Hydrogen-compatible fuel injector assembly

Abstract

The present invention provides a fuel injector assembly capable of delivering alternative fuels (such as hydrogen) and air to the secondary combustion zone without causing flame-holding or flashback problems. [Solution] A first housing portion 305 defines at least one fuel chamber 320, and a second housing portion 310 defines at least one mixing chamber 335. The fuel injection assembly 80 includes a fuel channel 330 extending along the central axis between the first housing portion 305 and the second housing portion 310. The fuel channel 330 is spaced apart along the length of the housing 300 and is in fluid communication with at least one fuel chamber 320 and at least one mixing chamber 335. Fluid channels 340, 345 are located in the second housing portion 310 and are in fluid communication with at least one mixing chamber 335 to facilitate the mixing of fuel and air. A combustor having the fuel injection assembly 80 is also provided.

Description

Technical Field

[0001] The present disclosure generally relates to a fuel injector assembly for a gas turbine combustor.

Background Art

[0002] Turbo machines are utilized 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 an oxidizer 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 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 injection assembly for a combustor of a gas turbine engine is provided. The fuel injection assembly includes a housing extending between a first end and a second end opposite the first end. The housing includes a first housing portion adjacent to the first end and a second housing portion adjacent to the second end. The first housing portion defines at least one fuel chamber, and the second housing portion defines at least one mixing chamber. The fuel injection assembly includes a plurality of fuel channels extending along a central axis between the first housing portion and the second housing portion. The plurality of fuel channels are in fluid communication with at least one fuel chamber and at least one mixing chamber. The plurality of fuel channels are spaced apart along the length of the housing. The fuel injection assembly also includes a first plurality of fluid channels located in the second housing portion and in fluid communication with at least one mixing chamber, and a second plurality of fluid channels located in the second housing portion and in fluid communication with at least one mixing chamber. The first set of fluid channels is arranged at a distance from the fuel channels, and the second set of fluid channels is arranged at a distance from the first set of fluid channels.

[0009] According to another embodiment, a combustor is provided. The combustor includes a combustion liner extending downstream and defining a combustion chamber; an outer sleeve positioned apart from the combustion liner, surrounding the combustion liner such that an annular portion is defined between the outer sleeve and the combustion liner; and a fuel injection assembly coupled to the outer sleeve and in fluid communication with a fuel source. The fuel injection assembly includes a housing extending between a first end and a second end opposite the first end. The housing includes a first housing portion adjacent to the first end and a second housing portion adjacent to the second end. The first housing portion defines at least one fuel chamber, and the second housing portion defines at least one mixing chamber. The fuel injection assembly includes a plurality of fuel channels extending along a central axis between the first housing portion and the second housing portion. The plurality of fuel channels are in fluid communication with at least one fuel chamber and at least one mixing chamber. The plurality of fuel channels are positioned apart along the length of the housing. The fuel injection assembly also includes a first plurality of fluid channels located in a second housing portion and in fluid communication with at least one mixing chamber, and a second plurality of fluid channels located in a second housing portion and in fluid communication with at least one mixing chamber. The first plurality of fluid channels are located apart from the plurality of fuel channels, and the second plurality of fluid channels are located apart from the first plurality of fluid channels.

[0010] These and other features, aspects, and advantages of the fuel injection assembly will be better 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] A complete and implementable disclosure of the fuel injection assembly, including the best modes of fabrication and use of the system and method, directed to those skilled in the art, is described herein with reference to the accompanying drawings. [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 3] This is a perspective 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 4A] This is a top view of the fuel injection assembly shown in Figure 3, according to an embodiment of the present disclosure. [Figure 4B] This is a bottom view of the fuel injection assembly shown in Figure 3, according to an embodiment of the present disclosure. [Figure 5] This is a cross-sectional view of the fuel injection assembly of Figure 3 along line VV in Figure 3, according to an embodiment of the present disclosure. [Figure 6] This is a cross-sectional view of the fuel injection assembly of Figure 3 along the line VI-VI in Figure 3, according to an embodiment of the present disclosure. [Figure 7] This is a cross-sectional view of the fuel injection assembly of Figure 3 along line VII-VII in Figure 3, according to an embodiment of the present disclosure. [Figure 8A] This is a cross-sectional view of the fuel injection assembly of Figure 3 along the line VIII-VIII in Figure 3, according to an embodiment of the present disclosure. [Figure 8B] This is a detailed cross-sectional view of the fuel injection assembly shown in Figure 3, according to an embodiment of the present disclosure. [Modes for carrying out the invention]

[0013] Hereinafter, embodiments of the fuel injector and fuel injection assembly are given in detail, with the drawings showing one or more examples. Each example is provided for illustrative purposes of the Art and is not intended to limit the Art. Indeed, it will be apparent to those skilled in the art that modifications and changes can be made in the Art without departing from the scope or spirit of the claimed Art. For example, features illustrated or described as part of one embodiment can also be used in conjunction with another embodiment to bring about further embodiments. Accordingly, this disclosure is intended to encompass such modifications and changes within the scope of the appended claims and their equivalents.

[0014] The term “exemplary” is used herein to mean “serving as an example, case, or illustration.” Any implementation described herein as “exemplary” should not necessarily be construed as being preferable or advantageous to other implementations. In addition, unless otherwise specified, all embodiments described herein should be considered exemplary.

[0015] Modes for carrying out the invention use numerals and letters to refer to features in the drawings. Similar or identical reference numerals in the drawings and description are used to refer to similar or identical parts of the subject art. 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 any individual component.

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

[0017] As used herein, the terms “upstream” (or “forward”) and “downstream” (or “backward”) refer to relative directions of fluid flow in a fluid path. For example, “upstream” refers to the direction in which the fluid is flowing, and “downstream” refers to the direction in which the fluid is flowing. The term “radially” refers to a relative direction substantially perpendicular to the axial centerline of a particular component, the term “axially” refers to a relative direction substantially parallel and / or coaxial with the axial centerline of a particular component, and the term “circumferentially” refers to a relative direction extending around the axial centerline of a particular component.

[0018] Approximate terms such as “approximately,” “about,” “generally,” and “substantially” are not limited to specified exact values. In at least some cases, approximation may correspond to the precision of an instrument used to measure a value, or to the precision of a method or machine used to construct or manufacture a component and / or system. For example, approximation may refer to being within a margin of 1, 2, 4, 5, 10, 15, or 20% at any of the endpoints defining an individual value, a range of values, and / or a range of values. When used in the context of angles or directions, such terms include a range of plus or minus 5 degrees from the stated angle or direction. For example, “generally perpendicular” includes any direction, e.g., a direction within 5 degrees from perpendicular in a clockwise or counterclockwise direction.

[0019] Terms such as "coupled", "fixed", "attached", etc., unless otherwise specified herein, refer to both direct coupling, fixing or attachment and indirect coupling, fixing or attachment through one or more intermediate components or features. Terms such as "directly coupled", "directly fixed", "directly attached", etc., indicate that the first component is joined to the second component without an intervening structure. As used herein, the terms "comprises", "comprising", "includes", "including", "has", "having", or any other variation thereof, are intended to cover non-exclusive inclusion. For example, a process, method, article, or apparatus that includes a list of features is not necessarily limited to only those features, and may include other features not explicitly listed or other features inherent to such a process, method, article, or apparatus.

[0020] Here, throughout the specification and claims, ranges of limitation, unless the context or language specifically indicates otherwise, include all sub-ranges subsumed therein. For example, all ranges disclosed herein include their endpoints, and the endpoints are combinable independently of each other.

[0021] As used herein, the term "premix" can be used to describe a component, passage, or cavity upstream of each combustion zone where mixing of two (or more) fluids occurs. For example, "premix" may be used to describe a component, passage, or cavity where two fluids (such as fuel and air) are mixed together before being discharged from such a component, passage, or cavity (e.g., into a combustion zone).

[0022] Referring now to the drawings, FIG. 1 shows a schematic view of an exemplary embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine engine 10. Although industrial or land-based gas turbines are shown and described herein, the present disclosure is not limited to industrial or land-based gas turbine engines unless specifically recited in the claims. For example, the technology described herein can be used in any type of turbomachine including, but not limited to, steam turbines, aircraft gas turbines, or marine gas turbines.

[0023] As shown, the gas turbine engine 10 generally includes an inlet section 12, a compressor section 14 disposed downstream of the inlet section 12, a plurality of combustors 17 (shown in FIG. 2) within a combustion section 16 disposed downstream of the compressor section 14, a turbine section 18 disposed downstream of the combustion section 16, and an exhaust section 20 disposed downstream of the turbine section 18. Additionally, the gas turbine engine 10 may include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18. The shaft 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 shown) and a plurality of rotor blades 26 extending radially outward from each rotor disk 24 and connected to each rotor disk 24. Next, each rotor disk 24 may be coupled to an upstream portion of the shaft 22 extending through the compressor section 14 or form a part thereof. The compressor section 14 further includes a plurality of stationary vanes (not shown) disposed in stages and guiding the flow with respect to 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, a 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, a second flow of fuel and air may be introduced into the secondary combustion zone 74 by the fuel injection assembly 80.

[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 the fuel injection assembly 80, and the secondary combustion zone 74 may be defined from the fuel injection assembly 80 to the rear frame 118. In this arrangement, the foremost boundary of the fuel injection assembly 80 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 the fuel injection assemblies 80. 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 be coupled to the outer sleeve 48. For example, each fuel injection assembly 80 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. In this example, the radial direction is defined with respect to the axial centerline 170 of the combustor 17.

[0040] A fuel supply conduit 102 may be fluidically coupled to each fuel injection assembly 80. The fuel injection assembly 80 may be in fluid communication with a fuel source, such as a second fuel source 152, which is configured to supply a second fuel 160 to the fuel injection assembly 80 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 injection assembly 80 may be supplied with the same or different fuel as at least one fuel nozzle 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 injection assembly 80 before being injected into the secondary combustion zone 74 to form a mixture of compressed air 15 and the second fuel 160.

[0041] Figure 3 shows a perspective 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. For clarity, some features are indicated by dashed lines.

[0042] The fuel injection assembly 80 includes a housing 300 extending between a first end 301 and a second end 302 opposite the first end 301. As illustrated and described herein, the first end 301 is the air inlet end of the fuel injection assembly 80, and the second end 302 is the outlet end of the fuel injection assembly 80. The injection axis of the fuel injection assembly 80 extending between the first end 301 and the second end 302 (e.g., the central axis 510 in Figure 5) defines the axial or perpendicular direction of the fuel injection assembly 80, where the perpendicular ("V") direction is substantially parallel to the radial direction of the combustor 17. The housing 300 may also be elongated, such that the housing 300 extends along the longitudinal axis 308 between a third end 303 and a fourth end 304 of the housing 300. The housing 300 may have a longitudinal length ("L") greater than its lateral ("T") width, and the longitudinal and lateral directions may be perpendicular to each other in the perpendicular ("V") direction. In the legend of Figure 3, the vertical arrows point downward to indicate the direction of injection of the flow from the fuel injection assembly 80. See also Figure 8A, which shows the vertical axis 802.

[0043] The housing 300 includes a first housing portion 305 adjacent to the first end 301 and a second housing portion 310 adjacent to the second end 302. The first housing portion 305 may define at least one fuel chamber 320. The at least one fuel chamber 320 may extend along the longitudinal axis 308 between the third end 303 and the fourth end 304.

[0044] At least one fuel chamber 320 may be configured to fluidly communicate with a fuel source, such as a second fuel supply source 152 shown in Figure 2. For example, at least one fuel chamber 320 may be configured to receive a second fuel 160 from the second fuel supply source 152 via a fuel supply conduit 102. Furthermore, the first housing portion 305 may define one or more fuel openings 325 that fluidly communicate with at least one fuel chamber 320. One or more fuel openings 325 may fluidly communicate with the fuel supply conduit 102.

[0045] In at least one exemplary embodiment, the housing 300 may be positioned such that the first housing portion 305 defines an air plenum 315 between the first housing portion 305 and the second housing portion 310, with the first housing portion 305 being spaced apart from the second housing portion 310 in a vertical direction V (i.e., parallel to the central axis 510). The air plenum 315 may be configured to fluidly communicate with the annular portion 47 of the combustor 17 shown in Figure 2. For example, the air plenum 315 may be configured to receive at least a portion of the compressed air 15 through the annular portion 47.

[0046] As shown in Figures 3 and 5, the housing 300 includes a plurality of fuel channels 330 that are in fluid communication with at least one fuel chamber 320 and extend between a first housing portion 305 and a second housing portion 310. At least a portion of the air plenum 315 may be defined between the plurality of fuel channels 330. In other words, the plurality of fuel channels 330 may extend through the air plenum and be enclosed by the air plenum 315. Furthermore, the plurality of fuel channels 330 may be spaced apart along the length of the housing 300, such as along the longitudinal axis 308 between a third end 303 and a fourth end 304. For example, the plurality of fuel channels 330 may be spaced evenly apart along the longitudinal axis 308.

[0047] In at least one exemplary embodiment, the second housing portion 310 defines at least one mixing chamber 335. The at least one mixing chamber 335 may extend along the longitudinal axis 308 between the third end 303 and the fourth end 304. Furthermore, a plurality of fuel channels 330 are in fluid communication with at least one mixing chamber 335.

[0048] The second housing portion 310 also defines a plurality of fluid channels or flow paths. For example, the second housing portion 310 defines a first plurality of fluid channels 340, a second plurality of fluid channels 345, and a third plurality of fluid channels 350, as will be described in detail below with reference to Figures 5 to 8. Each of the first plurality of fluid channels 340, the second plurality of fluid channels 345, and the third plurality of fluid channels 350 may be spaced apart along the length of the housing 300, such as along the longitudinal axis 308 between the third end 303 and the fourth end 304. For example, each of the first plurality of fluid channels 340, the second plurality of fluid channels 345, and the third plurality of fluid channels 350 may be spaced evenly apart along the longitudinal axis 308.

[0049] In at least one exemplary embodiment, the housing 300 of the fuel injection assembly 80 includes one or more mounting structures 355 extending from one or more corners of the housing 300. One or more mounting structures 355 may be configured to couple the fuel injection assembly 80 to the combustor 17. For example, one or more mounting structures 355 may couple the fuel injection assembly 80 to the outer sleeve 48 of the combustor 17 (as shown in Figure 2). Furthermore, one or more mounting structures 355 may define one or more openings 360 for receiving one or more fasteners, such as screws or bolts, for securing the fuel injection assembly 80 to the combustor 17.

[0050] Figure 4A shows a top view of the fuel injection assembly 80 of Figure 3 according to an embodiment of the present disclosure. Figure 4B shows a bottom view of the fuel injection assembly 80 of Figure 3 according to an embodiment of the present disclosure.

[0051] In at least one exemplary embodiment, the fuel injection assembly 80 includes at least one elongated fuel injector. The at least one fuel injector includes a plurality of fuel channels 330, a first plurality of fluid channels 340, a second plurality of fluid channels 345, and a third plurality of fluid channels 350. Referring to Figures 4A to 4B, the fuel injection assembly 80 may also include a first elongated fuel injector 400 and a second elongated fuel injector 405. The first elongated fuel injector 400 and the second elongated fuel injector 405 may extend along a longitudinal axis 308 between a third end 303 and a fourth end 304. Furthermore, the first elongated fuel injector 400 may be positioned axially separated from the second elongated fuel injector 405 (i.e., laterally separated). For example, the first elongated fuel injector 400 may be adjacent to the first side surface 401, and the second elongated fuel injector 405 may be adjacent to the second side surface.

[0052] The first elongated fuel injector 400 may be similar to or identical to the second elongated fuel injector 405. For example, both the first elongated fuel injector 400 and the second elongated fuel injector 405 include a plurality of fuel channels 330, a first plurality of fluid channels 340, a second plurality of fluid channels 345, and a third plurality of fluid channels 350. In some exemplary embodiments, the fuel injection assembly 80 may include three or more elongated fuel injectors. In additional exemplary embodiments, the fuel injection assembly 80 may include one of the elongated fuel injectors as shown in Figure 8.

[0053] Referring to Figure 4A, at least one fuel chamber 320 may include a first fuel chamber 410 and a second fuel chamber 415. At least one fuel chamber 320 may also define a slot 420 between the first fuel chamber 410 and the second fuel chamber 415. The slot 420 may be in fluid communication with an air plenum 315.

[0054] In at least one exemplary embodiment, the first fuel chamber 410 and the second fuel chamber 415 are fluidically coupled. For example, the first fuel chamber 410 and the second fuel chamber 415 may be fluidically coupled adjacent to one or both of the third end 303 and the fourth end 304. Furthermore, the first fuel chamber 410 and the second fuel chamber 415 may be fluidically coupled to one or more fuel openings 325. Moreover, the first fuel chamber 410 may be in fluid communication with a plurality of fuel channels 330 of the first elongated fuel injector 400, and the second fuel chamber 415 may be in fluid communication with a plurality of fuel channels 330 of the second elongated fuel injector 405.

[0055] Referring here to Figure 4B, at least one mixing chamber 335 of the fuel injection assembly 80 may include a first mixing chamber 425 and a second mixing chamber 430. For example, the first mixing chamber 425 may be associated with a first elongated fuel injector 400, and the second mixing chamber 430 may be associated with a second elongated fuel injector 405. Thus, the first mixing chamber 425 may be in fluid communication with a plurality of fuel channels 330, a first plurality of fluid channels 340, a second plurality of fluid channels 345, and a third plurality of fluid channels 350 of the first elongated fuel injector 400, and the second mixing chamber 430 may be in fluid communication with a plurality of fuel channels 330, a first plurality of fluid channels 340, a second plurality of fluid channels 345, and a third plurality of fluid channels 350 of the second elongated fuel injector 405.

[0056] In at least one exemplary embodiment, the first mixing chamber 425 is fluidically isolated from the second mixing chamber 430. For example, the second housing portion 310 may include a partition 435 extending along the longitudinal axis 308 between a third end 303 and a fourth end 304 between the first elongated fuel injector 400 and the second elongated fuel injector 405. In other exemplary embodiments, the fuel injection assembly includes a single mixing chamber that fluidly communicates with multiple fuel channels 330 of both the first elongated fuel injector 400 and the second elongated fuel injector 405, multiple first fluid channels 340, multiple second fluid channels 345, and multiple third fluid channels 350.

[0057] Figure 5 shows a cross-sectional view of the fuel injection assembly 80 of Figure 3 along line VV in Figure 3, according to an embodiment of the present disclosure.

[0058] In at least one exemplary embodiment, each of the plurality of fuel channels 330 includes a fuel outlet nozzle 500 that extends at least partially into one of at least one mixing chambers 335. The fuel outlet nozzle 500 may have a conical shape. For example, the fuel outlet angle 505 may be defined between the outer surface of the fuel outlet nozzle 500 and a central axis 510 that extends along the fuel channel 330 between a first end 301 and a second end 302. The fuel outlet angle 505 may be between about 5° and about 20°. For example, in some embodiments, the fuel outlet angle 505 may be about 10°.

[0059] As shown in Figure 5, the first plurality of fluid channels 340 may be arranged in the second housing portion 310 of the housing 300 at a first fluid channel angle 515. The first fluid channel angle 515 may be defined between a first fluid channel axis 520 extending through each of the fluid channels of the first plurality of fluid channels 340 and a central axis 510. In at least one exemplary embodiment, the first fluid channel angle 515 is equal to the fuel outlet angle 505. For example, the first fluid channel angle 515 may be between about 5° and about 20°. For example, in some embodiments, the first fluid channel angle 515 may be about 10°. In some exemplary embodiments, each of the first plurality of fluid channels 340 may have a substantially cylindrical or conical shape.

[0060] Figure 6 shows a cross-sectional view of the fuel injection assembly 80 of Figure 3 along line VI-VI in Figure 3, according to an embodiment of the present disclosure.

[0061] In at least one exemplary embodiment, each of the second plurality of fluid channels 345 is positioned in the second housing portion 310 of the housing 300 at a second fluid channel angle 600. The second fluid channel angle 600 may be defined between the second fluid channel axis 605 and the central axis 510. The second fluid channel angle 600 may be greater than one or both of the fuel outlet angle 505 and the first fluid channel angle 515. For example, the second fluid channel angle 600 may be between about 15° and about 35°. More specifically, the second fluid channel angle 600 may be about 20°. In some exemplary embodiments, each of the second plurality of fluid channels 345 may have a substantially cylindrical or conical shape.

[0062] Furthermore, as shown in Figure 6, the third plurality of fluid channels 350 are arranged in the second housing portion 310 of the housing 300 along the central axis 510. For example, the third plurality of fluid channels 350 extend parallel to the plurality of fuel channels 330. In at least one alternative embodiment, the third plurality of fluid channels 350 may be inclined with respect to the central axis 510. For example, the third plurality of fluid channels 350 may be inclined between about 0° and about 5° with respect to the central axis 510. In some exemplary embodiments, the third plurality of fluid channels 350 may have a substantially cylindrical or oval shape.

[0063] Figure 7 shows a cross-sectional view of the fuel injection assembly 80 of Figure 3 along line VII-VII in Figure 3, according to an embodiment of the present disclosure.

[0064] As described above with respect to Figures 4A to 4B, the fuel injection assembly 80 may include a first elongated fuel injector 400 and a second elongated fuel injector 405. As shown in Figure 7, the first elongated fuel injector 400 and the second elongated fuel injector 405 include a first row 700 and a second row 705 of the first plurality of fluid channels 340. The first row 700 and the second row 705 of the first plurality of fluid channels 340 are located on both sides of the plurality of fuel channels 330. For example, the first row 700 and the second row 705 of the first plurality of fluid channels 340 may be located on both sides of a central axis 510 (Figures 5 to 6) extending through the plurality of fuel channels 330. Furthermore, the first plurality of fluid channels 340 in the first row 700 and the second row 705 may be adjacent to the plurality of fuel channels 330 so that they are aligned with the plurality of fuel channels 330 (for example, in the longitudinal direction). In at least one exemplary embodiment, the first plurality of fluid channels 340 in the first row 700 and the second row 705 may be arranged equally spaced between the third end 303 and the fourth end 304.

[0065] In at least one exemplary embodiment, the first elongated fuel injector 400 and the second elongated fuel injector 405 also include a first row 710 of a second plurality of fluid channels 345 and a second row 715 of a second plurality of fluid channels 345. The first row 710 of the second plurality of fluid channels 345 and the second row 715 of the second plurality of fluid channels 345 are located on both sides of a central axis 510 (Figures 5-6) extending through the plurality of fuel channels 330. Furthermore, the first row 710 of the second plurality of fluid channels 345 and the second row 715 of the second plurality of fluid channels 345 are located on both sides of the plurality of fuel channels 330 and the first plurality of fluid channels 340. For example, the first row 710 of the second plurality of fluid channels 345 is adjacent to the first row 700 of the first plurality of fluid channels 340, and the second row 715 of the second plurality of fluid channels 345 is adjacent to the second row 705 of the first plurality of fluid channels 340.

[0066] Furthermore, as shown in Figure 7, the first row 710 and the second row 715 of the second plurality of fluid channels 345 are offset (for example, longitudinally) from the first row 700 and the second row 705 of the first plurality of fluid channels 340. For example, the first plurality of fluid channels 340 in the first row 700 and the second row 705 may be located between the second plurality of fluid channels 345 in the first row 710 and the second row 715. In at least one exemplary embodiment, the second plurality of fluid channels 345 in the first row 710 and the second row 715 may be arranged equally spaced between the third end 303 and the fourth end 304.

[0067] Referring further to Figure 7, the third plurality of fluid channels 350 may be arranged in the same row as the plurality of fuel channels 330 that extend between the third end 303 and the fourth end 304 of the first elongated fuel injector 400 and the second elongated fuel injector 405. For example, each of the plurality of fuel channels 330 may be arranged between adjacent fluid channels of the third plurality of fluid channels 350. Furthermore, the plurality of fuel channels 330 and the third plurality of fluid channels 350 may be arranged equally spaced between the third end 303 and the fourth end 304.

[0068] Figure 8A shows a cross-sectional view of the fuel injection assembly 80 of Figure 3 along line VIII-VIII in Figure 3, according to an embodiment of the present disclosure. Figure 8B shows a detailed cross-sectional view of the fuel injection assembly 80 of Figure 3, according to an embodiment of the present disclosure.

[0069] In at least one exemplary embodiment, the longitudinal axis 800 extends along the fuel injection assembly 80 between the third end 303 and the fourth end 304. For example, the longitudinal axis 800 may extend through the centers of a plurality of fuel channels 330 between the third end 303 and the fourth end 304. Furthermore, although only one elongated fuel injector of the fuel injection assembly 80 is shown in Figure 8A, the fuel injection assembly 80 may include two or more elongated fuel injectors, such as the first elongated fuel injector 400 and the second elongated fuel injector 405 described above.

[0070] In at least one exemplary embodiment, the second plurality of fluid channels 345 are inclined in a secondary direction along the longitudinal axis 800 with respect to a vertical axis 802 perpendicular to the longitudinal axis 800. The vertical axis 802 may also extend through each of the second plurality of fluid channels 345 parallel to the central axis 510. For example, the second plurality of fluid channels 345 in the first row 710 may be inclined in a first direction indicated by a first directional arrow 805, and the second plurality of fluid channels 345 in the second row 715 may be inclined in a second direction indicated by a second directional arrow 810. As shown in Figure 8A, the first direction may be substantially opposite to the second direction. For example, the first directional arrow 805 may extend toward a fourth end 304, and the second directional arrow 810 may extend toward a third end 303. In other exemplary embodiments, the first directional arrow 805 may extend toward the third end 303, and the second directional arrow 810 may extend toward the fourth end 304.

[0071] Furthermore, as shown in Figure 8B, the secondary direction angle 815 may be defined between the vertical axis 802 and each of the first directional arrow 805 and the second directional arrow 810. For example, the second plurality of fluid channels 345 in the first row 710 and the second row 715 may define a secondary direction angle 815 with respect to the vertical axis 802. In at least one exemplary embodiment, the secondary direction angle 815 is between about 0° and about 25° with respect to the vertical axis 802. For example, in some particular embodiments, the secondary direction angle 815 may be about 12°. More specifically, in some exemplary embodiments, the secondary direction angle 815 may be about 12.2° with respect to the vertical axis 802.

[0072] During operation, at least one fuel chamber 320 of the fuel injection assembly 80 is configured to receive fuel such as a second fuel 160 from a second fuel source 152. The second fuel 160 is delivered from at least one fuel chamber 320 to at least one mixing chamber 335 via a plurality of fuel channels 330 and a fuel outlet nozzle 500. Furthermore, air such as compressed air 15 is introduced into at least one mixing chamber 335 via a first plurality of fluid channels 340, a second plurality of fluid channels 345, and a third plurality of fluid channels 350 to create a vortex structure to facilitate the mixing of fuel and air. For example, the compressed air 15 is introduced into at least one mixing chamber 335 via the first plurality of fluid channels 340 at a first fluid channel angle 515 and via the second plurality of fluid channels 345 at a second fluid channel angle 600, as described above with respect to Figures 5 and 6. Furthermore, as described above with respect to Figures 8A to 8B, the compressed air 15 is also delivered to at least one mixing chamber 335 at a secondary angle via a second plurality of fluid channels 345. For example, the compressed air 15 enters at least one mixing chamber 335 via a second plurality of fluid channels 345 in the first row 710 in the first direction 805, and via a second plurality of fluid channels 345 in the second row 715 in the second direction 810.

[0073] In at least one exemplary embodiment, the angle at which compressed air 15 enters at least one mixing chamber 335 through the second plurality of fluid channels 345 is greater than the angle at which compressed air 15 enters at least one mixing chamber 335 through the first plurality of fluid channels 340. Thus, the first portion of compressed air 15 entering at least one mixing chamber 335 through the second plurality of fluid channels 345 intersects with the second portion of compressed air 15 entering through the first plurality of fluid channels 340. The first portion of compressed air 15 moves inward toward the central axis 510 extending through the plurality of fuel channels 330, while the second portion of air and at least a portion of the fuel are pushed outward from the central axis 510. Thus, a plurality of double vortices are formed within at least one mixing chamber 335, promoting the mixing of air and fuel within the at least one mixing chamber 335 to form an air-fuel mixture. The air-fuel mixture may be injected from at least one mixing chamber into the secondary combustion zone 74 of the combustor 17. Such a configuration reduces the possibility of flashback and flame hold when burning highly reactive fuels (such as hydrogen) or fuel mixtures containing a large amount of hydrogen. Furthermore, the improved mixture achieved by the fuel injection assembly 80 promotes complete combustion of the fuel, thereby reducing the formation of undesirable emissions.

[0074] 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.

[0075] Further aspects of the present invention are provided by the subject matter of the following clauses.

[0076] A fuel injection assembly for a combustor of a gas turbine engine, comprising a housing extending between a first end and a second end opposite to the first end, the housing comprising a first housing portion adjacent to the first end and a second housing portion adjacent to the second end, wherein the first housing portion defines at least one fuel chamber and the second housing portion defines at least one mixing chamber, and a plurality of fuel channels extending along a central axis between the first housing portion and the second housing portion, wherein the plurality of fuel channels define at least one fuel chamber and at least one A fuel injection assembly comprising: a plurality of fuel channels that are in fluid communication with a mixing chamber and are spaced apart along the length of the housing; a first plurality of fluid channels located in a second housing portion and in fluid communication with at least one mixing chamber, wherein the first plurality of fluid channels are spaced apart from the plurality of fuel channels; and a second plurality of fluid channels located in a second housing portion and in fluid communication with at least one mixing chamber, wherein the second plurality of fluid channels are spaced apart from the first plurality of fluid channels.

[0077] A fuel injection assembly comprising one or more of these provisions, wherein a second plurality of fluid channels are longitudinally offset from a first plurality of fluid channels.

[0078] A fuel injection assembly comprising a third plurality of fluid channels located in a second housing portion and in fluid communication with at least one mixing chamber, wherein the third plurality of fluid channels are spaced apart along the length of the housing, and each fuel channel of the plurality of fuel channels is located between adjacent fluid channels of the third plurality of fluid channels, one or more of these provisions.

[0079] A fuel injection assembly comprising one or more of these clauses, including a fuel outlet nozzle in which multiple fuel channels extend into at least one mixing chamber.

[0080] A fuel injection assembly comprising one or more of the following features: the fuel outlet nozzle has a conical shape, the outer surface of the fuel outlet nozzle defines a fuel outlet angle with respect to the central axis, and the fuel outlet angle is approximately 10°.

[0081] A fuel injection assembly comprising one or more of the following clauses, wherein each fluid channel of a first plurality of fluid channels defines a first fluid channel angle with respect to a central axis and a first axis extending through each of the fluid channels of the first plurality of fluid channels, and each fluid channel of a second plurality of fluid channels defines a second fluid channel angle with respect to a central axis and a second axis extending through each of the fluid channels of the second plurality of fluid channels, the second fluid channel angle being greater than the first fluid channel angle.

[0082] A fuel injection assembly having one or more of the following conditions: the first fluid channel angle is approximately 10°, the second fluid channel angle is approximately 20°, and the second plurality of fluid channels define a secondary angle with respect to a vertical axis extending through each of the second plurality of fluid channels parallel to the central axis, the secondary angle being approximately 12°.

[0083] A fuel injection assembly comprising one or more of the following clauses, wherein the first plurality of fluid channels includes a first row of the first fluid channels and a second row of the first fluid channels, with the first row of the first fluid channels and the second row of the first fluid channels positioned on either side of the central axis, and the second plurality of fluid channels includes a first row of the second fluid channels and a second row of the second fluid channels, with the first row of the second fluid channels and the second row of the second fluid channels positioned on either side of the central axis.

[0084] A fuel injection assembly comprising one or more of these clauses, wherein the first row of the second fluid channel is inclined in a first direction, the second row of the second fluid channel is inclined in a second direction, and the first direction is opposite to the second direction.

[0085] One or more fuel injection assemblies of these terms, wherein a first row of first fluid channels and a second row of first fluid channels are longitudinally aligned with a plurality of fuel channels.

[0086] A fuel injection assembly comprising a plurality of fuel channels, a first plurality of fluid channels, and a second plurality of fluid channels, each comprising elongated fuel injectors, and a fuel injection assembly comprising two or more elongated fuel injectors, one or more of these provisions.

[0087] A combustor comprising a combustion liner extending downstream and defining a combustion chamber, an outer sleeve positioned apart from the combustion liner and surrounding the combustion liner such that an annular portion is defined between the outer sleeve and the combustion liner, and 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 end and a second end opposite the first end, the housing comprising a first housing portion adjacent to the first end and a second housing portion adjacent to the second end, the first housing portion defining at least one fuel chamber and the second housing portion defining at least one mixing chamber, and a central axis between the first housing portion and the second housing portion. A combustor comprising: a plurality of fuel channels extending along a length, the plurality of fuel channels being in fluid communication with at least one fuel chamber and at least one mixing chamber, and the plurality of fuel channels being spaced apart along the length of the housing; a first plurality of fluid channels located in a second housing portion and in fluid communication with at least one mixing chamber, the first plurality of fluid channels being spaced apart from the plurality of fuel channels; and a second plurality of fluid channels located in a second housing portion and in fluid communication with at least one mixing chamber, the second plurality of fluid channels being spaced apart from the first plurality of fuel channels.

[0088] One or more combustors of these clauses, wherein at least one fuel chamber is in fluid communication with a fuel source via a fuel supply conduit, and the fuel source supplies a fuel containing pure hydrogen or a fuel mixture of hydrogen and natural gas, with hydrogen being the majority component of the fuel mixture.

[0089] One or more combustors of these terms, wherein the housing defines an air plenum between a first housing portion and a second housing portion, at least a portion of a plurality of fuel channels extends through the air plenum, and a plurality of first fluid channels and a plurality of second fluid channels are in fluid communication with the air plenum.

[0090] One or more of these combustors, in which the air plenum is in fluid communication with the annular portion.

[0091] A combustor comprising a third plurality of fluid channels arranged in a second housing portion and in fluid communication with at least one mixing chamber, wherein the third plurality of fluid channels are spaced apart along the length of the housing, and each fuel channel of the plurality of fuel channels is located between adjacent fluid channels of the third plurality of fluid channels, one or more of these provisions.

[0092] A combustor having one or more of the following conditions, wherein each of the first plurality of fluid channels defines a first fluid channel angle with respect to a central axis and a first axis extending through each of the fluid channels of the first plurality of fluid channels, and each of the second plurality of fluid channels defines a second fluid channel angle with respect to a central axis and a second axis extending through each of the fluid channels of the second plurality of fluid channels, the second fluid channel angle being greater than the first fluid channel angle.

[0093] A combustor having one or more of the following conditions: the first fluid channel angle is approximately 10°, the second fluid channel angle is approximately 20°, and the second plurality of fluid channels define a secondary angle with respect to a vertical axis extending through each of the second plurality of fluid channels parallel to the central axis, the secondary angle being approximately 12°.

[0094] One or more of these combustors, wherein the first plurality of fluid channels include a first row of the first fluid channels and a second row of the first fluid channels, the second row of the fluid channels being located on both sides of the central axis, and the second plurality of fluid channels include a first row of the second fluid channels and a second row of the second fluid channels, the first row of the second fluid channels and the second row of the second fluid channels being located on both sides of the central axis.

[0095] A combustor of one or more of these clauses, wherein the first row of the second fluid channel is inclined in a first direction, the second row of the second fluid channel is inclined in a second direction, and the first direction is opposite to the second direction. [Explanation of symbols]

[0096] 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 300 Housing 301 First end 302 Second end 303 Third end 304 The fourth end 305 First housing section 308 Longitudinal axis 310 Second housing section 315 Air Plenum 320 Fuel Chamber 325 Fuel opening 330 Multiple fuel channels 335 Mixing Chamber 340 First Multiple Fluid Channels 345 Second Multiple Fluid Channels 350 Third Multiple Fluid Channels 355 Mounting Structure 360 Opening 400 First elongated fuel injector 401 First Aspect 405 Second elongated fuel injector 410 First fuel chamber 415 Second fuel chamber 420 slots 425 First mixing chamber 430 Second mixing chamber 435 dividers 500 Fuel Outlet Nozzle 505 Fuel outlet angle 510 Center axis 515 First fluid channel angle 520 First fluid channel axis 600 Second fluid channel angle 605 Second fluid channel axis 700 1st column 705 Second column 710 First column 715 Second column 800 Longitudinal axis 802 vertical axis 805 First directional arrow 810 Second directional arrow 815 Secondary direction angle V vertical direction T horizontal direction L Longitudinal direction

Claims

1. A fuel injection assembly (80) for a combustor (17) of a gas turbine engine (10), A housing (300) extending between a first end (301) and a second end (302) opposite to the first end, wherein the housing (300) includes a first housing portion (305) adjacent to the first end (301) and a second housing portion (310) adjacent to the second end (302), wherein the first housing portion (305) defines at least one fuel chamber (320) and the second housing portion (310) defines at least one mixing chamber (335), A plurality of fuel channels (330) extending along a central axis (510) between the first housing portion (305) and the second housing portion (310), wherein the plurality of fuel channels (330) are in fluid communication with the at least one fuel chamber (320) and the at least one mixing chamber (335), and the plurality of fuel channels (330) are spaced apart along the length of the housing (300), A first plurality of fluid channels (340) are arranged in the second housing portion (310) and are in fluid communication with the at least one mixing chamber (335), wherein the first plurality of fluid channels (340) are arranged apart from the plurality of fuel channels (330), A second plurality of fluid channels (345) are arranged in the second housing (310) portion and are in fluid communication with the at least one mixing chamber (335), wherein the second plurality of fluid channels (345) are arranged apart from the first plurality of fluid channels (340) and A fuel injection assembly (80) comprising:

2. The fuel injection assembly (80) according to claim 1, wherein the second plurality of fluid channels (345) are longitudinally offset from the first plurality of fluid channels (340).

3. The second housing portion (310) further comprises a third plurality of fluid channels (350) arranged therein and in fluid communication with the at least one mixing chamber (335), The third plurality of fluid channels (350) are arranged spaced apart along the length of the housing (300), Each of the plurality of fuel channels (330) is positioned between adjacent fluid channels of the third plurality of fluid channels (350). The fuel injection assembly (80) according to claim 1.

4. The fuel injection assembly (80) according to claim 1, wherein the plurality of fuel channels (330) include a fuel outlet nozzle (500) that extends at least partially into the at least one mixing chamber (335).

5. The fuel outlet nozzle (500) has a conical shape, The outer surface of the fuel outlet nozzle (500) defines a fuel outlet angle (505) with respect to the central axis (510), The fuel outlet angle (505) is approximately 10°. The fuel injection assembly (80) according to claim 4.

6. Each of the first plurality of fluid channels (340) defines a first fluid channel angle (515) with respect to the central axis (510), and a first axis (520) extending through each of the fluid channels of the first plurality of fluid channels (340). Each of the second plurality of fluid channels (345) defines a second fluid channel angle (600) with respect to the central axis (510), and a second axis (605) extending through each of the fluid channels of the second plurality of fluid channels (345). The second fluid channel angle (600) is greater than the first fluid channel angle (515). The fuel injection assembly (80) according to claim 1.

7. The first fluid channel angle (515) is approximately 10°. The second fluid channel angle (600) is approximately 20°. The second plurality of fluid channels (345) define a secondary angle (815) with respect to a vertical axis (802) extending through each of the second plurality of fluid channels (345) that is parallel to the central axis (510), The aforementioned secondary angle (815) is approximately 12°. The fuel injection assembly (80) according to claim 6.

8. The first plurality of fluid channels (340) includes a first row (700) of the first fluid channels (340) and a second row (705) of the first fluid channels (340), wherein the first row (700) and the second row (705) of the first fluid channels are arranged on both sides of the central axis (510). The second plurality of fluid channels (345) includes a first row (710) of the second fluid channels (345) and a second row (715) of the second fluid channels (345), wherein the first row (710) and the second row (715) of the second fluid channels are arranged on both sides of the central axis (510). The fuel injection assembly (80) according to claim 1.

9. The first row (710) of the second fluid channel (345) is inclined in the first direction, The second row (715) of the second fluid channel (345) is inclined in the second direction, The first direction is opposite to the second direction. The fuel injection assembly (80) according to claim 8.

10. The fuel injection assembly (80) according to claim 8, wherein the first row (700) of the first fluid channel (340) and the second row (705) of the first fluid channel (340) are longitudinally aligned with the plurality of fuel channels (330).

11. The elongated fuel injectors (400, 405) include the plurality of fuel channels (330), the first plurality of fluid channels (340), and the second plurality of fluid channels (345), The fuel injection assembly (80) comprises two or more of the elongated fuel injectors (400, 405), The fuel injection assembly (80) according to claim 1.

12. 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 outer sleeve (48) and the combustion liner (46). A fuel injection assembly (80) coupled to the outer sleeve (48) and in fluid communication with a fuel source (152), wherein the fuel injection assembly (80) is defined according to any one of claims 1 to 11. A combustion device (17) equipped with this.

13. The combustor (17) according to claim 12, wherein at least one fuel chamber (320) is in fluid communication with the fuel source (152) via a fuel supply conduit (102), and the fuel source (152) supplies a fuel comprising pure hydrogen or a fuel mixture of hydrogen and natural gas, wherein hydrogen constitutes the majority component of the fuel mixture.

14. The housing (300) defines an air plenum (315) between the first housing portion (305) and the second housing portion (310), At least a portion of the plurality of fuel channels (330) extends through the air plenum (315), The first plurality of fluid channels (340) and the second plurality of fluid channels (345) are in fluid communication with the air plenum (315). The combustor (17) according to claim 12.

15. The combustor (17) according to claim 14, wherein the air plenum (315) is in fluid communication with the annular portion (47).

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