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    Birdstrike resistant swirler support for combustion chamber dome
    5.
    发明公开
    Birdstrike resistant swirler support for combustion chamber dome 失效
    VogelschlagbeständigerWirbelvorrichtungsträgereines Brennkammerdomes。

    公开(公告)号：EP0549184A1

    公开(公告)日：1993-06-30

    申请号：EP92311192.6

    申请日：1992-12-09

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Koshoffer, John Michael ,  Cooper, James Neil ,  Haas, Mary Catherine ,  Reinhold, James Norman, Jr.

    IPC: F23R3/28

    CPC classification number: F23R3/283

    Abstract: A backing support or bumper (50) mounted downstream of the disk shaped flange (40) of the venturi in adjacently lying fuel cup assemblies in a gas turbine combustor and extends to a mid portion of each flange to prevent rotation of the flange and possible disengagement of the fuel nozzle in the event of a bird strike or impact by a foreign object on the dome of the combustor or on the flange itself.The invention provides for a single or double supporting bumper faces or a pair of supporting surfaces on the bumper.

    Abstract translation: 背衬支撑件或保险杠（50），其安装在文丘里管的盘形凸缘（40）的下游，位于燃气轮机燃烧器中的相邻位置的燃料杯组件中，并延伸到每个凸缘的中间部分，以防止凸缘的旋转和可能的分离 在鸟类撞击或外来物体撞击在燃烧室的圆顶或凸缘本身上的情况下，燃料喷嘴。本发明提供了缓冲器上的单个或双重支撑保险杠面或一对支撑表面。

    Fuel nozzle for gas turbine engines
    8.
    发明公开
    Fuel nozzle for gas turbine engines 审中-公开
    BrennstoffdüsefürGasturbinen

    公开(公告)号：EP1760403A2

    公开(公告)日：2007-03-07

    申请号：EP06254482.0

    申请日：2006-08-29

    Applicant: General Electric Company

    Inventor： Held, Timothy James ,  Cooper, James Neil

    IPC: F23R3/28 ,  F23R3/36 ,  F23L7/00 ,  F23D11/38

    CPC classification number: F23L7/007 ,  F23D11/24 ,  F23D11/386 ,  F23D2209/30 ,  F23D2214/00 ,  F23L7/005 ,  F23R3/14 ,  F23R3/286 ,  F23R3/36 ,  Y02E20/344

    Abstract: A gas turbine engine (10) fuel nozzle (100) includes an axis of symmetry (143) extending therethrough, the nozzle body (110) including a first passage (142) extending coaxially therethrough, a second passage (152), and a third passage (162), the second passage circumscribing the first passage, the third passage formed radially outward of the second passage, and a nozzle tip (112) coupled to the nozzle body, the nozzle tip including at least one primary discharge opening (170) in flow communication with the first passage, at least one secondary discharge opening (172) in flow communication with the second passage, and at least one tertiary discharge opening in flow communication with the third passage.

    Abstract translation: 燃气涡轮发动机（10）燃料喷嘴（100）包括延伸穿过其中的对称轴（143），所述喷嘴体（110）包括同轴地延伸穿过其中的第一通道（142），第二通道（152）和第三通道 通道（162），第二通道限定第一通道，第三通道形成在第二通道的径向外侧;以及喷嘴头（112），其连接到喷嘴体，喷嘴尖端包括至少一个主排出口（170） 与所述第一通道流动连通，与所述第二通道流动连通的至少一个次级排放开口（172）以及与所述第三通道流动连通的至少一个第三排放口。

    Fuel injector laminated fuel strip
    9.
    发明公开
    Fuel injector laminated fuel strip 有权
    Laminierte Brennstofflamelle einerBrennstoffeinspritzdüse

    公开(公告)号：EP1369644A1

    公开(公告)日：2003-12-10

    申请号：EP03253522.1

    申请日：2003-06-04

    Applicant: GENERAL ELECTRIC COMPANY ,  Parker-Hannifin Corporation

    Inventor： Laing, Peter ,  Wrubel, Michael Peter ,  Savel, Barry Walford ,  Harvey, Rex Jay ,  Mancini, Alfred Albert ,  Cooper, James Neil ,  Mains, Robert Thane

    IPC: F23R3/28 ,  F23R3/34 ,  F23D11/36 ,  F02C7/22

    CPC classification number: F23R3/28 ,  F23D11/36 ,  F23D2900/00003 ,  F23R3/343

    Abstract: A gas turbine engine fuel injector conduit includes a single feed strip (62) having a single bonded together pair of lengthwise extending plates (76, 78). Each of the plates has a single row (80) of widthwise spaced apart and lengthwise extending parallel grooves (84). Opposing grooves (84) in each of the plates are aligned forming internal fuel flow passages (90) through the strip from an inlet end (66) to an outlet end (69). The feed strip (62) includes a substantially straight middle portion (64) between the inlet end (66) and the outlet end (69). In one alternative, the middle portion (64) has a radius of curvature (R) greater than a length (L) of the middle portion (64). The feed strip (62) has at least one acute bend (65) between the inlet end (66) and the middle portion (64) and a bend (68) between the outlet end (69) and the middle portion (64). The feed strip (62) has fuel inlet holes in the inlet end (66) connected to the internal fuel flow passages (90).

    Abstract translation: 燃气涡轮发动机燃料喷射器管道包括具有单个粘合在一起的一对纵向延伸板（76,78）的单个进给条（62）。 每个板具有宽度方向间隔且纵向延伸的平行凹槽（84）的单排（80）。 每个板中的相对的凹槽（84）对准，从入口端（66）到出口端（69）通过带形成内部燃料流动通道（90）。 进料条（62）包括在入口端（66）和出口端（69）之间的基本直的中间部分（64）。 在一个替代方案中，中间部分（64）的曲率半径（R）大于中间部分（64）的长度（L）。 进料条（62）在入口端（66）和中间部分（64）之间具有至少一个急弯部（65）和在出口端（69）和中间部分（64）之间的弯曲部分（68）。 进料条（62）在连接到内部燃料流动通道（90）的入口端（66）中具有燃料入口孔。

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