 105 at least partially defines a combustion chamber 109. The combustor wall 105 can be various walls within the combustor 103 such as a dome wall (e.g., the dome wall 46 of FIG. 2), a combustor liner (e.g., the combustor liner 40 of FIG. 2, the inner liner 42 of FIG. 2, the outer liner 41 of FIG. 2, or a combination thereof), or a combination thereof that at least partially defines the combustion chamber 109.

[0057] The fuel nozzle 101 includes a fuel nozzle body 102. The fuel nozzle body 102 defines a fuel nozzle centerline 104. The fuel nozzle body 102 defines a central channel 112. The central channel 112 extends between a fuel nozzle air inlet 106 and a fuel nozzle outlet 108. The fuel nozzle air inlet 106 is formed as at least one of a channel, a slot, a set of holes, or a combination thereof extending through a respective portion of the fuel nozzle body 102. The fuel nozzle air inlet 106 is fluidly connected with an air source, such as compressed air from one or more of the compressed air passage 32 (FIGS. 2-3) or the compressor section 12 (FIGS. 2-3). The fuel nozzle 101 opens to the combustion chamber 109 at the fuel nozzle outlet 108.

[0058] The central channel 112 is split into at least two sections: a compressed air passage 114 and a mixing tube 116. The compressed air passage 114 extends axially with respect to the fuel nozzle centerline 104 from the fuel nozzle air inlet 106 and to the mixing tube 116. The mixing tube 116 extends axially with respect to the fuel nozzle centerline 104 from the compressed air passage 114 and to the fuel nozzle outlet 108. Further delineation between the compressed air passage 114 and the mixing tube 116 with respect to flows of fluids within the compressed air passage 114 and the mixing tube 116 will be described in further detail below.

[0059] The fuel nozzle body 102 includes an inner fuel nozzle body surface 110. The inner fuel nozzle body surface 110 defines the central channel 112. The fuel nozzle body 102 can be a tapered shape that converges towards the fuel nozzle centerline 104 along a direction parallel to the fuel nozzle centerline 104 (e.g. from the fuel nozzle air inlet 106 to the fuel nozzle outlet 108). That is, a cross-sectional area of the fuel nozzle body 102 measured in a direction perpendicular to the fuel nozzle centerline 104 decreases from an upstream portion to a downstream portion of the fuel nozzle body 102.

[0060] The fuel nozzle 101 can include a centerbody 118. The centerbody 118 extends axially through the compressed air passage 114 of the central channel 112 along the fuel nozzle centerline 104. The centerbody 118 is one of coupled to or integrally formed with a respective portion of the fuel nozzle body 102. The centerbody 118 includes an outer centerbody surface 120 that is a radially outer surface of the centerbody 118 with respect to the fuel nozzle centerline 104. Although the centerbody 118 is illustrated, it is contemplated that the fuel nozzle 101 can be formed without the centerbody 118.

[0061] The fuel nozzle 101 comprises a splitter 126. The splitter 126 is located within the compressed air passage 114. The splitter 126 is annular about the fuel nozzle centerline 104. The splitter 126 defines an inner splitter surface 128 and an outer splitter surface 130 located radially outwardly of the inner splitter surface 128 with respect to the fuel nozzle centerline 104. The splitter 126 can have a tapered shape that is parallel to the tapered shape of the fuel nozzle body 102. That is, the splitter 126 can converge towards the fuel nozzle centerline 104 along a direction that is parallel with the fuel nozzle centerline 104 (e.g. from the fuel nozzle air inlet 106 to the fuel nozzle outlet 108). Said another way, a cross-sectional area of the splitter 126 measured in a direction perpendicular to the fuel nozzle centerline 104 decreases from an upstream portion to a downstream portion of the splitter 126. Additionally or alternatively, the splitter 126 can be tapered at an angle β with respect to a reference line parallel to the fuel nozzle centerline 104. In a non-limiting example, the angle β can be in a range from greater than or equal to 10° and less than or equal to 45°.

[0062] The splitter 126 is defined as a portion of the fuel nozzle 101 that splits the compressed air passage 114 of the central channel 112 into two separate channels. Specifically, the splitter 126 separates an inner air flow path 134 formed between the fuel nozzle centerline 104 and the inner splitter surface 128, and an outer air flow path 138 formed between the outer splitter surface 130 and the inner fuel nozzle body surface 110. The inner air flow path 134 extends circumferentially about the fuel nozzle centerline 104 greater than or equal to π / 8 radians and less than or equal to 27 radians. The outer air flow path 138 extends circumferentially about the fuel nozzle centerline 104 greater than or equal to π / 8 radians and less than or equal to 2π radians.

[0063] The fuel nozzle 101 can include a flange 132. The flange 132 is located at an upstream end of the outer air flow path 138. That is, the flange 132 at least partially defines the outer air flow path 138. The flange 132 extends towards the fuel nozzle centerline 104 from the inner fuel nozzle body surface 110. The flange 132 can have a linear or non-linear shape, such as a hooked shape including in non-limiting examples, an L-shape, or a J-shape. That is, the flange 132 can be a hooked flange.

[0064] The fuel nozzle 101 can include a swirler 136. The swirler 136 can be formed as a set of vanes extending into the inner air flow path 134. That is, the swirler 136 can include a vane extending from at least one of the inner splitter surface 128, the outer centerbody surface 120, or a combination thereof. Although the swirler 136 is illustrated, it is contemplated that the fuel nozzle 101 can be formed without the swirler 136.

[0065] The fuel nozzle 101 includes a set of fluid diodes 140. The set of fluid diodes 140 includes a subset of outer air flow path diodes 141 located within the compressed air passage 114. Each diode of the subset of outer air flow path diodes 141 can be formed as a set of protrusions extending into and defining the outer air flow path 138. That is, the subset of outer air flow path diodes 141 are circumferentially spaced, axially spaced, or a combination thereof within the outer air flow path 138.

[0066] The mixing tube 116 is defined by the inner fuel nozzle body surface 110 and confronts the combustion chamber 109. The mixing tube 116 is located downstream of the compressed air passage 114. That is, the mixing tube 116 is located downstream of the inner air flow path 134 and the outer air flow path 138 and upstream of the combustion chamber 109. Additionally or alternatively, the mixing tube 116 can be located downstream of the splitter 126, the centerbody 118, or both the splitter 126 and the centerbody 118.

[0067] The combustor portion 100 is fluidly coupled to a fuel supply 150. The fuel supply 150 includes a fuel source 154 (e.g., fuel source 34 of FIGS. 2-3, or another fuel source). The fuel source is any suitable container, vessel, or space configured to hold a volume of fuel that is fed to the combustor portion 100 during operation of the combustor portion 100. As a non-limiting example, the fuel source 154 can be a container located within the combustor portion 100. As a non-limiting example, the fuel source 154 can be located exterior the combustor portion 100. As a non-limiting example, the fuel source 154 can be located exterior a turbine engine (e.g., the turbine engine 10 of FIG. 1) including the combustor portion 100. As a non-limiting example, the fuel source 154 can be located within a wing of an aircraft including the turbine engine (e.g. the turbine engine 10 of FIG. 1) having the combustor portion 100.

[0068] The fuel supply 150 includes a set of fuel inlet passages 152, and a set of fuel orifices 156. The fuel nozzle body 102 can at least partially define the set of fuel inlet passages 152. The set of fuel inlet passages 152 is formed as at least one of a channel, a slot, a set of holes, or a combination thereof extending through a respective portion of the fuel nozzle body 102. The set of fuel inlet passages 152 is fluidly coupled to the fuel source 154 by a series of tubes, conduits, passageways, or a combination thereof illustrated in phantom lines. The set of fuel inlet passages 152 opens to the central channel 112 at the set of fuel orifices 156. That is, each fuel inlet passage of the set of fuel inlet passages 152 opens to the central channel 112 at a respective fuel orifice of the set of fuel orifices 156. Although the set of fuel inlet passages 152 is depicted on a portion of the fuel nozzle body 102 that is parallel with the fuel nozzle centerline 104, the set of fuel inlet passages 152 can alternatively or additionally be disposed on the tapered portion of the fuel nozzle body 102. That is, while illustrated as downstream of a downstream terminal end 124 of the centerbody 118, it is contemplated in a different and non-limiting example that the set of fuel inlet passages 152 can axially overlap the centerbody 118. It is further contemplated that in a different and non-limiting example, the set of fuel orifices 156 is located downstream of the outer air flow path 138 and the set of fluid diodes 140.

[0069] In operation of the combustor portion 100, a flow of air (A) is provided to the central channel 112 from the air source through the fuel nozzle air inlet 106. The flow of air (A) splits into multiple air flows illustrated as a first air flow (A1) and a second air flow (A2). The first air flow (A1) flows through the inner air flow path 134 including over the swirler 136. The swirler 136 imparts swirl to the first air flow (A1). Air emitted by the inner air flow path 134 and supplied to the mixing tube 116 is therefore illustrated as a swirled air flow (AS). The second air flow (A2) flows through the outer air flow path 138 including over the subset of outer air flow path diodes 141. The flange 132 guides a portion of the air (A) into the outer air flow path 138 as the second air flow (A2). The flange 132 also acts to limit a volume and pressure of the portion of the air (A) that flows into the outer air flow path 138 as the second air flow (A2). The subset of outer air flow path diodes 141 generates vortices or eddies within the outer air flow path 138. Air emitted by the outer air flow path 138 and supplied to the mixing tube 116 is illustrated as a turbulent air flow (AT). The second air flow (A2) is in a range of greater than or equal to 5% and less than or equal to 50% of the total flow of air (A). In a non-limiting example, the second air flow (A2) is in a range of greater than or equal to 5% and less than or equal to 20% of the total flow of air (A). In another non-limiting example, the second air flow (A2) is in a range of greater than or equal to 10% and less than or equal to 15% of the total flow of air (A).

[0070] In operation of the combustor portion 100, a flow of fuel (F) is provided to the fuel supply 150. The flow of the fuel (F) is provided to the central channel 112 from the fuel source 154 through the fuel inlet passage 152. The flow of fuel (F) is emitted by the set of fuel orifices 156 and is supplied to the mixing tube 116. The flow of fuel (F) contains any suitable fuel. As a non-limiting example, the flow of fuel (F) includes a flow of H2 fuel (e.g., 100% gaseous H2 fuel, 100% liquid H2 fuel, or H2 fuel mixed with another fuel or fluid).

[0071] The fuel (F) mixes with the turbulent air flow (AT) and the swirled air flow (AS) in the mixing tube 116 to define a fuel-air mixture (M). The fuel-air mixture (M) is fed to the combustion chamber 109 through the fuel nozzle outlet 108. The fuel-air mixture (M) is ignited within the combustion chamber 109 to define a flame within the combustion chamber 109. The combustion of the fuel-air mixture (M) generates combustion pressure waves (C) within the combustion chamber 109. The combustion pressure waves (C) are defined by a frequency (CF) and an amplitude (CA). The combustion frequency (CF) is greater than or equal to 100 Hertz and less than or equal to 5000 Hertz. The combustion frequency (CF) varies greatly based on the characteristics of the fuel-air mixture (M) (e.g., a profile of the fuel-air mixture (M), an amount of fuel within the fuel-air mixture (M), etc.), and a geometry of the combustion chamber 109 where the fuel-air mixture (M) is ignited.

[0072] The set of fluid diodes 140 being present in the compressed air passage 114 results in minimal resistance to forward flow towards the combustion chamber 109 while providing high resistance to back flow away from the combustion chamber 109. Particularly, the set of fluid diodes 140 acts as a damper of the combustion pressure waves (C) by generating mixture pressure waves (W) within the fuel-air mixture (M). The mixture pressure waves (W) are defined by a frequency (WF) and an amplitude (WA). During operation, it is contemplated that at least some of the combustion pressure waves (C) can flow backwards and into the mixing tube 116 along the fuel nozzle centerline 104. The mixture pressure waves (W) travelling towards the fuel nozzle centerline 104 from the outer air flow path 138 interact with these combustion pressure waves (C) that backflow into the mixing tube 116. This interaction between the combustion pressure waves (C) and the mixture pressure waves (W) is called phase interaction. The frequency (WF) is selected to reduce the amplitude (CA) through the phase interaction. As a non-limiting example, the mixture pressure waves (W) are selected to be at a frequency (WF) or combination of frequencies that dampens the amplitude (CA) with respect to an amplitude (CA) if the set of fluid diodes 140 were not included. As used herein, the term “dampen” or iterations thereof in relation to frequencies refers to the reduction of the amplitude of a given wave. As a non-limiting example, the generation of the mixture pressure waves (W) at the frequency (WF) has been found to dampen the amplitude (CA) of the combustion pressure waves (C).

[0073] It is contemplated that the mixture pressure waves (W) within the central channel 112 cause the fuel-air mixture (M) to have a frequency (e.g., have a wave formation). Put another way, the fuel-air mixture (M) includes the mixture pressure waves (W) such that a form of the mixture pressure waves (W) is fed to the combustion chamber 109. The mixture pressure waves (W) interact with the combustion pressure waves (C) and at least partially offset the combustion pressure waves (C), thus lowering the overall amplitude (CA).

[0074] Damping strength of the set of fluid diodes 140 can be improved at higher frequencies (e.g. frequency (WF)). Further, damping strength of the set of fluid diodes 140 and pressure drop of the compressed air (A) is proportional to a flow rate of the compressed air (A). Damping efficiency of the set of fluid diodes 140 increases with relatively longer protruding lengths of the set of fluid diodes 140.

[0075] The dampening of the combustion pressure waves (C) has been found to reduce the negative impacts associated with the combustion pressure waves (C). As a non-limiting example, combustion pressure waves (C) with a higher amplitude have been found to create acoustic oscillations within the combustion chamber 109 that if left unchecked can damage sections of the combustor portion 100 or otherwise cause undesired flow characteristics or profiles of the combustion flame or combustion gases associated with the combustion of the fuel-air mixture (M). The undesired flow characteristics or profiles of the combustion flame, in turn, create a non-uniform temperature distribution or flow distribution at a combustor outlet that is ultimately fed to a downstream portion of the turbine engine (e.g., the turbine section 16 of FIG. 1). As such, leaving the combustion pressure waves (C) unchecked (e.g., undampened by the set of fluid diodes 140) at least one of damages the combustor portion 100, reduces the efficiency of the combustor portion 100, or a combination thereof.

[0076] The dampening of the combustion pressure waves (C) is especially important when the flow of fuel (F) contains a H2 fuel. H2 fuel, in comparison with conventional fuels, has a higher flame speed. The higher flame speed, in turn, generates combustion pressure waves (C) having a higher amplitude (CA) than the amplitude of the combustion pressure waves of traditional fuels. If left unchecked, the combustion pressure waves (C) associated with H2 fuels can damage the combustor portion 100 and cause undesired flame shaping at the combustor outlet.

[0077] The combustor portion 100 is especially well suited for use where the flow of fuel (F) contains H2 fuel. The combination of the swirled air flow (AS) and the turbulent air flow (AT) ensures a homogenous mixture of fuel and air of the fuel-air mixture (M), thus reducing the likelihood of pockets or concentrations of fuel to be formed within the fuel-air mixture (M). H2 fuels have a higher burn velocity and greater chance for flashback. The elimination of or reduction of the large concentrations of fuel within the fuel-air mixture (M) reduces the likelihood of flashback occurring by reducing the locations where the flame can spread.

[0078] FIG. 4 illustrates a cross-sectional forward looking aft view of the fuel nozzle 101 along line IV-IV of FIG. 3. The fuel nozzle body 102 circumscribes the splitter 126. The inner splitter surface 128 together with the centerbody 118 at least partially defines the inner air flow path 134. The inner fuel nozzle body surface 110 together with the outer splitter surface 130 at least partially defines the outer air flow path 138. The swirler 136 can be disposed within the inner air flow path 134.

[0079] The fuel nozzle 101 includes a plurality of walls 160. The plurality of walls 160 extend radially between the outer splitter surface 130 and the inner fuel nozzle body surface 110, and axially along a length of the outer air flow path 138 with respect to the fuel nozzle centerline 104. Although the plurality of walls 160 is depicted as including six walls, it is contemplated that the plurality of walls 160 can include any number of walls greater than or equal to two. The outer air flow path 138 is defined circumferentially with respect to the fuel nozzle centerline 104 between a pair of circumferentially opposing walls of the plurality of walls 160. That is, the outer air flow path 138 is defined by the inner fuel nozzle body surface 110, the outer splitter surface 130 and the plurality of walls 160. The set of fluid diodes 140, particularly the subset of outer air flow path diodes 141, extends circumferentially from the plurality of walls 160. That is, the set of fluid diodes 140 is disposed within the outer air flow path 138. For purposes of illustration, a dashed line separates the set of fluid diodes 140 from the plurality of walls 160. However, the set of fluid diodes 140 is integrally formed with the plurality of walls 160.

[0080] FIG. 5 depicts a top view of a portion of the fuel nozzle 101 along sectional line V-V of FIG. 4. The outer air flow path 138 includes an example of the set of fluid diodes 140 including the subset of outer air flow path diodes 141. Each diode of the set of fluid diodes 140 projects away from one of the plurality of walls 160. For purposes of illustration, dashed lines separate the set of fluid diodes 140 from the plurality of walls 160.

[0081] Each diode of the set of fluid diodes 140 has a wave shaped cross-sectional area. That is, each diode of the set of fluid diodes 140 has a curved or hook shaped cross-sectional area that points in a downstream direction relative to a flow of fluid flowing over the set of fluid diodes 140. For example, each outer air flow path diode of the subset of outer air flow path diodes 141 has a hook shape cross-section that points in a downstream direction relative to the second air flow (A2).

[0082] In operation, as the second air flow (A2) passes through the outer air flow path 138 and over the subset of outer air flow path diodes 141, the second air flow A2 turns, forming vortices depicted as the turbulent air flow (AT).

[0083] FIG. 6 is a schematic top view of a portion of an exemplary fuel nozzle 201 suitable for use as the fuel nozzle 101 of FIGS. 3-5. The fuel nozzle 201 is similar to the fuel nozzle 101 (FIGS. 3-5), therefore, like parts will be identified with like numerals increased to the 200 series with it being understood that the description of the fuel nozzle 101 applies to the fuel nozzle 201 unless noted otherwise.

[0084] The fuel nozzle 201 includes an outer air flow path 238. The fuel nozzle 201 includes a plurality of walls 260 and a set of fluid diodes 240. The set of fluid diodes 240 is located along a respective portion of the plurality of walls 260. The set of fluid diodes 240 extends from a respective portion of the plurality of walls 260 and into the outer air flow path 238.

[0085] The set of fluid diodes 240 is similar to the set of fluid diodes 140 (FIGS. 3-5) in that each fluid diode of the set of fluid diodes 240 projects away from one wall of the plurality of walls 260. For purposes of illustration, a dashed line separates the set of fluid diodes 240 from the plurality of walls 260. Each fluid diode of the set of fluid diodes 240, however, has a linear shape, such as a rectangular shape or a rhomboid shape, as opposed to the wave shape of the set of fluid diodes 140 of FIGS. 3-5.

[0086] Each fluid diode of the set of fluid diodes 240 protrudes at an angle 262 with respect to one of the plurality of walls 260. For example, each fluid diode of the set of fluid diodes 240 can be angled to point in a downstream direction relative to a flow of fluid flowing over the set of fluid diodes 240. For example, each outer air flow path diode of a subset of outer air flow path diodes 241 points in a downstream direction relative to the second air flow (A2). The value of the angle 262 can be in a range of greater than 0° and less than or equal to 45°. In a non-limiting example, the angle 262 is 30°. It is contemplated that a larger value of the angle 262 can create more turbulence and higher resistance to reverse flow, which can increase the damping efficiency of the set of fluid diodes 240. However, it is also contemplated that a larger value of the angle 262 increases pressure drop in a forward direction of the fluid flowing over the set of fluid diodes 240. It has been found that the angle 262 being within the aforementioned range results in a balance between creating turbulence and resistance to reverse flow with increased pressure drop in the forward direction. It is contemplated that the angle 262 of each fluid diode of the set of fluid diodes 240 can be the same, different, or a combination thereof.

[0087] In operation, as the second air flow (A2) passes through the outer air flow path 238 and over each fluid diode of the set of fluid diodes 240, the second air flow (A2) turns forming vortices depicted as the turbulent air flow (AT).

[0088] FIG. 7 is a schematic cross-sectional side view of a combustor portion 300 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 300 is similar to the combustor portion 100 (FIGS. 3-4), therefore, like parts will be identified with like numerals increased to the 300 series with it being understood that the description of the combustor portion 100 applies to the combustor portion 200 unless noted otherwise.

[0089] The combustor portion 300 includes a fuel nozzle 301 with a set of fluid diodes 340, and a combustor 303. The combustor 303 includes a combustor wall 305 including a fuel nozzle opening 307 and at least partially defining a combustion chamber 309. The fuel nozzle 301 includes a fuel nozzle body 302 defining a fuel nozzle centerline 304. The fuel nozzle body 302 includes an inner fuel nozzle body surface 310 defining a central channel 312 extending between a fuel nozzle air inlet 306 and a fuel nozzle outlet 308. The combustor portion 300 is fluidly coupled to a fuel supply 350. The fuel supply 350 includes a fuel source 354, a set of fuel inlet passages 352, and a set of fuel orifices 356.

[0090] The combustor portion 300 is similar to the combustor portion 100 (FIGS. 3-4) in that the central channel 312 is split into at least two sections: a compressed air passage 314 and a mixing tube 316. The compressed air passage 314, however, does not include a centerbody (e.g. centerbody 118 of FIGS. 3-4) and includes an upstream portion 364 and a downstream portion 366, the upstream portion 364 including an upstream splitter 326, an upstream flange 332, and an optional upstream swirler 336, and the downstream portion 366 including a downstream splitter 327, a downstream flange 333, and an optional downstream swirler 337, as opposed to the compressed air passage 114 (FIGS. 3-4) which includes a single splitter 126, a single flange 132, and a single optional swirler 136. Further, the set of fluid diodes 340 includes a subset of upstream air flow path diodes 342 and a subset of downstream air flow path diodes 343 as opposed to a single subset of outer air flow path diodes 141 (FIGS. 3-4) of the set of fluid diodes 140 (FIGS. 3-4).

[0091] The upstream splitter 326 is annular about the fuel nozzle centerline 304. The upstream splitter 326 defines an inner splitter surface 328 and an outer splitter surface 330 located radially outward of the inner splitter surface 328 with respect to the fuel nozzle centerline 304. The upstream splitter 326 is defined as a portion of the fuel nozzle 301 that splits the upstream portion 364 of the compressed air passage 314 into two separate channels. Specifically, the upstream splitter 326 separates an inner upstream air flow path 334 formed by the inner splitter surface 328, and an outer upstream air flow path 338 formed between the outer splitter surface 330 and the inner fuel nozzle body surface 310. The upstream swirler 336 can optionally be formed as a set of vanes extending into the inner upstream air flow path 334. The downstream splitter 327 is annular about the fuel nozzle centerline 304.

[0092] The downstream splitter 327 defines an inner splitter surface 329 and an outer splitter surface 331 located radially outward of the inner splitter surface 329 with respect to the fuel nozzle centerline 304. The downstream splitter 327 is defined as a portion of the fuel nozzle 301 that splits the downstream portion 366 of the compressed air passage 314 into two separate channels. Specifically, the downstream splitter 327 separates an inner downstream air flow path 335 formed by the inner splitter surface 329, and an outer downstream air flow path 339 formed between the outer splitter surface 331 and the inner fuel nozzle body surface 310. The downstream swirler 337 can be formed as a set of vanes extending into the inner downstream air flow path 335.

[0093] Each diode of the subset of upstream air flow path diodes 342 can be formed as a set of protrusions extending into and defining the outer upstream air flow path 338. Each diode of the subset of downstream air flow path diodes 343 can be formed as a set of protrusions extending into and defining the outer downstream air flow path 339. The set of fluid diodes 340 can take the shape of the set of fluid diodes 140 (FIG. 5), the set of fluid diodes 240 (FIG. 6), or a combination thereof. That is, the combustor portion 300 can include a plurality of walls extending radially between the outer splitter surface 330 and the inner fuel nozzle body surface 310, and axially along a length of the outer upstream air flow path 338 with respect to the fuel nozzle centerline 304, and a plurality of walls extending radially between the outer splitter surface 331 and the inner fuel nozzle body surface 310, and axially along a length of the outer downstream air flow path 339 with respect to the fuel nozzle centerline 304, with the set of fluid diodes 340 being formed integrally with the plurality of walls.

[0094] By increasing an amount of fluid diodes in the combustor portion 300 compared to the combustor portion 100 (FIGS. 3-4), damping strength of the combustor portion 300 is improved. Particularly, with the set of fluid diodes 340 including two subsets, namely the subset of upstream air flow path diodes 342 and the subset of downstream air flow path diodes 343, there are more fluid diodes overall and correspondingly more out of phase interactions of the mixture pressure waves (W) (FIG. 3) with combustion pressure waves (C) (FIG. 3), which ultimately further reduces the amplitude of the mixture pressure waves (W). It is contemplated that the fluid diodes dampen a broad range of frequencies of the combustion pressure waves (C) (FIG. 3) within the turbine engine 10 (FIG. 1).

[0095] FIG. 8 is a schematic cross-sectional side view of a combustor portion 400 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 400 is similar to the combustor portion 100 (FIGS. 3-4), 300 (FIG. 7), therefore, like parts will be identified with like numerals increased to the 400 series with it being understood that the description of the combustor portion 100, 300 applies to the combustor portion 400 unless noted otherwise.

[0096] The combustor portion 400 includes a fuel nozzle 401 with a set of fluid diodes 440, and a combustor 403. The combustor 403 includes a combustor wall 405 including a fuel nozzle opening 407 and at least partially defining a combustion chamber 409. The fuel nozzle 401 includes a fuel nozzle body 402 defining a fuel nozzle centerline 404. The fuel nozzle body 402 includes an inner fuel nozzle body surface 410 defining a central channel 412 extending between a fuel nozzle inlet 406 and a fuel nozzle outlet 408.

[0097] The combustor portion 400 is similar to the combustor portion 100 (FIGS. 3-4), 200 (FIG. 7) in that there is an inner air flow path 434 and an outer air flow path 438. The fuel nozzle body 402, however, includes a swirler 436 having a set of swirler vanes 468 at least partially defining the inner fuel nozzle body surface 410 and both an inner air flow path 434 and an outer air flow path 438. Further, the set of fluid diodes 440 includes a subset of swirler outer air flow path diodes 444 located within the outer air flow path 438 of the swirler 436 as opposed to separate from the swirler 136 as in the combustor portion 100 (FIGS. 3-4), 200 (FIG. 7).

[0098] The swirler 436 can be integrally formed with the fuel nozzle body 402 as illustrated, or can be separate therefrom. The set of swirler vanes 468 at least partially defines at least two air flow paths, namely the inner air flow path 434 and the outer air flow path 438. That is, the set of swirler vanes 468 splits the central channel 412 into at least two separate flow paths. The inner air flow path 434 extends along the fuel nozzle centerline 404 through the swirler 436. The outer air flow path 438 is formed within the set of swirler vanes 468.

[0099] In operation of the combustor portion 400, a flow of air (A) is provided to the central channel 412 from the air source through the fuel nozzle inlet 406. The flow of air (A) splits into multiple air flows illustrated as a first air flow (A1) and a second air flow (A2). The first air flow (A1) flows through the inner air flow path 434 along the fuel nozzle centerline 404. The second air flow (A2) flows through the outer air flow path 438 including along the set of swirler vanes 468 and over the subset of swirler outer air flow path diodes 444. The subset of swirler outer air flow path diodes 444 generates vortices or eddies within the second air flow (A2), while also simultaneously generating swirl of the second air flow (A2). Air emitted by the outer air flow path 438 is therefore both swirled and turbulent. By generating both swirl and turbulence together, acoustic energy associated with combustion pressure waves (C) (FIG. 3) is dissipated.

[0100] FIG. 9 is a schematic cross-sectional view from forward looking aft of a combustor portion 700 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 700 is similar to the combustor portion 100 (FIGS. 3-4), 300 (FIG. 7), 400 (FIG. 8); therefore, like parts will be identified with like numerals increased to the 700 series with it being understood that the description of the combustor portion 100, 300, 400 applies to the combustor portion 700 unless noted otherwise.

[0101] The combustor portion 700 includes a fuel nozzle 701 with a set of fluid diodes 740. The fuel nozzle 701 includes a fuel nozzle body 702 defining a fuel nozzle centerline 704. The fuel nozzle body 702 includes an inner fuel nozzle body surface 710 defining a central channel 712 extending along the fuel nozzle centerline 704.

[0102] The combustor portion 700 is similar to the combustor portion 100 (FIGS. 3-4) in that the fuel nozzle 701 includes a swirler 736 located within the central channel 712. The swirler 736, however, includes a set of swirler vanes 768, and the set of fluid diodes 740, however, includes a subset of swirler vane diodes 749 located on the set of swirler vanes 768.

[0103] The set of swirler vanes 768 can extend into the central channel 712 from the inner fuel nozzle body surface 710 towards the fuel nozzle centerline 704. Each swirler vane diode of the subset of swirler vane diodes 749 is formed in the shape of a tube extending along the set of swirler vanes 768 within the swirler 736. The subset of swirler vane diodes 749 can be directly attached to the set of swirler vanes 768 as exemplified by a swirler vane diode 749a. Additionally or alternatively, the subset of swirler vane diodes 749 can be attached to the set of swirler vanes 768 by a strut 770 as exemplified by a swirler vane diode 749b.

[0104] In operation of the combustor portion 700, a flow of air (A) is provided to the central channel 712 from the air source. The flow of air (A) flows through the swirler 736 including along the set of swirler vanes 768 and over the subset of swirler vane diodes 749. The subset of swirler vane diodes 749 generates vortices or eddies within flow of air (A), while also simultaneously generating swirl of the flow of air (A). Air emitted by fuel nozzle 701 is therefore both swirled and turbulent. By generating both swirl and turbulence together, acoustic energy associated with combustion pressure waves (C) (FIG. 3) is dissipated.

[0105] FIG. 10 is a schematic cross-sectional side view of a combustor portion 500 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 500 is similar to the combustor portion 100 (FIGS. 3-4), 300 (FIG. 7), 400 (FIG. 8), 700 (FIG. 9); therefore, like parts will be identified with like numerals increased to the 500 series with it being understood that the description of the combustor portion 100, 300, 400, 700 applies to the combustor portion 500 unless noted otherwise.

[0106] The combustor portion 500 includes a fuel nozzle 501 with a set of fluid diodes 540, and a combustor 503. The combustor 503 includes a combustor wall 505 including a fuel nozzle opening 507 and at least partially defining a combustion chamber 509. The fuel nozzle 501 includes a fuel nozzle body 502 defining a fuel nozzle centerline 504. The fuel nozzle body 502 includes an inner fuel nozzle body surface 510 defining a central channel 512 extending between a fuel nozzle air inlet 506 and a fuel nozzle outlet 508. The central channel 512 is split into at least two sections: a compressed air passage 514 and a mixing tube 516. The compressed air passage 514 includes a splitter 526 defining an inner splitter surface 528 and an outer splitter surface 530 located radially outward of the inner splitter surface 528 with respect to the fuel nozzle centerline 504. The splitter 526 splits the compressed air passage 514 into an inner air flow path 534 formed by the inner splitter surface 528, and an outer air flow path 538 formed between the outer splitter surface 530 and the inner fuel nozzle body surface 510. The fuel nozzle 501 can include a flange 532 located at an upstream end of the outer air flow path 538. The fuel nozzle 501 optionally includes a swirler 536 located within the inner air flow path 534.

[0107] The combustor portion 500 is similar to the combustor portion 100 (FIGS. 3-4) in that the combustor portion 500 includes a fuel supply 550 with a set of fuel inlet passages 552, a fuel source 554 and a set of fuel orifices 556. The fuel supply 550, however, also includes a fuel manifold 551 and a fuel distribution passage 553. Further, the set of fluid diodes 540 is similar to the set of fluid diodes 140 (FIGS. 3-4) in that the set of fluid diodes 540 includes a subset of outer air flow path diodes 541 located within the compressed air passage 514. The set of fluid diodes 540, however, also includes a subset of fuel inlet passage diodes 545 located within the set of fuel inlet passages 552 and a subset of fuel distribution passage diodes 546 located within the fuel distribution passage 553.

[0108] The fuel manifold 551 is defined as a distribution channel that distributes fuel received from the fuel distribution passage 553 to the set of fuel inlet passages 552. The set of fuel inlet passages 552 fluidly couples the set of fuel orifices 556 with the fuel manifold 551. The fuel manifold 551 is at least partially formed by the fuel nozzle body 502. As a non-limiting example, the fuel manifold 551 can be integrally formed with the fuel nozzle body 502. The fuel distribution passage 553 is a tube, conduit, passageway, or a combination thereof which fluidly couples the fuel manifold 551 with a fuel source 554.

[0109] The set of fluid diodes 540 can take the shape of the set of fluid diodes 140 (FIG. 5), the set of fluid diodes 240 (FIG. 6), or a combination thereof. Each diode of the subset of fuel inlet passage diodes 545 can be formed as a set of protrusions extending into and defining the set of fuel inlet passages 552. That is, the subset of fuel inlet passage diodes 545 can be integrally formed with and protrude from an inner wall of the fuel inlet passage 552. Each diode of the subset of fuel distribution passage diodes 546 can be formed as a set of protrusions extending into and defining the fuel distribution passage 553. That is, the subset of fuel distribution passage diodes 546 can be integrally formed with and protrude from an inner wall of the fuel distribution passage 553.

[0110] In operation, a flow of fuel (F) is provided to the fuel supply 550. Particularly, a flow of fuel (F) is provided to the central channel 512 from the fuel source 554. The fuel source 554 is located exterior to the fuel nozzle body 502. Thus, the flow of fuel (F) flows through the fuel distribution passage 553 to the fuel manifold 551, which distributes the flow of fuel (F) to the set of fuel inlet passages 552. The flow of the fuel (F) is emitted by the set of fuel orifices 556 and is supplied to the mixing tube 516.

[0111] Combustion pressure waves (e.g. combustion pressure waves (C) of FIG. 3) associated with the fuel (F) are generated in operation of the combustor portion 500. The subsets of the set of fluid diodes 540 located within the fuel supply 550, particularly the subset of fuel inlet passage diodes 535 located within the set of fuel inlet passages 552, and the subset of fuel distribution passage diodes 546 located within the fuel distribution passage 553, generate mixture pressure waves (e.g. mixture pressure waves (W) of FIG. 3) in the fuel-air mixture (M). The combustion pressure waves are at least partially offset by the mixture pressure waves interacting with the combustion pressure waves.

[0112] FIG. 11 is a schematic cross-sectional side view of a combustor portion 600 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 600 is similar to the combustor portion 100 (FIGS. 3-4), 300 (FIG. 7), 400 (FIGS. 8-9), 500 (FIG. 10); therefore, like parts will be identified with like numerals increased to the 600 series with it being understood that the description of the combustor portion 100, 300, 400, 500 applies to the combustor portion 600 unless noted otherwise.

[0113] The combustor portion 600 includes a fuel nozzle 601 with a set of fluid diodes 640, and a combustor 603. The combustor 603 includes a combustor wall 605 including a fuel nozzle opening 607 and at least partially defining a combustion chamber 609. The fuel nozzle 601 includes a fuel nozzle body 602 defining a fuel nozzle centerline 604. The fuel nozzle body 602 includes an inner fuel nozzle body surface 610 defining a central channel 612 extending between a fuel nozzle air inlet 606 and a fuel nozzle outlet 608. The central channel 612 is split into at least two sections: a compressed air passage 614 and a mixing tube 616. The compressed air passage 614 includes an outer air flow path 638. The fuel nozzle 601 comprises a centerbody 618. The centerbody 618 has an outer centerbody surface 620, that is a radially outer surface of the centerbody 618 with respect to the fuel nozzle centerline 604. The outer air flow path 638 is formed between the inner fuel nozzle body surface 610 and the outer centerbody surface 620. The fuel nozzle 601 is fluidly coupled to a fuel supply 650.

[0114] The combustor portion 600 is similar to the combustor portion 100 (FIGS. 3-4) in that the combustor portion 600 includes the centerbody 618, and the fuel supply 650. The combustor portion 600, particularly the fuel supply 650, however, also includes a centerbody fuel passage 657 within the centerbody 618 and opening to the central channel 612 at a set of centerbody fuel orifices 658, as opposed to the centerbody 118 of FIGS. 3-4. Further, the set of fluid diodes 640 is similar to the set of fluid diodes 140 (FIGS. 3-4) in that the set of fluid diodes 640 includes a subset of air flow path diodes 647 located within the compressed air passage 614. The set of fluid diodes 640, however, also includes a subset of centerbody fuel diodes 648 located within the centerbody fuel passage 657.

[0115] The fuel nozzle 601 optionally includes a swirler 636. The swirler 636 can be formed as a set of vanes extending into the inner air flow path 634. That is, the swirler 636 can include a vane extending from at least one of the inner fuel nozzle body surface 610 and the outer centerbody surface 620, or a combination thereof.

[0116] The fuel supply 650 includes the centerbody fuel passage 657, the set of centerbody fuel orifices 658, and a fuel source 654. The set of centerbody fuel orifices 658 is formed as at least one of a channel, a slot, a set of holes, or a combination thereof extending through a respective portion of a downstream terminal end 624 of the centerbody 618. The centerbody fuel passage 657 is fluidly coupled to the fuel source 654 by a series of tubes, conduits, passageways, or a combination thereof illustrated in phantom lines.

[0117] The set of fluid diodes 640 includes the subset of air flow path diodes 647 located within the compressed air passage 614. The subset of air flow path diodes 647 can be located upstream of the swirler 636. Each diode of the subset of air flow path diodes 647 can be formed as a set of protrusions extending into and defining the outer air flow path 638. The subset of air flow path diodes 647 can take the shape of the set of fluid diodes 140 (FIG. 5), the set of fluid diodes 240 (FIG. 6), or a combination thereof. That is, the combustor portion 600 can include a plurality of walls extending radially with respect to the fuel nozzle centerline 604 between the inner fuel nozzle body surface 610 and the outer centerbody surface 620, with the subset of air flow path diodes 647 being formed integrally with the plurality of walls.

[0118] The set of fluid diodes 640 includes the subset of centerbody fuel diodes 648 located within the centerbody 618. Each diode of the subset of centerbody fuel diodes 648 can be formed as a set of protrusions extending into and defining the centerbody fuel passage 657. The subset of centerbody fuel diodes 648 can take the shape of the set of fluid diodes 140 (FIG. 5), the set of fluid diodes 240 (FIG. 6), or a combination thereof. That is, the combustor portion 600 can include a plurality of walls extending radially with respect to the fuel nozzle centerline 604 between the fuel nozzle centerline 604 and an inner centerbody surface 622, with the subset of centerbody fuel diodes 648 being formed integrally with the plurality of walls.

[0119] In operation, a flow of fuel (F) is provided to the fuel supply 650. Particularly, a flow of fuel (F) is provided to the centerbody fuel passage 657 from the fuel source 654. The fuel source 654 is located exterior to the fuel nozzle body 602. The flow of the fuel (F) is emitted by the set of centerbody fuel orifices 658 and is supplied to the mixing tube 616. By supplying the fuel (F) from the centerbody fuel passage 657, which includes the subset of centerbody fuel diodes 648, the impact of flow oscillations and flame oscillations associated with variations in a flow rate of the fuel (F) are minimized. Also, flame or hot gases from the combustion chamber 609 are prevented from creeping into a flow path of the fuel (F).

[0120] In operation, a flow of air (A) is supplied to the compressed air passage 614. By staggering the swirler 636 and the subset of air flow path diodes 647, particularly such that the subset of air flow path diodes 647 is upstream of the swirler 636 (e.g. a distance from the subset of air flow path diodes 647 to the fuel nozzle air inlet 606 is shorter than a distance from the swirler 636 to the fuel nozzle air inlet 606), can prevent any combustion waves (e.g. the combustion pressure waves (C) of FIG. 3) from affecting an upstream compressor (e.g. the compressor section 12 of FIG. 1).

[0121] To the extent not already described, the different features and structures of the various embodiments can be used in combination, or in substitution with each other as desired. All combinations or permutations of features described herein are covered by this disclosure. It should be understood that none of the configurations described herein are mutually exclusive. Each combustor portion 31 (FIG. 2) can be identical or non-identical to each other. As a non-limiting example, a combustor portion can output a mixture pressure wave (W) at a frequency (WF) having a first value, while a combustor portion can output a mixture pressure wave (W) at a frequency (WF) having a second value, different from the first value. In another example, a set of fluid diodes of a single combustor portion can include multiple subsets of the set of fluid diodes. It is contemplated, for example, that a compressed air passage can include one or multiple subsets of fluid diodes, and a fuel supply can simultaneously include one or more multiple subsets of fluid diodes.

[0122] The disclosed combustor portions and fuel nozzles each including a set of fluid diodes can reduce the negative impacts associated with combustion pressure waves. By providing a set of fluid diodes located within a compressed air passage or a fuel supply, desired flow characteristics or profiles of a combustion flame or combustion gases can be achieved. The set of fluid diodes thereby prevents damage to the combustor portion related to acoustic oscillations associated with combustion.

[0123] Benefits of the disclosed combustor portions are especially applicable to combustor portions fed with H2 fuel. The higher flame speed of H2 fuel compared to conventional fuel results in combustion pressure waves having a higher amplitude than that of combustion pressure waves of traditional fuels. A pressure wave generated by the set of fluid diodes is used to offset or otherwise dampen the effect of acoustic oscillations or acoustic pressure waves that are generated by combustion of fuel within the combustion chamber.

[0124] This written description uses examples to describe aspects of the disclosure described herein, including the best mode, and also to enable any person skilled in the art to practice aspects of the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of aspects of the disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

[0125] Further aspects are provided by the subject matter of the following clauses:

[0126] A gas turbine engine comprising: a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section having a fuel nozzle comprising: a fuel nozzle body defining a central channel, the central channel comprising a compressed air passage and a mixing tube, the fuel nozzle body defining a fuel nozzle centerline; an inner air flow path supplying a first air flow to the mixing tube; an outer air flow path, circumscribing the inner air flow path, and supplying a second air flow to the mixing tube; a set of fluid diodes including a subset of the set of fluid diodes located within the outer air flow path and generating a set of vortices within the outer air flow path; and a fuel supply including a set of fuel orifices through which a fuel flow is supplied to the mixing tube.

[0127] The gas turbine engine of any preceding clause, wherein the outer air flow path is at least partially defined by a flange extending from the fuel nozzle body and into the compressed air passage.

[0128] The gas turbine engine of any preceding clause, wherein the flange is a hooked flange.

[0129] The gas turbine engine of any preceding clause, wherein the fuel nozzle further comprises a pair of circumferentially opposing walls defining the outer air flow path circumferentially therebetween.

[0130] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the outer air flow path extends from the pair of circumferentially opposing walls and into the outer air flow path.

[0131] The gas turbine engine of any preceding clause, wherein the outer air flow path extends circumferentially about the fuel nozzle centerline greater than or equal to π / 8 radians and less than or equal to 2π radians.

[0132] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located in the outer air flow path includes a plurality of fluid diodes circumferentially spaced within the outer air flow path.

[0133] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located in the outer air flow path includes a plurality of fluid diodes axially spaced within the outer air flow path.

[0134] The gas turbine engine of any preceding clause, wherein the fuel nozzle further includes an annular splitter that separates the inner air flow path and the outer air flow path, the annular splitter being tapered at an angle β with respect to a reference line parallel to the fuel nozzle centerline, the angle β being in a range from greater than or equal to 10° and less than or equal to 45°.

[0135] The gas turbine engine of any preceding clause, wherein the annular splitter is an upstream annual splitter, the inner air flow path is an inner upstream air flow path, the outer air flow path is an outer downstream air flow path, and wherein the fuel nozzle further includes a downstream annular splitter separating an inner downstream air flow path and an outer downstream air flow path.

[0136] The gas turbine engine of any preceding clause, wherein the fuel nozzle further includes a centerbody extending axially along the fuel nozzle centerline through the compressed air passage.

[0137] The gas turbine engine of any preceding clause, wherein the set of fuel orifices is located downstream of a downstream terminal end of the centerbody.

[0138] The gas turbine engine of any preceding clause, wherein the set of fuel orifices is located downstream of the outer air flow path and the subset of the set of fluid diodes located within the outer air flow path.

[0139] The gas turbine engine of any preceding clause, wherein the set of fluid diodes generates a pressure wave having a frequency of greater than or equal to 100 Hertz and less than or equal to 5000 Hertz.

[0140] The gas turbine engine of any preceding clause, wherein a fluid diode of the set of fluid diodes has a wave or linear shape.

[0141] The gas turbine engine of any preceding clause, wherein a fluid diode of the set of fluid diodes has a linear shape protruding from a wall at an angle in a range from greater than or equal to 0° and less than or equal to 45°.

[0142] The gas turbine engine of any preceding clause, wherein the fuel nozzle further comprises a swirler located within the inner air flow path and imparting a swirl to the first air flow.

[0143] The gas turbine engine of any preceding clause, wherein: the swirler is an upstream swirler; the subset of the set of fluid diodes located within the outer air flow path is a subset of upstream air flow path diodes; the fuel nozzle further includes a downstream swirler located downstream of the upstream swirler; and the set of fluid diodes further includes a subset of downstream air flow path diodes located downstream of the subset of upstream air flow path diodes.

[0144] The gas turbine engine of any preceding clause, wherein the outer air flow path is at least partially defined by an upstream flange extending from the fuel nozzle body and into the compressed air passage and a downstream flange extending from the fuel nozzle body and into the compressed air passage.

[0145] The gas turbine engine of any preceding clause, wherein the upstream flange is a hooked flange and the downstream flange is a hooked flange.

[0146] The gas turbine engine of any preceding clause, wherein the fuel nozzle further comprises a swirler located within the compressed air passage, and the set of fluid diodes includes a subset of the set of fluid diodes located within the swirler.

[0147] The gas turbine engine of any preceding clause, wherein the swirler is integrally formed with the fuel nozzle body.

[0148] The gas turbine engine of any preceding clause, wherein the swirler defines the inner air flow path and the outer air flow path.

[0149] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the swirler is located within the outer air flow path defined by the swirler.

[0150] The gas turbine engine of any preceding clause, wherein the swirler includes a set of vanes, and the subset of the set of fluid diodes located within the swirler extends from a vane of the set of vanes.

[0151] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the swirler is formed in the shape of a tube extending along a vane of the set of vanes.

[0152] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the swirler is directly attached to a vane of the set of vanes.

[0153] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the swirler is attached to a vane of the set of vanes by a strut.

[0154] The gas turbine engine of any preceding clause, wherein the set of fluid diodes further includes a subset of the set of fluid diodes located within the fuel supply and generating vortices within the fuel flow.

[0155] The gas turbine engine of any preceding clause, wherein the set of fuel orifices includes a plurality of fuel orifices, the fuel supply includes a fuel distribution passage fluidly coupled to two or more fuel orifices of the set of fuel orifices, and the set of fluid diodes includes a subset of the set of fluid diodes located within the fuel distribution passage.

[0156] The gas turbine engine of any preceding clause, wherein the fuel distribution passage is located exterior to the fuel nozzle body.

[0157] The gas turbine engine of any preceding clause, wherein the fuel supply includes a set of fuel inlet passages that each open to the mixing tube at a respective fuel orifice of the set of fuel orifices, and the set of fluid diodes includes a subset of the set of fluid diodes at least partially located in the fuel inlet passage.

[0158] The gas turbine engine of any preceding clause, wherein the fuel nozzle further comprises a centerbody coupled to the fuel nozzle body and extending axially with respect to the fuel nozzle centerline through the compressed air passage, wherein at least a portion of the fuel supply is formed within the centerbody, and wherein the set of fluid diodes includes a subset of the set of fluid diodes located within the portion of the fuel supply formed within the centerbody.

[0159] The gas turbine engine of any preceding clause, wherein the fuel supply feeds a flow of hydrogen-containing fuel to the mixing tube.

Examples

Embodiment Construction

[0016]Aspects of the disclosure described herein are directed to a gas turbine engine including a combustion section. The combustion section includes a fuel nozzle. The fuel nozzle includes a fuel nozzle body defining an air supply opening to a mixing tube. The fuel nozzle also includes a fuel supply opening to the mixing tube. The mixing tube opens to a combustion chamber. A set of fluid diodes is located in one or both of the air supply and the fuel supply.

[0017]During operation, a flow of compressed air is fed to the air supply, and a flow of fuel (e.g. gaseous hydrogen fuel) is fed to the fuel supply, and the flows of compressed air and fuel are mixed in the mixing tube. The set of fluid diodes generates pressure waves within one or both of the air supply and the fuel supply. The pressure waves generated by the set of fluid diodes are used to offset or otherwise dampen the effect of acoustic oscillations or acoustic pressure waves that are generated by combustion of fuel within ...

TECHNICAL FIELD

[0001] The present subject matter relates generally to a gas turbine engine including a fuel nozzle.BACKGROUND

[0002] Turbine engines are driven by a flow of combustion gases passing through the engine to rotate a multitude of turbine blades, which, in turn, rotate a compressor to provide compressed air to the combustor for combustion. A combustor can be provided within the turbine engine and is fluidly coupled with a turbine into which the combusted gases flow.

[0003] The use of hydrocarbon fuels in the combustor of a turbine engine is known. Generally, air and fuel are fed to a combustion chamber, the air and fuel are mixed, and then the fuel is burned in the presence of the air to produce hot gas. The hot gas is then fed to a turbine where it cools and expands to produce power. By-products of the fuel combustion typically include environmentally unwanted byproducts, such as nitrogen oxide and nitrogen dioxide (collectively called NOx), carbon monoxide (CO), unburned hydrocarbon (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides, including oxides of sulfur (e.g., SO2 and SO3).BRIEF DESCRIPTION OF DRAWINGS

[0004] A full and enabling disclosure of the present disclosure, including the best mode thereof, directed to one of ordinary skill in the art is set for in the specification, which makes reference to the appended figures, in which:

[0005] FIG. 1 is a schematic representation of a turbine engine, the turbine engine including a compression section, a combustion section, and a turbine section.

[0006] FIG. 2 is a schematic view of the combustion section of FIG. 1 along line II-II in accordance with various aspects described herein.

[0007] FIG. 3 is a schematic side cross-sectional view of an exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0008] FIG. 4 is a schematic cross-sectional view as seen from sight line IV-IV of FIG. 3 from forward looking aft, further illustrating the fuel nozzle, in accordance with various aspects described herein.

[0009] FIG. 5 is a schematic top view along line V-V of FIG. 4 of an exemplary set of fluid diodes having a wave shape suitable for use as the set of fluid diodes of FIGS. 4-5.

[0010] FIG. 6 is a schematic top view of another exemplary set of fluid diodes having a linear shape suitable for use as the set of fluid diodes of FIGS. 4-5.

[0011] FIG. 7 is a schematic side cross-sectional view of another exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0012] FIG. 8 is a schematic side cross-sectional view of another exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0013] FIG. 9 is a schematic cross-sectional view from forward looking aft of another exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0014] FIG. 10 is a schematic side cross-sectional view of another exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.

[0015] FIG. 11 is a schematic side cross-sectional view of an exemplary combustor portion including a fuel nozzle suitable for use as the combustor portion and the fuel nozzle of FIG. 2, in accordance with various aspects described herein.DETAILED DESCRIPTION

[0016] Aspects of the disclosure described herein are directed to a gas turbine engine including a combustion section. The combustion section includes a fuel nozzle. The fuel nozzle includes a fuel nozzle body defining an air supply opening to a mixing tube. The fuel nozzle also includes a fuel supply opening to the mixing tube. The mixing tube opens to a combustion chamber. A set of fluid diodes is located in one or both of the air supply and the fuel supply.

[0017] During operation, a flow of compressed air is fed to the air supply, and a flow of fuel (e.g. gaseous hydrogen fuel) is fed to the fuel supply, and the flows of compressed air and fuel are mixed in the mixing tube. The set of fluid diodes generates pressure waves within one or both of the air supply and the fuel supply. The pressure waves generated by the set of fluid diodes are used to offset or otherwise dampen the effect of acoustic oscillations or acoustic pressure waves that are generated by combustion of fuel within the combustion chamber.

[0018] The fuel nozzle is especially well adapted for the use of hydrogen fuel (hereinafter, “H2 fuel”). Specifically, the fuel nozzle is especially well adapted to feed a flow of H2 fuel to the combustion chamber. The flow of H2 fuel can include a gaseous H2 fuel, a liquid H2 fuel, or a combination thereof. The flow of H2 fuel can further be mixed with other fuels or fluids such as, but not limited to, natural gas, coke oven gas, diesel, Jet-A, or the like. H2 fuels, when compared to traditional fuels (e.g., carbon fuels, petroleum fuels, etc.), have a higher burn temperature and velocity. When ignited, H2 fuels generate relatively large acoustic pressure waves in comparison with traditional fuels. The use of fluid diodes in one or both of the flows of compressed air and fuel dampens the effects of the acoustic pressure waves associated with the ignition of H2 fuels in the combustion chamber.

[0019] For purposes of illustration, the present disclosure will be described with respect to a turbine engine. It will be understood, however, that aspects of the disclosure described herein are not so limited and that a combustion section as described herein can be implemented in engines, including but not limited to turbojet, turboprop, turboshaft, and turbofan engines. Aspects of the disclosure discussed herein may have general applicability within non-aircraft engines having a combustor, such as other mobile applications and non-mobile industrial, commercial, and residential applications.

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

[0021] As used herein, the term “swirled” fluid flow or iterations thereof refers to an axisymmetric fluid flow having a circumferential rotation, or swirl, about a central axis. The amount of swirl that fluid flow has is quantified by a swirl number. The swirl number is defined as an integral of the tangential momentum to the axial momentum of the flow of fluid with respect to the central axis.

[0022] As used herein, the term “turbulent” fluid flow or iterations thereof refers to a non-laminar, chaotic and localized fluid flow. Turbulence, for example, can be in the form of a localized swirls, vortices or eddies. The turbulence of a turbulent fluid flow is quantified through use of turbulent kinetic energy and the Reynolds number of the fluid.

[0023] In relation to one another, the swirl of a fluid flow refers to a large-scale organized rotational movement of the fluid flow, while the turbulence of a fluid flow refers to a localized chaotic movement of the fluid flow. It will be appreciated that a fluid flow can include both swirl and turbulence.

[0024] The word “exemplary” is used herein to mean “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other implementations. Additionally, unless specifically identified otherwise, all embodiments described herein should be considered exemplary.

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

[0026] The terms “forward” and “aft” refer to relative positions within a turbine engine or vehicle and refer to the normal operational attitude of the turbine engine or vehicle. For example, with regard to a turbine engine, forward refers to a position closer to an engine inlet and aft refers to a position closer to an engine exhaust.

[0027] As used herein, the term “upstream” refers to a direction that is opposite the fluid flow direction, and the term “downstream” refers to a direction that is in the same direction as the fluid flow. The term “fore” or “forward” means in front of something and “aft” or “rearward” means behind something. For example, when used in terms of fluid flow, fore / forward can mean upstream and aft / rearward can mean downstream.

[0028] The term “fluid” may be a gas or a liquid. The term “fluidly coupled” means that a fluid is capable of making the connection between the areas specified.

[0029] The term “nozzle” has been used in various ways in the context of turbine engines. In the instant application, “nozzle” refers to a component having a portion for fluid coupling to a fuel supply and having at least one portion for fluidly coupling with a combustor portion, a combustor liner, a combustion chamber, or combinations thereof.

[0030] Additionally, as used herein, the terms “radial” or “radially” refer to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to a direction along a ray extending between a center longitudinal axis of the engine and an outer engine circumference.

[0031] All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, aft, etc.) are only used for identification purposes to aid the reader's understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of aspects of the disclosure described herein. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and can include intermediate structural elements between a collection of elements and relative movement between elements unless otherwise indicated. As such, connection references do not necessarily infer that two elements are directly connected and in fixed relation to one another. The exemplary drawings are for purposes of illustration only, and the dimensions, positions, order, and relative sizes reflected in the drawings attached hereto can vary.

[0032] The singular forms “a”, “an”, and “the” include plural references unless the context clearly dictates otherwise. Furthermore, as used herein, the term “set” or a “set” of elements can be any number of elements, including only one.

[0033] Uses of “and” and “or” are to be construed broadly. For example, and without limitation, uses of “and” do not necessarily require all elements or features listed, and uses of “or” are inclusive unless such a construction would be illogical.

[0034] Approximating language, as used herein throughout the specification and claims, is applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about”, “approximately”, “generally”, and “substantially”, are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or machines for constructing or manufacturing the components and systems. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or machines for constructing or manufacturing the components and systems. For example, the approximating language may refer to being within a 1, 2, 4, 5, 10, 15, or 20 percent margin in either individual values, range(s) of values and endpoints defining range(s) of values. Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other.

[0035] “Proximate” as used herein is a descriptor for locating parts described herein. Further, the term “proximate” means nearer or closer to the part recited than the following part. For example, a first aperture proximate a wall, the first aperture located upstream from a second aperture means that the first aperture is closer to the wall than the first aperture is to the second aperture.

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

[0037] Additional non-limiting examples of the memory can 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, the like, or any suitable combination of these types of memory. In one example, the program code can be stored within the memory in a machine-readable format accessible by the processor. Additionally, the memory can store various data, data types, sensed or measured data values, inputs, generated or processed data, or the like, accessible by the processor in providing instruction, control, or operation to affect a functional or operable outcome, as described herein. In another non-limiting example, a controller can be configured for comparing a first value with a second value and operating and controlling operations of additional components based on the satisfying 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 can result in actions, functions, or operations controllable by the controller.

[0038] FIG. 1 is a schematic view of a turbine engine 10. As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 can include, at least, a compressor section 12, a combustion section 14, and a turbine section 16 in a serial flow arrangement. A drive shaft 18 rotationally couples the compressor section 12 and turbine section 16, such that rotation of one affects the rotation of the other and defines a rotational axis 20 for the turbine engine 10. The turbine engine 10 includes an engine casing 29. The engine casing 29 houses at least a portion of the compressor section 12, the combustion section 14, and the turbine section 16.

[0039] The compressor section 12 can include a low-pressure (LP) compressor 22, and a high-pressure (HP) compressor 24 serially fluidly coupled to one another. The turbine section 16 can include an HP turbine 26, and an LP turbine 28 serially fluidly coupled to one another. The drive shaft 18 can operatively couple the LP compressor 22, the HP compressor 24, the HP turbine 26 and the LP turbine 28 together. Alternatively, the drive shaft 18 can include an LP drive shaft and an HP drive shaft. The LP drive shaft can couple the LP compressor 22 to the LP turbine 28, and the HP drive shaft can couple the HP compressor 24 to the HP turbine 26. An LP spool is defined as the combination of the LP compressor 22, the LP turbine 28, and the LP drive shaft such that the rotation of the LP turbine 28 can apply a driving force to the LP drive shaft, which in turn can rotate the LP compressor 22. An HP spool is defined as the combination of the HP compressor 24, the HP turbine 26, and the HP drive shaft such that the rotation of the HP turbine 26 can apply a driving force to the HP drive shaft which in turn can rotate the HP compressor 24.

[0040] The compressor section 12 includes a plurality of axially spaced stages (not illustrated). Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The compressor blades for a stage of the compressor section 12 can be mounted to a disk, which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the compressor section 12 can be mounted to a shroud or casing, which can extend circumferentially about and enshroud one or more sections of the turbine engine 10. It will be appreciated that the representation of the compressor section 12 is merely schematic and that there can be any number of blades, vanes and stages. Further, it is contemplated that there can be any number of other components within the compressor section 12.

[0041] Similar to the compressor section 12, the turbine section 16 includes a plurality of axially spaced stages, with each stage having a set of circumferentially-spaced, rotating blades and a set of circumferentially-spaced, stationary vanes. The turbine blades for a stage of the turbine section 16 can be mounted to a disk which is mounted to the drive shaft 18. Each set of blades for a given stage can have its own disk. The vanes of the turbine section 16 can be mounted to the shroud or casing in a circumferential manner. It is noted that there can be any number of blades, vanes and turbine stages as the illustrated turbine section 16 is merely a schematic representation. Further, it is contemplated that there can be any number of other components within the turbine section 16.

[0042] The combustion section 14 is provided serially between the compressor section 12 and the turbine section 16. The combustion section 14 is fluidly coupled to at least a portion of the compressor section 12 and the turbine section 16 such that the combustion section 14 at least partially fluidly couples the compressor section 12 to the turbine section 16. As a non-limiting example, the combustion section 14 can be fluidly coupled to the HP compressor 24 at an upstream end of the combustion section 14 and to the HP turbine 26 at a downstream end of the combustion section 14. The combustion section 14 includes a combustor 30.

[0043] The turbine engine 10 includes a fuel source 34. The fuel source 34 is any suitable container or vessel adapted to store a volume of fuel. The fuel within the fuel source 34 can have various states. As a non-limiting example, the fuel within the fuel source 34 can be a solid, a liquid, or a gas. The fuel source 34 is provided exterior the engine casing 29. The fuel source 34 can be provided exterior the turbine engine 10. As a non-limiting example, the turbine engine 10 can be coupled to an aircraft having a wing. The wing can include the fuel source 34. The fuel source 34 is configured to feed a flow of the fuel to the combustion section 14, specifically the combustor 30. While only a single fuel source 34 is illustrated, it will be appreciated that the turbine engine 10 can include or otherwise be coupled to any number of one or more fuel sources having any number 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 illustrated) upstream of the compressor section 12, where the air is compressed defining a pressurized air. At least a portion of the pressurized air then flows into the combustion section 14 where the pressurized air is mixed with fuel from the fuel source 34 and ignited, thereby generating combustion gases. Some work is extracted from these combustion gases by the turbine section 16, which in turn drives the compressor section 12 and the fan section through the drive shaft 18. The combustion gases are ultimately discharged from the turbine engine 10 via an exhaust section (not illustrated) downstream of the turbine section 16. The pressurized air flow and the combustion gases can together define a working air flow that flows through the compressor section 12, the combustion section 14, and the turbine section 16 of the turbine engine 10.

[0045] FIG. 2 depicts a cross-sectional view of the combustion section 14 along line II-II of FIG. 1. The combustor 30 can have a can, can-annular, or annular arrangement depending on the type of engine in which the combustor 30 is located. In a non-limiting example, the combustor 30 can have a combination arrangement located with the engine casing 29. The engine casing 29 can enshroud or cover at least a portion of the combustion section 14. The combustion section 14 includes a combustion section centerline 33. The combustion section 14 can be collinear with the rotational axis 20 such that the combustion section centerline 33 extends along the rotational axis 20. Alternatively, at least a portion of the combustion section centerline 33 can be offset from the rotational axis 20. The combustion section centerline 33 defines a radial direction Rd, an axial direction Ad and a circumferential direction Cd.

[0046] The combustor 30 includes a combustor liner 40. The combustor liner 40 can include an outer liner 41 and an inner liner 42 concentric with respect to each other and arranged in an annular fashion about the engine centerline or rotational axis 20. The combustor liner 40 can have various configurations. As a non-limiting example, the combustor liner 40 can extend continuously about an entirety of a circumferential extent the combustion section centerline 33 in the circumferential direction Cd. As a non-limiting example, the combustor liner 40 can extend continuously about less than the entirety of the circumferential extent the combustion section centerline 33 in the circumferential direction Cd. As a non-limiting example, the combustor liner 40 can be segmented (e.g., formed of two or more bodies coupled to one another) in the circumferential direction Cd, the axial direction Ad, the radial direction Rd, or a combination thereof. As a non-limiting example, the combustor liner 40 can include two or more circumferential segments, with each segment of the two or more circumferential segments extending circumferentially about less than the entirety of the circumferential extent the combustion section centerline 33 in the circumferential direction Cd. The two or more circumferential segments, when coupled to each other, will collectively extend about the entirety of the circumferential extent the combustion section centerline 33 in the circumferential direction Cd.

[0047] The combustor 30 can include a dome wall 46 interconnecting opposing portions of the combustor liner 40. As a non-limiting example, the dome wall 46 can extend radially between the outer liner 41 and the inner liner 42. The dome wall 46 can be formed substantially perpendicular to the combustion section centerline 33. The dome wall 46, like the combustor liner 40, can extend continuously about an entirety of the circumferential extent of the combustion section centerline 33 in the circumferential direction Cd. Alternatively, the dome wall 46 can 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 combustor liner 40 includes a set of fuel nozzle openings 72. As illustrated, the dome wall 46 includes the set of fuel nozzle openings 72. It will be appreciated, however, that at least one fuel nozzle opening of the set of fuel nozzle openings 72 can be located along a respective portion of the combustor liner 40.

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

[0050] The combustor liner 40 and the dome wall 46 (if included) collectively form the combustion chamber 50. The combustion chamber 50 is arranged annularly about the combustion section centerline 33 in the circumferential direction Cd.

[0051] A compressed air passage 32 can be defined at least in part by both the combustor liner 40 and the engine casing 29. As a non-limiting example, the combustor liner 40 is spaced from the engine casing 29 to define the compressed air passage 32 therebetween. The compressed air passage 32 is fluidly coupled to the compressor section 12 (FIG. 1).

[0052] The combustion section 14 can include an annular arrangement of combustor portions 31 disposed around the centerline or rotational axis 20 of the turbine engine 10 in the circumferential direction Cd. It will be appreciated that one or more combustor portions of the annular arrangement of combustor portions 31 can be radially or axially offset in the radial direction Rd or axial direction Ad, respectively. The combustor portions 31 can, in some configurations, include or be configured as combustor cups, fuel cups, or nozzle cups.

[0053] Each combustor portion of the annular arrangement of combustor portions 31 includes a fuel nozzle assembly 48. For purposes of illustration, only a singular fuel nozzle assembly 48 is shown, however, it will be appreciated that each combustor portion of the annular arrangement of combustor portions 31 can include a respective fuel nozzle assembly 48. Each fuel nozzle assembly 48 includes a fuel nozzle 38 that extends through a respective one fuel nozzle opening of the set of fuel nozzle openings 72.

[0054] During operation, a fuel (F) is fed from the fuel source 34 and to the combustion chamber 50 through the annular array of combustor portions 31. Specifically, the fuel (F) is fed to the combustion chamber 50 through the fuel nozzle 38 of at least one combustor portion of the annular array of combustor portions 31. The fuel (F) includes any suitable fuel, including gaseous fuel, such as H2 fuel. As a non-limiting example, the fuel (F) can include 100% H2 (e.g., without diluents). In some examples, the fuel (F) can be a combination of fuels using other fuels with H2 fuels. For example, the fuel (F) can comprise H2 fuel and methane, such as in the form of natural gas. A controller 60 can be connected to and at least partially control operation of the fuel source 34, the fuel nozzle assembly 48, or both. The controller 60 can include a processor 62 and a memory 64.

[0055] FIG. 3 is a schematic cross-sectional side view of a combustor portion 100 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 100 is similar to the combustor portion 31 (FIG. 2); therefore, like parts will be identified with like names with it being understood that the description of the combustor portion 31 applies to the combustor portion 100 unless noted otherwise.

[0056] The combustor portion 100 includes a fuel nozzle 101 with a set of fluid diodes 140 and a combustor 103. The combustor 103 includes a combustor wall 105. The combustor wall 105 includes a fuel nozzle opening 107. The combustor wall 105 at least partially defines a combustion chamber 109. The combustor wall 105 can be various walls within the combustor 103 such as a dome wall (e.g., the dome wall 46 of FIG. 2), a combustor liner (e.g., the combustor liner 40 of FIG. 2, the inner liner 42 of FIG. 2, the outer liner 41 of FIG. 2, or a combination thereof), or a combination thereof that at least partially defines the combustion chamber 109.

[0057] The fuel nozzle 101 includes a fuel nozzle body 102. The fuel nozzle body 102 defines a fuel nozzle centerline 104. The fuel nozzle body 102 defines a central channel 112. The central channel 112 extends between a fuel nozzle air inlet 106 and a fuel nozzle outlet 108. The fuel nozzle air inlet 106 is formed as at least one of a channel, a slot, a set of holes, or a combination thereof extending through a respective portion of the fuel nozzle body 102. The fuel nozzle air inlet 106 is fluidly connected with an air source, such as compressed air from one or more of the compressed air passage 32 (FIGS. 2-3) or the compressor section 12 (FIGS. 2-3). The fuel nozzle 101 opens to the combustion chamber 109 at the fuel nozzle outlet 108.

[0058] The central channel 112 is split into at least two sections: a compressed air passage 114 and a mixing tube 116. The compressed air passage 114 extends axially with respect to the fuel nozzle centerline 104 from the fuel nozzle air inlet 106 and to the mixing tube 116. The mixing tube 116 extends axially with respect to the fuel nozzle centerline 104 from the compressed air passage 114 and to the fuel nozzle outlet 108. Further delineation between the compressed air passage 114 and the mixing tube 116 with respect to flows of fluids within the compressed air passage 114 and the mixing tube 116 will be described in further detail below.

[0059] The fuel nozzle body 102 includes an inner fuel nozzle body surface 110. The inner fuel nozzle body surface 110 defines the central channel 112. The fuel nozzle body 102 can be a tapered shape that converges towards the fuel nozzle centerline 104 along a direction parallel to the fuel nozzle centerline 104 (e.g. from the fuel nozzle air inlet 106 to the fuel nozzle outlet 108). That is, a cross-sectional area of the fuel nozzle body 102 measured in a direction perpendicular to the fuel nozzle centerline 104 decreases from an upstream portion to a downstream portion of the fuel nozzle body 102.

[0060] The fuel nozzle 101 can include a centerbody 118. The centerbody 118 extends axially through the compressed air passage 114 of the central channel 112 along the fuel nozzle centerline 104. The centerbody 118 is one of coupled to or integrally formed with a respective portion of the fuel nozzle body 102. The centerbody 118 includes an outer centerbody surface 120 that is a radially outer surface of the centerbody 118 with respect to the fuel nozzle centerline 104. Although the centerbody 118 is illustrated, it is contemplated that the fuel nozzle 101 can be formed without the centerbody 118.

[0061] The fuel nozzle 101 comprises a splitter 126. The splitter 126 is located within the compressed air passage 114. The splitter 126 is annular about the fuel nozzle centerline 104. The splitter 126 defines an inner splitter surface 128 and an outer splitter surface 130 located radially outwardly of the inner splitter surface 128 with respect to the fuel nozzle centerline 104. The splitter 126 can have a tapered shape that is parallel to the tapered shape of the fuel nozzle body 102. That is, the splitter 126 can converge towards the fuel nozzle centerline 104 along a direction that is parallel with the fuel nozzle centerline 104 (e.g. from the fuel nozzle air inlet 106 to the fuel nozzle outlet 108). Said another way, a cross-sectional area of the splitter 126 measured in a direction perpendicular to the fuel nozzle centerline 104 decreases from an upstream portion to a downstream portion of the splitter 126. Additionally or alternatively, the splitter 126 can be tapered at an angle β with respect to a reference line parallel to the fuel nozzle centerline 104. In a non-limiting example, the angle β can be in a range from greater than or equal to 10° and less than or equal to 45°.

[0062] The splitter 126 is defined as a portion of the fuel nozzle 101 that splits the compressed air passage 114 of the central channel 112 into two separate channels. Specifically, the splitter 126 separates an inner air flow path 134 formed between the fuel nozzle centerline 104 and the inner splitter surface 128, and an outer air flow path 138 formed between the outer splitter surface 130 and the inner fuel nozzle body surface 110. The inner air flow path 134 extends circumferentially about the fuel nozzle centerline 104 greater than or equal to π / 8 radians and less than or equal to 27 radians. The outer air flow path 138 extends circumferentially about the fuel nozzle centerline 104 greater than or equal to π / 8 radians and less than or equal to 2π radians.

[0063] The fuel nozzle 101 can include a flange 132. The flange 132 is located at an upstream end of the outer air flow path 138. That is, the flange 132 at least partially defines the outer air flow path 138. The flange 132 extends towards the fuel nozzle centerline 104 from the inner fuel nozzle body surface 110. The flange 132 can have a linear or non-linear shape, such as a hooked shape including in non-limiting examples, an L-shape, or a J-shape. That is, the flange 132 can be a hooked flange.

[0064] The fuel nozzle 101 can include a swirler 136. The swirler 136 can be formed as a set of vanes extending into the inner air flow path 134. That is, the swirler 136 can include a vane extending from at least one of the inner splitter surface 128, the outer centerbody surface 120, or a combination thereof. Although the swirler 136 is illustrated, it is contemplated that the fuel nozzle 101 can be formed without the swirler 136.

[0065] The fuel nozzle 101 includes a set of fluid diodes 140. The set of fluid diodes 140 includes a subset of outer air flow path diodes 141 located within the compressed air passage 114. Each diode of the subset of outer air flow path diodes 141 can be formed as a set of protrusions extending into and defining the outer air flow path 138. That is, the subset of outer air flow path diodes 141 are circumferentially spaced, axially spaced, or a combination thereof within the outer air flow path 138.

[0066] The mixing tube 116 is defined by the inner fuel nozzle body surface 110 and confronts the combustion chamber 109. The mixing tube 116 is located downstream of the compressed air passage 114. That is, the mixing tube 116 is located downstream of the inner air flow path 134 and the outer air flow path 138 and upstream of the combustion chamber 109. Additionally or alternatively, the mixing tube 116 can be located downstream of the splitter 126, the centerbody 118, or both the splitter 126 and the centerbody 118.

[0067] The combustor portion 100 is fluidly coupled to a fuel supply 150. The fuel supply 150 includes a fuel source 154 (e.g., fuel source 34 of FIGS. 2-3, or another fuel source). The fuel source is any suitable container, vessel, or space configured to hold a volume of fuel that is fed to the combustor portion 100 during operation of the combustor portion 100. As a non-limiting example, the fuel source 154 can be a container located within the combustor portion 100. As a non-limiting example, the fuel source 154 can be located exterior the combustor portion 100. As a non-limiting example, the fuel source 154 can be located exterior a turbine engine (e.g., the turbine engine 10 of FIG. 1) including the combustor portion 100. As a non-limiting example, the fuel source 154 can be located within a wing of an aircraft including the turbine engine (e.g. the turbine engine 10 of FIG. 1) having the combustor portion 100.

[0068] The fuel supply 150 includes a set of fuel inlet passages 152, and a set of fuel orifices 156. The fuel nozzle body 102 can at least partially define the set of fuel inlet passages 152. The set of fuel inlet passages 152 is formed as at least one of a channel, a slot, a set of holes, or a combination thereof extending through a respective portion of the fuel nozzle body 102. The set of fuel inlet passages 152 is fluidly coupled to the fuel source 154 by a series of tubes, conduits, passageways, or a combination thereof illustrated in phantom lines. The set of fuel inlet passages 152 opens to the central channel 112 at the set of fuel orifices 156. That is, each fuel inlet passage of the set of fuel inlet passages 152 opens to the central channel 112 at a respective fuel orifice of the set of fuel orifices 156. Although the set of fuel inlet passages 152 is depicted on a portion of the fuel nozzle body 102 that is parallel with the fuel nozzle centerline 104, the set of fuel inlet passages 152 can alternatively or additionally be disposed on the tapered portion of the fuel nozzle body 102. That is, while illustrated as downstream of a downstream terminal end 124 of the centerbody 118, it is contemplated in a different and non-limiting example that the set of fuel inlet passages 152 can axially overlap the centerbody 118. It is further contemplated that in a different and non-limiting example, the set of fuel orifices 156 is located downstream of the outer air flow path 138 and the set of fluid diodes 140.

[0069] In operation of the combustor portion 100, a flow of air (A) is provided to the central channel 112 from the air source through the fuel nozzle air inlet 106. The flow of air (A) splits into multiple air flows illustrated as a first air flow (A1) and a second air flow (A2). The first air flow (A1) flows through the inner air flow path 134 including over the swirler 136. The swirler 136 imparts swirl to the first air flow (A1). Air emitted by the inner air flow path 134 and supplied to the mixing tube 116 is therefore illustrated as a swirled air flow (AS). The second air flow (A2) flows through the outer air flow path 138 including over the subset of outer air flow path diodes 141. The flange 132 guides a portion of the air (A) into the outer air flow path 138 as the second air flow (A2). The flange 132 also acts to limit a volume and pressure of the portion of the air (A) that flows into the outer air flow path 138 as the second air flow (A2). The subset of outer air flow path diodes 141 generates vortices or eddies within the outer air flow path 138. Air emitted by the outer air flow path 138 and supplied to the mixing tube 116 is illustrated as a turbulent air flow (AT). The second air flow (A2) is in a range of greater than or equal to 5% and less than or equal to 50% of the total flow of air (A). In a non-limiting example, the second air flow (A2) is in a range of greater than or equal to 5% and less than or equal to 20% of the total flow of air (A). In another non-limiting example, the second air flow (A2) is in a range of greater than or equal to 10% and less than or equal to 15% of the total flow of air (A).

[0070] In operation of the combustor portion 100, a flow of fuel (F) is provided to the fuel supply 150. The flow of the fuel (F) is provided to the central channel 112 from the fuel source 154 through the fuel inlet passage 152. The flow of fuel (F) is emitted by the set of fuel orifices 156 and is supplied to the mixing tube 116. The flow of fuel (F) contains any suitable fuel. As a non-limiting example, the flow of fuel (F) includes a flow of H2 fuel (e.g., 100% gaseous H2 fuel, 100% liquid H2 fuel, or H2 fuel mixed with another fuel or fluid).

[0071] The fuel (F) mixes with the turbulent air flow (AT) and the swirled air flow (AS) in the mixing tube 116 to define a fuel-air mixture (M). The fuel-air mixture (M) is fed to the combustion chamber 109 through the fuel nozzle outlet 108. The fuel-air mixture (M) is ignited within the combustion chamber 109 to define a flame within the combustion chamber 109. The combustion of the fuel-air mixture (M) generates combustion pressure waves (C) within the combustion chamber 109. The combustion pressure waves (C) are defined by a frequency (CF) and an amplitude (CA). The combustion frequency (CF) is greater than or equal to 100 Hertz and less than or equal to 5000 Hertz. The combustion frequency (CF) varies greatly based on the characteristics of the fuel-air mixture (M) (e.g., a profile of the fuel-air mixture (M), an amount of fuel within the fuel-air mixture (M), etc.), and a geometry of the combustion chamber 109 where the fuel-air mixture (M) is ignited.

[0072] The set of fluid diodes 140 being present in the compressed air passage 114 results in minimal resistance to forward flow towards the combustion chamber 109 while providing high resistance to back flow away from the combustion chamber 109. Particularly, the set of fluid diodes 140 acts as a damper of the combustion pressure waves (C) by generating mixture pressure waves (W) within the fuel-air mixture (M). The mixture pressure waves (W) are defined by a frequency (WF) and an amplitude (WA). During operation, it is contemplated that at least some of the combustion pressure waves (C) can flow backwards and into the mixing tube 116 along the fuel nozzle centerline 104. The mixture pressure waves (W) travelling towards the fuel nozzle centerline 104 from the outer air flow path 138 interact with these combustion pressure waves (C) that backflow into the mixing tube 116. This interaction between the combustion pressure waves (C) and the mixture pressure waves (W) is called phase interaction. The frequency (WF) is selected to reduce the amplitude (CA) through the phase interaction. As a non-limiting example, the mixture pressure waves (W) are selected to be at a frequency (WF) or combination of frequencies that dampens the amplitude (CA) with respect to an amplitude (CA) if the set of fluid diodes 140 were not included. As used herein, the term “dampen” or iterations thereof in relation to frequencies refers to the reduction of the amplitude of a given wave. As a non-limiting example, the generation of the mixture pressure waves (W) at the frequency (WF) has been found to dampen the amplitude (CA) of the combustion pressure waves (C).

[0073] It is contemplated that the mixture pressure waves (W) within the central channel 112 cause the fuel-air mixture (M) to have a frequency (e.g., have a wave formation). Put another way, the fuel-air mixture (M) includes the mixture pressure waves (W) such that a form of the mixture pressure waves (W) is fed to the combustion chamber 109. The mixture pressure waves (W) interact with the combustion pressure waves (C) and at least partially offset the combustion pressure waves (C), thus lowering the overall amplitude (CA).

[0074] Damping strength of the set of fluid diodes 140 can be improved at higher frequencies (e.g. frequency (WF)). Further, damping strength of the set of fluid diodes 140 and pressure drop of the compressed air (A) is proportional to a flow rate of the compressed air (A). Damping efficiency of the set of fluid diodes 140 increases with relatively longer protruding lengths of the set of fluid diodes 140.

[0075] The dampening of the combustion pressure waves (C) has been found to reduce the negative impacts associated with the combustion pressure waves (C). As a non-limiting example, combustion pressure waves (C) with a higher amplitude have been found to create acoustic oscillations within the combustion chamber 109 that if left unchecked can damage sections of the combustor portion 100 or otherwise cause undesired flow characteristics or profiles of the combustion flame or combustion gases associated with the combustion of the fuel-air mixture (M). The undesired flow characteristics or profiles of the combustion flame, in turn, create a non-uniform temperature distribution or flow distribution at a combustor outlet that is ultimately fed to a downstream portion of the turbine engine (e.g., the turbine section 16 of FIG. 1). As such, leaving the combustion pressure waves (C) unchecked (e.g., undampened by the set of fluid diodes 140) at least one of damages the combustor portion 100, reduces the efficiency of the combustor portion 100, or a combination thereof.

[0076] The dampening of the combustion pressure waves (C) is especially important when the flow of fuel (F) contains a H2 fuel. H2 fuel, in comparison with conventional fuels, has a higher flame speed. The higher flame speed, in turn, generates combustion pressure waves (C) having a higher amplitude (CA) than the amplitude of the combustion pressure waves of traditional fuels. If left unchecked, the combustion pressure waves (C) associated with H2 fuels can damage the combustor portion 100 and cause undesired flame shaping at the combustor outlet.

[0077] The combustor portion 100 is especially well suited for use where the flow of fuel (F) contains H2 fuel. The combination of the swirled air flow (AS) and the turbulent air flow (AT) ensures a homogenous mixture of fuel and air of the fuel-air mixture (M), thus reducing the likelihood of pockets or concentrations of fuel to be formed within the fuel-air mixture (M). H2 fuels have a higher burn velocity and greater chance for flashback. The elimination of or reduction of the large concentrations of fuel within the fuel-air mixture (M) reduces the likelihood of flashback occurring by reducing the locations where the flame can spread.

[0078] FIG. 4 illustrates a cross-sectional forward looking aft view of the fuel nozzle 101 along line IV-IV of FIG. 3. The fuel nozzle body 102 circumscribes the splitter 126. The inner splitter surface 128 together with the centerbody 118 at least partially defines the inner air flow path 134. The inner fuel nozzle body surface 110 together with the outer splitter surface 130 at least partially defines the outer air flow path 138. The swirler 136 can be disposed within the inner air flow path 134.

[0079] The fuel nozzle 101 includes a plurality of walls 160. The plurality of walls 160 extend radially between the outer splitter surface 130 and the inner fuel nozzle body surface 110, and axially along a length of the outer air flow path 138 with respect to the fuel nozzle centerline 104. Although the plurality of walls 160 is depicted as including six walls, it is contemplated that the plurality of walls 160 can include any number of walls greater than or equal to two. The outer air flow path 138 is defined circumferentially with respect to the fuel nozzle centerline 104 between a pair of circumferentially opposing walls of the plurality of walls 160. That is, the outer air flow path 138 is defined by the inner fuel nozzle body surface 110, the outer splitter surface 130 and the plurality of walls 160. The set of fluid diodes 140, particularly the subset of outer air flow path diodes 141, extends circumferentially from the plurality of walls 160. That is, the set of fluid diodes 140 is disposed within the outer air flow path 138. For purposes of illustration, a dashed line separates the set of fluid diodes 140 from the plurality of walls 160. However, the set of fluid diodes 140 is integrally formed with the plurality of walls 160.

[0080] FIG. 5 depicts a top view of a portion of the fuel nozzle 101 along sectional line V-V of FIG. 4. The outer air flow path 138 includes an example of the set of fluid diodes 140 including the subset of outer air flow path diodes 141. Each diode of the set of fluid diodes 140 projects away from one of the plurality of walls 160. For purposes of illustration, dashed lines separate the set of fluid diodes 140 from the plurality of walls 160.

[0081] Each diode of the set of fluid diodes 140 has a wave shaped cross-sectional area. That is, each diode of the set of fluid diodes 140 has a curved or hook shaped cross-sectional area that points in a downstream direction relative to a flow of fluid flowing over the set of fluid diodes 140. For example, each outer air flow path diode of the subset of outer air flow path diodes 141 has a hook shape cross-section that points in a downstream direction relative to the second air flow (A2).

[0082] In operation, as the second air flow (A2) passes through the outer air flow path 138 and over the subset of outer air flow path diodes 141, the second air flow A2 turns, forming vortices depicted as the turbulent air flow (AT).

[0083] FIG. 6 is a schematic top view of a portion of an exemplary fuel nozzle 201 suitable for use as the fuel nozzle 101 of FIGS. 3-5. The fuel nozzle 201 is similar to the fuel nozzle 101 (FIGS. 3-5), therefore, like parts will be identified with like numerals increased to the 200 series with it being understood that the description of the fuel nozzle 101 applies to the fuel nozzle 201 unless noted otherwise.

[0084] The fuel nozzle 201 includes an outer air flow path 238. The fuel nozzle 201 includes a plurality of walls 260 and a set of fluid diodes 240. The set of fluid diodes 240 is located along a respective portion of the plurality of walls 260. The set of fluid diodes 240 extends from a respective portion of the plurality of walls 260 and into the outer air flow path 238.

[0085] The set of fluid diodes 240 is similar to the set of fluid diodes 140 (FIGS. 3-5) in that each fluid diode of the set of fluid diodes 240 projects away from one wall of the plurality of walls 260. For purposes of illustration, a dashed line separates the set of fluid diodes 240 from the plurality of walls 260. Each fluid diode of the set of fluid diodes 240, however, has a linear shape, such as a rectangular shape or a rhomboid shape, as opposed to the wave shape of the set of fluid diodes 140 of FIGS. 3-5.

[0086] Each fluid diode of the set of fluid diodes 240 protrudes at an angle 262 with respect to one of the plurality of walls 260. For example, each fluid diode of the set of fluid diodes 240 can be angled to point in a downstream direction relative to a flow of fluid flowing over the set of fluid diodes 240. For example, each outer air flow path diode of a subset of outer air flow path diodes 241 points in a downstream direction relative to the second air flow (A2). The value of the angle 262 can be in a range of greater than 0° and less than or equal to 45°. In a non-limiting example, the angle 262 is 30°. It is contemplated that a larger value of the angle 262 can create more turbulence and higher resistance to reverse flow, which can increase the damping efficiency of the set of fluid diodes 240. However, it is also contemplated that a larger value of the angle 262 increases pressure drop in a forward direction of the fluid flowing over the set of fluid diodes 240. It has been found that the angle 262 being within the aforementioned range results in a balance between creating turbulence and resistance to reverse flow with increased pressure drop in the forward direction. It is contemplated that the angle 262 of each fluid diode of the set of fluid diodes 240 can be the same, different, or a combination thereof.

[0087] In operation, as the second air flow (A2) passes through the outer air flow path 238 and over each fluid diode of the set of fluid diodes 240, the second air flow (A2) turns forming vortices depicted as the turbulent air flow (AT).

[0088] FIG. 7 is a schematic cross-sectional side view of a combustor portion 300 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 300 is similar to the combustor portion 100 (FIGS. 3-4), therefore, like parts will be identified with like numerals increased to the 300 series with it being understood that the description of the combustor portion 100 applies to the combustor portion 200 unless noted otherwise.

[0089] The combustor portion 300 includes a fuel nozzle 301 with a set of fluid diodes 340, and a combustor 303. The combustor 303 includes a combustor wall 305 including a fuel nozzle opening 307 and at least partially defining a combustion chamber 309. The fuel nozzle 301 includes a fuel nozzle body 302 defining a fuel nozzle centerline 304. The fuel nozzle body 302 includes an inner fuel nozzle body surface 310 defining a central channel 312 extending between a fuel nozzle air inlet 306 and a fuel nozzle outlet 308. The combustor portion 300 is fluidly coupled to a fuel supply 350. The fuel supply 350 includes a fuel source 354, a set of fuel inlet passages 352, and a set of fuel orifices 356.

[0090] The combustor portion 300 is similar to the combustor portion 100 (FIGS. 3-4) in that the central channel 312 is split into at least two sections: a compressed air passage 314 and a mixing tube 316. The compressed air passage 314, however, does not include a centerbody (e.g. centerbody 118 of FIGS. 3-4) and includes an upstream portion 364 and a downstream portion 366, the upstream portion 364 including an upstream splitter 326, an upstream flange 332, and an optional upstream swirler 336, and the downstream portion 366 including a downstream splitter 327, a downstream flange 333, and an optional downstream swirler 337, as opposed to the compressed air passage 114 (FIGS. 3-4) which includes a single splitter 126, a single flange 132, and a single optional swirler 136. Further, the set of fluid diodes 340 includes a subset of upstream air flow path diodes 342 and a subset of downstream air flow path diodes 343 as opposed to a single subset of outer air flow path diodes 141 (FIGS. 3-4) of the set of fluid diodes 140 (FIGS. 3-4).

[0091] The upstream splitter 326 is annular about the fuel nozzle centerline 304. The upstream splitter 326 defines an inner splitter surface 328 and an outer splitter surface 330 located radially outward of the inner splitter surface 328 with respect to the fuel nozzle centerline 304. The upstream splitter 326 is defined as a portion of the fuel nozzle 301 that splits the upstream portion 364 of the compressed air passage 314 into two separate channels. Specifically, the upstream splitter 326 separates an inner upstream air flow path 334 formed by the inner splitter surface 328, and an outer upstream air flow path 338 formed between the outer splitter surface 330 and the inner fuel nozzle body surface 310. The upstream swirler 336 can optionally be formed as a set of vanes extending into the inner upstream air flow path 334. The downstream splitter 327 is annular about the fuel nozzle centerline 304.

[0092] The downstream splitter 327 defines an inner splitter surface 329 and an outer splitter surface 331 located radially outward of the inner splitter surface 329 with respect to the fuel nozzle centerline 304. The downstream splitter 327 is defined as a portion of the fuel nozzle 301 that splits the downstream portion 366 of the compressed air passage 314 into two separate channels. Specifically, the downstream splitter 327 separates an inner downstream air flow path 335 formed by the inner splitter surface 329, and an outer downstream air flow path 339 formed between the outer splitter surface 331 and the inner fuel nozzle body surface 310. The downstream swirler 337 can be formed as a set of vanes extending into the inner downstream air flow path 335.

[0093] Each diode of the subset of upstream air flow path diodes 342 can be formed as a set of protrusions extending into and defining the outer upstream air flow path 338. Each diode of the subset of downstream air flow path diodes 343 can be formed as a set of protrusions extending into and defining the outer downstream air flow path 339. The set of fluid diodes 340 can take the shape of the set of fluid diodes 140 (FIG. 5), the set of fluid diodes 240 (FIG. 6), or a combination thereof. That is, the combustor portion 300 can include a plurality of walls extending radially between the outer splitter surface 330 and the inner fuel nozzle body surface 310, and axially along a length of the outer upstream air flow path 338 with respect to the fuel nozzle centerline 304, and a plurality of walls extending radially between the outer splitter surface 331 and the inner fuel nozzle body surface 310, and axially along a length of the outer downstream air flow path 339 with respect to the fuel nozzle centerline 304, with the set of fluid diodes 340 being formed integrally with the plurality of walls.

[0094] By increasing an amount of fluid diodes in the combustor portion 300 compared to the combustor portion 100 (FIGS. 3-4), damping strength of the combustor portion 300 is improved. Particularly, with the set of fluid diodes 340 including two subsets, namely the subset of upstream air flow path diodes 342 and the subset of downstream air flow path diodes 343, there are more fluid diodes overall and correspondingly more out of phase interactions of the mixture pressure waves (W) (FIG. 3) with combustion pressure waves (C) (FIG. 3), which ultimately further reduces the amplitude of the mixture pressure waves (W). It is contemplated that the fluid diodes dampen a broad range of frequencies of the combustion pressure waves (C) (FIG. 3) within the turbine engine 10 (FIG. 1).

[0095] FIG. 8 is a schematic cross-sectional side view of a combustor portion 400 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 400 is similar to the combustor portion 100 (FIGS. 3-4), 300 (FIG. 7), therefore, like parts will be identified with like numerals increased to the 400 series with it being understood that the description of the combustor portion 100, 300 applies to the combustor portion 400 unless noted otherwise.

[0096] The combustor portion 400 includes a fuel nozzle 401 with a set of fluid diodes 440, and a combustor 403. The combustor 403 includes a combustor wall 405 including a fuel nozzle opening 407 and at least partially defining a combustion chamber 409. The fuel nozzle 401 includes a fuel nozzle body 402 defining a fuel nozzle centerline 404. The fuel nozzle body 402 includes an inner fuel nozzle body surface 410 defining a central channel 412 extending between a fuel nozzle inlet 406 and a fuel nozzle outlet 408.

[0097] The combustor portion 400 is similar to the combustor portion 100 (FIGS. 3-4), 200 (FIG. 7) in that there is an inner air flow path 434 and an outer air flow path 438. The fuel nozzle body 402, however, includes a swirler 436 having a set of swirler vanes 468 at least partially defining the inner fuel nozzle body surface 410 and both an inner air flow path 434 and an outer air flow path 438. Further, the set of fluid diodes 440 includes a subset of swirler outer air flow path diodes 444 located within the outer air flow path 438 of the swirler 436 as opposed to separate from the swirler 136 as in the combustor portion 100 (FIGS. 3-4), 200 (FIG. 7).

[0098] The swirler 436 can be integrally formed with the fuel nozzle body 402 as illustrated, or can be separate therefrom. The set of swirler vanes 468 at least partially defines at least two air flow paths, namely the inner air flow path 434 and the outer air flow path 438. That is, the set of swirler vanes 468 splits the central channel 412 into at least two separate flow paths. The inner air flow path 434 extends along the fuel nozzle centerline 404 through the swirler 436. The outer air flow path 438 is formed within the set of swirler vanes 468.

[0099] In operation of the combustor portion 400, a flow of air (A) is provided to the central channel 412 from the air source through the fuel nozzle inlet 406. The flow of air (A) splits into multiple air flows illustrated as a first air flow (A1) and a second air flow (A2). The first air flow (A1) flows through the inner air flow path 434 along the fuel nozzle centerline 404. The second air flow (A2) flows through the outer air flow path 438 including along the set of swirler vanes 468 and over the subset of swirler outer air flow path diodes 444. The subset of swirler outer air flow path diodes 444 generates vortices or eddies within the second air flow (A2), while also simultaneously generating swirl of the second air flow (A2). Air emitted by the outer air flow path 438 is therefore both swirled and turbulent. By generating both swirl and turbulence together, acoustic energy associated with combustion pressure waves (C) (FIG. 3) is dissipated.

[0100] FIG. 9 is a schematic cross-sectional view from forward looking aft of a combustor portion 700 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 700 is similar to the combustor portion 100 (FIGS. 3-4), 300 (FIG. 7), 400 (FIG. 8); therefore, like parts will be identified with like numerals increased to the 700 series with it being understood that the description of the combustor portion 100, 300, 400 applies to the combustor portion 700 unless noted otherwise.

[0101] The combustor portion 700 includes a fuel nozzle 701 with a set of fluid diodes 740. The fuel nozzle 701 includes a fuel nozzle body 702 defining a fuel nozzle centerline 704. The fuel nozzle body 702 includes an inner fuel nozzle body surface 710 defining a central channel 712 extending along the fuel nozzle centerline 704.

[0102] The combustor portion 700 is similar to the combustor portion 100 (FIGS. 3-4) in that the fuel nozzle 701 includes a swirler 736 located within the central channel 712. The swirler 736, however, includes a set of swirler vanes 768, and the set of fluid diodes 740, however, includes a subset of swirler vane diodes 749 located on the set of swirler vanes 768.

[0103] The set of swirler vanes 768 can extend into the central channel 712 from the inner fuel nozzle body surface 710 towards the fuel nozzle centerline 704. Each swirler vane diode of the subset of swirler vane diodes 749 is formed in the shape of a tube extending along the set of swirler vanes 768 within the swirler 736. The subset of swirler vane diodes 749 can be directly attached to the set of swirler vanes 768 as exemplified by a swirler vane diode 749a. Additionally or alternatively, the subset of swirler vane diodes 749 can be attached to the set of swirler vanes 768 by a strut 770 as exemplified by a swirler vane diode 749b.

[0104] In operation of the combustor portion 700, a flow of air (A) is provided to the central channel 712 from the air source. The flow of air (A) flows through the swirler 736 including along the set of swirler vanes 768 and over the subset of swirler vane diodes 749. The subset of swirler vane diodes 749 generates vortices or eddies within flow of air (A), while also simultaneously generating swirl of the flow of air (A). Air emitted by fuel nozzle 701 is therefore both swirled and turbulent. By generating both swirl and turbulence together, acoustic energy associated with combustion pressure waves (C) (FIG. 3) is dissipated.

[0105] FIG. 10 is a schematic cross-sectional side view of a combustor portion 500 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 500 is similar to the combustor portion 100 (FIGS. 3-4), 300 (FIG. 7), 400 (FIG. 8), 700 (FIG. 9); therefore, like parts will be identified with like numerals increased to the 500 series with it being understood that the description of the combustor portion 100, 300, 400, 700 applies to the combustor portion 500 unless noted otherwise.

[0106] The combustor portion 500 includes a fuel nozzle 501 with a set of fluid diodes 540, and a combustor 503. The combustor 503 includes a combustor wall 505 including a fuel nozzle opening 507 and at least partially defining a combustion chamber 509. The fuel nozzle 501 includes a fuel nozzle body 502 defining a fuel nozzle centerline 504. The fuel nozzle body 502 includes an inner fuel nozzle body surface 510 defining a central channel 512 extending between a fuel nozzle air inlet 506 and a fuel nozzle outlet 508. The central channel 512 is split into at least two sections: a compressed air passage 514 and a mixing tube 516. The compressed air passage 514 includes a splitter 526 defining an inner splitter surface 528 and an outer splitter surface 530 located radially outward of the inner splitter surface 528 with respect to the fuel nozzle centerline 504. The splitter 526 splits the compressed air passage 514 into an inner air flow path 534 formed by the inner splitter surface 528, and an outer air flow path 538 formed between the outer splitter surface 530 and the inner fuel nozzle body surface 510. The fuel nozzle 501 can include a flange 532 located at an upstream end of the outer air flow path 538. The fuel nozzle 501 optionally includes a swirler 536 located within the inner air flow path 534.

[0107] The combustor portion 500 is similar to the combustor portion 100 (FIGS. 3-4) in that the combustor portion 500 includes a fuel supply 550 with a set of fuel inlet passages 552, a fuel source 554 and a set of fuel orifices 556. The fuel supply 550, however, also includes a fuel manifold 551 and a fuel distribution passage 553. Further, the set of fluid diodes 540 is similar to the set of fluid diodes 140 (FIGS. 3-4) in that the set of fluid diodes 540 includes a subset of outer air flow path diodes 541 located within the compressed air passage 514. The set of fluid diodes 540, however, also includes a subset of fuel inlet passage diodes 545 located within the set of fuel inlet passages 552 and a subset of fuel distribution passage diodes 546 located within the fuel distribution passage 553.

[0108] The fuel manifold 551 is defined as a distribution channel that distributes fuel received from the fuel distribution passage 553 to the set of fuel inlet passages 552. The set of fuel inlet passages 552 fluidly couples the set of fuel orifices 556 with the fuel manifold 551. The fuel manifold 551 is at least partially formed by the fuel nozzle body 502. As a non-limiting example, the fuel manifold 551 can be integrally formed with the fuel nozzle body 502. The fuel distribution passage 553 is a tube, conduit, passageway, or a combination thereof which fluidly couples the fuel manifold 551 with a fuel source 554.

[0109] The set of fluid diodes 540 can take the shape of the set of fluid diodes 140 (FIG. 5), the set of fluid diodes 240 (FIG. 6), or a combination thereof. Each diode of the subset of fuel inlet passage diodes 545 can be formed as a set of protrusions extending into and defining the set of fuel inlet passages 552. That is, the subset of fuel inlet passage diodes 545 can be integrally formed with and protrude from an inner wall of the fuel inlet passage 552. Each diode of the subset of fuel distribution passage diodes 546 can be formed as a set of protrusions extending into and defining the fuel distribution passage 553. That is, the subset of fuel distribution passage diodes 546 can be integrally formed with and protrude from an inner wall of the fuel distribution passage 553.

[0110] In operation, a flow of fuel (F) is provided to the fuel supply 550. Particularly, a flow of fuel (F) is provided to the central channel 512 from the fuel source 554. The fuel source 554 is located exterior to the fuel nozzle body 502. Thus, the flow of fuel (F) flows through the fuel distribution passage 553 to the fuel manifold 551, which distributes the flow of fuel (F) to the set of fuel inlet passages 552. The flow of the fuel (F) is emitted by the set of fuel orifices 556 and is supplied to the mixing tube 516.

[0111] Combustion pressure waves (e.g. combustion pressure waves (C) of FIG. 3) associated with the fuel (F) are generated in operation of the combustor portion 500. The subsets of the set of fluid diodes 540 located within the fuel supply 550, particularly the subset of fuel inlet passage diodes 535 located within the set of fuel inlet passages 552, and the subset of fuel distribution passage diodes 546 located within the fuel distribution passage 553, generate mixture pressure waves (e.g. mixture pressure waves (W) of FIG. 3) in the fuel-air mixture (M). The combustion pressure waves are at least partially offset by the mixture pressure waves interacting with the combustion pressure waves.

[0112] FIG. 11 is a schematic cross-sectional side view of a combustor portion 600 suitable for use within the turbine engine 10 of FIG. 1. The combustor portion 600 is similar to the combustor portion 100 (FIGS. 3-4), 300 (FIG. 7), 400 (FIGS. 8-9), 500 (FIG. 10); therefore, like parts will be identified with like numerals increased to the 600 series with it being understood that the description of the combustor portion 100, 300, 400, 500 applies to the combustor portion 600 unless noted otherwise.

[0113] The combustor portion 600 includes a fuel nozzle 601 with a set of fluid diodes 640, and a combustor 603. The combustor 603 includes a combustor wall 605 including a fuel nozzle opening 607 and at least partially defining a combustion chamber 609. The fuel nozzle 601 includes a fuel nozzle body 602 defining a fuel nozzle centerline 604. The fuel nozzle body 602 includes an inner fuel nozzle body surface 610 defining a central channel 612 extending between a fuel nozzle air inlet 606 and a fuel nozzle outlet 608. The central channel 612 is split into at least two sections: a compressed air passage 614 and a mixing tube 616. The compressed air passage 614 includes an outer air flow path 638. The fuel nozzle 601 comprises a centerbody 618. The centerbody 618 has an outer centerbody surface 620, that is a radially outer surface of the centerbody 618 with respect to the fuel nozzle centerline 604. The outer air flow path 638 is formed between the inner fuel nozzle body surface 610 and the outer centerbody surface 620. The fuel nozzle 601 is fluidly coupled to a fuel supply 650.

[0114] The combustor portion 600 is similar to the combustor portion 100 (FIGS. 3-4) in that the combustor portion 600 includes the centerbody 618, and the fuel supply 650. The combustor portion 600, particularly the fuel supply 650, however, also includes a centerbody fuel passage 657 within the centerbody 618 and opening to the central channel 612 at a set of centerbody fuel orifices 658, as opposed to the centerbody 118 of FIGS. 3-4. Further, the set of fluid diodes 640 is similar to the set of fluid diodes 140 (FIGS. 3-4) in that the set of fluid diodes 640 includes a subset of air flow path diodes 647 located within the compressed air passage 614. The set of fluid diodes 640, however, also includes a subset of centerbody fuel diodes 648 located within the centerbody fuel passage 657.

[0115] The fuel nozzle 601 optionally includes a swirler 636. The swirler 636 can be formed as a set of vanes extending into the inner air flow path 634. That is, the swirler 636 can include a vane extending from at least one of the inner fuel nozzle body surface 610 and the outer centerbody surface 620, or a combination thereof.

[0116] The fuel supply 650 includes the centerbody fuel passage 657, the set of centerbody fuel orifices 658, and a fuel source 654. The set of centerbody fuel orifices 658 is formed as at least one of a channel, a slot, a set of holes, or a combination thereof extending through a respective portion of a downstream terminal end 624 of the centerbody 618. The centerbody fuel passage 657 is fluidly coupled to the fuel source 654 by a series of tubes, conduits, passageways, or a combination thereof illustrated in phantom lines.

[0117] The set of fluid diodes 640 includes the subset of air flow path diodes 647 located within the compressed air passage 614. The subset of air flow path diodes 647 can be located upstream of the swirler 636. Each diode of the subset of air flow path diodes 647 can be formed as a set of protrusions extending into and defining the outer air flow path 638. The subset of air flow path diodes 647 can take the shape of the set of fluid diodes 140 (FIG. 5), the set of fluid diodes 240 (FIG. 6), or a combination thereof. That is, the combustor portion 600 can include a plurality of walls extending radially with respect to the fuel nozzle centerline 604 between the inner fuel nozzle body surface 610 and the outer centerbody surface 620, with the subset of air flow path diodes 647 being formed integrally with the plurality of walls.

[0118] The set of fluid diodes 640 includes the subset of centerbody fuel diodes 648 located within the centerbody 618. Each diode of the subset of centerbody fuel diodes 648 can be formed as a set of protrusions extending into and defining the centerbody fuel passage 657. The subset of centerbody fuel diodes 648 can take the shape of the set of fluid diodes 140 (FIG. 5), the set of fluid diodes 240 (FIG. 6), or a combination thereof. That is, the combustor portion 600 can include a plurality of walls extending radially with respect to the fuel nozzle centerline 604 between the fuel nozzle centerline 604 and an inner centerbody surface 622, with the subset of centerbody fuel diodes 648 being formed integrally with the plurality of walls.

[0119] In operation, a flow of fuel (F) is provided to the fuel supply 650. Particularly, a flow of fuel (F) is provided to the centerbody fuel passage 657 from the fuel source 654. The fuel source 654 is located exterior to the fuel nozzle body 602. The flow of the fuel (F) is emitted by the set of centerbody fuel orifices 658 and is supplied to the mixing tube 616. By supplying the fuel (F) from the centerbody fuel passage 657, which includes the subset of centerbody fuel diodes 648, the impact of flow oscillations and flame oscillations associated with variations in a flow rate of the fuel (F) are minimized. Also, flame or hot gases from the combustion chamber 609 are prevented from creeping into a flow path of the fuel (F).

[0120] In operation, a flow of air (A) is supplied to the compressed air passage 614. By staggering the swirler 636 and the subset of air flow path diodes 647, particularly such that the subset of air flow path diodes 647 is upstream of the swirler 636 (e.g. a distance from the subset of air flow path diodes 647 to the fuel nozzle air inlet 606 is shorter than a distance from the swirler 636 to the fuel nozzle air inlet 606), can prevent any combustion waves (e.g. the combustion pressure waves (C) of FIG. 3) from affecting an upstream compressor (e.g. the compressor section 12 of FIG. 1).

[0121] To the extent not already described, the different features and structures of the various embodiments can be used in combination, or in substitution with each other as desired. All combinations or permutations of features described herein are covered by this disclosure. It should be understood that none of the configurations described herein are mutually exclusive. Each combustor portion 31 (FIG. 2) can be identical or non-identical to each other. As a non-limiting example, a combustor portion can output a mixture pressure wave (W) at a frequency (WF) having a first value, while a combustor portion can output a mixture pressure wave (W) at a frequency (WF) having a second value, different from the first value. In another example, a set of fluid diodes of a single combustor portion can include multiple subsets of the set of fluid diodes. It is contemplated, for example, that a compressed air passage can include one or multiple subsets of fluid diodes, and a fuel supply can simultaneously include one or more multiple subsets of fluid diodes.

[0122] The disclosed combustor portions and fuel nozzles each including a set of fluid diodes can reduce the negative impacts associated with combustion pressure waves. By providing a set of fluid diodes located within a compressed air passage or a fuel supply, desired flow characteristics or profiles of a combustion flame or combustion gases can be achieved. The set of fluid diodes thereby prevents damage to the combustor portion related to acoustic oscillations associated with combustion.

[0123] Benefits of the disclosed combustor portions are especially applicable to combustor portions fed with H2 fuel. The higher flame speed of H2 fuel compared to conventional fuel results in combustion pressure waves having a higher amplitude than that of combustion pressure waves of traditional fuels. A pressure wave generated by the set of fluid diodes is used to offset or otherwise dampen the effect of acoustic oscillations or acoustic pressure waves that are generated by combustion of fuel within the combustion chamber.

[0124] This written description uses examples to describe aspects of the disclosure described herein, including the best mode, and also to enable any person skilled in the art to practice aspects of the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of aspects of the disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

[0125] Further aspects are provided by the subject matter of the following clauses:

[0126] A gas turbine engine comprising: a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section having a fuel nozzle comprising: a fuel nozzle body defining a central channel, the central channel comprising a compressed air passage and a mixing tube, the fuel nozzle body defining a fuel nozzle centerline; an inner air flow path supplying a first air flow to the mixing tube; an outer air flow path, circumscribing the inner air flow path, and supplying a second air flow to the mixing tube; a set of fluid diodes including a subset of the set of fluid diodes located within the outer air flow path and generating a set of vortices within the outer air flow path; and a fuel supply including a set of fuel orifices through which a fuel flow is supplied to the mixing tube.

[0127] The gas turbine engine of any preceding clause, wherein the outer air flow path is at least partially defined by a flange extending from the fuel nozzle body and into the compressed air passage.

[0128] The gas turbine engine of any preceding clause, wherein the flange is a hooked flange.

[0129] The gas turbine engine of any preceding clause, wherein the fuel nozzle further comprises a pair of circumferentially opposing walls defining the outer air flow path circumferentially therebetween.

[0130] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the outer air flow path extends from the pair of circumferentially opposing walls and into the outer air flow path.

[0131] The gas turbine engine of any preceding clause, wherein the outer air flow path extends circumferentially about the fuel nozzle centerline greater than or equal to π / 8 radians and less than or equal to 2π radians.

[0132] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located in the outer air flow path includes a plurality of fluid diodes circumferentially spaced within the outer air flow path.

[0133] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located in the outer air flow path includes a plurality of fluid diodes axially spaced within the outer air flow path.

[0134] The gas turbine engine of any preceding clause, wherein the fuel nozzle further includes an annular splitter that separates the inner air flow path and the outer air flow path, the annular splitter being tapered at an angle β with respect to a reference line parallel to the fuel nozzle centerline, the angle β being in a range from greater than or equal to 10° and less than or equal to 45°.

[0135] The gas turbine engine of any preceding clause, wherein the annular splitter is an upstream annual splitter, the inner air flow path is an inner upstream air flow path, the outer air flow path is an outer downstream air flow path, and wherein the fuel nozzle further includes a downstream annular splitter separating an inner downstream air flow path and an outer downstream air flow path.

[0136] The gas turbine engine of any preceding clause, wherein the fuel nozzle further includes a centerbody extending axially along the fuel nozzle centerline through the compressed air passage.

[0137] The gas turbine engine of any preceding clause, wherein the set of fuel orifices is located downstream of a downstream terminal end of the centerbody.

[0138] The gas turbine engine of any preceding clause, wherein the set of fuel orifices is located downstream of the outer air flow path and the subset of the set of fluid diodes located within the outer air flow path.

[0139] The gas turbine engine of any preceding clause, wherein the set of fluid diodes generates a pressure wave having a frequency of greater than or equal to 100 Hertz and less than or equal to 5000 Hertz.

[0140] The gas turbine engine of any preceding clause, wherein a fluid diode of the set of fluid diodes has a wave or linear shape.

[0141] The gas turbine engine of any preceding clause, wherein a fluid diode of the set of fluid diodes has a linear shape protruding from a wall at an angle in a range from greater than or equal to 0° and less than or equal to 45°.

[0142] The gas turbine engine of any preceding clause, wherein the fuel nozzle further comprises a swirler located within the inner air flow path and imparting a swirl to the first air flow.

[0143] The gas turbine engine of any preceding clause, wherein: the swirler is an upstream swirler; the subset of the set of fluid diodes located within the outer air flow path is a subset of upstream air flow path diodes; the fuel nozzle further includes a downstream swirler located downstream of the upstream swirler; and the set of fluid diodes further includes a subset of downstream air flow path diodes located downstream of the subset of upstream air flow path diodes.

[0144] The gas turbine engine of any preceding clause, wherein the outer air flow path is at least partially defined by an upstream flange extending from the fuel nozzle body and into the compressed air passage and a downstream flange extending from the fuel nozzle body and into the compressed air passage.

[0145] The gas turbine engine of any preceding clause, wherein the upstream flange is a hooked flange and the downstream flange is a hooked flange.

[0146] The gas turbine engine of any preceding clause, wherein the fuel nozzle further comprises a swirler located within the compressed air passage, and the set of fluid diodes includes a subset of the set of fluid diodes located within the swirler.

[0147] The gas turbine engine of any preceding clause, wherein the swirler is integrally formed with the fuel nozzle body.

[0148] The gas turbine engine of any preceding clause, wherein the swirler defines the inner air flow path and the outer air flow path.

[0149] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the swirler is located within the outer air flow path defined by the swirler.

[0150] The gas turbine engine of any preceding clause, wherein the swirler includes a set of vanes, and the subset of the set of fluid diodes located within the swirler extends from a vane of the set of vanes.

[0151] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the swirler is formed in the shape of a tube extending along a vane of the set of vanes.

[0152] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the swirler is directly attached to a vane of the set of vanes.

[0153] The gas turbine engine of any preceding clause, wherein the subset of the set of fluid diodes located within the swirler is attached to a vane of the set of vanes by a strut.

[0154] The gas turbine engine of any preceding clause, wherein the set of fluid diodes further includes a subset of the set of fluid diodes located within the fuel supply and generating vortices within the fuel flow.

[0155] The gas turbine engine of any preceding clause, wherein the set of fuel orifices includes a plurality of fuel orifices, the fuel supply includes a fuel distribution passage fluidly coupled to two or more fuel orifices of the set of fuel orifices, and the set of fluid diodes includes a subset of the set of fluid diodes located within the fuel distribution passage.

[0156] The gas turbine engine of any preceding clause, wherein the fuel distribution passage is located exterior to the fuel nozzle body.

[0157] The gas turbine engine of any preceding clause, wherein the fuel supply includes a set of fuel inlet passages that each open to the mixing tube at a respective fuel orifice of the set of fuel orifices, and the set of fluid diodes includes a subset of the set of fluid diodes at least partially located in the fuel inlet passage.

[0158] The gas turbine engine of any preceding clause, wherein the fuel nozzle further comprises a centerbody coupled to the fuel nozzle body and extending axially with respect to the fuel nozzle centerline through the compressed air passage, wherein at least a portion of the fuel supply is formed within the centerbody, and wherein the set of fluid diodes includes a subset of the set of fluid diodes located within the portion of the fuel supply formed within the centerbody.

[0159] The gas turbine engine of any preceding clause, wherein the fuel supply feeds a flow of hydrogen-containing fuel to the mixing tube.

Examples

Embodiment Construction

[0016]Aspects of the disclosure described herein are directed to a gas turbine engine including a combustion section. The combustion section includes a fuel nozzle. The fuel nozzle includes a fuel nozzle body defining an air supply opening to a mixing tube. The fuel nozzle also includes a fuel supply opening to the mixing tube. The mixing tube opens to a combustion chamber. A set of fluid diodes is located in one or both of the air supply and the fuel supply.

[0017]During operation, a flow of compressed air is fed to the air supply, and a flow of fuel (e.g. gaseous hydrogen fuel) is fed to the fuel supply, and the flows of compressed air and fuel are mixed in the mixing tube. The set of fluid diodes generates pressure waves within one or both of the air supply and the fuel supply. The pressure waves generated by the set of fluid diodes are used to offset or otherwise dampen the effect of acoustic oscillations or acoustic pressure waves that are generated by combustion of fuel within ...

Claims

1. A gas turbine engine comprising:a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section having a fuel nozzle comprising:a fuel nozzle body including an inner fuel nozzle body surface and defining a channel, the channel comprising a compressed air passage and a mixing tube, the fuel nozzle body defining a fuel nozzle centerline, and the mixing tube being located downstream of the compressed air passage;an inner air flow path supplying a first air flow to the mixing tube;an outer air flow path, circumscribing the inner air flow path, and supplying a second air flow to the mixing tube, wherein the outer air flow path is at least partially defined by the inner fuel nozzle body surface, and wherein the outer air flow path is at least partially defined by a flange extending from the inner fuel nozzle body surface toward the fuel nozzle centerline and into the compressed air passage;a set of fluid diodes including a subset of the set of fluid diodes located within the outer air flow path and generating a set of vortices within the outer air flow path; anda fuel supply including a set of fuel orifices through which a fuel flow is supplied to the mixing tube, wherein the set of fuel orifices is located downstream of the outer air flow path and downstream of the subset of the set of fluid diodes located within the outer air flow path.

2. (canceled)3. The gas turbine engine of claim 1, wherein the flange is located at an upstream end of the outer air flow path and is a hooked flange.

4. The gas turbine engine of claim 1, wherein the fuel nozzle further comprises a pair of circumferentially opposing walls defining the outer air flow path circumferentially therebetween.

5. The gas turbine engine of claim 4, wherein the subset of the set of fluid diodes located within the outer air flow path extends from the pair of circumferentially opposing walls and into the outer air flow path.

6. The gas turbine engine of claim 4, wherein the outer air flow path extends circumferentially about the fuel nozzle centerline greater than or equal to π / 8 radians and less than or equal to 2π radians.

7. The gas turbine engine of claim 4, wherein the subset of the set of fluid diodes located in the outer air flow path includes a plurality of fluid diodes circumferentially spaced within the outer air flow path.

8. The gas turbine engine of claim 1, wherein the fuel nozzle further includes an annular splitter that separates the inner air flow path and the outer air flow path, the annular splitter being tapered at an angle β with respect to a reference line parallel to the fuel nozzle centerline, the angle β being in a range from greater than or equal to 10° and less than or equal to 45°.

9. The gas turbine engine of claim 1, wherein the set of fluid diodes generates a pressure wave having a frequency of greater than or equal to 100 Hertz and less than or equal to 5000 Hertz.

10. The gas turbine engine of claim 1, wherein a fluid diode of the set of fluid diodes has a wave or linear shape.

11. The gas turbine engine of claim 1, wherein the fuel nozzle further comprises a swirler located within the inner air flow path and imparting a swirl to the first air flow.

12. The gas turbine engine of claim 11, wherein:the swirler is an upstream swirler;the subset of the set of fluid diodes located within the outer air flow path is a subset of upstream air flow path diodes;the fuel nozzle further includes a downstream swirler located downstream of the upstream swirler; andthe set of fluid diodes further includes a subset of downstream air flow path diodes located downstream of the subset of upstream air flow path diodes.

13. The gas turbine engine of claim 1, wherein the fuel nozzle further comprises a swirler located within the compressed air passage, and the set of fluid diodes includes a subset of the set of fluid diodes located within the swirler.

14. The gas turbine engine of claim 13, wherein the swirler includes a set of vanes, and the subset of the set of fluid diodes located within the swirler extends from a vane of the set of vanes.

15. The gas turbine engine of claim 1, wherein the set of fluid diodes further includes a subset of the set of fluid diodes located within the fuel supply and generating vortices within the fuel flow.

16. The gas turbine engine of claim 15, wherein the set of fuel orifices includes a plurality of fuel orifices, the fuel supply includes a fuel distribution passage fluidly coupled to two or more fuel orifices of the set of fuel orifices, and the set of fluid diodes includes a subset of the set of fluid diodes located within the fuel distribution passage.

17. The gas turbine engine of claim 16, wherein the fuel distribution passage is located exterior to the fuel nozzle body.

18. The gas turbine engine of claim 15, wherein the fuel supply includes a set of fuel inlet passages that each open to the mixing tube at a respective fuel orifice of the set of fuel orifices, and the set of fluid diodes includes a subset of the set of fluid diodes at least partially located in the fuel inlet passage.

19. The gas turbine engine of claim 15, wherein the fuel nozzle further comprises a centerbody coupled to the fuel nozzle body and extending axially with respect to the fuel nozzle centerline through the compressed air passage;wherein at least a portion of the fuel supply is formed within the centerbody; andwherein the set of fluid diodes includes a subset of the set of fluid diodes located within the portion of the fuel supply formed within the centerbody.

20. The gas turbine engine of claim 1, wherein the fuel supply feeds a flow of hydrogen-containing fuel to the mixing tube.

21. The gas turbine engine of claim 3, wherein the hooked flange has an L-shape or a J-shape.

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