EP3425275B1 - Joint de flexion pour buse d'injection de carburant - Google Patents

Joint de flexion pour buse d'injection de carburant Download PDF

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Publication number
EP3425275B1
EP3425275B1 EP18169078.5A EP18169078A EP3425275B1 EP 3425275 B1 EP3425275 B1 EP 3425275B1 EP 18169078 A EP18169078 A EP 18169078A EP 3425275 B1 EP3425275 B1 EP 3425275B1
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EP
European Patent Office
Prior art keywords
fuel
swirler
injector
wall
gap
Prior art date
Legal status (The legal status 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 status listed.)
Active
Application number
EP18169078.5A
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German (de)
English (en)
Other versions
EP3425275A1 (fr
Inventor
Neal A. Thomson
Troy Hall
Daniel Haggerty
Mark Caples
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Collins Engine Nozzles Inc
Original Assignee
Delavan Inc
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Publication date
Application filed by Delavan Inc filed Critical Delavan Inc
Publication of EP3425275A1 publication Critical patent/EP3425275A1/fr
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Publication of EP3425275B1 publication Critical patent/EP3425275B1/fr
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Classifications

    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation
    • 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
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon
    • 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
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • the present invention relates to injectors and nozzles for high temperature applications, and more particularly, to fuel injectors and nozzles for gas turbine engines.
  • a variety of devices and methods are known in the art for injecting fuel into gas turbine engines. Of such devices, many are directed to injecting fuel into combustors of gas turbine engines under high temperature conditions.
  • Fuel injectors for gas turbine engines on an aircraft direct fuel from a manifold to a combustion chamber of a combustor.
  • the fuel injector typically has an inlet fitting connected to the manifold for receiving the fuel, a fuel nozzle located within the combustor for spraying fuel into the combustion chamber, and a housing stem extending between and fluidly interconnecting the inlet fitting and the fuel nozzle.
  • the housing stem typically has a mounting flange for attachment to the casing of the combustor.
  • Fuel injectors are usually heat-shielded because of high operating temperatures arising from high temperature gas turbine compressor discharge air flowing around the housing stem and nozzle.
  • the heat shielding prevents the fuel passing through the injector from breaking down into its constituent components (i.e., "coking"), which may occur when the wetted wall temperatures of a fuel passage exceed 400° F.
  • the coke in the fuel passages of the fuel injector can build up to restrict fuel flow to the nozzle.
  • injectors have included annular stagnant air gaps as insulation between external walls, such as those in thermal contact with high temperature ambient conditions, and internal walls in thermal contact with the fuel.
  • the walls heretofore have been anchored at one end and free at the other end for relative movement. If the downstream tip ends of the walls are left free for relative movement, even a close fitting sliding interface between the downstream tip ends can allow fuel to pass into the air gap formed between the walls. This can result in carbon being formed in the air gap, which carbon is not as good an insulator as air.
  • the carbon may build up to a point where it blocks venting of the air gap to the stem, which can lead to an accumulation of fuel in the air gap. This can lead to diminished injector service life and may require frequent and costly cleaning of the fuel injector.
  • EP 1811229 discloses a fuel injector for a gas turbine engine according to the preamble of claim 1.
  • a bellows is disposed in an insulating gap to prevent fuel entering the gap.
  • US 4962889 discloses an injector tip including a valve member moveable relative to a valve seat member.
  • the valve seat member facilitates the adjustment of the valve cracking pressure.
  • US 5605287 discloses a fuel nozzle having an injector head, with a metering assembly disposed around a valve spool.
  • the metering assembly includes a slideable bellows adjacent a valve sleeve to vary the fuel metering area.
  • EP 1231378 discloses an electromagnetic fuel injector comprising a solenoid actuator for opening and closing a valve.
  • a flexible sealing means provides a spring bias to maintain the valve in a closed position.
  • the invention includes a fuel injector for a gas turbine engine.
  • the fuel injector comprises: a) an injector body having a feed arm with a nozzle body connected thereto; b) a fuel conduit fluidly connecting a fuel inlet portion of the feed arm to a fuel circuit in the nozzle body to form a fuel path through the injector body; c) an outer feed arm wall outboard of the fuel conduit; d) a prefilmer within the nozzle body operatively connected to the fuel conduit of the feed arm to define a portion of the fuel circuit in the nozzle body, wherein the fuel conduit of the feed arm and the prefilmer of the nozzle body form portions of an interior wall of the injector body; e) an outer nozzle body wall outboard of the prefilmer, wherein the outer nozzle body wall and outer feed arm wall form portions of an exterior wall of the injector body; f) a main insulative gap defined between the interior and exterior walls of
  • FIG. 1 a partial view of an exemplary embodiment of an injector in accordance with the invention is shown in Fig. 1 and is designated generally by reference character 200.
  • Other embodiments of injectors and nozzles in accordance with the invention, or aspects thereof, are provided in Figs. 2-5 , as will be described.
  • the devices and methods of the invention can be used in gas turbine engines, or in any other suitable application, for enhanced injector performance.
  • a fuel delivery passage 212 connects a fuel inlet of the injector with discharge outlet 204, allowing for a flow of fuel through the injector 200.
  • An interior wall 208 including fuel conduit 213 within feed arm 218 and prefilmer 227 in nozzle body 220, bounds one side of fluid delivery passage 212.
  • An insulative gap 206 exists between walls 208, 210, portions of which are generally annular. This helps insulate interior fuel passage 212 from ambient conditions. Insulative gap 206 is important for reducing or preventing coking that can occur if the fuel reaches temperatures around 400° F. Coking inside the fuel passage could eventually choke the fuel flow if unchecked.
  • walls 208, 210 need not have the same coefficient of thermal expansion. Thus in operating conditions there can be a significant difference in the thermal expansion of walls 208, 210.
  • walls 208 and 210 In order to reduce stress arising from the thermal gradients, walls 208 and 210 have downstream tip ends 214 that are moveable with respect to one another and form an interface that allows fluid to pass therebetween to gap 206.
  • Gap 206 continues from feed arm 218 through nozzle portion 220 of injector 200.
  • Flexure seal 222 divides gap 206 into a downstream portion 206a and upstream portion 206b. Flexure seal 222 discourages ambient fluids including fuel from entering upstream gap 206b through the opening between wall tips 214. This keeps upstream gap 206b clear from fuel and thus prevents coking buildup therein.
  • Flexure seal 222 is elongate and includes a portion generally sigmoid in shape, as shown in cross-section in Fig. 1 . It can therefore flex to accommodate different amounts of thermal expansion between interior and exterior walls 208, 210. Those skilled in the art will readily appreciate that a variety of suitable shapes can be used in lieu of the sigmoid shape shown in Fig.
  • Flexure seal 222 forms a portion of outer wall 210, joining the outer air cap (which includes outer air swirler 224) and feed arm 218 portions of outer wall 210. Another end 222b is joined to interior wall 208, to further extend the generally sigmoid cross-sectional shape of flexure seal 222. Flexure seal 222 can be joined to injector 200 by brazing, welding, fastening, or any other suitable joining method. Flexure seal 222 accommodates radial thermal expansion differences about the centerline of nozzle body 220. Flexure seal 222 also accommodates thermal expansion differences in other directions, such as the direction along the centerline of feed arm 218, which can also be significant.
  • a fuel swirler wall 226 is located radially inward from prefilmer portion 227 of annular wall 208, with a fuel prefilming chamber defined therebetween.
  • An inner air swirler 228 is disposed radially inward from fuel swirler wall 226 with an insulative gap 230 therebetween. In this manner, inner swirler 228 also acts as a heat shield insulating fuel in the prefilmer chamber from hot gases flowing through inner swirler 228.
  • nozzle 200 includes vents 244, which allow for air in gaps 206/230 to freely expand and contract with changes in temperature.
  • Vents 244 are openings at diametrical clearances between components, such as interfaces between tip ends 214, but can also include bores passing through single components such as inner air swirler 228 and outer wall 210.
  • fuel can be drawn into vents 244 by capillary action, gravity, and/or suction caused by the contraction of cooling air in gaps 206/230, for example when the engine shuts down. Subsequently, if the fuel is heated upon operation of injector 200, coking can occur within gaps 206/230.
  • flexure seal 222 has the advantage of discouraging fuel from passing through vents 244 into upstream portions of gap 206b.
  • an annular flexure beam 232 separates gap 230 into upstream and downstream portions 230a and 230b, respectively.
  • Flexure beam 232 is joined at one end to fuel swirler wall 226, and at its other end to inner air swirler 228. This configuration allows for relative thermal expansion differentials between walls 226, 228 while preventing coking in upstream gap 230a, which is contiguous with gap 206.
  • flexure beam 232 and flexure seal 222 working in conjunction can seal gaps 206/230 from fuel while still allowing for relative thermal expansion differences in the various parts of injector 200.
  • Gap 206 can be airtight. Gap 206 can contain a vacuum, which provides significant insulation between walls 208 and 210. It is also possible to fill gap 206 with air, which can also provide suitable insulation.
  • Noble gasses such as Argon, can also be used as an insulation gas in gap 206, with the advantage of superior heat shielding compared to air. Noble gasses also reduce oxidation of stainless steel, nickel, and other alloys commonly used in nozzle construction. A further advantage of using noble gasses is inflammability.
  • Other insulating materials can also be used, such as fiber insulation, insulating powders, and insulative slurries. Those skilled in the art will readily appreciate that any suitable insulation material can be used in gap 206.
  • gap 206 can be airtight, as discussed above, it is not necessary for gap 206 to be airtight. It is also contemplated that the main insulative gap can include stagnant air that is vented by an opening located in a region where fuel can not enter. For example, a vent into gap 206 can be included so as to allow venting of gap 206 with compressor discharge air such that fuel cannot enter gap 206.
  • flexure seal 222 has been shown as an individual component joined to other nozzle components, it is also possible for a flexure seal to be formed integrally with at least one other nozzle component.
  • the flexure seal can be formed integrally with an outer air swirler, e.g. swirler 224.
  • swirler 224 e.g. swirler 224
  • FIG. 2 shows another exemplary embodiment of an injector 600.
  • Injector 600 includes a single outer air swirler 624 and inner air swirler 628. A portion of outer air swirler 624 is joined to stem portion 618 to form exterior wall 610. Interior wall 608 is spaced apart from exterior wall 610 to form gap 606 much as described above. Flexure seal 622 is completely contained within gap 606 and forms no exterior surface of wall 610. One end of flexure seal 622 is joined to an inside surface of exterior wall 610 and the other end is joined to an outer surface of interior wall 608. A flexure beam 632 is also included, which operates in the same manner as flexure beam 232, described above. Welded aperture 638 is provided in exterior wall 610.
  • gap 606 Prior to welding aperture 638, gap 606 can be evacuated or filled with suitable insulating material, by any suitable process. The insulating material is then sealed in when aperture 638 is welded.
  • injector 600 could be introduced into a noble gas environment with aperture 638 open, allowing gas to enter gap 606. Welding aperture 638 within a noble gas environment seals gap 606, which remains filled with the noble gas. It is also possible to seal insulating material in a gap without using aperture 638. For example, nozzles without aperture 638 can nonetheless have insulating material sealed in their respective gap by brazing, welding, mechanical sealing or packing of respective components.
  • FIG. 3 shows a nozzle portion of a further exemplary embodiment of an injector 700 in accordance with the present invention.
  • Injector 700 includes interior and exterior walls 708, 710 with gap 706 sealed by flexure seal 722, much as described above.
  • Injector 700 further includes outer air swirler 724, fuel swirler wall 726, and inner air swirler 728, as described above.
  • injector 700 includes a c-seal 740, which seals gap 730 in a similar manner by resiliently engaging between inner air swirler 728 and fuel swirler wall 726.
  • c-seals, o-rings, e-rings, d-rings, or other suitable seals can also be used to seal gap 730.
  • c-seal 740 in conjunction with a noble gas insulator.
  • the inner air swirler 728 and c-seal 740 can be inserted into fuel swirler wall 726 while injector 700 is in an argon chamber.
  • Inner air swirler 728 can then be welded to feed arm 718.
  • Inner air swirler 728 and fuel swirler wall 726 compress c-seal 740, trapping the argon in gap 706.
  • FIG. 4 Yet another embodiment of a seal configuration is shown in Fig. 4 in conjunction with injector 800.
  • Injector 800 includes bellows 842, which cooperate with flexure seal 822 to seal gap 806 between walls 808, 810.
  • a c-seal or other suitable seal can be used in lieu of bellows 842 in the same general location by making gap 806 narrower and otherwise configuring gap 806 for sealing by c-seal, or other suitable seal type.
  • Injector 800 also includes a weld aperture 838 located on feed arm 818, which operates similar to weld aperture 638, described above.
  • An additional advantage of using a sealed insulating cavity in accordance with the invention is that the pressure gradient across the sealed cavity and the exterior of the inlet fitting of the injector can be reduced when compared to a vented air cavity.
  • the pressure inside the sealed cavity will be determined by the pressure of the gas during welding and the temperature of the gas during operation. Therefore, stress on the inlet fitting can be reduced by matching the desired operating pressure with the pressure of the gas at the time of manufacture.
  • the combustor pressure would be accounted for across two areas, the nozzle tip and the inlet, with each accounting for half of the total combustor pressure. In this manner, the full combustor pressure will not act on the inlet fitting.
  • injector 900 includes inner wall 908, exterior wall 910, with gap 906 therebetween, sigmoid seal 922, air cap 924, prefilmer 927, and fuel swirler 926 much as described above. Gap 930 between fuel swirler 926 and the inner air swirler is sealed by a two-part inner air swirler wall with upstream section 933 joined to downstream section 928, which is in turn joined to fuel swirler 926. A seal portion 932 of downstream section 928 is located between upstream section 933 and fuel swirler 926.
  • This two-part inner air swirler construction allows seal portion 932 of downstream section 928 of the inner air swirler to function much as flexure beams 232/632 described above. This allows the inner air swirler and upstream portion of the heat shield to be formed as one integral piece, thereby reducing the number of components and joints.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Claims (6)

  1. Injecteur de carburant (200) pour un moteur à turbine à gaz comprenant :
    a) un corps d'injecteur ayant un bras d'alimentation (218) avec un corps de buse (220) relié à celui-ci ;
    b) un conduit de carburant (213) reliant fluidiquement une partie d'entrée de carburant du bras d'alimentation à un circuit de carburant dans le corps de buse pour former un trajet de carburant à travers le corps d'injecteur ;
    c) une paroi de bras d'alimentation externe (210) à l'extérieur du conduit de carburant ;
    d) un préfilmeur (227) à l'intérieur du corps de buse relié de manière fonctionnelle au conduit de carburant du bras d'alimentation pour définir une partie du circuit de carburant dans le corps de buse, dans lequel le conduit de carburant du bras d'alimentation et le préfilmeur du corps de buse forment des parties d'une paroi intérieure (208) du corps d'injecteur ;
    e) une paroi de corps de buse externe (210) à l'extérieur du préfilmeur, dans lequel la paroi de corps de buse externe et la paroi de bras d'alimentation externe forment des parties d'une paroi extérieure du corps d'injecteur ;
    f) un espace isolant principal (206) défini entre les parois intérieure et extérieure du corps d'injecteur pour isoler thermiquement le trajet de carburant du corps d'injecteur des conditions ambiantes ;
    h) un tourbillonneur de carburant disposé radialement vers l'intérieur du préfilmeur avec une chambre de préfilmage définie entre le tourbillonneur de carburant et le préfilmeur ;
    caractérisé par :
    i) un tourbillonneur d'air interne (228) disposé radialement vers l'intérieur du tourbillonneur de carburant avec un espace isolant interne (230) défini entre le tourbillonneur d'air interne et le tourbillonneur de carburant, dans lequel l'espace isolant interne est en communication fluidique avec l'espace isolant principal du corps d'injecteur ; et
    j) une poutre de flexion annulaire (232) disposée dans l'espace isolant interne entre le tourbillonneur de carburant et le tourbillonneur d'air interne, dans lequel la poutre de flexion annulaire est jointe à une première extrémité au tourbillonneur de carburant et est jointe à une seconde extrémité au tourbillonneur d'air interne.
  2. Injecteur de carburant (200) selon la revendication 1, dans lequel la poutre de flexion annulaire (232) dans l'espace isolant interne (230) comporte une partie de poutre de flexion annulaire du tourbillonneur d'air interne (228) disposée entre une partie amont du tourbillonneur d'air interne et le tourbillonneur de carburant.
  3. Injecteur de carburant (200) selon la revendication 1 ou 2, dans lequel une partie de l'espace isolant principal (206) à l'intérieur du bras d'alimentation (218) est évacuée vers l'air d'évacuation de compresseur de moteur.
  4. Injecteur de carburant (200) selon l'une quelconque des revendications 1 à 3, comprenant en outre :
    g) un moyen d'isolation interne au corps d'injecteur pour sceller une partie de l'espace isolant principal (206) des fluides ambiants et fournir un mouvement relatif entre les parois intérieure (208) et extérieure (210) du corps d'injecteur.
  5. Injecteur de carburant (200) selon la revendication 4, dans lequel le moyen d'isolation comporte un joint de flexion généralement sigmoïde (222) disposé à travers une partie de l'espace isolant principal (206) entre la paroi extérieure (210) et le préfilmeur (227).
  6. Injecteur de carburant (200) selon une quelconque revendication précédente, dans lequel la poutre de flexion annulaire (232) interne au corps de buse isole l'espace isolant interne de tout fluide ambiant entrant dans l'espace isolant principal (206) à travers celui-ci et fournit des mouvements axial et radial relatifs entre une paroi de tourbillonneur de carburant (226) et le tourbillonneur d'air intérieur (228).
EP18169078.5A 2007-09-17 2008-09-17 Joint de flexion pour buse d'injection de carburant Active EP3425275B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US99405307P 2007-09-17 2007-09-17
EP08832161.7A EP2188569B1 (fr) 2007-09-17 2008-09-17 Joint de flexure pour la buse d'injection de carburant
PCT/US2008/076610 WO2009039142A2 (fr) 2007-09-17 2008-09-17 Joint flexible pour injecteur de carburant

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
EP08832161.7A Division EP2188569B1 (fr) 2007-09-17 2008-09-17 Joint de flexure pour la buse d'injection de carburant

Publications (2)

Publication Number Publication Date
EP3425275A1 EP3425275A1 (fr) 2019-01-09
EP3425275B1 true EP3425275B1 (fr) 2020-11-18

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP08832161.7A Active EP2188569B1 (fr) 2007-09-17 2008-09-17 Joint de flexure pour la buse d'injection de carburant
EP18169078.5A Active EP3425275B1 (fr) 2007-09-17 2008-09-17 Joint de flexion pour buse d'injection de carburant

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08832161.7A Active EP2188569B1 (fr) 2007-09-17 2008-09-17 Joint de flexure pour la buse d'injection de carburant

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EP (2) EP2188569B1 (fr)
WO (1) WO2009039142A2 (fr)

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US8196845B2 (en) * 2007-09-17 2012-06-12 Delavan Inc Flexure seal for fuel injection nozzle
US20090255258A1 (en) * 2008-04-11 2009-10-15 Delavan Inc Pre-filming air-blast fuel injector having a reduced hydraulic spray angle
US8015816B2 (en) 2008-06-16 2011-09-13 Delavan Inc Apparatus for discouraging fuel from entering the heat shield air cavity of a fuel injector
GB0916944D0 (en) 2009-09-28 2009-11-11 Rolls Royce Plc Air blast fuel injector
US9488105B2 (en) 2010-12-01 2016-11-08 Siemens Aktiengesellschaft Gas turbine assembly and method therefor
US20120137691A1 (en) * 2010-12-01 2012-06-07 Bottcher Andreas Gas turbine assembly and method therefor
US20120180494A1 (en) * 2011-01-14 2012-07-19 General Electric Company Turbine fuel nozzle assembly
US20130036740A1 (en) * 2011-08-09 2013-02-14 Ulrich Woerz Multi-fuel injection nozzle
CN103398398B (zh) * 2013-08-12 2016-01-20 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机燃烧室火焰筒与过渡段的双密封连接结构
US20160003157A1 (en) 2014-07-03 2016-01-07 United Technologies Corporation Additive manufactured tube assembly
US9759356B2 (en) * 2014-07-03 2017-09-12 United Technologies Corporation Insulated flowpath assembly
GB2571071B (en) 2018-02-09 2022-04-06 Rolls Royce Plc Nozzle for fuel injector with a sealing member
GB201909167D0 (en) 2019-06-26 2019-08-07 Rolls Royce Plc Fuel injector

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US4962889A (en) * 1987-12-11 1990-10-16 Fuel Systems Textron Inc. Airblast fuel injection with adjustable valve cracking pressure
US5605287A (en) * 1995-01-17 1997-02-25 Parker-Hannifin Corporation Airblast fuel nozzle with swirl slot metering valve
US6655611B2 (en) * 2001-02-12 2003-12-02 Delphi Technologies, Inc. Electromagnetic fuel injector comprising flexible element for positioning armature
US6622488B2 (en) * 2001-03-21 2003-09-23 Parker-Hannifin Corporation Pure airblast nozzle
US20060158091A1 (en) * 2005-01-20 2006-07-20 Jack Jiang Fluorescent lamp assembly
EP1811229B1 (fr) 2006-01-20 2021-04-28 Parker-Hannifin Corporation Buses d'injecteur de carburant pour moteurs de turbines à gaz
US7703287B2 (en) * 2006-10-31 2010-04-27 Delavan Inc Dynamic sealing assembly to accommodate differential thermal growth of fuel injector components

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Title
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Also Published As

Publication number Publication date
EP2188569A2 (fr) 2010-05-26
WO2009039142A3 (fr) 2010-04-15
EP3425275A1 (fr) 2019-01-09
EP2188569B1 (fr) 2018-04-25
WO2009039142A2 (fr) 2009-03-26

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