WO2009126534A1 - Composant de chambre de combustion et son procédé de fabrication - Google Patents

Composant de chambre de combustion et son procédé de fabrication Download PDF

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Publication number
WO2009126534A1
WO2009126534A1 PCT/US2009/039485 US2009039485W WO2009126534A1 WO 2009126534 A1 WO2009126534 A1 WO 2009126534A1 US 2009039485 W US2009039485 W US 2009039485W WO 2009126534 A1 WO2009126534 A1 WO 2009126534A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
component
unitary
annular
combustor
Prior art date
Application number
PCT/US2009/039485
Other languages
English (en)
Inventor
Marie Ann Mcmasters
Steven Joseph Lohmueller
Randall Charles Boehm
Original Assignee
General Electric Company
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US12/101,278 external-priority patent/US9188341B2/en
Priority claimed from US12/101,288 external-priority patent/US20090255256A1/en
Application filed by General Electric Company filed Critical General Electric Company
Priority to GB1016954.8A priority Critical patent/GB2470875B/en
Priority to CA2720262A priority patent/CA2720262A1/fr
Priority to JP2011504094A priority patent/JP2011520055A/ja
Priority to DE112009000822T priority patent/DE112009000822T5/de
Publication of WO2009126534A1 publication Critical patent/WO2009126534A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/34—Laser welding for purposes other than joining
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/20—Bonding
    • B23K26/32—Bonding taking account of the properties of the material involved
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/02—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape
    • B23K35/0222—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape for use in soldering, brazing
    • B23K35/0244—Powders, particles or spheres; Preforms made therefrom
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/10—Primary casings; Jackets or wrappings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/50—Inorganic material, e.g. metals, not provided for in B23K2103/02 – B23K2103/26
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/10—Energy storage using batteries

Definitions

  • This invention relates generally to combustors, and more specifically to fuel nozzle components having a unitary construction and fuel nozzle assemblies using such components.
  • Turbine engines typically include a plurality of fuel nozzles for supplying fuel to the combustor in the engine.
  • the fuel is introduced at the front end of a burner in a highly atomized spray from a fuel nozzle.
  • Compressed air flows in around the fuel nozzle and mixes with the fuel to form a fuel-air mixture, which is ignited by the burner.
  • many fuel injectors include pilot and main nozzles, with only the pilot nozzles being used during start-up, and both nozzles being used during higher power operation. The flow to the main nozzles is reduced or stopped during start-up and lower power operation.
  • Such injectors can be more efficient and cleaner- burning than single nozzle fuel injectors, as the fuel flow can be more accurately controlled and the fuel spray more accurately directed for the particular combustor requirement.
  • the pilot and main nozzles can be contained within the same nozzle assembly or can be supported in separate nozzle assemblies.
  • These dual nozzle fuel injectors can also be constructed to allow further control of the fuel for dual combustors, providing even greater fuel efficiency and reduction of harmful emissions.
  • the temperature of the ignited fuel-air mixture can reach an excess of 3500 0 F (1920 0 C). It is therefore important that the fuel supply and distribution systems are substantially leak free and are protected from the flames.
  • braze joints can increase the time needed to fabricate such components and can also complicate the fabrication process for any of several reasons, including: the need for an adequate region to allow for braze alloy placement; the need for minimizing unwanted braze alloy flow; the need for an acceptable inspection technique to verify braze quality; and, the necessity of having several braze alloys available in order to prevent the re-melting of previous braze joints.
  • numerous braze joints may result in several braze runs, which may weaken the parent material of the component. The presence of numerous braze joints can undesirably increase the weight and manufacturing cost of the component.
  • combustor components such as, for example, fuel nozzle components, that have unitary construction for reducing potential leakage and other undesirable effects described earlier. It is desirable to have a fuel nozzle that has fewer components using a unitary construction of complex components to reduce the cost and for ease of assembly. It is desirable to have a method of manufacturing unitary combustor components having complex three-dimensional geometries.
  • a combustor component comprising a body having a unitary construction, a fuel conduit located within the body, a fuel flow path located within the body that is oriented in a circumferential direction around an axis and in flow communication with the fuel conduit, and at least one orifice located in the body in flow communication with the fuel flow path such that a fuel entering the fuel conduit exits through the orifice.
  • the combustor component described above further comprises a centerbody having a unitary construction with the body, the centerbody having an annular wall surrounding the body and having a circumferential row of openings corresponding to a plurality of orifices arranged circumferentially around the axis.
  • a fuel nozzle comprises an annular fuel distributor having a unitary construction and having at least one fuel conduit within the body, an annular air-swirler located inside the unitary fuel distributor and a fuel injector located inside the annular air swirler capable of injecting a stream of fuel.
  • an air-swirler comprises an annular body, a row of outer vanes and a row of inner vanes on the body arranged circumferentially around an axis and an annular splitter located on the body, wherein the annular body, the row of outer vanes, the row of inner vanes and the annular splitter have a unitary construction.
  • a method for fabricating a unitary component for a combustor comprises the steps of determining three-dimensional information of the unitary component, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary component, and successively forming each layer of the unitary component by fusing a metallic powder using laser energy.
  • a combustor component comprises a body having a unitary construction wherein the body is made by using a rapid manufacturing process.
  • FIG. 1 is an isometric view of a fuel nozzle according to an exemplary embodiment of the present invention.
  • FIG. 2 is an axial cross sectional view of the exemplary embodiment of the present invention shown in FIG. 1.
  • FIG. 3 is a radial cross sectional view of the exemplary embodiment of the present invention shown in FIG. 1.
  • FIG. 4 is a radial cross sectional view of the exemplary embodiment of the present invention shown in FIG. 1.
  • FIG. 5 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. 5.
  • FIG. 7 is a radial cross sectional view of the alternative embodiment of the present invention shown in FIG. 5.
  • FIG. 8 is an isometric view of a cross section of the alternative embodiment of the present invention shown in FIG. 5.
  • FIG. 9 is a flow chart illustrating an exemplary embodiment of a method for fabricating unitary fuel nozzle components shown in FIG. 2 and FIG. 6
  • FIG. 1 shows a fuel nozzle 5 according to an exemplary embodiment of the present invention.
  • the fuel nozzle has an axis 11, a fuel nozzle tip 10 comprising a fuel supply conduit 12, 14 that receive and supply fuel into the fuel nozzle tip 10, a fuel distributor 60 that distributes the fuel, a center body 70, a mixing chamber 76 wherein fuel and air are mixed, and a heat shield 72.
  • a fuel supply conduit 12, 14 are shown, for example, that are coupled to corresponding fuel supply lines 16, 18.
  • a third supply line 20 supplies fuel to a pilot fuel injector 22 that is located along the axis inside the fuel nozzle tip 10.
  • FIG. 2 shows the fuel nozzle 5 having a unitary fuel distributor 60, a unitary air-swirler 50, and a pilot fuel injector 22.
  • unitary is used in this application to denote that the associated component is made as a single piece during manufacturing.
  • a unitary component has a monolithic construction for the entire component, and is different from a component that has been made from a plurality of component pieces that have been joined together to form a single component.
  • the fuel nozzle 5 is an example of a combustor component. It can be used to introduce fuel into a combustor environment, such as for example, in combustion rig tests, in gas turbine engines, or any combustors that use a fuel-air mixture for igniting a flame during combustion.
  • the fuel is supplied to nozzle 5 using one or more fuel supply lines, such as for example, shown as items 16, 18 and 20 in FIG. 2.
  • the fuel supply lines 16, 18 are connected using conventional coupling means to corresponding fuel conduits in the fuel nozzle 5.
  • two fuel conduits 12, 14 are shown as having a generally axial orientation, substantially parallel to the axis 11, having a cross sectional area "A".
  • the fuel conduits 12, 14 are formed within the body 61 of the unitary fuel distributor 60.
  • the body 61 of the unitary fuel distributor has an interior portion that is axisymmetric about the axis 11.
  • the interior portion of the body 61 has a substantially cylindrical portion 86 that can hold an air-swirler 50 described subsequently herein, and a conical portion 84 that is located axially forward from the cylindrical portion 86.
  • the conical portion 84 has a venturi 78 that forms a part of a mixing chamber 76 wherein the pilot fuel and air are mixed prior to combustion. When ignited, a flame is formed axially in front of the exit plane of the venturi 78.
  • the fuel entering the fuel conduits 12, 14 enters a main fuel circuit 65 (see FIG. 4) formed within the body 61 of the unitary fuel distributor 60.
  • the main fuel circuit 65 has a generally circumferential orientation around the axis 11 , and comprises a first fuel path 62 and a second fuel path 64, as shown in FIG. 2 and FIG. 4.
  • Fuel from the first fuel conduit 12 flows into the first fuel path 62 at a first fuel inlet 67 and fuel from the second fuel conduit 14 flows into the second fuel path 64 at a second fuel inlet 69.
  • fuel from the main fuel circuit 65 is directed outward from the fuel distributor 60 by a plurality of fuel orifices 68 that are located within the body 61.
  • each fuel orifice 68 is located inside a fuel post 66.
  • the fuel posts 66 are formed as a part of the body 61.
  • Each fuel orifice 68 is in flow communication with a fuel path 62, 64 of the main fuel circuit 65. Pressurized fuel from the main fuel circuit 65 enters the orifices 68 and is ejected out of the fuel nozzle 5. As shown in FIG.
  • the main fuel circuit 65 has a cross section area (denoted as "B") that varies in the circumferential direction.
  • the variation of cross section area "B” is sized using known methods so as to maintain a constant pressure within the main fuel circuit 65 as the fuel flows from the fuel inlets 67, 69 to a plurality of orifices 68 that are arranged in the circumferential direction in the body 61.
  • the distributor body 61 comprises an annular center body 70 having a unitary construction with the body 61.
  • the centerbody 70 has an annular outer wall 74 that surrounds the body 61 and forms an annular passage 49 for air flow.
  • a feed air stream 48 for cooling the fuel nozzle 5 enters the air flow passage 49 between the centerbody outer wall 74 and the distributor body 61 and flows past the fuel posts, facilitating the cooling of the fuel orifices 68.
  • the outer wall 74 has a plurality of openings 71 that are arranged in the circumferential direction, corresponding to the circumferential row of fuel orifices 68.
  • the centerbody wall 70 is cooled by a multi-hole cooling system which passes a portion of the feed air stream 48 entering the fuel nozzle 5 through one or more circumferential rows of openings 80.
  • the multi-hole cooling system of the centerbody may typically use one to four rows of openings 80.
  • the openings 80 may have a substantially constant diameter.
  • the openings 80 may be diffuser openings that have a variable cross sectional area.
  • FIG. 2 two circumferential rows of openings 80 are shown, each row having between 60 to 80 openings and each opening having a diameter varying between about .020 inches and 0.030 inches. As shown in FIGs.
  • the openings 80 can have a complex orientation in the axial, radial and tangential directions within the outer wall 74. Additional rows of cooling holes 82 arranged in the circumferential direction in the centerbody 70 are provided to direct the feed air stream 48 toward other parts of the fuel distributor 60.
  • the body 61 comprises an annular heat shield 72 located at one end of the body 61.
  • the heat shield 72 shields the body 61 from the flame that is 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 direct cooling air that impinges on the heat shield 72.
  • the holes typically have a diameter of at least 0.020 inches.
  • a circumferential row having between 50 to 70 holes, with a hole size between about 0.026 inches to about 0.030 inches was used.
  • the exemplary embodiments of the present invention shown herein comprise a unitary air-swirler 50 that receives an air stream and swirls it in the axial and circumferential directions.
  • the unitary air-swirler 50 has a plurality of inner vanes 52 arranged circumferentially around a swirler body 51.
  • the inner vanes 52 extend in the radial direction between the body 51 and an annular splitter 53.
  • the unitary air-swirler 50 has a plurality of outer vanes 54 arranged circumferentially on the splitter 53 and extend radially outward from the splitter 53.
  • the splitter 53 splits the air stream entering the fuel nozzle 5 into an inner air stream 40 and an outer air stream 42.
  • the inner air stream 40 is swirled by the inner vanes 52 and the outer air stream 42 is swirled by the outer vanes 54. It is possible, by appropriate orientation of the vanes 52, 54, to swirl the inner air stream 40 and outer air stream 42 in the same circumferential direction ("co-swirl") or in the opposite circumferential directions. In the exemplary embodiments shown herein, the inner air stream 40 and the outer air stream 42 are co-swirled.
  • the swirled inner air stream 40 exiting from the inner vanes 52 enters an inner passage 44 that is bounded by the interior of the annular splitter 53. From the inner passage 44, the swirling air enters a diverging portion 56 of the splitter
  • a conventional fuel injector 22 is shown in FIG. 2, comprising a fuel-swirler 28 and a pilot fuel injector orifice 26.
  • the swirled outer air stream leaving the outer vanes 54 enters an annular outer passage 46 formed between the radially outer portion of the splitter 53 and the radially interior side of the unitary fuel distributor body 61.
  • the swirled air streams and fuel ejected from the pilot fuel injector 22 mix within a mixing chamber 76 formed by a venturi 78 inside the distributor body 61.
  • the fuel-air mixture thus formed moves axially forward and exits the fuel nozzle 5 and ignited to create a combustion flame.
  • the fuel nozzle body 61 has a heat shield 72 located at the axially aft end of the body 61 to protect the fuel nozzle from the flame.
  • FIG. 5, FIG. 6, FIG. 7 and FIG. 8 show an alternative embodiment of the present invention.
  • This alternative embodiment uses a conventional fuel injector 22 and a unitary air-swirler 50 similar to the ones described previously.
  • the unitary fuel distributor 160 is different from the previously described embodiment shown in FIG. 1.
  • the unitary fuel distributor 160 has a body 161 having fuel conduits 112, 114 and a main fuel circuit 165 in flow communication with the fuel conduits.
  • the main fuel circuit 165 comprises a first fuel path 162 and a second fuel path 164.
  • a plurality of fuel orifices 168 that are arranged circumferentially eject the fuel from the fuel paths 162, 164 into a plurality of recesses 173 and out of the fuel nozzle 105.
  • a feed air stream 148 enters the unitary fuel distributor body 161 through a circumferential row of openings 147 and enters an annular air passage 149 surrounding a venturi 178.
  • An annular heat shield 172 is located at the axially aft end of the venturi 178. The annular heat shield is cooled by impingement using cooling air directed through a circumferential row of cooling holes 182.
  • the unitary fuel distributor body 161 has a cylindrical portion 186 that is located axially forward from the venturi 178.
  • a unitary air-swirler 50 similar to the one described previously is located within the cylindrical portion 186.
  • a conventional fuel injector 22 is located within the unitary air- swirler 50.
  • FIG. 7 shows a radial cross sectional view of the alternative embodiment of the fuel nozzle 105.
  • FIG. 8 shows an isometric view of a cross section of the alternative embodiment of the fuel nozzle 105.
  • the unitary fuel distributor 60 of the exemplary embodiment shown in FIG. 2 and the unitary fuel distributor 160 of the alternative embodiment shown in FIG. 6 can be made using rapid manufacturing processes such as Direct Metal Laser Sintering (DMLS), Laser Net Shape Manufacturing (LNSM), electron beam sintering and other known processes in the manufacturing.
  • DMLS is a preferred method of manufacturing unitary fuel nozzle components such as the fuel distributors 60, 160 and swirler 50 described herein.
  • FIG. 9 is a flow chart illustrating an exemplary embodiment of a method 200 for fabricating unitary fuel nozzle components described herein, such as the fuel distributors 60, 160 and air-swirler 50 shown in FIG. 2 and FIG. 6.
  • Method 200 includes fabricating unitary fuel distributor 60 (shown in FIG. 2), unitary fuel distributor 160 (shown in FIG. 6) and air-swirler 50 (shown in FIG. 2 and FIG. 6) using Direct Metal Laser Sintering (DMLS).
  • DMLS is a known manufacturing process that fabricates metal components using three-dimensional information, for example a three-dimensional computer model, of the component.
  • the three- dimensional information is converted into a plurality of slices, each slice defining a cross section of the component for a predetermined height of the slice.
  • the component is then "built-up" slice by slice, or layer by layer, until finished.
  • Each layer of the component is formed by fusing a metallic powder using a laser.
  • method 200 includes the step 205 of determining three- dimensional information of each unitary fuel nozzle component 50, 60, 160 (shown in FIG. 2 and FIG. 6) and the step 210 of converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary fuel nozzle component 50, 60, 160.
  • Each unitary fuel nozzle component 50, 60, 160 is then fabricated using DMLS, or more specifically each layer is successively formed 215 by fusing a metallic powder using laser energy.
  • Each layer has a size between about 0.0005 inches and about 0.001 inches.
  • Unitary fuel nozzle components 50, 60, 160 may be fabricated using any suitable laser sintering machine.
  • suitable laser sintering machines include, but are not limited to, an EOSINT.RTM. M 270 DMLS machine, a PHENIX PM250 machine, and/or an EOSINT.RTM. M 250 Xtended DMLS machine, available from EOS of North America, Inc. of Novi, Michigan.
  • the metallic powder used to fabricate unitary fuel nozzle components 50, 60, 160 is preferably a powder including cobalt chromium, but may be any other suitable metallic powder, such as, but not limited to, HS 1888 and INCO625.
  • the metallic powder can have a particle size of between about 10 microns and 74 microns, preferably between about 15 microns and about 30 microns.
  • SLS Selective Laser Sintering
  • DSLS Direct Selective Laser Sintering
  • EBS Electron Beam Sintering
  • EBM Electron Beam Melting
  • LENS Laser Engineered Net Shaping
  • LNSM Laser Net Shape Manufacturing
  • DMD Direct Metal Deposition

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Mechanical Engineering (AREA)
  • Plasma & Fusion (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Powder Metallurgy (AREA)
  • Laser Beam Processing (AREA)
  • Gas Burners (AREA)

Abstract

L’invention concerne un procédé permettant de fabriquer un composant unitaire pour une chambre de combustion. Ledit procédé comprend les étapes consistant à déterminer les informations tridimensionnelles du composant unitaire (60), convertir les informations tridimensionnelles en une pluralité de tranches délimitant chacune une couche transversale du composant unitaire (60), et former successivement chaque couche du composant unitaire (60) en faisant fondre une poudre métallique au moyen d’une énergie laser. L’invention concerne un composant de chambre de combustion (60, 50) qui comprend un corps (61, 51) avec une construction unitaire, le corps (61, 51) étant fabriqué selon un procédé de fabrication rapide.
PCT/US2009/039485 2008-04-11 2009-04-03 Composant de chambre de combustion et son procédé de fabrication WO2009126534A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB1016954.8A GB2470875B (en) 2008-04-11 2009-04-03 Combustor component and method of manufacture
CA2720262A CA2720262A1 (fr) 2008-04-11 2009-04-03 Composant de chambre de combustion et son procede de fabrication
JP2011504094A JP2011520055A (ja) 2008-04-11 2009-04-03 燃焼器部品及び製造方法
DE112009000822T DE112009000822T5 (de) 2008-04-11 2009-04-03 Brennerkomponente und Verfahren zur Herstellung

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US12/101,278 US9188341B2 (en) 2008-04-11 2008-04-11 Fuel nozzle
US12/101,288 US20090255256A1 (en) 2008-04-11 2008-04-11 Method of manufacturing combustor components
US12/101,288 2008-04-11
US12/101,278 2008-04-11

Publications (1)

Publication Number Publication Date
WO2009126534A1 true WO2009126534A1 (fr) 2009-10-15

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PCT/US2009/039485 WO2009126534A1 (fr) 2008-04-11 2009-04-03 Composant de chambre de combustion et son procédé de fabrication

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JP (1) JP2011520055A (fr)
CA (1) CA2720262A1 (fr)
DE (1) DE112009000822T5 (fr)
GB (1) GB2470875B (fr)
WO (1) WO2009126534A1 (fr)

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EP2400222A1 (fr) * 2010-06-28 2011-12-28 Siemens Aktiengesellschaft Appareil de combustion
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EP2971684A4 (fr) * 2013-03-14 2016-03-09 United Technologies Corp Bouclier thermique à paroi creuse pour un composant d'injecteur de carburant
US9498848B2 (en) 2013-01-30 2016-11-22 Rolls-Royce Plc Method of manufacturing a wall
US9528705B2 (en) 2014-04-08 2016-12-27 General Electric Company Trapped vortex fuel injector and method for manufacture
US9551490B2 (en) 2014-04-08 2017-01-24 General Electric Company System for cooling a fuel injector extending into a combustion gas flow field and method for manufacture
EP3361161A1 (fr) * 2017-02-13 2018-08-15 Ansaldo Energia Switzerland AG Ensemble brûleur pour chambre de combustion d'une centrale électrique à turbine à gaz et chambre de combustion comprenant ledit ensemble brûleur
US11199328B2 (en) 2017-02-13 2021-12-14 Ansaldo Energia Switzerland AG Method for manufacturing a burner assembly for a gas turbine combustor and burner assembly for a gas turbine combustor

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CN105829800B (zh) * 2013-12-23 2019-04-26 通用电气公司 用于空气协助的燃料喷射的燃料喷嘴结构
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JP6804755B2 (ja) * 2015-11-26 2020-12-23 ウエムラ技研株式会社 渦巻型噴射ノズル
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JP2011520055A (ja) 2011-07-14
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CA2720262A1 (fr) 2009-10-15
DE112009000822T5 (de) 2011-03-03

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