JP2011520055A - Combustor parts and manufacturing method - Google Patents

Abstract

Disclosed is a method of manufacturing a single part of a combustor, the method comprising measuring three-dimensional information of a single part (60), each of the three-dimensional information comprising It comprises the steps of converting into a plurality of prescribed sections and the step of successively forming each layer of a single part (60) by melting the metal powder using laser energy. Also disclosed is a combustor component (60, 50) comprising a body (61, 51) having a single structure, wherein the body (61, 51) is manufactured using a high speed manufacturing process.
[Selection] Figure 9

Description

  The present invention relates generally to combustors, and more particularly to a fuel nozzle component having a unitary structure and a fuel nozzle assembly using such a component.

  Turbine engines typically include a plurality of fuel nozzles that supply fuel to a combustor within the engine. Fuel is introduced from the fuel nozzle into the tip of the burner in the form of a highly atomized spray. Compressed air flows around the fuel nozzle and mixes with the fuel to form an air / fuel mixture that is ignited by the burner. Due to the limited availability of fuel pressure and the wide range of fuel flow required, many fuel injectors include a pilot nozzle and a main nozzle, only the pilot nozzle is used during start-up, both nozzles being high power Used during operation. The flow to the main nozzle decreases or stops during start-up and low power operation. Such injectors are more efficient and cleaner than single-nozzle fuel injectors because they can control fuel flow more precisely and direct fuel spray more accurately to specific combustor requirements. Can burn. The pilot nozzle and the main nozzle may be housed in the same nozzle assembly or may be supported by separate nozzle assemblies. These dual nozzle fuel injectors can also be configured to allow further control of the fuel for the two combustors, providing even better fuel efficiency and reduced harmful emissions. The temperature of the ignited air-fuel mixture reaches 35000F (19200C) or more. It is therefore important that the fuel delivery system is substantially leak free and protected from flame.

  Because conventional fuel nozzle designs include complex assemblies and connections of more than 30 parts, conventional combustor components, such as fuel nozzles, are typically expensive to manufacture and / or repair. More specifically, by using brazed joints, the need for adequate areas to allow braze alloy placement; the need to minimize unnecessary braze alloy flow; verify brazing quality To produce such parts, for example, due to the need for an acceptable inspection system for; and the need to provide several brazing alloys to prevent remelting of previous brazed joints. The time required may increase and further complicate the manufacturing process. Furthermore, brazing may be performed a plurality of times due to an increase in brazing joint, which may weaken the base material of the component. Increased braze joints can increase part weight and manufacturing costs, which is undesirable.

US Patent Application Publication No. 2005 / 133527A1

  Accordingly, a combustor component, such as a fuel nozzle component, having a single structure to reduce potential leakage and other undesirable effects described above is desirable. A fuel nozzle with fewer parts is desirable, using a single structure composite part to reduce cost and simplify assembly. A method of manufacturing a single combustor part having a complex three-dimensional shape is desirable.

  The above requirements include a body having a single structure, a fuel conduit disposed within the body, and a fuel flow path disposed within the body and in fluid communication with the fuel conduit and oriented circumferentially about an axis. And a combustor component disposed in the body in fluid communication with the fuel flow path and comprising at least one orifice through which fuel entering the fuel conduit exits can be satisfied. .

  In another embodiment, the combustor component is a central body having a unitary structure with the body, having an annular wall surrounding the body, and a plurality of orifices arranged circumferentially around the axis And a central body having a circumferential row of openings corresponding to.

  In another aspect of the invention, the fuel nozzle comprises a single-structure annular fuel distributor having at least one fuel conduit in the body, an annular air swirler disposed within the single fuel distributor, It consists of the fuel injector which is arrange | positioned inside an annular air swirl | blade and can inject a fuel flow.

  In another aspect of the invention, the air swirler includes an annular body, an outer blade row and an inner blade row on the body arranged circumferentially around an axis, and an annular shunt disposed on the body. The annular body, the outer blade row, the inner blade row and the annular flow divider have a single structure.

  In another aspect of the present invention, a method of manufacturing a single part of a combustor includes measuring a three-dimensional information of a single part, and a plurality of three-dimensional information each defining a cross-sectional layer of the single part. It comprises the steps of converting into sections and successively forming each layer of a single part by melting metal powder using laser energy.

  In another aspect of the invention, the combustor component comprises a body having a unitary structure, and the body is manufactured using a high speed manufacturing process.

  The subject matter regarded as the invention is particularly pointed out and distinctly claimed in the concluding portion of the specification. However, the present invention may be best understood by referring to the following description taken in conjunction with the accompanying drawings.

2 is an isometric view of a fuel nozzle according to an exemplary embodiment of the present invention. FIG. FIG. 2 is an axial cross-sectional view of the exemplary embodiment of the present invention shown in FIG. FIG. 2 is a radial cross-sectional view of the exemplary embodiment of the present invention shown in FIG. FIG. 2 is a radial cross-sectional view of the exemplary embodiment of the present invention shown in FIG. FIG. 6 is an isometric view of a fuel nozzle according to an alternative embodiment of the present invention. FIG. 6 is an axial cross-sectional view of the alternative embodiment of the present invention shown in FIG. FIG. 6 is a radial cross-sectional view of the alternative embodiment of the present invention shown in FIG. FIG. 6 is an isometric view of a cross section of the alternative embodiment of the present invention shown in FIG. 7 is a flowchart illustrating an exemplary embodiment of a method of manufacturing the single fuel nozzle component shown in FIGS. 2 and 6.

  Referring to the drawings wherein like reference numerals indicate like elements throughout the several views, FIG. 1 shows a fuel nozzle 5 according to an exemplary embodiment of the present invention. The fuel nozzle comprises a shaft 11, a fuel nozzle tip 10 comprising fuel supply conduits 12, 14 that receive and supply fuel, a fuel distributor 60 that distributes fuel, a central body 70, and fuel and air. A mixing chamber 76 for mixing and a heat shield 72 are provided. In the exemplary embodiment shown in FIG. 1, two fuel supply conduits 12, 14 are shown, for example connected to corresponding fuel supply lines 16, 18. The third supply line 20 supplies fuel to a pilot fuel injector 22 disposed along the axis inside the fuel nozzle tip 10.

  The components and features of the exemplary embodiment of the invention shown in FIG. 1 are clearly seen in the axial cross-sectional view shown in FIG. FIG. 2 shows a fuel nozzle 5 having a single fuel distributor 60, a single air swirler 50, and a pilot fuel injector 22. The term “single” is used in this application to indicate that the relevant part is manufactured as a single unit at the time of manufacture. Thus, a single part has an integral structure of the entire part and is different from a part manufactured from a plurality of part pieces that are joined to form a single part.

  The fuel nozzle 5 is an example of a combustor component. This can be used, for example, to introduce fuel into a combustion environment such as in a combustion rig test, in a gas turbine, or in a combustor that uses a mixture to ignite a flame during combustion. The fuel is supplied to the nozzle 5 using, for example, one or more fuel supply lines as shown in members 16, 18 and 20 of FIG. The fuel supply lines 16, 18 are connected to corresponding fuel conduits in the fuel nozzle 5 using conventional coupling means. In the exemplary embodiment shown in FIG. 2, the two fuel conduits 12, 14 are shown having a generally axial orientation substantially parallel to the axis 11 and have a cross-sectional area “A”. The fuel conduits 12, 14 are formed in the body 61 of the single fuel distributor 60. The single fuel distributor body 61 has an interior that is axisymmetric with respect to the axis 11. The inside of the main body 61 has a substantially cylindrical portion 86 that can hold an air swirler 50 that will be described later in this specification, and a conical portion 84 that is disposed axially forward from the cylindrical portion 86. The conical portion 84 has a venturi 78 that forms part of a mixing chamber 76 where pilot fuel and air mix before combustion. When ignited, a flame is formed axially in front of the venturi 78 exit plane.

  Fuel entering the fuel conduits 12, 14 enters a main fuel circuit 65 (see FIG. 4) formed in the body 61 of the single fuel distributor 60. In the exemplary embodiment shown herein, the main fuel circuit 65 has a generally circumferential orientation about the axis 11 and, as shown in FIGS. 2 and 4, the first fuel path 62 and the second fuel. It consists of a path 64. Fuel from the first fuel conduit 12 flows into the first fuel passage 62 at the first fuel inlet 67, and fuel from the second fuel conduit 14 flows into the second fuel passage 64 at the second fuel inlet 69. Although two axial fuel conduits 12, 14 and corresponding circumferential fuel passages 62, 64 are shown in the embodiments herein, as will be appreciated by those skilled in the art, in the single fuel distributor 60, the others It is possible and have other orientations of fuel conduits and fuel passages of the structure and are within the scope of the present invention.

  As shown in FIGS. 2 and 4, the fuel from the main fuel circuit 65 is guided outward from the fuel distributor 60 by a plurality of fuel orifices 68 disposed in the main body 61. In the exemplary embodiment shown in FIGS. 2, 3 and 4, each fuel orifice 68 is disposed within a fuel column 66. The fuel column 66 is formed as a part of the main body 61. Each fuel orifice 68 is in fluid communication with the fuel passages 62, 64 of the main fuel circuit 65. Pressurized fuel from the main fuel circuit 65 enters the orifice 68 and is discharged out of the fuel nozzle 5. As shown in FIG. 4, the main fuel circuit 65 has a cross-sectional area (indicated by “B”) that changes in the circumferential direction. The change in cross-sectional area “B” is known to maintain a constant pressure in the main fuel circuit 65 as fuel flows from the fuel inlets 67, 69 to a plurality of orifices 68 arranged in the circumferential direction of the body 61. Dimensioned using the method.

  In the exemplary embodiment of the fuel nozzle 5 shown in FIG. 2, the distributor body 61 comprises an annular central body 70 having a unitary structure with the body 61. The central body 70 has an annular outer wall 74 that surrounds the body 61 and forms an annular passage 49 for air flow. A supply air flow 48 that cools the fuel nozzle 5 enters an air flow passage 49 between the central body outer wall 74 and the distributor body 61 and flows through the fuel column to facilitate cooling of the fuel orifice 68. The outer wall 74 has a plurality of openings 71 arranged in the circumferential direction corresponding to the fuel orifices 68 in the circumferential row. The fuel discharged from the orifice 68 exits the fuel nozzle 5 through the opening 71 and enters the combustor. There may be a small gap between the inner diameter of the outer wall 74 and the outer end of the fuel column 66. In the exemplary embodiment shown in FIGS. 1 and 4, this spacing is from about 0.000 inches to about 0.010 inches.

  In the exemplary embodiment shown in FIG. 2, the central body wall 70 is cooled by a multi-hole cooling system that allows one or more circumferential rows of openings 80 to pass through a portion of the supply air flow 48 that enters the fuel nozzle 5. Central body perforated cooling systems typically use one to four rows of openings 80. The opening 80 has a substantially constant diameter. Alternatively, the opening 80 may be a diffusion opening having a variable cross-sectional area. In FIG. 2, two rows of circumferential openings 80 are shown, each row having 60-80 openings, each opening varying between about 0.020 inches and 0.030 inches. Has a diameter. As shown in FIGS. 1, 2, and 3, the openings 80 can have complex axial, radial, and tangential orientations in the outer wall 74. A further row of cooling holes 82 arranged in the circumferential direction of the central body 70 is provided to guide the supply air flow 48 to other parts of the fuel distributor 60. In the exemplary embodiment shown in FIGS. 1 and 2, the body 61 includes an annular heat shield 72 disposed at one end of the body 61. The heat shield 72 protects the main body 61 from flames formed during combustion in the combustor. The heat shield 72 is cooled by one or more circumferential rows of holes 82 having an axial orientation as shown in FIGS. 1 and 2 that guide cooling air impinging on the heat shield 72. In the single structure of the fuel distributor 60, the holes generally have a diameter of at least 0.020 inches. In the exemplary and alternative embodiments shown herein, a circumferential row having 50 to 70 holes with a hole size of about 0.026 inches to about 0.030 inches was used.

  The exemplary embodiment of the invention shown herein comprises a single air swirler 50 that receives an air flow and swirls it axially and circumferentially. The single air swirler 50 has a plurality of inner blades 52 arranged circumferentially around the swirler main body 51. The inner blade 52 extends in the radial direction between the main body 51 and the annular flow divider 53. The single air swirler 50 has a plurality of outer blades 54 arranged circumferentially on the flow divider 53 and extending radially outward from the flow divider 53. The flow divider 53 divides the air flow entering the fuel nozzle 5 into an inner air flow 40 and an outer air flow 42. Inner air flow 40 is swirled by inner vanes 52 and outer air flow 42 is swirled by outer vanes 54. By properly orienting the vanes 52, 54, the inner air flow 40 and the outer air flow 42 can be swung in the same circumferential direction (“same turn”) or in opposite circumferential directions. In the exemplary embodiment shown herein, the inner air stream 40 and the outer air stream 42 are swirling. The swirled inner air stream 40 exiting the inner vane 52 enters an inner passage 44 surrounded by the interior of the annular flow divider 53. From the inner passage 44, the swirling air enters the branch 56 of the flow divider 53 and mixes with the fuel spray injected by the pilot fuel injector 22. A conventional fuel injector 22 is shown in FIG. 2 and comprises a fuel swirler 28 and a pilot fuel injector orifice 26. The swirled outer air flow exiting the outer vanes 54 enters an annular outer passage 46 formed between the radially outer portion of the flow divider 53 and the radially inner surface of the single fuel distributor body 61. The swirled air flow and the fuel injected from the pilot fuel injector 22 are mixed in the mixing chamber 76 formed by the venturi 78 inside the distributor main body 61. The air-fuel mixture thus formed moves forward in the axial direction, exits the fuel nozzle 5, and is ignited to generate a combustion flame. As described above, the fuel nozzle body 61 has the heat shield 72 disposed at the axial rear end of the body 61 in order to protect the fuel nozzle from the flame.

  5, 6, 7 and 8 show an alternative embodiment of the present invention. This alternative embodiment uses a conventional fuel injector 22 and a single air swirler 50 similar to that described above. The single fuel distributor 160 is different from the previous embodiment shown in FIG. The single fuel distributor 160 has a body 161 having fuel conduits 112, 114 and a main fuel circuit 165 in fluid communication with the fuel conduit. As shown in FIG. 7, the main fuel circuit 165 includes a first fuel path 162 and a second fuel path 164. The plurality of fuel orifices 168 arranged in the circumferential direction inject fuel from the fuel passages 162 and 164 into the plurality of recesses 173 and out of the fuel nozzle 105. In the alternative embodiment shown herein, the supply air stream 148 enters the single fuel distributor body 161 through the circumferential row of openings 147 and enters the annular air passage 149 that surrounds the venturi 178. The annular heat shield 172 is disposed at the rear end of the venturi 178 in the axial direction. The annular heat shield is cooled by a collision with cooling air guided through a circumferential array of cooling holes 182. The single fuel distributor body 161 has a cylindrical portion 186 disposed axially forward from the venturi 178. A single air swirler 50 similar to that described above is disposed within the cylindrical portion 186. As described above, the conventional fuel injector 22 is disposed within the single air swirler 50. FIG. 7 shows a radial cross-sectional view of an alternative embodiment of the fuel nozzle 105. FIG. 8 shows a cross-sectional isometric view of an alternative embodiment of the fuel nozzle 105.

  The single fuel distributor 60 of the exemplary embodiment shown in FIG. 2 and the single fuel distributor 160 of the alternative embodiment shown in FIG. 6 are made of direct metal laser sintering (DMLS), laser net shape manufacturing (LNSM). ), High speed manufacturing processes such as electron beam sintering and other known manufacturing processes. DMLS is a preferred method of manufacturing single fuel nozzle components such as the fuel distributors 60, 160 and swirlers 50 described herein.

  FIG. 9 is a flowchart illustrating an exemplary embodiment of a method 200 for manufacturing a single fuel nozzle component as described herein, such as the fuel distributors 60, 160 and the air swirler 50 shown in FIGS. It is. The method 200 includes direct metal laser sintering (DMLS) using a single fuel distributor 60 (shown in FIG. 2), a single fuel distributor 160 (shown in FIG. 6), and an air swirler 50 (FIG. 2). And a step shown in FIG. 6). DMLS is a known manufacturing process for manufacturing metal parts using three-dimensional information of the parts, for example, a three-dimensional computer model. The three-dimensional information is converted into a plurality of sections, and each section defines a cross section of the part with respect to a section having a predetermined height. The parts are then “configured” one piece at a time, or one layer at a time, until completed. Each layer of the component is formed by melting metal powder using a laser.

  Accordingly, the method 200 includes measuring 205 the three-dimensional information of each single fuel nozzle part 50, 60, 160 (shown in FIGS. 2 and 6) and the three-dimensional information for each single fuel nozzle part 50. , 60, and 160, converting 210 into a plurality of sections defining a cross-sectional layer. Thereafter, each single fuel nozzle component 50, 60, 160 is manufactured using DMLS, that is, more specifically, each layer is continuously formed by melting metal powder using laser energy. (Step 215). Each layer has a dimension of about 0.0005 inches to about 0.001 inches. The single fuel nozzle components 50, 60, 160 may be manufactured using a suitable laser sintering machine. Examples of suitable laser sintering machines include, but are not limited to, EOS of North America, Inc., Novi, Michigan. Available from EOSINT. RTM. M270 DMLS machine, PHENIX PM250 machine, and / or EOSINT. RTM. M250 Xtended DMLS machine. The metal powder used to manufacture the single fuel nozzle component 50, 60, 160 is preferably a powder comprising cobalt chromium, but other suitable metal powders such as, but not limited to, HS1888 and INCO625. Good. The metal powder may have a particle size of about 10 microns to 74 microns, preferably about 15 microns to about 30 microns.

  A method of manufacturing a single combustor component, such as a fuel nozzle component, has been described herein using DMLS as the preferred method, but as will be appreciated by those skilled in the art, a multilayer structure or additional manufacturing Other suitable high speed manufacturing methods using can also be used. These alternative high speed manufacturing methods include, but are not limited to, selective laser sintering (SLS), 3D printing methods such as inkjet and laser jet, stereolithography (stereolithography), direct selective laser sintering. (DSLS), electron beam sintering method (EBS), electron beam melting method (EBM), laser technology net shape method (LENS), laser net shape manufacturing method (LNSM) and direct metal deposition method (DMD).

  When referring to the methods and / or fuel nozzle elements / parts / etc. Described and / or illustrated in the present invention, the articles “one”, “its” and “above” refer to one or more elements / parts / Etc. exist. The terms “consisting of”, “including”, and “having” are inclusive and mean that there may be additional elements / parts / etc. Other than the listed elements / parts / etc.

  This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to make and use the invention. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other embodiments include equivalent structural elements in which they have structural elements that do not differ from the language of the claims, or that they have non-essential differences from the language of the claims. In some cases, it is intended to be within the scope of the claims.

Claims (41)

  A method of manufacturing a single part of a fuel nozzle (5), the step of measuring three-dimensional information of the single part (60), and a cross-section of the single part (60) each comprising the three-dimensional information. A method comprising the steps of converting a plurality of sections defining a layer and successively forming each layer of said single part (60) by melting metal powder using laser energy.   The method of claim 1, wherein measuring the three-dimensional information of the single part further comprises measuring a three-dimensional model of the single part (60).   The step of successively forming each layer of the single part by melting metal powder using laser energy further comprises melting a powder comprising at least one of cobalt chrome, HS188 and INCO625. The method according to 1.   The step of successively forming each layer of the single part by melting metal powder using laser energy further comprises melting metal powder having a particle size of about 10 microns to about 75 microns. The method according to 1.   The step of successively forming each layer of the single part by melting metal powder using laser energy further comprises melting metal powder having a particle size of about 15 microns to about 30 microns. 4. The method according to 4.   The method of claim 1, wherein measuring the three-dimensional information of the single part further comprises measuring a three-dimensional model of the single part (60) having an internal conduit (65).   The method of claim 1, wherein measuring the three-dimensional information of the single part further comprises measuring a three-dimensional model of the single part (60) having a plurality of holes (82).   The method of claim 1, wherein measuring the three-dimensional information of the single part further comprises measuring a three-dimensional model of the single part (50) having a plurality of vanes (52, 54). .   The method of claim 1, wherein the single piece is a fuel distributor (60).   The method of claim 1, wherein the single piece is an air swirler (50).   Combustor component (60, 50), comprising a body (61, 51) having a unitary structure, said body (61, 51) being manufactured using a high speed manufacturing process.   The combustor component (60, 50) according to claim 11, wherein the high speed manufacturing process is a laser sintering process.   A combustor component (60, 50) according to claim 11, wherein the high speed manufacturing process is DMLS.   The combustor component (60) of claim 11, wherein the body (61) has an internal conduit (65).   The combustor component (60) of claim 11, wherein the body (61) has a row of holes (82).   The combustor component (60) of claim 11, wherein the component is a fuel distributor (60).   The combustor component (50) of claim 11, wherein the component is an air swirler (50).   The combustor component (50) of claim 11, wherein the component is an air swirler (50) having at least one row of vanes (52).   The combustor component (60) of claim 11, wherein the component is a fuel nozzle component (60).   The combustor component (60) of claim 19, wherein the fuel nozzle component is a fuel distributor (60). A body (61) having a unitary structure;
A fuel conduit (12) disposed within the body (61) and oriented generally axially;
A fuel flow path (62) disposed within the body (61) and in fluid communication with the fuel conduit (12) and oriented circumferentially about an axis (11);
Combustor component disposed in the body (61) in fluid communication with the fuel flow path (62) and comprising at least one orifice (68) through which fuel entering the fuel conduit (12) exits (60).   The combustor component (60) of claim 21, wherein fuel entering the fuel conduit (12) exits through an orifice (68) and enters a recess (68) in the body (61).   A central body (70) having a single structure with the body (61), comprising an annular wall (74) surrounding the body (61) and arranged circumferentially around the shaft (11) The combustor component (60) of claim 22, further comprising the central body (70) having a circumferential array of openings (71) corresponding to the plurality of orifices (68) formed.   24. The at least one circumferential row of apertures (80) disposed on the wall (74) to allow cooling air to flow over a portion of the wall (74). Combustor component (60).   A combustor component (60) according to claim 24, wherein the opening (80) is a diffusion hole.   The combustion of claim 21, further comprising an annular heat shield (72) disposed at one end of the body (61) and capable of protecting the body (61) from a flame located axially rearward therefrom. Instrument parts (60).   27. A combustor component (60) according to claim 26, wherein the body (61) has a circumferential array of axial openings (82) through which cooling air can flow toward the heat shield (72). A body (61) having a unitary structure;
A plurality of fuel conduits (12, 14) disposed within the body (61) and oriented substantially axially and having a substantially constant flow area;
A flow passage area disposed within the body (61), in fluid communication with at least one of the fuel conduits (12, 14), circumferentially oriented around the shaft (11) and changing in the circumferential direction A plurality of fuel flow paths (62, 64) having:
Disposed in the body (61) in fluid communication with at least one of the plurality of fuel flow paths (62, 64), arranged circumferentially around the shaft 11, and connected to the fuel conduit (12, 14). A fuel distributor (60) comprising a plurality of orifices (68) through which fuel enters and exits.   29. The fuel distributor (60) of claim 28, wherein fuel entering the fuel conduit (12) exits through the orifice (68) and enters a plurality of recesses (68) in the body (61).   A central body (70) having a single structure with the body (61), comprising an annular wall (74) surrounding the body (61), and a circumferential row corresponding to the plurality of orifices (68) 29. The fuel distributor (60) of claim 28, further comprising the central body (70) having an opening (71).   31. The at least one circumferential row of apertures (80) disposed on the wall (74) to allow cooling air to flow over a portion of the wall (74). Fuel distributor (60).   32. The fuel distributor (60) according to claim 31, wherein the opening (80) is a diffusion hole.   29. The fuel of claim 28, further comprising an annular heat shield (72) disposed at one end of the body (61) and capable of protecting the body (61) from a flame located axially rearward therefrom. Distributor (60).   34. A fuel distributor (60) according to claim 33, wherein the body (61) has a circumferential array of axial openings (82) through which cooling air can flow toward the heat shield (72). Having at least one fuel conduit (12) having a unitary structure and oriented generally axially within the body (61), in fluid communication with said fuel conduit (12) and around the shaft (11) An annular fuel distributor (60) having at least one fuel flow path (62) in the body (61) oriented circumferentially;
An annular air swirler (50) disposed radially within the single fuel distributor (60) and capable of swirling the incoming air stream;
Fuel disposed radially within the annular air swirler (50) and capable of injecting a fuel stream into the mixing chamber (76) such that fuel and air mix in the mixing chamber (76). A fuel nozzle (5) consisting of an injector (22).   A central body (70) having a unitary structure with the body (61), comprising an annular wall (74) surrounding the body (61), disposed within the body (61), 36. The fuel nozzle (35) of claim 35, further comprising said central body (70) having a circumferential array of openings (71) corresponding to a plurality of orifices (68) arranged circumferentially around 11). 5).   The at least one circumferential row of apertures (80) disposed on the wall (74) and capable of flowing cooling air over a portion of the wall (74). The fuel nozzle (5).   38. A fuel nozzle (5) according to claim 37, wherein the opening (80) is a diffusion hole.   36. The fuel of claim 35, further comprising an annular heat shield (72) disposed at one end of the body (61) and capable of protecting the body (61) from a flame located axially rearward therefrom. Nozzle (5).   40. A fuel nozzle (42) according to claim 39, further comprising at least one row of axial holes (82) disposed on the body (61) through which cooling air can flow toward the heat shield (72). 5). An annular body (51);
An outer blade row (54) disposed on the annular body (51) and arranged circumferentially around the shaft (11);
An inner blade row (52) disposed on the annular body (51), arranged circumferentially around the shaft (11) and radially inward with respect to the outer blade row (54). )When,
An annular flow divider (53) disposed on the annular body (51), the annular body (51), the outer blade row (54), the inner blade row (52) and the annular flow divider (53). ) Is an air swirler (50) having a single structure.

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