知搜-全球专利检索

  1. Login
  2. Sign Up

Search Results

119 records (took 0.037 seconds)

    INTEGRATED THRUST REVERSER ACTUATION SYSTEM
    5.
    发明申请
    INTEGRATED THRUST REVERSER ACTUATION SYSTEM 审中-公开
    集成式逆变器启动系统

    公开(公告)号：US20160186688A1

    公开(公告)日：2016-06-30

    申请号：US14293605

    申请日：2014-06-02

    Applicant: GE Aviation Systems LLC

    Inventor： John S. Mears ,  George Stephen Billisits ,  Chad Russell Wentling

    IPC: F02K1/56 ,  F02C7/20

    CPC classification number: F02K1/56 ,  F02C7/20 ,  F02K1/09 ,  F02K1/15 ,  F02K1/72 ,  F02K1/763 ,  F05D2250/34 ,  F05D2260/57 ,  F05D2270/60 ,  F05D2270/62 ,  F05D2270/64 ,  F05D2270/66

    Abstract: A turbofan engine having a turbine engine, a nacelle surrounding a portion of the turbine engine, and a thrust reverser. The thrust reverser comprises a movable control surface movable to and from a reversing position and a thrust reverser actuation system having at least one actuator operably coupled to the movable control surface to move the movable control surface into and out of the reversing position. A guide comprising a rail and a bogie having at least one rotatable bearing surface coupled to the rail for relative translational movement between the rail and bogie connects the turbine engine to the movable control surface such that operation of the at least one actuator moves the movable control surface by translation movement between the rail and the bogie.

    Abstract translation: 具有涡轮发动机，围绕涡轮发动机的一部分的机舱和推力反向器的涡轮风扇发动机。 推力反向器包括可移动到可逆位置的可移动控制表面和推力反向器致动系统，其具有可操作地联接到可移动控制表面的至少一个致动器，以将可移动控制表面移入和移出反转位置。 包括轨道和转向架的引导件具有联接到轨道的至少一个可旋转支承表面，用于在轨道和转向架之间的相对平移运动将涡轮发动机连接到可移动控制表面，使得至少一个致动器的操作使可移动控制器 轨道与转向架之间的平移运动。

    AXIAL COMPRESSOR
    7.
    发明申请
    AXIAL COMPRESSOR 有权
    轴压缩机

    公开(公告)号：US20130280053A1

    公开(公告)日：2013-10-24

    申请号：US13917933

    申请日：2013-06-14

    Applicant: ALSTOM Technology Ltd

    Inventor： Marco MICHELI ,  Wolfgang KAPPIS ,  Luis Federico PUERTA

    IPC: F04D19/00

    CPC classification number: F04D19/00 ,  F01D5/142 ,  F01D5/146 ,  F04D29/544 ,  F05D2250/34 ,  F05D2250/38

    Abstract: The axial compressor has a two-stage guide vane cascade at the discharge-side end of the rotor. The guide vanes of the second stage of the cascade are staggered in the circumferential direction in relation to the guide vanes of the first stage in such a way that vortex streamers created by the guide vanes of the first stage cannot impinge upon the guide vanes of the second stage.

    Abstract translation: 轴向压缩机在转子的排出侧端部具有两级导叶叶栅级联。 级联的第二级的引导叶片相对于第一级的引导叶片在圆周方向上交错，使得由第一级的导向叶片产生的涡旋飘带不会撞击到第一级的导向叶片 第二阶段

    Translating variable area fan nozzle providing an upstream bypass flow exit
    9.
    发明授权
    Translating variable area fan nozzle providing an upstream bypass flow exit 有权
    翻译可变区域风扇喷嘴，提供上游旁路流出口

    公开(公告)号：US08402765B2

    公开(公告)日：2013-03-26

    申请号：US12485551

    申请日：2009-06-16

    Applicant: Daniel M. Amkraut ,  Michael John Layland ,  Norman John James

    Inventor： Daniel M. Amkraut ,  Michael John Layland ,  Norman John James

    IPC: F02K1/09 ,  F02K3/075 ,  F02K1/70

    CPC classification number: F02K1/763 ,  F02K1/09 ,  F02K1/30 ,  F02K1/70 ,  F02K1/72 ,  F02K3/06 ,  F05D2250/34 ,  Y10T74/18576 ,  Y10T74/18648

    Abstract: A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.

    Abstract translation: 用于涡轮风扇发动机的可变区域风扇喷嘴组件包括具有后边缘的机舱和具有前边缘和第一端的平移喷嘴段。 喷嘴段可移动地设置在后边缘之后，使得当喷嘴段处于展开位置时，在后边缘和前边缘之间限定上游旁路流出口。 偏转器设置在靠近第一端的后边缘和前边缘之间。 偏转器基本上防止在接近第一端的区域中旁路流离开上游旁路流出口。

    THRUST INVERTER
    10.
    发明申请
    THRUST INVERTER 有权
    逆变器

    公开(公告)号：US20120217320A1

    公开(公告)日：2012-08-30

    申请号：US13510352

    申请日：2010-10-26

    Applicant: Guy Bernard Vauchel ,  Pierre Caruel ,  Andre Baillard ,  Peter Segat

    Inventor： Guy Bernard Vauchel ,  Pierre Caruel ,  Andre Baillard ,  Peter Segat

    IPC: B63H11/10

    CPC classification number: F02K1/72 ,  B64D29/06 ,  B64D29/08 ,  F01D25/24 ,  F01D25/243 ,  F01D25/28 ,  F02C7/20 ,  F02K1/54 ,  F02K1/64 ,  F02K1/68 ,  F05D2250/34

    Abstract: The present invention relates to a thrust inverter for a turbojet engine nacelle (1) including at least one outer cowl (11) that is movable between a closed position and a thrust inversion position, said movable cowl also being able to be opened into a supporting position towards which said movable cowl is hinged and guided through the use of a guiding means that is suitable to said movable cowl and located substantially on a pylon, to which the nacelle is intended to be attached and at least one front frame (15) capable of being mounted downstream from an air blower housing for said turbojet engine and directly or indirectly holds at least one flow diversion means (12). Said thrust inverter is characterized in that the front frame is detachably connected to the housing in a translatable manner along at least one related guiding member (17) once said front frame is detached from the housing.

    Abstract translation: 本发明涉及一种用于涡轮喷气发动机机舱（1）的推力逆变器，其包括至少一个能够在关闭位置和推力倒置位置之间移动的外罩（11），所述可动罩也能够被打开成支撑 所述可移动整流罩铰接并引导通过使用适于所述可移动整流罩并且基本上位于所述机舱旨在附接的塔架上的导向装置的位置，以及至少一个前框架（15）能够 被安装在用于所述涡轮喷气发动机的鼓风机壳体的下游，并且直接或间接保持至少一个分流装置（12）。 所述推力逆变器的特征在于，一旦所述前框架与壳体分离，前框架可沿着至少一个相关的引导构件（17）以可平移的方式可拆卸地连接到壳体。

Patent Agency Ranking