Hydrogen-compatible fuel injectors and assemblies

Abstract

We provide hydrogen-compatible fuel injectors for gas turbine engine combustors. [Solution] The fuel injector 200 includes an annular body extending from a first end 301 to a second end 302, and a fuel circuit 340 at least partially located on the annular body. The annular body defines a central axis 303 extending from the first end to the second end. The fuel circuit includes a fuel plenum 345, a primary fuel outlet 348 fluidly communicating with the fuel plenum and extending along the central axis, and a plurality of secondary fuel outlets 350 fluidly communicating with the fuel plenum and arranged radially around the primary fuel outlet. The fuel injector also includes a first plurality of fluid channels 325 arranged radially around the central axis, and a second plurality of fluid channels arranged radially around the first plurality of fluid channels.

Description

Technical Field

[0001] The present disclosure generally relates to fuel injectors for gas turbine combustors.

Background Art

[0002] Turbo machines are used in various industries and applications for energy transfer purposes. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid entering the gas turbine engine and supplies the compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed within the combustion section and burned within the combustion chamber to generate high-pressure and high-temperature combustion gases. The combustion gases flow from the combustion section into the turbine section, where they expand to generate work. For example, the expansion of the combustion gases in the turbine section can rotate a rotor shaft connected to a generator to generate electricity. Then, the combustion gases exit the gas turbine engine through the exhaust section.

[0003] In some combustors, the generation of combustion gases occurs in two or more axially spaced-apart stages. Such combustors are herein referred to as including an "axial fuel staging" (AFS) system, which delivers fuel and oxidant to one or more fuel injectors downstream of the head end of the combustor. In a combustor having an AFS system, a primary fuel nozzle at the upstream end of the combustor injects fuel and air (or a fuel / air mixture) axially into a primary combustion zone, and an AFS fuel injector located at a location downstream of the primary fuel nozzle injects fuel and air (or a second fuel / air mixture) as a crossflow into a secondary combustion zone downstream of the primary combustion zone. The crossflow generally crosses the flow of combustion products from the primary combustion zone.

[0004] Conventional gas turbine engines include one or more combustors that burn a mixture of natural gas and air in a combustion chamber to produce high-pressure, high-temperature combustion gases. By-products include nitrogen oxides (NOx), carbon dioxide (CO2), and other pollutants, which are generated and emitted through the exhaust section. Regulatory requirements for low emissions from gas turbines are becoming increasingly stringent, and environmental agencies worldwide are now demanding even lower emissions of NOx and other pollutants from both new and existing gas turbines.

[0005] Burning a mixture of natural gas and a large amount of hydrogen in a combustor, and / or burning pure hydrogen instead of natural gas, significantly reduces or eliminates CO2 emissions. However, because the combustion characteristics of hydrogen differ from those of natural gas, conventional combustion systems, including conventional AFS fuel injectors, cannot burn high levels of hydrogen and / or pure hydrogen without problems. For example, burning high levels of hydrogen and / or pure hydrogen in a conventional combustion system can promote flashback or flame-holding conditions, where the combustion flame moves towards the fuel supplied by the injector, potentially causing serious damage to the injector in a relatively short time.

[0006] Therefore, there is a need in the art for a fuel injector that can deliver alternative fuels (such as hydrogen) and air to the secondary combustion zone without causing flame-holding or flashback problems. [Overview of the Initiative]

[0007] The embodiments and advantages of the fuel injectors and fuel injection assemblies described herein are partially described in the following description, or become apparent from the description, or can be learned through practice of the art.

[0008] According to one embodiment, a fuel injector for a gas turbine combustor is provided. The fuel injector includes an annular body extending from a first end to a second end, and a fuel circuit at least partially located on the annular body. The annular body defines a central axis extending from the first end to the second end. The fuel circuit includes a fuel plenum, a primary fuel outlet fluidly communicating with the fuel plenum and extending along the central axis, and a plurality of secondary fuel outlets fluidly communicating with the fuel plenum and arranged radially around the primary fuel outlet. The fuel injector also includes a first plurality of fluid channels arranged radially around the central axis, and a second plurality of fluid channels arranged radially around the first plurality of fluid channels. The first plurality of fluid channels fluidly communicate with a plurality of secondary fuel outlets.

[0009] According to another embodiment, a combustor is provided. The combustor includes at least one fuel source, a combustion liner extending downstream and defining a combustion chamber, an outer sleeve disposed apart from the combustion liner and surrounding the combustion liner such that an annular portion is defined between the combustion liner and the outer sleeve, and a fuel injection assembly in fluid communication with at least one fuel source. The fuel injection assembly includes a housing extending between a first end and a second end. The first end of the housing defines a fuel chamber in fluid communication with at least one fuel source, and the second end of the housing defines at least one mixing chamber. At least one fuel injector is disposed in the housing and in fluid communication with the fuel chamber and at least one mixing chamber. The at least one fuel injector includes an annular body extending from the first end to the second end, and a fuel circuit at least partially disposed in the annular body. The annular body defines a central axis extending from the first end to the second end. The fuel circuit includes a fuel inlet nozzle fluid-communicating with a fuel chamber, a fuel plenum fluid-communicating with the fuel inlet nozzle, a primary fuel outlet fluid-communicating with the fuel plenum and extending along a central axis, a plurality of secondary fuel outlets fluid-communicating with the fuel plenum and arranged radially around the primary fuel outlet, a first plurality of fluid channels arranged radially around a central axis, and a second plurality of fluid channels arranged radially around the first plurality of fluid channels. The first plurality of fluid channels fluid-communicate with the plurality of secondary fuel outlets.

[0010] These and other features, aspects, and advantages of the fuel injector and fuel injection assembly will be best understood by referring to the following description and the appended claims. The appended drawings, which are incorporated herein and constitute part of this specification, illustrate embodiments of the art and, together with the description in the specification, are useful in explaining the principles of the art.

[0011] This specification, with reference to the accompanying drawings, provides a complete and implementable disclosure of the fuel injector and fuel injection assembly, including the best modes of fabrication and use of the system and method intended for those skilled in the art. [Brief explanation of the drawing]

[0012] [Figure 1] This is a schematic diagram of a turbomachinery according to an embodiment of the present disclosure. [Figure 2] This is a schematic diagram of a combustor that may be used in the turbomachinery shown in Figure 1, according to an embodiment of the present disclosure. [Figure 3A] This is a perspective view of a fuel injector that may be used in the combustor shown in Figure 2, according to an embodiment of the present disclosure. [Figure 3B] This is an internal cross-sectional view of the fuel injector shown in Figure 3A, according to an embodiment of the present disclosure. [Figure 3C] This is a bottom view of the fuel injector shown in Figure 3A, according to an embodiment of the present disclosure. [Figure 3D] This is a perspective cross-sectional view of the fuel injector shown in Figure 3A according to an embodiment of the present disclosure. [Figure 3E] This is a cross-sectional view of the fuel injector shown in Figure 3A according to an embodiment of the present disclosure. [Figure 3F] This is a cross-sectional view of the fuel injector shown in Figure 3A along line FF in Figure 3C, according to an embodiment of the present disclosure. [Figure 4A] This is a top view of a fuel injection assembly that may be used in the combustor shown in Figure 2, according to an embodiment of the present disclosure. [Figure 4B] This is a side view of the fuel injection assembly shown in Figure 4A, according to an embodiment of the present disclosure. [Figure 4C] This is a bottom view of the fuel injection assembly shown in Figure 4A, according to an embodiment of the present disclosure. [Figure 4D] This is an end view of the fuel injection assembly shown in Figure 4A, according to an embodiment of the present disclosure. [Figure 4E] This is a cross-sectional side view of the fuel injection assembly of Figure 4A along line EE, according to an embodiment of the present disclosure. [Figure 4F] This is a cross-sectional view of the fuel injection assembly shown in Figure 4A along line FF in Figure 4B, according to an embodiment of the present disclosure. [Figure 4G] This is a detailed cross-sectional view of the fuel injection assembly shown in Figure 4F, according to an embodiment of the present disclosure. [Figure 5A]A cross-sectional view of a fuel injector according to an embodiment of the present disclosure. [Figure 5B] A bottom perspective view of the fuel injector of FIG. 5A according to an embodiment of the present disclosure.

Embodiments for Carrying Out the Invention

[0013] Here, embodiments of the present fuel injector and fuel injection assembly will be referred to in detail. In the drawings, one or more examples thereof are shown. Each example is provided for the purpose of explaining the present technology and does not limit the present technology. In fact, it will be apparent to those skilled in the art that modifications and changes are possible in the present technology without departing from the scope or spirit of the claimed technology. For example, features illustrated or described as part of one embodiment can also be used with another embodiment to yield a further embodiment. Accordingly, the present disclosure is intended to cover such modifications and changes within the scope of the appended claims and their equivalents.

[0014] The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described as "exemplary" herein should not necessarily be construed as being more preferred or advantageous than other implementations. In addition, unless otherwise specified, all embodiments described herein should be considered exemplary.

[0015] Embodiments for carrying out the invention use numerical and alphanumeric codes to refer to features within the drawings. Similar or like codes in the drawings and description are used to refer to similar or like parts of the subject technology. As used herein, the terms "first," "second," and "third" can be used interchangeably to distinguish one component from another and are not intended to imply the position or importance of individual components.

[0016] The term "fluid" can refer to a gas or a liquid. The term "fluid communication" means that a fluid can flow or be conveyed between specified areas.

[0017] As used herein, the terms "upstream" (or "forward") and "downstream" (or "rearward") refer to the relative direction with respect to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction in which the fluid flows. The term "radially" refers to a relative direction that is substantially perpendicular to the axial centerline of a particular component, the term "axially" refers to a relative direction that is substantially parallel and / or coaxial with the axial centerline of a particular component, and the term "circumferentially" refers to a relative direction that extends around the axial centerline of a particular component.

[0018] Approximating terms such as "about", "approximately", "generally", and "substantially" are not limited to the exact values specified. In at least some cases, the language indicating approximation may correspond to the accuracy of the equipment for measuring the value, or to the accuracy of the method or machine for constructing or manufacturing the component and / or system. For example, the language indicating approximation may refer to being within a margin of 1, 2, 4, 5, 10, 15, or 20% of any of the individual values, ranges of values, and / or endpoints defining the range of values. When used in the context of an angle or direction, such terms include within the range of plus or minus 5 degrees of the described angle or direction. For example, "generally perpendicular" includes directions within 5 degrees of perpendicular in either direction, clockwise or counterclockwise.

[0019] Terms such as “combined,” “fixed,” and “attached” refer to both direct joining, fixing, or attachment and indirect joining, fixing, or attachment via one or more intermediate components or features, unless otherwise specified herein. Terms such as “directly combined,” “directly fixed,” and “directly attached” indicate that a first component is joined to a second component without an intervening structure. As used herein, the terms “comprises,” “comprising,” “includes,” “including,” “has,” “having,” or any other variations thereof are intended to encompass non-exclusive inclusion. For example, a process, method, article, or apparatus containing a list of features is not necessarily limited to those features alone, and may include other features not expressly enumerated, or other features specific to such process, method, article, or apparatus.

[0020] Here, and throughout the specification and claims, the limitation of scope includes all sub-scopes that are identified and contained therein unless otherwise indicated by context or wording. For example, all scopes disclosed herein include endpoints, which are independently combinable with respect to one another.

[0021] As used herein, the term “premixing” may be used to describe an upstream component, passage, or cavity in each combustion zone where mixing of two (or more) fluids occurs. For example, “premixing” may be used to describe a component, passage, or cavity in which two fluids (such as fuel and air) are mixed together before being discharged from such component, passage, or cavity (for example, into the combustion zone).

[0022] Referring here to the drawings, Figure 1 shows a schematic diagram of an exemplary embodiment of a turbomachinery, which in the illustrated embodiment is a gas turbine engine 10. Although industrial or onshore gas turbines are shown and described herein, this disclosure is not limited to industrial or onshore gas turbine engines unless specifically stated in the claims. For example, the technologies described herein can be used in any type of turbomachinery, including, but not limited to, steam turbines, aircraft gas turbines, or marine gas turbines.

[0023] As shown in the figure, the gas turbine engine 10 generally includes an inlet section 12, a compressor section 14 located downstream of the inlet section 12, a plurality of combustors 17 (shown in Figure 2) in a combustion section 16 located downstream of the compressor section 14, a turbine section 18 located downstream of the combustion section 16, and an exhaust section 20 located downstream of the turbine section 18. In addition, the gas turbine engine 10 may include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18. The shafts 22 may be coupled to a generator (not shown) for generating electricity.

[0024] The compressor section 14 may generally include a plurality of rotor disks 24 (one of which is illustrated) and a plurality of rotor blades 26 extending radially outward from each rotor disk 24 and connected to each rotor disk 24. Each rotor disk 24 may then be coupled to or form part of the upstream portion of a shaft 22 extending through the compressor section 14. The compressor section 14 further includes a plurality of fixed vanes (not shown) arranged in stages on the rotor blades 26 to guide the flow toward the rotor blades 26.

[0025] The turbine section 18 may generally include a plurality of rotor disks 28 (one of which is illustrated) and a plurality of rotor blades 30 extending radially outward from each rotor disk 28 and interconnected with each rotor disk 28. Each rotor disk 28 may then be coupled to or form part of the downstream portion of a shaft 22 extending through the turbine section 18. The turbine section 18 further includes an outer casing 31 circumferentially surrounding the downstream portion of the shaft 22 and the rotor blades 30, thereby at least partially defining a hot gas path 32 through the turbine section 18. The turbine section 18 further includes a plurality of fixed vanes (not shown) arranged in stages with the rotor blades 30 and directing flow toward the rotor blades 30.

[0026] During operation, a working fluid such as air flows through the inlet section 12 into the compressor section 14, where it is gradually compressed by multiple compressor stages of rotor blades 26 and fixed vanes, thus supplying compressed air 15 to the combustors 17 of the combustion section 16. The compressed air 15 is mixed with fuel and burned in each combustor 17 to produce combustion gases 34. The combustion gases 34 flow from the combustion section 16 through the hot gas path 32 into the turbine section 18, where energy (kinetic energy and / or thermal energy) is transferred from the combustion gases 34 to the rotor blades 30, causing the shaft 22 to rotate. This mechanical rotational energy can then be used to power the compressor section 14 and / or generate electricity. The combustion gases 34 exiting the turbine section 18 are then exhausted from the gas turbine engine 10 through the exhaust section 20.

[0027] Figure 2 is a schematic diagram of a combustor 17 that may be included in the combustion section 16 of a gas turbine engine 10. The combustion section 16 may be a cannular combustion system. In a cannular combustion system, multiple combustors 17 (e.g., 8, 10, 12, 14, 16, or more) are arranged in an annular array around the shaft 22.

[0028] As shown in Figure 2, the combustor 17 may define a cylindrical coordinate system. The cylindrical coordinate system may define an axial direction A (e.g., downstream direction) substantially parallel to and / or along the axial centerline 170 of the combustor 17, a radial direction R perpendicular to the axial centerline 170, and a circumferential direction C extending around the axial centerline 170.

[0029] The combustor 17 includes a combustion liner 46 that defines a combustion chamber 70 in which combustion occurs. The combustion liner 46 may be positioned within an outer sleeve 48 such that an annular portion 47 is formed between the combustion liner 46 and the outer sleeve 48 (i.e., it may be circumferentially enclosed by the outer sleeve 48). The combustion liner 46 can contain combustion gases and transport them to the turbine section 18. As shown in Figure 2, the combustion liner 46 may extend between at least one fuel nozzle 40 and the rear frame 118. The combustion liner 46 may have a substantially cylindrical liner portion and a tapered transition portion separate from the substantially cylindrical liner portion, as in many conventional combustion systems. Alternatively, the combustion liner 46 may have a unibody configuration in which the substantially cylindrical portion and the tapered portion are integrated with each other. Thus, the description of the combustion liner 46 herein is intended to encompass both conventional combustion systems having separate liners and transition pieces and combustion systems having a unibody liner. Furthermore, the present disclosure is also applicable to combustion systems in which the transition piece and the first-stage nozzle of the turbine section 18 are integrated into a single unit (without the rear frame 118), which may be called a “transition nozzle” or “integrated outlet piece.”

[0030] Figure 2 shows a combustor 17 having both at least one fuel nozzle 40 and a fuel injection assembly 80 (also called an axial fuel staging ("AFS") system), as will be further described herein. At least one fuel nozzle 40 may be located at the front end of the combustor 17. Fuel may be introduced into at least one fuel nozzle 40 through a fuel supply conduit 38 extending through an end cover 42. At least one fuel nozzle 40 delivers fuel and compressed air 15 into a primary combustion zone 72 where combustion occurs. In some embodiments, the fuel and compressed air 15 are combined as a mixture (i.e., "premixed") before reaching the primary combustion zone 72.

[0031] To define an annular section 47 through which compressed air 15 flows to the head end of the combustor 17, the combustion liner 46 may be surrounded by an outer sleeve 48 positioned radially outward from the combustion liner 46. For example, the compressed air 15 may enter the annular section 47 through the outer sleeve 48 (e.g., via an impingement hole adjacent to the rear frame 118) and move toward the end cover 42, so that the compressed air 15 in the annular section 47 flows in the opposite direction to the combustion gas 172 in the combustion liner 46 (34 in Figure 1). Heat is convectivally transferred from the combustion liner 46 to the compressed air 15, thus cooling the combustion liner 46 and warming the compressed air 15.

[0032] In some exemplary embodiments, the outer sleeve 48 may include a flow sleeve and an impingement sleeve coupled together. The flow sleeve may be located at the front end, and the impingement sleeve may be located at the rear end. Alternatively, the outer sleeve 48 may have a configuration of a single body (or "uni-sleeve") in which the flow sleeve and the impingement sleeve are integrated with each other in the axial direction. As stated above, the description of the outer sleeve 48 herein is intended to encompass both conventional combustion systems having separate flow sleeves and impingement sleeves and combustion systems having a uni-sleeve outer sleeve.

[0033] The forward casing 50 and the end cover 42 of the combustor 17 define a head end air plenum 122 which includes at least one fuel nozzle 40. The at least one fuel nozzle 40 may be any type of fuel nozzle, such as a bundle fuel nozzle or a swirl nozzle (often called a “swozle”). The at least one fuel nozzle 40 may be located within the head end air plenum 122 which is at least partially defined by the forward casing 50. In many embodiments, the at least one fuel nozzle 40 may extend from the end cover 42. For example, each of the at least one fuel nozzle 40 may be coupled to the rear surface of the end cover 42 via a flange (not shown). As shown in Figure 2, the at least one fuel nozzle 40 may be partially enclosed by a combustion liner 46. The rear end or downstream end of the at least one fuel nozzle 40 extends through or collectively defines a cap plate 44 which defines the upstream end of the combustion chamber 70.

[0034] A first fuel source, such as a first fuel supply source 150 configured to supply the first fuel 158 to at least one fuel nozzle 40, and at least one fuel nozzle 40 may be in fluid communication. In many embodiments, the first fuel 158 may be a fuel mixture containing natural gas (e.g., one or more of methane, ethane, propane, or other suitable natural gases) and hydrogen. In some embodiments, hydrogen may constitute the majority of the fuel mixture (e.g., more than 50%). In other embodiments, the first fuel 158 may be pure natural gas or pure hydrogen (e.g., 100% hydrogen, which may or may not contain any trace amounts of contaminants), so that the first fuel is not a mixture of multiple fuels. In exemplary embodiments, the first fuel 158 and compressed air 15 may be mixed together in at least one fuel nozzle 40 before being discharged (or injected) into the primary combustion zone 72 by at least one fuel nozzle 40 to form a first mixture of compressed air 15 and the first fuel 158.

[0035] The forward casing 50 can be fluidly and mechanically connected to a compressor discharge casing 60 that defines a high-pressure plenum 66 around the combustion liner 46 and outer sleeve 48. Compressed air 15 from the compressor section 14 travels through the high-pressure plenum 66 and enters the combustor 17 through an opening (not shown) at the downstream end of the outer sleeve 48 (indicated by an arrow near the rear frame 118). The compressed air moves upstream through the annular section 47, is rotated by the end cover 42 and enters at least one fuel nozzle 40 to cool the head end. In particular, the compressed air 15 flows from the high-pressure plenum 66 into the annular section 47 at the rear end of the combustor 17 through an opening defined in the outer sleeve 48. The compressed air 15 moves upstream from the rear end of the combustor 17 to the head end air plenum 122, where it reverses direction and enters at least one fuel nozzle 40.

[0036] In the exemplary embodiment shown in Figure 2, the fuel injection assembly 80 is provided to deliver a second fuel / air mixture to a secondary combustion zone 74 downstream of the primary combustion zone 72. For example, the second flow of fuel and air may be introduced into the secondary combustion zone 74 by at least one fuel injector 200.

[0037] The primary combustion zone 72 and the secondary combustion zone 74 may each be a part of the combustion chamber 70 and therefore may be defined by the combustion liner 46. For example, the primary combustion zone 72 may be defined from the outlet of at least one fuel nozzle 40 to at least one fuel injector 200, and the secondary combustion zone 74 may be defined from at least one fuel injector 200 to the rear frame 118. In this arrangement, the foremost boundary of at least one fuel injector 200 may define the end of the primary combustion zone 72 and the beginning of the secondary combustion zone 74 (for example, at the axial position where the second flow of fuel and air is introduced).

[0038] Such a combustion system having axially separated combustion zones is described as an "axial fuel staging" (AFS) system. The fuel injection assemblies 80 may be arranged circumferentially apart from one another on the outer sleeve 48 (for example, equally spaced in some embodiments). In some exemplary embodiments, the combustor 17 may include four fuel injection assemblies 80 arranged circumferentially apart from one another and configured to inject a second mixture of fuel and air into the secondary combustion zone 74 via at least one fuel injector 200. In other exemplary embodiments, the combustor 17 may include any number of fuel injection assemblies 80 (e.g., 1, 2, 3, or up to 10).

[0039] As shown in Figure 2, each fuel injection assembly 80 may include at least one fuel injector 200. The fuel injector 200 may be coupled to the outer sleeve 48. For example, the fuel injector 200 may be coupled to the radially outer surface of the outer sleeve 48 and extend radially through the annular portion 47 between the outer sleeve 48 and the combustion liner 46.

[0040] The fuel supply conduit 102 may be fluidically coupled to each fuel injector 200. Each fuel injector 200 may be in fluid communication with a fuel source, such as a second fuel source 152 configured to supply a second fuel 160 to each fuel injector 200 via the fuel supply conduit 102. The second fuel source 152 may be the same as or different from the first fuel source 150 so that the fuel injectors 200 may be supplied with the same or different fuel as the fuel nozzles 40. In many embodiments, the second fuel 160 may be a fuel mixture containing natural gas (e.g., one or more of methane, ethane, propane, or other suitable natural gases) and hydrogen. In some embodiments, hydrogen may be the majority component of the fuel mixture (e.g., more than 50%). In other embodiments, the second fuel 160 may be pure natural gas or pure hydrogen (e.g., 100% hydrogen, which may or may not contain any trace amounts of contaminants) so that the first fuel is not a mixture of multiple fuels. In exemplary embodiments, the second fuel 160 and compressed air 15 may be mixed together in the fuel injector 200 before being injected into the secondary combustion zone 74 to form a mixture of compressed air 15 and the second fuel 160.

[0041] Figure 3A shows a perspective view of a fuel injector 200 that may be used in the combustor 17 of Figure 2 according to an embodiment of the present disclosure. Figure 3B shows an internal cross-sectional view of the fuel injector 200 of Figure 3A according to an embodiment of the present disclosure. Figure 3C shows a bottom view of the fuel injector 200 of Figure 3A according to an embodiment of the present disclosure. Figure 3D shows a perspective cross-sectional view of the fuel injector 200 of Figure 3A according to an embodiment of the present disclosure. Figure 3E shows a cross-sectional view of the fuel injector 200 of Figure 3A according to an embodiment of the present disclosure. Figure 3F is a cross-sectional view of the fuel injector of Figure 3A along line FF of Figure 3C according to an embodiment of the present disclosure. As described above, the fuel injector 200 may be one of a plurality of fuel injectors 200 arranged circumferentially around the combustor 17.

[0042] In at least one exemplary embodiment, the fuel injector 200 includes an annular body 300 extending between a first end 301 and a second end 302. The annular body 300 defines a central axis 303 extending from the first end 301 to the second end 302. The annular body 300 may include a first end portion 305, a second end portion 310, and a plurality of supports 315 extending between the first end portion 305 and the second end portion 310. For example, the plurality of supports 315 may be coupled between the periphery of the first end portion 305 and the periphery of the second end portion 310, and arranged spaced apart around them. Furthermore, the annular body 300 may define a chamber 320 between the first end portion 305, the second end portion 310, and the plurality of supports 315. The chamber 320 may be configured to be in fluid communication with the annular portion 47 of the combustor 17 (as shown in Figure 2). Thus, the chamber 320 can receive at least a portion of the compressed air 15 from the annular portion 47.

[0043] As shown in Figures 3A and 3B, the second end portion 310 includes a base portion 312 adjacent to the second end portion 302 and a top portion 314 extending from the base portion 312 toward the first end portion 301. For example, the top portion 314 extends into the chamber 320. In at least one exemplary embodiment, as shown, the base portion 312 may have a substantially cylindrical shape (for example, adjacent to the second end portion 302), and the top portion 314 may have a substantially conical shape.

[0044] Referring to Figures 3A and 3C, the second end portion 310 of the annular body 300 defines a first plurality of fluid channels 325 and a second plurality of fluid channels 330 arranged radially around the center axis 303. For example, the first plurality of fluid channels 325 may be arranged around the center axis 303 of the first ring 333, or the second plurality of fluid channels 330 may be arranged around the center axis 303 of the second ring 335. The second ring 335 of the second plurality of fluid channels 330 may be externally tangent to the first ring 333 of the first plurality of fluid channels 325. The first plurality of fluid channels 325 and the second plurality of fluid channels 330 may be arranged equally spaced around the center axis 303 (i.e., equally spaced in the circumferential direction). Furthermore, the second plurality of fluid channels 330 may be circumferentially offset from the first plurality of fluid channels 325. For example, each of the second plurality of fluid channels 330 may be circumferentially positioned between adjacent first plurality of fluid channels 325, with radial separation from them, as shown in at least Figures 3A and 3C.

[0045] In at least one exemplary embodiment, each of the first plurality of fluid channels 325 and each of the second plurality of fluid channels 330 have a conical shape. In other exemplary embodiments, each of the first plurality of fluid channels 325 and each of the second plurality of fluid channels 330 have a cylindrical shape.

[0046] In at least one exemplary embodiment, the number of first multiple fluid channels 325 may be equal to the number of second multiple fluid channels 330. For example, as shown in Figures 3A to 3D, there may be four of the first multiple fluid channels 325 and four of the second multiple fluid channels 330. However, it should be understood that there may be any number of first multiple fluid channels 325 and second multiple fluid channels 330. For example, there may be two or more of the first multiple fluid channels 325 and two or more of the second multiple fluid channels 330. Furthermore, in other exemplary embodiments, the number of first multiple fluid channels 325 may be different from the number of second multiple fluid channels 330.

[0047] Referring here to Figure 3B, at least a portion of the fuel circuit 340 is located in the annular body 300 of the fuel injector 200. For example, the first end portion 305 of the annular body 300 may define the fuel circuit 340. The fuel circuit 340 extends along the central axis 303 and includes a fuel inlet nozzle 343, a fuel plenum 345 in fluid communication with the fuel inlet nozzle 343, a primary fuel outlet 348 in fluid communication with the fuel plenum 345, and a plurality of secondary fuel outlets 350 in fluid communication with the fuel plenum 345. The fuel inlet nozzle 343 may be configured to receive a second fuel 160 from a second fuel source 152 via a fuel supply conduit 102 shown in Figure 2. The fuel plenum 345 may be configured to receive the second fuel 160 from the fuel inlet nozzle 343 and distribute the second fuel 160 to the primary fuel outlet 348 and the plurality of secondary fuel outlets 350. Furthermore, the primary fuel outlet 348 may be defined by at least a portion of the first end portion 305 and the second end portion 310 so that the first end portion 305 and the second end portion 310 are fluidly coupled.

[0048] As shown in Figure 3B, the primary fuel outlet 348 extends from the fuel plenum 345 along the center axis 303. Multiple secondary fuel outlets 350 are arranged around the primary fuel outlet 348, radially separated from it. For example, the multiple secondary fuel outlets 350 may be arranged equally separated around the center axis 303 and the primary fuel outlet 348. In at least one exemplary embodiment, the multiple secondary fuel outlets 350 are in fluid communication with the first multiple fluid channels 325. For example, the multiple secondary fuel outlets 350 may be aligned with the first multiple fluid channels 325, or may extend at least partially therein.

[0049] Referring here to Figure 3D, the primary fuel outlet 348 and the multiple secondary fuel outlets 350 have a substantially conical shape. For example, the outer surface of the primary fuel outlet 348 and the outer surfaces of the multiple secondary fuel outlets 350 are tapered from the first end 301 to the second end 302. The outer surface of the primary fuel outlet 348 may define a first fuel outlet wall angle 355 with respect to the centerline axis 303, as shown in Figure 3D. Similarly, the centerlines 326 of the multiple secondary fuel outlets 350 may define a second fuel outlet centerline angle 360, as also shown in Figure 3D. In some exemplary embodiments, the first fuel outlet wall angle 355 and the second fuel outlet centerline angle 360 ​​are equal. For example, the first fuel outlet wall angle 355 and the second fuel outlet centerline angle 360 ​​may be about 10°. In other exemplary embodiments, the first fuel outlet wall angle 355 may be between approximately 5° and approximately 30°, and the second fuel outlet centerline angle 360 ​​may be between approximately 5° and approximately 60°.

[0050] Referring to Figure 3E, the outer surfaces of the first plurality of fluid channels 325 define a first fluid channel angle 370 with respect to the centerline axis 303. In at least one exemplary embodiment, the first fluid channel angle 370 is equal to one or both of the first fuel outlet wall angle 355 and the second fuel outlet centerline angle 360. For example, the first fluid channel angle 370 may be about 10°. In other exemplary embodiments, the first fluid channel angle 370 may be between about 5° and about 30°.

[0051] Referring now to Figure 3F, which shows a cross-sectional view of the fuel injector in Figure 3A along line FF in Figure 3C, the second set of fluid channels 330 define a second fluid channel angle 375 with respect to the centerline axis 303 and the second fluid channel centerline axis 380. In some exemplary embodiments, the second fluid channel angle 375 may be greater than the first fluid channel angle 370. For example, the second fluid channel angle 375 may be about 20°. In other exemplary embodiments, the second fluid channel angle 375 may be between 10° and 60°.

[0052] Referring to Figures 3B to 3E, the fuel injector 200 defines a mixing chamber 365 downstream of the primary fuel outlet 348, the multiple secondary fuel outlets 350, the first multiple fluid channels 325, and the second multiple fluid channels 330. For example, the second end portion 310 of the fuel injector 200 may define at least a portion of the mixing chamber 365.

[0053] During operation, the fuel inlet nozzle 343 receives the second fuel 160 from the second fuel source 152 via the fuel supply conduit 102 (as shown in Figure 2). The second fuel 160 flows from the fuel inlet nozzle 343 to the fuel plenum 345, where it is distributed to the primary fuel outlet 348 and a plurality of secondary fuel outlets 350. The primary fuel outlet 348 and the plurality of secondary fuel outlets 350 are configured to inject the second fuel 160 into the mixing chamber 365. The plurality of secondary fuel outlets 350 may collectively inject about 30% to 70% of the fuel received from the fuel plenum 345 into the mixing chamber 365. For example, the plurality of secondary fuel outlets 350 may inject a higher percentage (more than 50%) of fuel into the mixing chamber 365 than the primary fuel outlet 348.

[0054] As described above, the chamber 320 is in fluid communication with the annular portion 47 of the combustor 17 (shown in Figure 2). Therefore, the chamber 320 is configured to receive at least a portion of the compressed air 15. The first plurality of fluid channels 325 and the second plurality of fluid channels 330 are in fluid communication with the chamber 320 and are configured to guide at least a portion of the compressed air 15 into the mixing chamber 365. The compressed air 15 mixes with the second fuel 160 in the mixing chamber 365 to form a fuel-air mixture.

[0055] Furthermore, compressed air 15 is introduced into the mixing chamber 365 from a first plurality of fluid channels 325 at a first fluid channel angle 370 (Figure 3B) and from a second plurality of fluid channels 330 at a second fluid channel angle 375 (Figure 3F). The second fuel 160 is introduced into the mixing chamber 365 from a primary fuel outlet 348 along the center axis 303 and from a plurality of secondary fuel outlets 350 at a second fuel outlet center axis angle 360 ​​(Figure 3D). By introducing the compressed air 15 and the second fuel 160 at such angles with respect to the center axis 303, a vortex structure is created that promotes the mixing of fuel and air.

[0056] For example, a first portion of the compressed air 15 flows through a first set of fluid channels 325 at a first fluid channel angle 370 and is discharged into the mixing chamber 365, and a second portion of the compressed air 15 also flows through a second set of fluid channels 330 at a second fluid channel angle 375 and is also discharged into the mixing chamber 365. Since the second fluid channel angle 375 is greater than the first fluid channel angle 370, the second portion of the compressed air 15 intersects with the first portion of the compressed air 15. The second portion of the compressed air 15 also intersects with at least a portion of the second fuel 160 entering the mixing chamber 365 from one or both of the primary fuel outlet 348 and the set of secondary fuel outlets 350. The second portion of the compressed air 15 moves inward toward the center axis 303, and the first portion of the compressed air 15 and at least a portion of the second fuel 160 are pushed outward from the center axis 303. Therefore, a double vortex is formed within the mixing chamber 365, promoting the mixing of air and fuel to form an air-fuel mixture. Alternatively, a double vortex may be formed by one pair of each of the first plurality of fluid channels 325 and the second plurality of fluid channels 330. For example, in an exemplary embodiment where four of the first plurality of fluid channels 325 and four of the second plurality of fluid channels 330 are present, four double vortices may be formed within the mixing chamber 365. From the mixing chamber 365, the fuel-air mixture may be injected into the secondary combustion zone 74 of the combustor 17 (Figure 2).

[0057] Figure 4A shows a top view of a fuel injection assembly 80 that may be used in the combustor 17 of Figure 2 according to an embodiment of the present disclosure. Figure 4B shows a side view of the fuel injection assembly 80 of Figure 4A according to an embodiment of the present disclosure. Figure 4C shows a bottom view of the fuel injection assembly 80 of Figure 4A according to an embodiment of the present disclosure. Figure 4D shows an end view of the fuel injection assembly 80 of Figure 4A according to an embodiment of the present disclosure. Figure 4E shows a cross-sectional view of the fuel injection assembly 80 of Figure 4A along line EE of Figure 4A according to an embodiment of the present disclosure. Figure 4F shows a cross-sectional view of the fuel injection assembly 80 of Figure 4A along line FF of Figure 4B according to an embodiment of the present disclosure. Figure 4G shows a detailed cross-sectional view of the fuel injection assembly 80 of Figure 4F according to an embodiment of the present disclosure.

[0058] The fuel injection assembly 80 includes a housing 400 extending between a first end 401 and a second end 402, as shown in Figure 4D. The housing 400 includes a first portion 403 adjacent to the first end 401 and a second portion 408 adjacent to the second end 402. Furthermore, a plurality of support structures 415 are coupled between the first portion 403 and the second portion 408. The housing 400 defines an air plenum 420 (Figures 4F to 4G) between the first portion 403, the second portion 408, and the plurality of support structures 415.

[0059] The housing 400 may include one or more mounting structures 435 configured to mount the housing 400 on the combustor 17. For example, one or more mounting structures 435 may be configured to secure the housing 400 to the outer sleeve 48 of the combustor (as shown in Figure 2). One or more mounting structures 435 may define at least one opening for receiving at least one fastener, such as a bolt, pin, or screw, for securing the housing 400 to the combustor 17. Furthermore, one or more mounting structures 435 may extend at least partially from around the second portion 408 of the housing 400. In other exemplary embodiments, one or more mounting structures 435 may extend at least partially from around the first portion 403 of the housing 400.

[0060] In at least one exemplary embodiment, a first portion 403 of the housing 400 defines a fuel chamber 405 (shown in Figures 4E to 4F), and a second portion 408 of the housing 400 defines at least one mixing chamber 410 (shown in Figures 4F to 4G). The fuel chamber 405 is configured to be in fluid communication with a fuel source, such as a second fuel supply source 152. For example, the fuel chamber 405 may be in fluid communication with the second fuel supply source 152 via a fuel supply conduit 102 shown in Figure 2.

[0061] In at least one exemplary embodiment, a plurality of fuel injectors 200 are arranged in a housing 400. For example, the plurality of fuel injectors 200 may be at least partially arranged within the air plenum 420 of the housing 400. The plurality of fuel injectors 200 may be in fluid communication downstream of a fuel chamber 405 and in fluid communication upstream of at least one mixing chamber 410. In such an arrangement, the fuel chamber 405 is common to the plurality of fuel injectors 200.

[0062] Referring to Figure 4C, the multiple fuel injectors 200 may be arranged in at least one row in the housing 400. For example, the housing 400 may include a first row 425 and a second row 430 of the multiple fuel injectors 200. The first row 425 and the second row 430 may each contain the same number of multiple fuel injectors 200. For example, each of the first row 425 and the second row 430 may contain four of the multiple fuel injectors 200 aligned axially with each other. In another exemplary embodiment, the first row 425 and the second row 430 may contain two or more of the multiple fuel injectors 200. In yet another exemplary embodiment, the housing 400 may contain three or more rows of the multiple fuel injectors 200. In yet another exemplary embodiment, the first row 425 of the fuel injectors 200 may be axially offset from the second row 430 of the fuel injectors 200.

[0063] Each of the multiple fuel injectors 200 is the same as or similar to the fuel injector 200 described above with respect to Figures 3A to 3F. For example, referring to Figures 4F to 4G, the fuel circuit 340 is in fluid communication with the fuel chamber 405 and the multiple fuel injectors 200. More specifically, the fuel circuit 340 includes a primary fuel outlet 348 and multiple secondary fuel outlets 350 for each fuel injector 200. The primary fuel outlet 348 and the multiple secondary fuel outlets 350 may extend from a first portion 403 to a second portion 408 of the housing 400. Furthermore, the primary fuel outlet 348 and the multiple secondary fuel outlets 350 may extend at least partially within the second portion 408 of the housing 400. Furthermore, the primary fuel outlet 348 and the multiple secondary fuel outlets 350 may be in direct fluid communication with the fuel chamber 405, as shown in Figures 4F to 4G. In other exemplary embodiments, the primary fuel outlet 348 and a number of secondary fuel outlets 350 may be in fluid communication with the fuel chamber 405 via either or both of the fuel inlet nozzle 343 and the fuel plenum 345, as shown in Figures 3B and 3D.

[0064] The multiple fuel injectors 200 also include a first plurality of fluid channels 325 and a second plurality of fluid channels 330. For example, a second portion 408 of the housing 400 may define the first plurality of fluid channels 325 and the second plurality of fluid channels 330. As shown in Figures 4F to 4G, the first plurality of fluid channels 325 and the second plurality of fluid channels 330 are in fluid communication with the air plenum 420 and at least one mixing chamber 410. Furthermore, a plurality of secondary fuel outlets 350 extend at least partially into the first plurality of fluid channels 325. Furthermore, a primary fuel outlet 348 may extend at least partially into at least one mixing chamber 410. Each of the mixing chambers 410 may be the same as or similar to the mixing chamber 365 described with respect to Figures 3A to 3F.

[0065] In at least one exemplary embodiment, at least one mixing chamber 410 is in fluid communication with the combustor 17 (Figure 2). For example, a plurality of fuel injectors 200 are configured to receive a second fuel 160 through a fuel chamber 405 and deliver the second fuel 160 to at least one mixing chamber 410 through a primary fuel outlet 348 and a plurality of secondary fuel outlets 350 of each fuel injector 200. Furthermore, each of the plurality of fuel injectors 200 receives at least a portion of compressed air 15 through an air plenum 420 and delivers the compressed air 15 to at least one mixing chamber 410 through a first plurality of fluid channels 325 and a second plurality of fluid channels 330. Thus, the compressed air 15 mixes with the second fuel 160 in at least one mixing chamber 410 to form a fuel-air mixture.

[0066] As described above with respect to Figures 3A to 3F, the mixing of the second fuel 160 and compressed air 15 in at least one mixing chamber 410 is enhanced based on the compressed air 15 entering at least one mixing chamber from the first plurality of fluid channels 325 at a first fluid channel angle 370 (Figure 3B) and from the second plurality of fluid channels 330 at a second fluid channel angle 375 (Figure 3F), and based on the second fuel 160 entering at least one mixing chamber 410 along the centerline axis 303 from the primary fuel outlet 348 and from the plurality of secondary fuel outlets 350 (shown in Figure 3D) at a second fuel outlet centerline angle 360. By delivering compressed air 15 and the second fuel 160 to at least one mixing chamber 410 at such angles, a double vortex structure is generated within the at least one mixing chamber 410, which enhances the mixing of the compressed air 15 and the second fuel 160 while reducing the possibility of flashback and / or flame holding within the mixing chamber 410. The at least one mixing chamber 410 of the housing 400 is in fluid communication with the combustor 17. Thus, the fuel-air mixture is injected from the at least one mixing chamber 410 into the secondary combustion zone 74 of the combustor 17 (as shown in Figure 2).

[0067] Figure 5A shows a cross-sectional view of a fuel injector 500 according to an embodiment of the present disclosure. Figure 5B shows a bottom perspective view of the fuel injector 500 of Figure 5A according to an embodiment of the present disclosure. The fuel injector 500 may be incorporated into the fuel injection assembly 80 instead of the fuel injector 200 described in relation to Figures 3A to 4G. Furthermore, the fuel injector 500 may be the same as or similar to the fuel injector 200 described in relation to Figures 3A to 3F.

[0068] For example, the fuel injector 500 includes a fuel circuit 340. The fuel circuit 340 includes a primary fuel outlet 348 and a plurality of secondary fuel outlets 350. Although not shown in Figures 5A to 5B, the fuel circuit 340 may also include one or both of a fuel inlet nozzle 343 and a fuel plenum 345. The fuel injector 500 also includes a first plurality of fluid channels 325 and a second plurality of fluid channels 330.

[0069] In at least one exemplary embodiment, the fuel injector 500 defines a plurality of wall extensions 505. The plurality of wall extensions 505 extend from the internal surface of the mixing chamber 365 adjacent to the second plurality of fluid channels 330. The plurality of wall extensions 505 may be arranged radially spaced evenly around the central axis 303. More specifically, in some exemplary embodiments, the plurality of wall extensions 505 may be arranged between the second plurality of fluid channels 330. Furthermore, the plurality of wall extensions 505 may be integrated with the fuel injector 200, such as being integrated with the mixing chamber 365. For example, the plurality of wall extensions 505 include isosurfaces or three-dimensional surfaces extending from the internal surface of the mixing chamber 365.

[0070] In at least one exemplary embodiment, the plurality of wall extensions 505 are positioned in a low-speed region of the mixing chamber 365. For example, in the absence of the plurality of wall extensions 505, the velocity of the second fuel 160 and compressed air 15 entering the mixing chamber 365 may be lower in such a low-speed region than in the surrounding area. Therefore, to prevent fuel from entering the low-speed region and thereby prevent flame retention in such a low-speed region, the plurality of wall extensions 505 may be configured to fill such a low-speed region.

[0071] This specification discloses the present invention, including its best mode, using examples, and enables any person skilled in the art to practice the invention, including the fabrication and use of any device or system, and the execution of any incorporated method. The patentable scope of the present invention is defined by the claims and may include other examples that a person skilled in the art may conceive. Such other embodiments are intended to be within the scope of the claims if they include structural elements that are not different from the language of the claims, or equivalent structural elements that do not substantially differ from the language of the claims.

[0072] Further aspects of the present invention are summarized by the subject matter of the following sections.

[0073] A fuel injector for a gas turbine combustor, comprising: an annular body extending from a first end to a second end, the annular body defining a central axis extending from the first end to the second end; a fuel circuit at least partially disposed on the annular body, the fuel circuit comprising: a fuel plenum; a primary fuel outlet fluidly communicating with the fuel plenum and extending along a central axis; a plurality of secondary fuel outlets fluidly communicating with the fuel plenum and arranged radially around the primary fuel outlet; and a first plurality of fluid channels arranged radially around a central axis, the first plurality of fluid channels fluidly communicating with a plurality of secondary fuel outlets; and a second plurality of fluid channels arranged radially around the first plurality of fluid channels.

[0074] A fuel injector having a primary fuel outlet and each of the multiple secondary fuel outlets having a conical shape, wherein the primary fuel outlet forms a first fuel outlet wall angle with respect to the center axis, and each of the multiple secondary fuel outlets forms a second fuel outlet centerline angle with respect to the center axis, one or more of these provisions.

[0075] One or more fuel injectors having a first fuel outlet wall angle of approximately 10° and a second fuel outlet centerline angle of approximately 10°.

[0076] A fuel injector comprising one or more of the following features: a plurality of secondary fuel outlets arranged at equal intervals around a central axis, a plurality of first fluid channels arranged at equal intervals around a central axis, and a plurality of second fluid channels arranged at equal intervals around a central axis.

[0077] One or more fuel injectors of these types, wherein multiple secondary fuel outlets are circumferentially aligned with a first set of fluid channels, and a second set of fluid channels are circumferentially offset from the first set of fluid channels.

[0078] One or more fuel injectors of these terms, wherein each of the second fluid channels forms a second fluid channel angle with respect to the central axis, and the second fluid channel angle is approximately 20°.

[0079] A fuel injector comprising one or more of the following provisions: a plurality of secondary fuel outlets comprising four secondary fuel outlets, a first plurality of fluid channels comprising four fluid channels, and a second plurality of fluid channels comprising four fluid channels.

[0080] One or more fuel injectors from these provisions, further comprising a mixing chamber located downstream of a primary fuel outlet, a plurality of secondary fuel outlets, a first plurality of fluid channels, and a second plurality of fluid channels, and having fluid communication with the primary fuel outlet, the plurality of secondary fuel outlets, the first plurality of fluid channels, and the second plurality of fluid channels.

[0081] One or more fuel injectors, wherein each fluid channel of the first plurality of fluid channels and each fluid channel of the second plurality of fluid channels have a conical shape.

[0082] A fuel injector comprising one or more of the following features, wherein the annular body defines a plurality of wall extensions extending from the inner surface of the annular body, the plurality of wall extensions are spaced apart around a central axis, and each wall extension of the plurality of wall extensions is positioned between circumferentially adjacent fluid channels of a second plurality of fluid channels.

[0083] A combustor comprising: a combustion liner extending downstream and defining a combustion chamber; an outer sleeve disposed apart from the combustion liner, surrounding the combustion liner such that an annular portion is defined between the combustion liner and the outer sleeve; a fuel injection assembly coupled to the outer sleeve and in fluid communication with a fuel source, wherein the fuel injection assembly comprises: a housing extending between a first housing end and a second housing end, the first housing end defining a fuel chamber configured to receive fuel from a fuel source, and the second housing end defining at least one mixing chamber; and at least one fuel injector disposed in the housing and in fluid communication with the fuel chamber and at least one mixing chamber, wherein at least one fuel injector extends from the first end to the second A combustor comprising: an annular body extending to the end thereof, the annular body defining a central axis extending from a first end to a second end; a fuel circuit at least partially disposed on the annular body, the fuel circuit comprising a fuel plenum fluid-communicating with a fuel chamber, a primary fuel outlet fluid-communicating with the fuel plenum and extending along the central axis, and a plurality of secondary fuel outlets fluid-communicating with the fuel plenum and arranged radially around the primary fuel outlet; and at least one fuel injector comprising a first plurality of fluid channels arranged radially around the central axis, the first plurality of fluid channels fluid-communicating with a plurality of secondary fuel outlets, and a second plurality of fluid channels arranged radially around the first plurality of fluid channels.

[0084] One or more of these combustors, wherein at least one fuel injector comprises a first plurality of fuel injectors arranged in a first row, and a second plurality of fuel injectors arranged in a second row adjacent to the first row.

[0085] One or more of these combustors, wherein a first plurality of fluid channels and a second plurality of fluid channels are in fluid communication with an annular portion between the combustion liner and the outer sleeve.

[0086] A combustor having one or more of the following features, wherein the primary fuel outlet and each of the multiple secondary fuel outlets are conical in shape, the primary fuel outlet forms a first fuel outlet wall angle with respect to the centerline axis, and each of the multiple secondary fuel outlets forms a second fuel outlet centerline angle with respect to the centerline axis.

[0087] One or more combustors having a first fuel outlet wall angle of approximately 10° and a second fuel outlet centerline angle of approximately 10°.

[0088] A combustor having one or more of the following features: a plurality of secondary fuel outlets arranged at equal intervals around a central axis, a plurality of first fluid channels arranged at equal intervals around a central axis, and a plurality of second fluid channels arranged at equal intervals around a central axis.

[0089] A combustor of one or more of these terms, wherein multiple secondary fuel outlets are circumferentially aligned with a first set of fluid channels, and a second set of fluid channels are circumferentially offset from the first set of fluid channels.

[0090] One or more combustors of these terms, wherein each of the second set of fluid channels forms a second fluid channel angle with respect to the central axis, and the second fluid channel angle is approximately 20°.

[0091] A combustor according to one or more of these provisions, wherein an annular body defines a plurality of wall extensions extending from the inner surface of the annular body, the plurality of wall extensions are spaced apart around a central axis, and each wall extension of the plurality of wall extensions is positioned between circumferentially adjacent fluid channels of a second plurality of fluid channels.

[0092] A combustor comprising a fuel supply conduit connected to a fuel source, wherein the fuel source supplies a fuel containing pure hydrogen or a fuel mixture of hydrogen and natural gas, and hydrogen is the majority component of the fuel mixture, one or more of these clauses. [Explanation of Symbols]

[0093] 10 Gas turbine engines 12 Entrance Section 14 Compressor Section 15 Compressed air 16 Combustion Section 17 Combustor 18 Turbine Section 20 Exhaust Section 22 shafts 24 Rotor Discs 26 rotor blades 28 Rotor Discs 30 rotor blades 31 Outer casing 32 High-temperature gas pathway 34 Combustion gases 38 Fuel supply conduit 40 Fuel Nozzles 42 End cover 44 Cap Plates 46 Combustion Liner 47 Ring section 48 Outer sleeve 50 Front casing 60 Compressor discharge casing 66 High-pressure plenum 70 Combustion Chamber 72 Primary Combustion Zone 74 Secondary combustion zone 80 Fuel injection assembly 102 Fuel supply conduit 118 Rear frame 122 Head end air plenum 150 First fuel source 152 Second fuel source, fuel source 158 First fuel 160 Second fuel 170 Axial centerline 172 Combustion gases 200 fuel injector 300 Ring-shaped body 301 First end 302 Second end 303 Centerline axis 305 First end portion 310 Second end portion 312 Base part 314 Top part 315 Multiple supports 320 Chambers 325 First Multiple Fluid Channels 326 center line 330 Second Multiple Fluid Channels 333 The First Ring 335 The Second Ring 340 fuel circuit 343 Fuel Inlet Nozzle 345 Fuel Plenum 348 Primary fuel outlet 350 Multiple secondary fuel outlets 355 First fuel outlet wall angle 360 Second fuel outlet centerline angle 365 Mixing Chamber 370 First fluid channel angle 375 Second fluid channel angle 380 centerline axis 400 Housing 401 First end 402 Second end 403 Part 1 405 Fuel Chamber 408 Part 2 410 Mixing Chamber 415 Multiple support structures 420 Air Plenum 425 1st column 430 Second column 435 One or more mounting structures 500 fuel injector 505 Multiple wall extensions A-axis R radial direction C circumferential direction

Claims

1. A fuel injector (200, 500) for the combustor (17) of a gas turbine engine (10), An annular body (300) extending from a first end (301) to a second end (302), wherein the annular body (300) defines a central axis (303) extending from the first end (301) to the second end (302), A fuel circuit (340) at least partially disposed on the annular body (300), wherein the fuel circuit (340) comprises a fuel plenum (345), a primary fuel outlet (348) that is in fluid communication with the fuel plenum (345) and extends along the central axis (303), and a plurality of secondary fuel outlets (350) that are in fluid communication with the fuel plenum (345) and are arranged radially around the primary fuel outlet (348), A plurality of first fluid channels (325) arranged radially around the central axis (303), wherein the plurality of first fluid channels (325) are in fluid communication with the plurality of secondary fuel outlets (350), A second plurality of fluid channels (330) are arranged radially around the first plurality of fluid channels (325), A fuel injector (200, 500) is provided.

2. The primary fuel outlet (348) and each of the plurality of secondary fuel outlets (350) have a conical shape. The primary fuel outlet (348) forms a first fuel outlet wall angle (355) with respect to the central axis (303), The fuel injector (200, 500) according to claim 1, wherein each of the plurality of secondary fuel outlets (350) forms a second fuel outlet centerline angle (360) with respect to the centerline axis (303).

3. The first fuel outlet wall angle (355) is approximately 10°, The second fuel outlet centerline angle (360°) is approximately 10°. The fuel injector (200, 500) according to claim 2.

4. The plurality of secondary fuel outlets (350) are arranged equally spaced apart around the central axis (303), The first plurality of fluid channels (325) are arranged equally spaced apart around the central axis (303), The second plurality of fluid channels (330) are arranged to be equally spaced apart around the central axis (303). The fuel injector (200, 500) according to claim 1.

5. The plurality of secondary fuel outlets (350) are aligned circumferentially with the first plurality of fluid channels (325), The second plurality of fluid channels (330) are offset circumferentially from the first plurality of fluid channels (325). The fuel injector (200, 500) according to claim 4.

6. Each of the second plurality of fluid channels (330) forms a second fluid channel angle (375) with respect to the central axis (303). The second fluid channel angle (375) is approximately 20°. The fuel injector (200, 500) according to claim 1.

7. The aforementioned plurality of secondary fuel outlets (350) are equipped with four secondary fuel outlets, The first plurality of fluid channels (325) comprises four fluid channels, The second plurality of fluid channels (330) comprises four fluid channels. The fuel injector (200, 500) according to claim 1.

8. The fuel injector (200, 500) according to claim 1, wherein the first plurality of fluid channels (325) and the second plurality of fluid channels (330) have a conical shape.

9. The fuel injector (200, 500) according to claim 1, further comprising a mixing chamber (365) located downstream of the primary fuel outlet (348), the plurality of secondary fuel outlets (350), the first plurality of fluid channels (325), and the second plurality of fluid channels (330), and in fluid communication with the primary fuel outlet (348), the plurality of secondary fuel outlets (350), the first plurality of fluid channels (325), and the second plurality of fluid channels (330).

10. The mixing chamber (365) defines a plurality of wall extensions (505) extending from the inner surface of the mixing chamber (365), and the plurality of wall extensions (505) are arranged spaced apart around the central axis (303). Each of the plurality of wall extensions (505) is located between adjacent fluid channels in the circumferential direction of the second plurality of fluid channels (330). The fuel injector (200, 500) according to claim 9.

11. Combustor (17), A combustion liner (46) extends downstream and defines the combustion chamber (70), An outer sleeve (48) is disposed at a distance from the combustion liner (46), and the annular portion (47) surrounds the combustion liner (46) such that it is defined between the combustion liner (46) and the outer sleeve (48). A fuel injection assembly (80) is coupled to the outer sleeve (48) and is in fluid communication with a fuel source (152), wherein the fuel injection assembly (80) A housing (400) extending between a first housing end (401) and a second housing end (402), wherein the first housing end (401) defines a fuel chamber (405) configured to receive fuel from the fuel source (152), and the second housing end (402) defines at least one mixing chamber (410), The housing (400) is provided with at least one fuel injector (200, 500) which is in fluid communication with the fuel chamber (405) and the at least one mixing chamber (410), A fuel injection assembly (80) and Equipped with, The combustor (17) wherein the at least one fuel injector (200, 500) is defined according to any one of claims 1 to 10.

12. The at least one fuel injector (200, 500) A first set of fuel injectors arranged in a first row (425), A second set of fuel injectors arranged in a second row (430) adjacent to the first row (425), The combustor (17) according to claim 11, comprising:

13. The combustor (17) according to claim 11, wherein the first plurality of fluid channels (325) and the second plurality of fluid channels (330) are in fluid communication with the annular portion (47) between the combustion liner (46) and the outer sleeve (48).

14. The combustor (17) according to claim 11, further comprising a fuel supply conduit (102) connected to the fuel source (152), wherein the fuel source (152) supplies a fuel comprising pure hydrogen or a fuel mixture of hydrogen and natural gas, and hydrogen is the majority component of the fuel mixture.

15. A gas turbine engine (10) comprising a compressor section (14), a combustion section (16) downstream of the compressor section (14), and a turbine section (18) located downstream of the compressor section (14), wherein the combustion section (16) includes the combustor (17) as defined in any one of claims 11 to 14.

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