APPROACH FOR A FUEL INJECTION ARRANGEMENT WITH A COOLING CIRCUIT AND COMBUSTION CHAMBER PROVIDED THEREFORE

Abstract

A combustion chamber (17) includes a combustion lining (46) that defines a combustion space (70). The combustion chamber further includes an outer casing (48) that is spaced apart from the combustion lining such that an annular space (47) is defined between the combustion lining and the outer casing. The combustion chamber further includes a fuel injection assembly with a projection (300). The projection includes an inner flange (304) coupled to the combustion lining, an outer flange (302) spaced apart from the inner flange, and a body (306) extending between the outer flange and the inner flange. The projection defines a cooling circuit (318) that is fluidically coupled to the annular space and has a plurality of outlet channels (336) defined in the inner flange.

Description

AREA

[0001] The present disclosure relates generally to fuel injection arrangements for gas turbine combustion chambers and in particular to fuel injection arrangements comprising components with cooling circuits for use with an axial fuel staging system (AFS system) associated with these combustion chambers. In particular, the invention claimed herein relates to combustion chambers and components for use in these combustion chambers, as set out in the accompanying claims. STATE OF THE ART

[0002] Turbomachinery is used in a variety of industries and applications for power transmission. For example, a gas turbine engine generally includes, in serial flow order, a compressor section, a combustion section, a turbine section (e.g., an expansion turbine section), and an exhaust section. The compressor section progressively increases the pressure of a working fluid entering the gas turbine engine and delivers this compressed working fluid to the combustion section. The compressed working fluid and a fuel (e.g., natural gas) mix within the combustion section and burn in a combustion chamber to produce combustion gases at high pressure and temperature. The combustion gases flow from the combustion section into the turbine section, where they expand to produce work.For example, the expansion of combustion gases in the turbine section can rotate a rotor shaft, which is connected to a generator to produce electricity. The combustion gases then leave the gas turbine engine via the exhaust section.

[0003] In some combustion chambers, the combustion gases are generated in two or more axially spaced stages. Such combustion chambers are referred to herein as those incorporating an "axial fuel staging system" (AFS system) that supplies fuel and an oxidizer to one or more fuel injectors downstream of the combustion chamber head. In a combustion chamber with an AFS system, a primary fuel injector at an upstream end of the combustion chamber injects fuel and air (or a fuel / air mixture) axially into a primary combustion zone, and an AFS fuel injector located downstream of the primary fuel injector 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 runs perpendicular to the flow of combustion products from the primary combustion zone.

[0004] AFS systems often include an adapter that couples the fuel injector to the combustion chamber. This adapter may be coupled to the combustion chamber's combustion lining and is therefore directly exposed to high-temperature combustion gases. These high-temperature gases can damage the adapter and / or the fuel injector, thus shortening the hardware's lifespan over time. Consequently, improved cooling systems for the adapter in an AFS system would be beneficial. SHORT DESCRIPTION

[0005] The invention claimed herein is defined and set forth in the accompanying claims. Aspects and advantages of the combustion chambers, the attachment, and the method for producing the attachment according to the present disclosure are partly set forth in the following description, or are evident from the description, or can be learned through practical application of the technology.

[0006] According to one embodiment, a combustion chamber is provided. The combustion chamber includes a combustion lining that defines a combustion chamber. The combustion chamber further includes an outer casing that is spaced apart from the combustion lining such that an annular space is defined between the combustion lining and the outer casing. The combustion chamber further includes a fuel injection assembly with a projection that is coupled to at least one of the combustion lining and the outer casing. The projection includes an inner flange that is coupled to the combustion lining, an outer flange that is spaced apart from the inner flange, and a body that extends between the outer flange and the inner flange. The inner flange includes an outer wall, an inner wall, and an impact plate arranged between the outer wall and the inner wall.The approach defines a cooling circuit with a post-impact chamber defined in the inner flange between the inner wall and the impact plate; and a plurality of outlet channels defined in the inner flange that fluidically couple the post-impact chamber to the annular space.

[0007] A cooling circuit, as used in this document, does not necessarily refer to a closed fluid circuit, but more generally to, for example, any flow channel that is connected to a source of fresh cooling fluid and a drain for "used" cooling fluid, i.e., cooling fluid that has already been heated in heat exchange with a structure to be cooled.

[0008] According to a further embodiment, a component for a fuel injection arrangement is provided. The component includes an outer flange. The component further includes an inner flange comprising an outer wall, an inner wall, and an impact plate arranged between the outer wall and the inner wall. The component further includes a body extending between the outer flange and the inner flange. The component defines a cooling circuit. The cooling circuit includes a post-impact chamber defined in the inner flange between the impact plate and the inner wall. The cooling circuit further includes a plurality of outlet channels defined in the inner flange extending from the post-impact chamber.

[0009] In other respects, an approach for use in a fuel injection arrangement for use in a combustion chamber is described as set forth herein and / or set forth in one of the accompanying claims, which includes the features relating to an approach as set forth in one of the embodiments described herein and / or accompanying claims.

[0010] According to a further embodiment, a method for producing a fuel injection assembly is provided. The method includes (a) blasting a layer of powder into a powder bed to form a molten region, the powder bed being arranged on a build plate. The method further includes (b) providing a subsequent layer of powder over the powder bed by guiding a recoater arm over the powder bed from a first side of the powder bed. The method further includes (c) repeating steps (a) and (b) until the assembly is formed on the build plate. The assembly includes an outer flange. The assembly further includes an inner flange having an outer wall, an inner wall, and an impact plate arranged between the outer wall and the inner wall. The assembly further includes a body extending between the outer flange and the inner flange.The approach defines a cooling circuit. The cooling circuit includes a post-impact chamber defined in the inner flange between the impact plate and the inner wall. The cooling circuit further includes a plurality of outlet channels defined in the inner flange extending from the post-impact chamber.

[0011] These and other features, aspects, and advantages of the present combustion chamber, the present approach, and the present method for manufacturing the approach will be better understood with reference to the following description and the accompanying claims. The accompanying drawings, which are integrated into and form part of this patent specification, illustrate embodiments of the technology and, together with the description, serve to explain the principles of the technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] A complete and further disclosure of the present combustion chamber, the present approach and the present method for manufacturing the approach, including the best way of manufacturing and using the present systems and methods, which is directed to persons skilled in the art, is set forth in the patent specification, which refers to the accompanying figures in which: Fig. 1 a schematic illustration of a turbomachine according to embodiments of the present disclosure; Fig. 2 a cross-sectional view of a combustion chamber according to embodiments of the present disclosure, as used with the turbomachine of Fig. 1 can be used, illustrates; Fig. 3 Schematic cross-sectional view of a fuel injection arrangement of an axial fuel stage system of the combustion chamber along the in Fig. 2 line 3-3 shown according to the embodiments of the present disclosure; Fig. 4 schematically an enlarged view of a section of a fuel injection assembly of the combustion chamber of Fig. 3 illustrated according to embodiments of the present disclosure; Fig. 5 schematically a cross-sectional view of the fuel injection arrangement of the combustion chamber along the in Fig. 3 line 5-5 is illustrated according to the embodiments of the present disclosure; Fig. 6 a perspective view of an approach used in the fuel injection arrangement of the Fig. 3, Fig. 4 to Fig. 5 is used, as illustrated by embodiments of the present disclosure; Fig. 7 a cross-sectional view of the in Fig. The approach shown in section 6 is illustrated according to embodiments of the present disclosure; Fig. 8 a cross-sectional plan view of a section of the inner flange of the in Fig. The approach shown in section 6 is illustrated according to embodiments of the present disclosure; Fig. 9 a diagram / block view of an additive manufacturing system for producing an object according to embodiments of the present disclosure; and Fig. 10 is a flowchart of a method for producing a mixture according to the embodiments of the present disclosure. DETAILED DESCRIPTION

[0013] Reference will now be made in detail to embodiments of the present combustion chamber, the present approach, and the present method for manufacturing the approach, one or more examples of which are illustrated in the drawings. Each example is provided to illustrate the technology, not to limit it. Indeed, it will be obvious to those skilled in the art that modifications and variations can be made to the present technology without departing from the scope of protection or the spirit of the claimed technology. For example, features illustrated or described as part of one embodiment can be used with another embodiment to produce yet another embodiment.It is therefore intended that the present disclosure covers such changes and deviations insofar as they fall within the scope of protection of the accompanying claims and their equivalents.

[0014] The word "exemplary" is used herein to mean "serving as an example, case, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferable or advantageous over other implementations. Additionally, unless expressly identified otherwise, all embodiments described herein are to be considered exemplary.

[0015] In the detailed description, numerical and letter designations are used to refer to features in the drawings. Identical or similar designations in the drawings and the description have been used to refer to identical or similar parts of the invention. In the sense used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0016] The term "fluid" can refer to a gas or a liquid. The term "fluid compound" means that a fluid is capable of forming a connection between the aforementioned areas.

[0017] In the sense used herein, the terms "upstream" (or "front") and "downstream" (or "back") refer to the relative direction with respect to fluid flow 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. However, in the sense used herein, the terms "upstream" and "downstream" can also refer to an electric current.The term “radial” refers to the relative direction that is essentially perpendicular to an axial centerline of a given component, the term “axial” refers to the relative direction that is essentially parallel and / or coaxial to an axial centerline of a given component, and the term “circumferential” refers to the relative direction that extends around the axial centerline of a given component.

[0018] Approximate terms such as "about," "approximately," "generally," and "essentially" are not limited to the precisely specified value. In at least some cases, the language of approximation may correspond to the accuracy of an instrument used to measure the value or the accuracy of the processes or machinery used to design or manufacture the components and / or systems. For example, the language of approximation may refer to being within a range of 1, 2, 4, 5, 10, 15, or 20 percent, either for individual values, for one or more ranges of values, and / or for endpoints that define one or more ranges of values.When used in the context of an angle or direction, such terms include values ​​within ten degrees greater or lesser than the stated angle or direction. For example, "generally vertical" includes directions within ten degrees vertical in any direction, such as clockwise or counterclockwise.

[0019] The terms "coupled," "attached," "attached to," and the like refer to both direct coupling, fastening, or attachment and indirect coupling, fastening, or attachment through one or more intervening components or features, unless otherwise specified herein. The terms "comprises," "comprehensive," "includes," "includes," "exhibits," "possesses," or any other variation thereof, as used herein, are intended to cover non-exclusive inclusion. For example, a process, procedure, object, or facility that includes a list of features is not necessarily limited to those features but may also include other features not expressly listed or inherent to the process, procedure, object, or facility.Unless expressly stated otherwise, “and / or” refers to one or more of the following: A is true (or present) and B is false (or not present), A is false (or not present) and B is true (or present), and both A and B are true (or present).

[0020] Here, and throughout the entire description and claims, domain boundaries are combined and exchanged, whereby these domains are identified and include all subdomains contained therein, unless otherwise indicated by the context or language. For example, all domains disclosed herein are understood to include endpoints, the endpoints being independently combinable with one another.

[0021] Now illustrated with reference to the drawings Fig. Figure 1 shows a schematic representation of an embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine engine 10. Although an industrial or land-based gas turbine is shown and described herein, the present disclosure is not limited to an industrial or land-based gas turbine engine unless otherwise specified in the claims. For example, the technology described herein can be used in any type of turbomachine, including, but not limited to, a steam turbine, an aircraft gas turbine, or a marine gas turbine.

[0022] As shown, the gas turbine engine 10 generally includes an inlet section 12, a compressor section 14 arranged downstream of the inlet section 12, a plurality of combustion chambers 17 (as in Fig. 2) in a combustion section 16 arranged downstream of the compressor section 14, a turbine section 18 arranged downstream of the combustion section 16 and an exhaust section 20 arranged downstream of the turbine section 18. In addition, the gas turbine engine 10 can include one or more shafts 22 which are coupled between the compressor section 14 and the turbine section 18.

[0023] The compressor section 14 can 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 of them. Each rotor disk 24 can in turn be coupled to or form an upstream section of the shaft 22 extending through the compressor section 14. The compressor section 14 further includes a plurality of stationary guide vanes (not shown) arranged in steps with the rotor blades 26 and directing the flow onto the rotor blades 26.

[0024] The turbine section 18 can generally include a plurality of rotor disks 28 (one of which is shown) and a plurality of rotor blades 30 extending radially outward from and connected to each rotor disk 28. Each rotor disk 28 can, in turn, be coupled to or form a downstream section of the shaft 22 extending through the turbine section 18. The turbine section 18 further includes an outer casing 31 circumferentially surrounding the shaft 22 section and the rotor blades 30, thereby defining at least a part of a hot gas path 32 through the turbine section 18. The turbine section 18 also includes a plurality of stationary guide vanes (not shown) arranged in steps with the rotor blades 30, directing the flow toward the rotor blades 30.

[0025] During operation, a working fluid, such as air, flows through the inlet section 12 and into the compressor section 14, where the air is progressively compressed by several compressor stages consisting of rotating blades and stationary guide vanes, thus providing compressed air to the combustion chambers 17 of the combustion section 16. The compressed air is mixed with fuel and combusted in each combustion chamber 17 to produce combustion gases 34. The combustion gases 34 flow through the hot gas path 32 from the combustion section 16 into the turbine section 18, where energy (kinetic and / or thermal) is transferred from the combustion gases 34 to the rotor blades 30, causing the shaft 22 to rotate. The mechanical rotational energy can then be used to power the compressor section 14 and / or to generate electricity.The combustion gases 34 exiting the turbine section 18 can then be expelled from the gas turbine engine 10 via the exhaust section 20.

[0026] Fig. Figure 2 is a schematic representation of a combustion chamber 17 as it may be enclosed in an annular tube combustion system 16 for the gas turbine engine 10. In an annular tube combustion system, a plurality of combustion chambers 17 (e.g., 8, 10, 12, 14, 16 or more) are positioned in an annular arrangement around the shaft 22, which connects the compressor section 14 to the turbine section 18.

[0027] As in Fig. As shown in Figure 2, the combustion chamber 17 can define an axial direction A extending along an axial centerline 170. The combustion chamber 17 can also define a circumferential direction C extending around the axial direction A and the axial centerline 170. Furthermore, the combustion chamber 17 can define a radial direction R perpendicular to the axial direction A and the axial centerline 170. The combustion chamber 17 can extend (e.g., generally axially) from a front end 338 and a rear end 340. For example, the front end or, relative to the flow of combustion gases 172, the upstream end 338 can include an end cover 42 to which one or more fuel nozzles 40 are coupled, and the rear end or, relative to the flow of combustion gases 172, the downstream end 340 can be located on a rear frame 118 that defines an outlet of the combustion chamber 17.

[0028] As in Fig. As shown in Figure 2, the combustion chamber 17 encloses a combustion lining 46, which defines a combustion chamber 70. The combustion lining 46 can be positioned within an outer casing 48 (i.e., surrounded by it circumferentially), so that an annular space 47 is formed between them. The combustion lining 46 can contain combustion gases and convey them to the turbine section 18. The combustion lining 46 defines the combustion chamber 70 in which the combustion takes place. As shown in Fig. As shown in Figure 2, the combustion lining 46 can extend between fuel nozzles 40 and a rear frame 118. The combustion lining 46 can have a generally cylindrical lining section and a conical transition section that is separate from the generally cylindrical lining section, as in many conventional combustion systems. Alternatively, the combustion lining 46 can have a single-body construction (or “unibody construction”) in which the generally cylindrical section and the conical section are integrated together. Therefore, any discussion of the combustion lining 46 herein is intended to include both conventional combustion systems with separate lining and transition section and those combustion systems with a unibody lining.Furthermore, the present disclosure is equally applicable to such combustion systems in which the transition piece and the nozzle of the first stage of the turbine section 18 are integrated into a single unit (e.g. without rear frame 118), which is sometimes referred to as the ‘transition nozzle’ or ‘integrated outlet piece’.

[0029] Fig. Figure 2 illustrates a combustion chamber 17 comprising both fuel nozzles 40 and one or more fuel injection assemblies 80 (also referred to as an axial fuel staging system (AFS system)), as further discussed herein. The at least one fuel nozzle 40 can be positioned at the front end of the combustion chamber 17. The fuel can be supplied by fuel supply lines 38 extending through an end cover 42 and into the fuel nozzles 40. The fuel nozzles 40 deliver the fuel and compressed air 15 into a primary combustion zone 72, where combustion takes place. In some embodiments, the fuel and compressed air 15 are combined to form a mixture before reaching the primary combustion zone 72.

[0030] The combustion lining 46 can be surrounded by an outer casing 48, which is radially spaced outwards from the combustion lining 46 to define an annular space 47 through which compressed air 15 flows to a front or head end of the combustion chamber 17. For example, compressed air 15 can enter the annular space 47 through the outer casing 48 (e.g., through blowholes near the rear frame 118) and flow towards the end cover 42, so that the compressed air 15 flows in the annular space 47 in the opposite direction to the combustion gases 172 (34 in Fig. 1) flows in the combustion lining 46. By convection, heat is transferred from the combustion lining 46 to the compressed air 15, thereby cooling the combustion lining 46 and heating the compressed air 15.

[0031] In some embodiments, the outer casing 48 can enclose a flow sleeve and an impact sleeve coupled together. The flow sleeve can be located at the front end and the impact sleeve can be located at the rear end. Alternatively, the outer casing 48 can have a single body construction (or “unisleeve” construction) in which the flow sleeve and the impact sleeve are integrated axially. As before, any discussion of the outer casing 48 herein is intended to include both conventional combustion systems with a separate flow sleeve and impact sleeve and combustion systems with a unisleeve outer casing.

[0032] The front housing 50 and the end cover 42 of the combustion chamber 17 define the air collection space 122 at the head end, which encloses the one or more fuel nozzles 40. The fuel nozzles 40 can be any type of fuel nozzle, such as tube bundle fuel nozzles (often referred to as "micromixers") or swirl nozzles (often referred to as "swozzles"). The fuel nozzles 40 can be positioned within the air collection space 122 at the head end, which is defined at least partially by the front housing 50. In many embodiments, the fuel nozzles 40 can extend from the end cover 42. For example, each fuel nozzle 40 can be coupled to a rear surface of the end cover 42 via a flange (not shown). As in Fig. As shown in Figure 2, the at least one fuel nozzle 40 can be partially surrounded by the combustion lining 46 or a cylindrical inlet flow conditioner (not shown separately). The rear or downstream ends of the fuel nozzles 40 extend through a cover plate 44 or jointly define one, which defines the upstream end of the combustion chamber 70.

[0033] The fuel nozzles 40 can be in fluid communication with a first fuel supply 150, which is configured to supply the fuel nozzles 40 with a first fuel 158. In many embodiments, the first fuel 158 can be a fuel mixture containing natural gas (such as one or more of methane, ethane, propane, or another suitable natural gas) and hydrogen. In other embodiments, the first fuel 158 can be pure natural gas or pure hydrogen (e.g., 100% hydrogen, which may or may not contain some trace amount of impurities), so that the first fuel is not a mixture of several fuels. In other embodiments, the first fuel 158 can be a mixture of hydrogen and natural gas, with hydrogen being the main component (i.e., more than 50%).In exemplary embodiments, the first fuel 158 and the compressed air 15 can mix in the fuel nozzles 40 to form a first mixture of compressed air 15 and the first fuel 158 before being expelled (or injected) from the fuel nozzles 40 into the primary combustion zone 72.

[0034] The front housing 50 can be fluidically and mechanically connected to a compressor discharge housing 60, which forms a high-pressure chamber 66 around the combustion liner 46 and the outer casing 48. Compressed air 15 from the compressor section 14 flows through the high-pressure chamber 66 and enters the combustion chamber 17 via openings (not shown) in the downstream end of the outer casing 48 (as indicated by arrows near a rear frame 118). Compressed air 15 flows upstream through the annular space 47 and is deflected by the end cover 42 to enter the fuel nozzles 40 and cool the head end. Specifically, compressed air 15 flows from the high-pressure chamber 66 through openings defined in the outer casing 48 into the annular space 47 at a rear end of the combustion chamber 17.The compressed air 15 flows upstream from the rear end of the combustion chamber 17 to the air collection chamber 122 at the head end, where the compressed air 15 reverses its direction and enters the fuel nozzles 40.

[0035] In the exemplary embodiment, one or more fuel injection arrangements 80 are provided to supply a second fuel / air mixture to a secondary combustion zone 74 downstream of the primary combustion zone 72. For example, a second stream of fuel 152 and air 15 can be introduced into the secondary combustion zone 74 through one or more fuel injection nozzles 400.

[0036] The primary combustion zone 72 and the secondary combustion zone 74 can each be sections of the combustion chamber 70 and can therefore be defined by the combustion lining 46. For example, the primary combustion zone 72 can be defined from a fuel nozzle outlet 40 to the fuel injector 400, and the secondary combustion zone 74 can be defined from the fuel injector 400 to the rear frame 118. In this arrangement, the foremost boundary of the fuel injector 400 can define the end of the primary combustion zone 72 and the beginning of the secondary combustion zone 74 (e.g., at an axial location where a second fuel and air flow is introduced).

[0037] Such a combustion system with axially separated combustion zones is referred to as an "axial fuel staging system" (AFS system). The fuel injection assemblies 80 can be spaced apart from one another circumferentially on the outer casing 48 (in some embodiments, for example, uniformly spaced). In many embodiments, the combustion chamber 17 can include four fuel injection assemblies 80, which are spaced apart from one another and configured to inject a second fuel-air mixture via the fuel injection nozzle 400 into a secondary combustion zone 74. In further embodiments, the combustion chamber 17 can include any number of fuel injection assemblies 80 (e.g., 1, 2, 3, or up to 10).

[0038] As in Fig. As shown in Figure 2, each fuel injection arrangement 80 can include a fuel injection nozzle 400 and a projection 300, which is aligned circumferentially and axially with the fuel injection nozzle 400. In many embodiments, the fuel injection nozzle 400 can be coupled to the projection 300. In some embodiments (not shown), the fuel injection nozzle 400 can be radially spaced from the projection 300. The projection 300 can extend through the annular space 47 and be coupled to the combustion lining 46 and / or the outer casing 48. In some embodiments, the projection 300 can be coupled to one of the combustion lining 46 and the outer casing 48 and be in contact with the other.

[0039] A fuel supply line 102 can be fluidically coupled to the fuel injector 400. The fuel injector 400 can be fluidly connected to a second fuel supply 152, which is configured to supply the fuel injector 400 with a second fuel 160 via the fuel supply line 102. The second fuel supply 152 can be the same as the first fuel supply 150 or different from it, so that the fuel injector 400 can be supplied with the same or a different fuel than the fuel injectors 40. In many embodiments, the second fuel 160 can be a fuel mixture containing natural gas (such as methane, ethane, propane, or another suitable natural gas) and hydrogen. In further embodiments, the second fuel 160 can be pure natural gas or pure hydrogen (e.g.,100% pure hydrogen (which may or may not contain a certain amount of trace impurities), so that the first fuel is not a mixture of several fuels. In other embodiments, the second fuel 160 can be a mixture of hydrogen and natural gas, with hydrogen being the main component (i.e., more than 50%). In exemplary embodiments, the second fuel 160 and the compressed air 15 can be mixed together in the fuel injection nozzle 400 to form a mixture of compressed air 15 and the second fuel 160 before it is injected through the inlet 300 and into the combustion chamber 70, and in particular into the secondary combustion zone 74.

[0040] With reference to Fig. Figure 3 is a cross-sectional view of combustion chamber 17 along the in Fig. Figure 2 illustrates the combustion chamber according to embodiments of the present disclosure. As shown, the combustion lining 46 defines the combustion chamber 70. The outer casing 48 is spaced (e.g., radially) from the combustion lining 46, such that an annular space 47 is defined between the combustion lining 46 and the outer casing 48. The high-pressure chamber 66 can be defined radially outside the outer casing 48.

[0041] The fuel injection assembly 80 can be positioned within the annular space 47 and fluidically coupled to the combustion chamber 70 and the high-pressure chamber 66. The fuel injection assembly includes the extension 300 and the fuel injection nozzle 400 coupled to the extension 300. The fuel injection nozzle and the extension 300 can generally extend along an injection axis 202 (e.g., radially, relative to the combustion chamber centerline 170). In many embodiments, the extension 300 includes an outer flange 302, an inner flange 304, and a body 306. The outer flange 302 can be coupled to or in contact with the outer casing 48. In some embodiments, the outer flange 302 can be rigidly coupled to the outer casing 48 (e.g., via a welded and / or brazed connection). In other embodiments, the outer flange 302 can be detachably coupled to the outer casing 48 (e.g.via one or more fastening elements). The inner flange 304 can be coupled to or in contact with the combustion lining 46. For example, the inner flange 304 can be rigidly coupled to the combustion lining 46 (e.g., via a welded and / or brazed connection). The body 306 can extend (e.g., radially, relative to the combustion chamber centerline 170) between the outer flange 302 and the inner flange 304. It is understood that the radial direction relative to the combustion chamber centerline 170 can also be described as the axial direction relative to the injection axis 202 of the fuel injection assembly 80.

[0042] The inner flange 304 encloses an outer wall 308, an inner wall 310, and an impact plate 312, which is positioned between (e.g., radially) the outer wall 308 and the inner wall 310. The impact plate 312 can define a plurality of impact openings 316. The inner flange 304 can further enclose a circumferential surface 314, which extends radially between the inner wall 310 and the outer wall 308. The circumferential surface 314 can be rigidly coupled to the combustion lining 46.

[0043] In exemplary embodiments, the assembly 300 can define a cooling circuit 318 for cooling the assembly 300 and / or the fuel injection nozzle 400. The cooling circuit 318 can be annular, such that it is defined around (and surrounds) the injection axis 202. The cooling circuit 318 includes at least one inlet 320, which is defined in a radially outer surface 322 of the outer flange 302. In this way, the cooling circuit 318 can receive a flow of pressurized coolant (e.g., air) from the high-pressure chamber 66 via the inlet(s) 320. The cooling circuit 318 can further include an inlet chamber 324, which is defined in the outer flange 302. The inlet chamber 324 can receive coolant (e.g., air) from the inlet(s) 320.

[0044] In many embodiments, the cooling circuit 318 can further include a pre-impact chamber 326, which is defined in the inner flange 304 between (e.g., radially between) the outer wall 308 and the impact plate 312. Furthermore, the cooling circuit 318 can include a post-impact chamber 328, which is defined in the inner flange 304 between the impact plate 312 and the inner wall 310. The inlet chamber 324 can be fluidically coupled to the pre-impact chamber 326 via a channel 325 defined in the body 306. The channel 325 can extend (e.g., radially) through the body 306 between the inlet chamber 324 and the pre-impact chamber 326. In one embodiment, the channel 325 can extend circumferentially around the body 306, while in other embodiments two or more channels 325 can extend partially around the circumference of the body 306.

[0045] The pre-impact chamber 326 and the post-impact chamber 328 can be fluidically coupled to each other via the plurality of impact openings 316 defined in the impact plate 312. In exemplary embodiments, the cooling circuit 318 can further include a plurality of outlet channels 336 defined in the inner flange and fluidically coupled to the annular space 47. In particular, the plurality of outlet channels 336 can generally extend radially (with respect to the radial direction of the combustion chamber 17) between the post-impact chamber 328 and the annular space 47. That is, the plurality of outlet channels 336 can extend from the post-impact chamber 328 to expel coolant (e.g., air) from the cooling circuit 318 into the annular space 47.

[0046] In many embodiments, the innermost surface of the inner flange 304 can at least partially define the combustion chamber 70 (and thus be directly exposed to the combustion gases flowing through it). In exemplary embodiments, the innermost surface of the inner flange 304 can be coated with a thermal barrier layer 334 (“TBC”) to increase the resistance of the attachment 300 to the high temperatures of the combustion gases and thereby preserve the usable lifetime of the hardware of the attachment 300.

[0047] As in Fig. As shown in Figure 3, the fuel injection arrangement 80 can further include a fuel injection nozzle 400 coupled to the extension 300. The fuel injection nozzle 400 can include an injection channel 402 extending along the injection axis 202 from a main inlet 401 to a main outlet 403. In many embodiments, the fuel injection nozzle 400 can extend through the extension 300. The injection channel 402 of the fuel injection nozzle 400 can receive air from the high-pressure chamber 66 and fuel from the fuel ports 406, which mix within the injection channel 402 and are supplied to the combustion chamber 70 as a fuel / air mixture. More precisely, the fuel / air mixture is supplied radially within the fuel injection arrangement 80 to the secondary combustion zone 74.

[0048] Referring now to Fig. Figure 4 is an enlarged view of a section of Fig. 3 illustrates this. That is to say, Fig. Figure 4 illustrates a section of the approach 300 of the fuel injection arrangement 80 of the combustion chamber 17, as coupled to the combustion lining 46. As shown in Fig. As shown in Figure 4, the inner wall 310 can define an outer surface 330 and an inner surface 332. In exemplary embodiments, the outer surface 330 can be the innermost surface of the inner flange 304, such that the TBC 334 is arranged on the outer surface 330. That is, the outer surface 330 can be coated with the TBC 334 to improve the heat and / or oxidation resistance of the attachment 300 to the hot combustion gases (172 in Fig. 2) to increase.

[0049] The plurality of impact openings 316 can each be dimensioned and oriented such that they direct coolant (e.g., air) from the pre-impact chamber 326 in discrete jets to impact the inner wall 310 (in particular, an inner surface 332 of the inner wall 310). The individual air jets impact (or strike) the inner surface 332 and create a thin air boundary layer above the inner surface 332, which enables optimal heat transfer between the inner wall 310 and the air in the post-impact chamber 328. For example, the impact openings 316 can orient the cooling air so that it is perpendicular to the surface it strikes, e.g., the inner surface 332 of the inner wall 310. Once the air has impacted the inner wall 310, it can be referred to as "post-impact air" and / or "used cooling air" because the air has undergone energy transfer and therefore exhibits different properties.For example, the used cooling air may have a higher temperature and lower pressure than the pre-impact air (i.e., the cooling in the pre-impact chamber 326), because the used cooling air has removed heat from the inner wall 310 during the impact process.

[0050] By using impact air to cool the inner wall 310, the TBC 334 arranged on the outer surface 330 is advantageously protected, thereby increasing the service life of the hardware of the assembly 300. For example, cooling the inner wall 310 advantageously prevents the TBC 334 from blistering or from flaking off or detaching from the outer surface 330 due to heat from the combustion chamber 70.

[0051] In many embodiments, the approach 300, as in Fig. Figure 4 shows that the heat transfer projections 366 include one or more heat transfer projections 366 extending from the inner wall 310 into the post-impact space 328. The heat transfer projections 366 can be ribs or blocks that enhance heat transfer between the impact air and the inner wall 310. As shown, the heat transfer projections 366 can be radially aligned with the impact openings 316, such that an imaginary radial line at the location of the impact openings 316 and the heat transfer projections 366 would intersect both the impact openings 316 and the heat transfer projections 366.

[0052] With reference to Fig. Figure 5 is a cross-sectional view of the combustion chamber 17 along the in Fig. 3, line 5-5, is illustrated according to embodiments of the present disclosure. As shown in Fig. As shown in Figure 5, the approach 300 can generally extend axially between a front end or, relative to the flow of combustion gases 172, an upstream end 342 and a rear end or, relative to the flow of combustion gases 172, a downstream end 344 (where the axial direction is defined relative to the centerline axis 170 of the combustion chamber 17).

[0053] In exemplary embodiments, at least one outlet channel 336 of the plurality of outlet channels 336 can be angled towards the front end 342 of the projection 300 (e.g., opposite to the axial direction). That is, the plurality of outlet channels 336 can each extend from the post-impact chamber 328 to the annular chamber 47 at an angle relative to the axial direction R and the radial direction A. More precisely, in an axial-radial plane (as in Fig. (5 shown) the plurality of outlet channels 336 extend from the post-impact chamber 328 towards the front end 342 to the annular chamber 47 in an inclined or oblique manner (i.e., at a non-perpendicular angle) with respect to the axial direction A and the radial direction R. The use of angled outlet channels 336 advantageously prevents flow vortices within the annular chamber 47. For example, air 15 can flow through the annular chamber 47 opposite to the axial direction A to the fuel nozzles 40, where the air 15 is mixed with fuel and injected into the combustion chamber 70. By using angled outlet channels 336, the air 15 passing through the annular chamber 47 is advantageously not disturbed by the spent cooling air expelled from the outlet channels 336. Due to the angular orientation of the outlet channels 336, the outlet channels 336 can have an elongated outlet opening (i.e.,The end of the outlet channel 336 is defined in the outer wall 308 of the inner flange 304). The elliptical and / or non-circular shape of the outlet openings is best illustrated in . Fig. 6 and Fig. 8 visible.

[0054] In many embodiments, at least two of the multiple outlet channels 336 can define different diameters 346, 348. For example, as in Fig. As shown in Figure 5, a first outlet channel 336 of the plurality of outlet channels 336 defines a first diameter 346. A second outlet channel 336 of the plurality of outlet channels 336 can define a second diameter 348. The first diameter 346 can differ from the second diameter 348 (e.g., be larger or smaller). In the illustrated embodiment, the second diameter 348 can be larger than the first diameter 346. In some embodiments, each outlet channel 336 of the plurality of outlet channels 336 defines a different diameter. In other embodiments, a first group of outlet channels 336 can define the first diameter 346, and a second group of outlet channels 336 can define the second diameter 348.The first group and the second group can be arranged alternately with respect to the axial direction A, such that each outlet channel 336 of the first group is positioned between two outlet channels 336 of the second group.

[0055] In exemplary embodiments, a rear end of the inner flange 304 can be solid. That is, the rear end of the inner flange 304 can enclose a solid region 350 in which outlet channels 336 are located in fluid communication with the annular space 47. This advantageously prevents interaction between the outlet air from the cooling circuit 318 and the air 15 through the annular space 47 at the rear end of the extension 300, thereby reducing turbulence and wake zones. Conversely, the front end of the inner flange 304 can include one or more outlet channels 336, which advantageously reduce or eliminate wake flows 15 generated by the flow around the body 306 of the extension 300.

[0056] With reference to Fig. Figure 6 illustrates a perspective view of an approach 300 according to embodiments of the present disclosure. As shown, the approach 300 can define a main channel 352 extending through the outer flange 302, the body 306, and the inner flange 304. The main channel 352 can generally have the form of a slot or a geometric stadium (e.g., a rectangle with circular or rounded ends). Furthermore, the cooling circuit 318 can, as shown, include at least two inlets 320A, 320B arranged on opposite sides of the main channel 352 (e.g., diametrically opposed to each other). In particular, the cooling circuit 318 can include a first inlet 320A on a first side of the main channel 352 and a second inlet 320B arranged on a second side of the main channel 352.In many embodiments, the element 300 can include other openings that are not in fluid communication with the cooling circuit 318, such as bolt holes, dowel holes, or other openings. For example, the outer flange 302 can define bolt holes 354 for coupling the outer flange 302 to the outer casing 48. The first inlet 320A and the second inlet 320B can each be arranged between two bolt holes 354.

[0057] With reference to Fig. 7 and Fig. 8 illustrates Fig. 7 a perspective cross-sectional view of a section of the approach 300, showing details of the cooling circuit 318, and Fig. Figure 8 illustrates a cross-sectional plan view of an inner flange section 304 of the projection 300. As in Fig. As shown in Figure 7, the extension 300 includes the outer flange 302, the inner flange 304, and the body 306, which extends between the outer flange 302 and the inner flange 304. The cooling circuit 318 can include the inlet 320 defined in the outer flange 302 and an inlet chamber 324 defined in the outer flange 302 and fluidically connected to the inlet 320. The channel 325 formed in the body 306 can fluidically connect the inlet chamber 324 in the outer flange 302 and the pre-impact chamber 326 in the inner flange 304. The inner flange 304 of the extension 300 includes the impact plate 312, which fluidically connects the pre-impact chamber 326 and the post-impact chamber 328 via a plurality of openings. The numerous outlet channels 336 expel the coolant (e.g., air) from the cooling circuit 318.

[0058] As in Fig. As shown in Figure 8, the approach 300 can include a first wall 356 and a second wall 358, which divide the cooling circuit 318 into a first section 360 and a second section 362. The first section 360 and the second section 362 can be fluidically isolated from each other. The first section 360 can be in fluid communication with the first inlet 320A ( Fig. 6) stand and the second section 362 can be in fluid contact with the second inlet 320B ( Fig. 6) stand. By dividing the cooling circuit 318 into several sections, the ideal pressure within the cooling circuit 318 can be maintained. Additionally, the plurality of outlet channels 336 can be spaced apart from one another around the inner flange 304 in many embodiments. For example, the plurality of outlet channels 336 can be spaced evenly or unevenly from one another. Furthermore, the plurality of outlet channels 336 can be arranged closer to the circumferential surface 314 than to the body 306. As described above, the rear end of the inner flange 304 can enclose a solid region 350 without outlet channels 336.

[0059] To illustrate an example of an additive manufacturing system and process, shows Fig. 9 a diagram / block view of an additive manufacturing system 1000 for producing an object 1220, such as an approach 300 described herein. Fig. Figure 9 can represent an additive manufacturing system configured for direct metal laser sintering (DMLS) or direct metal laser melting (DMLM). The additive manufacturing system 1000 produces objects such as object 1220 (which can be representative of the approach 300 described herein). For example, object 1220 can be manufactured layer by layer by sintering or melting a powder material (not shown) using an energy beam 1360 generated by a source such as a laser 1200. The powder to be melted by the energy beam is fed from the hopper 1260 and evenly distributed over a build plate 1002 using a recoater arm 1160 to maintain the powder at a level 1180 and to remove excess powder material extending above the powder level 1180 into a waste container 1280.The recoater arm 1160 moves in a recoater direction 1340 to distribute the powder over the build plate 1002. The energy beam 1360 sinters or melts a cross-sectional layer of the object 1220, which is being built under the control of the electroplating scanner 1320. The build plate 1002 is lowered, and another layer of powder is distributed over the build plate and the object being built, followed by the successive melting / sintering of the powder by the laser 1200.

[0060] The process is repeated until object 1220 is completely built from the molten / sintered powder material. The laser 1200 can be controlled by a computer system that includes a processor and memory.

[0061] The computer system can determine a scan pattern for each layer and control the laser 1200 to irradiate the powder material according to the scan pattern. After the manufacturing of object 1220 is complete, various post-processing procedures can be applied to it. These include the removal of excess powder, for example, by blowing or vacuuming. Other post-processing procedures include stress relief. Additionally, thermal and chemical post-processing methods can be used for the final finishing of object 1220 (e.g., applying a TBC layer 334).

[0062] Fig. Figure 10 is a flowchart of a series of steps 1602 to 1606 that define a method 1600 for producing the formulation 300 according to embodiments of the present disclosure. The method 1600 can be carried out using an additive manufacturing system, such as the additive manufacturing system 1000 described herein or another suitable system. As shown in Fig. As shown in Figure 10, the method 1600 includes a step 1602 of blasting a layer of powder into a powder bed 1120 to form a fused region. In many embodiments, as shown in Fig.As shown in Figure 9, the powder bed 1120 is arranged on the build plate 1002 such that the fused region is firmly attached to the build plate 1002. The method 1600 can include a step 1604 of providing a subsequent powder layer from a first side of the powder bed 1120 over the powder bed 1120 (e.g., applied in the recoater direction 1340). The method 1600 further includes a step 1606 of repeating steps 1602 and 1604 until the build-up 300 is formed in the powder bed 1120.

[0063] In many embodiments, the approach 300 described herein can be formed in one piece as a single component. That is, each of the subcomponents, e.g., the flanges 302, 304, and the body 306, and each other subcomponent of the approach 300 (e.g., impact plate 312) can be manufactured together as a single body. In exemplary embodiments, this can be achieved by using an additive manufacturing system and process, such as direct metal laser sintering (DMLS), direct metal laser melting (DMLM), or other suitable additive manufacturing techniques. In other embodiments, other manufacturing techniques, such as casting or other suitable techniques, can be used.

[0064] In this respect, the Approach 300 can be integrally manufactured as a single piece of continuous metal using additive manufacturing processes, thus requiring fewer subcomponents and / or connections compared to previous designs. Integrally manufacturing the Approach 300 through additive manufacturing can advantageously improve the entire assembly process. For example, integral manufacturing reduces the number of individual parts that need to be assembled, thereby reducing the associated assembly time and overall costs. Furthermore, existing problems, such as those related to leakage, the quality of connections between individual parts, and overall performance, can be advantageously mitigated. Finally, integral manufacturing of the Approach 300 can advantageously reduce its weight compared to other manufacturing methods.

[0065] This written description uses examples to disclose the invention, including best practices, and also to enable a person skilled in the art to apply the invention, including the manufacture and use of any devices or systems and the performance of any methods contained herein. The scope of protection of the invention claimed herein is defined by the accompanying claims and may include further embodiments than those described above, which are apparent to persons skilled in the art.

[0066] Further aspects of the invention are provided by the subject matter of the following paragraphs: A combustion chamber comprising: a combustion lining defining a combustion chamber; an outer casing spaced apart from the combustion lining such that an annular space is defined between the combustion lining and the outer casing; and a fuel injection arrangement with a projection coupled to at least one of the combustion lining and the outer casing, the projection comprising an inner flange coupled to the combustion lining, an outer flange spaced apart from the inner flange, and a body extending between the outer flange and the inner flange, the inner flange including an outer wall, an inner wall, and an impact plate arranged between the outer wall and the inner wall; the projection defining a cooling circuit comprising a post-impact space defined in the inner flange between the impact plate and the inner wall;and a multitude of outlet channels defined in the inner flange that fluidically couple the post-impact space with the annular space.

[0067] The combustion chamber according to one of the preceding paragraphs, wherein at least one outlet channel of the plurality of outlet channels is angled towards a front end of the extension.

[0068] The combustion chamber according to one of the preceding paragraphs, wherein at least two of the multiple exhaust ports define different diameters.

[0069] The combustion chamber according to one of the preceding paragraphs, wherein the plurality of exhaust ports are spaced apart around the inner flange.

[0070] The combustion chamber according to one of the preceding paragraphs, wherein a rear end of the inner flange is solid and free of exhaust ports.

[0071] The combustion chamber according to one of the preceding paragraphs, wherein the impact plate defines a plurality of impact openings and wherein the inner wall partially defines the combustion chamber.

[0072] The combustion chamber according to any of the preceding paragraphs, wherein the cooling circuit further comprises: an inlet chamber defined in the outer flange; a pre-impact chamber defined in the inner flange between the outer wall and the impact plate; and a channel defined in the body extending between the inlet chamber and the pre-impact chamber.

[0073] The combustion chamber according to one of the preceding paragraphs, wherein the multitude of exhaust channels extends directly from the post-impact space.

[0074] The combustion chamber according to one of the preceding paragraphs, further comprising one or more heat transfer projections extending from the inner wall and into the post-impact space.

[0075] The combustion chamber according to one of the preceding paragraphs, wherein the approach defines a main channel extending through the outer flange, the body and the inner flange, and wherein the cooling circuit includes at least two inlets on opposite sides of the main channel.

[0076] An approach for a fuel injection arrangement, wherein the approach comprises: an outer flange; an inner flange, the inner flange having an outer wall, an inner wall and an impact plate arranged between the outer wall and the inner wall; and a body extending between the outer flange and the inner flange; wherein the approach defines a cooling circuit, comprising: a post-impact chamber defined in the inner flange between the impact plate and the inner wall; and a plurality of outlet channels defined in the inner flange extending from the post-impact chamber.

[0077] The approach according to one of the preceding paragraphs, wherein at least one outlet channel of the plurality of outlet channels is angled towards a front end of the approach.

[0078] The approach according to one of the preceding sections, wherein at least two outlet channels of the plurality of outlet channels define different diameters.

[0079] The approach according to one of the preceding paragraphs, wherein the multitude of outlet channels are spaced apart around the inner flange.

[0080] The approach according to one of the preceding paragraphs, wherein a rear end of the inner flange is solid and free of outlet channels.

[0081] The approach according to one of the preceding paragraphs, wherein the impact plate defines a plurality of impact openings.

[0082] The approach according to one of the preceding paragraphs, further comprising one or more heat transfer projections extending from the inner wall into the post-impact space.

[0083] A method for producing a fuel injection assembly, the method comprising: (a) blasting a layer of powder into a powder bed to form a molten region, the powder bed being arranged on a build plate; (b) providing a subsequent layer of powder over the powder bed by guiding a recoater arm over the powder bed from a first side of the powder bed; and (c) repeating steps (a) and (b) until the assembly is formed on the build plate, the assembly comprising: an outer flange; an inner flange, the inner flange having an outer wall, an inner wall, and an impact plate arranged between the outer wall and the inner wall; and a body extending between the outer flange and the inner flange; the assembly defining a cooling circuit comprising: a post-impact chamber defined in the inner flange between the impact plate and the inner wall;and a multitude of outlet channels defined in the inner flange and extending from the post-impact space;

[0084] A gas turbine engine comprising: a compressor section; a turbine section; and a combustion section arranged between the compressor section and the turbine section, the combustion section comprising a combustion chamber comprising: a combustion lining defining a combustion space; an outer casing spaced apart from the combustion lining such that an annular space is defined between the combustion lining and the outer casing;A fuel injection arrangement with a projection coupled to at least one combustion liner and outer casing, the projection comprising an outer flange, an inner flange coupled to the combustion liner, and a body extending between the outer flange and the inner flange, the inner flange including an outer wall, an inner wall, and an impact plate arranged between the outer wall and the inner wall; the projection defining a cooling circuit comprising: a post-impact chamber defined in the inner flange between the impact plate and the inner wall; and a plurality of outlet channels defined in the inner flange that fluidically couple the post-impact chamber to the annular space.

Claims

[1] Combustion chamber (17), comprising: a combustion lining (46) that defines a combustion chamber (70); an outer casing (48) which is spaced apart from the combustion lining (46) such that an annular space (47) is defined between the combustion lining and the outer casing; and a fuel injection arrangement (80) with a projection (300) connected to the combustion lining (46) and the outer casing (48), wherein the projection has an outer flange (302) coupled to the outer casing (48), an inner flange (304) coupled to the combustion lining (46), and a body (306) extending between the outer flange (302) and the inner flange (304), wherein the projection defines a cooling circuit (318) fluidically coupled to the annular space (47) and includes a plurality of outlet channels (336) defined in the inner flange (304). [2] Combustion chamber according to claim 1, wherein at least one outlet channel (336) of the plurality of outlet channels of the extension is angled towards a front end (342) of the extension. [3] Combustion chamber according to one of the preceding claims, wherein at least two outlet channels (336) of the plurality of outlet channels of the attachment define different diameters (346, 348). [4] Combustion chamber according to one of the preceding claims, wherein the extension (300) comprises a rear end of the inner flange which is solid and free of exhaust ports and / or wherein the plurality of exhaust ports is spaced apart around the inner flange. [5] Combustion chamber according to one of the preceding claims, wherein the inner flange (304) of the extension (300) comprises an inner wall (310) and an impact plate (312) which is arranged offset from the inner wall in the direction of the outer flange (302), and wherein a post-impact space (328) is defined in the inner flange between the impact plate (312) and the inner wall (310). [6] Combustion chamber according to the preceding claim, wherein the impact plate (312) defines a plurality of impact openings (316). [7] Combustion chamber according to one of the two preceding claims, wherein the inner flange (304) of the attachment further comprises an outer wall (308) opposite the inner wall and is offset from the inner wall (310) in the direction of the outer flange (302); wherein the cooling circuit (318) of the attachment further comprises: an inlet chamber (324) defined in the outer flange (302); a pre-impact space (326) defined in the inner flange (304) between the outer wall (308) and the impact plate (312); and a channel (325) that is defined in the body and extends between the inlet chamber and the pre-impact chamber. [8] Combustion chamber according to one of the three preceding claims, wherein the plurality of outlet channels (336) extends directly from the post-impact chamber (328). [9] Combustion chamber according to one of the preceding claims, wherein the projection (300) further comprises one or more heat transfer projections (366) extending from the inner wall (310) into a space defined inside the inner flange (304), and in particular into the post-impact space as defined in claim 5. [10] Combustion chamber according to one of the preceding claims, wherein the approach defines a main channel (352) extending through the outer flange (302), the body (306) and the inner flange (304), and wherein the cooling circuit (318) includes at least two inlets (320A, 320B) on opposite sides of the main channel. [11] Combustion chamber according to one of the preceding claims, wherein the inner wall (310) of the inner flange (204) of the extension (300) defines a part of a wall of the combustion chamber. [12] Combustion chamber according to one of the preceding claims, wherein the attachment is a one-piece formed, seamless unibody element. [13] Approach (300) for a fuel injection arrangement for use in a combustion chamber according to one of the preceding claims, wherein the approach comprises: an outer flange (302); an inner flange (304), wherein the inner flange comprises: an outer wall (308), an inner wall (310), wherein the outer wall is offset from the inner wall in the direction of the outer flange, and an impact plate (312) arranged between the outer wall and the inner wall of the inner flange; and a body (306) extending between the outer flange and the inner flange; wherein the approach defines a cooling circuit (318), comprising: a post-impact space (328) defined in the inner flange (304) between the impact plate (312) and the inner wall (310); and a plurality of outlet channels (336) defined in the inner flange and extending from the post-impact space. [14] Approach according to the preceding claim, wherein at least one outlet channel (336) of the plurality of outlet channels is angled towards a front end of the approach and / or wherein at least two outlet channels (336) of the plurality of outlet channels define different diameters (346, 348) and / or wherein the plurality of outlet channels is spaced apart around the inner flange (304) and / or wherein a rear end of the inner flange is solid and free of outlet channels. [15] Method for producing a fuel injection assembly, the method comprising: (a) Blasting a layer of powder into a powder bed to form a molten region, wherein the powder bed is arranged on a build plate; (b) Providing a subsequent powder layer over the powder bed by guiding a recoater arm over the powder bed from a first side of the powder bed; and (c) Repeat steps (a) and (b) until the embossing is formed on the building plate, the embossing comprising: an outer flange; an inner flange, wherein the inner flange is an outer wall, an inner wall and an impact plate positioned between the outer wall and the inner wall; and a body extending between the outer flange and the inner flange; where the approach defines a cooling circuit, encompassing: a post-impact space defined in the inner flange between the impact plate and the inner wall; and a multitude of outlet channels defined in the inner flange and extending from the post-impact space.

Images