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    DE-COUPLE GEARED TURBO-FAN ENGINE AND AIRCRAFT
    3.
    发明申请
    DE-COUPLE GEARED TURBO-FAN ENGINE AND AIRCRAFT 审中-公开
    DE-COUPLE齿轮涡轮发动机和飞机

    公开(公告)号：US20140252161A1

    公开(公告)日：2014-09-11

    申请号：US14188989

    申请日：2014-02-25

    申请人： United Technologies Corporation

    发明人： Robert L. Gukeisen

    IPC分类号： B64D27/14 ,  F02C7/36 ,  B64D27/12

    CPC分类号： B64D27/14 ,  B64D35/02 ,  F02C3/10 ,  F02C3/107 ,  F02C7/36 ,  F02K1/52 ,  F02K1/60 ,  F02K1/70 ,  F02K1/78 ,  F02K3/068 ,  Y02T50/671

    摘要： A turbofan engine includes a core engine section including a compressor section feeding air to a combustor to generate high speed exhaust gases that drive a turbine section all disposed about an engine axis, a geartrain driven by the core engine section, a fan section driven by the geartrain about a fan axis spaced apart from the engine axis, and an accessory gearbox driven by the geartrain and mounted apart from the core engine section and the fan section.

    摘要翻译： 涡轮风扇发动机包括：核心发动机部分，其包括压缩机部分，其将空气供给到燃烧器，以产生驱动涡轮部分全部设置在发动机轴线周围的高速废气;由所述核心发动机部分驱动的齿轮组; 围绕与发动机轴线间隔开的风扇轴的齿轮箱，以及由齿条驱动并与核心发动机部分和风扇部分分开安装的附件齿轮箱。

    Turbomachine thrust reverser
    6.
    发明授权
    Turbomachine thrust reverser 有权

    公开(公告)号：US10145335B2

    公开(公告)日：2018-12-04

    申请号：US13712240

    申请日：2012-12-12

    申请人： United Technologies Corporation

    发明人： Robert L. Gukeisen ,  Claude Mercier ,  Robert E. Malecki

    IPC分类号： F02K1/72 ,  F02K1/58 ,  F02K1/64 ,  F02C7/20 ,  B64D29/06

    摘要： An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position.

    TURBOMACHINE THRUST REVERSER
    8.
    发明申请
    TURBOMACHINE THRUST REVERSER 审中-公开

    公开(公告)号：US20140246514A1

    公开(公告)日：2014-09-04

    申请号：US13712240

    申请日：2012-12-12

    申请人： United Technologies Corporation

    发明人： Robert L. Gukeisen ,  Claude Mercier ,  Robert E. Malecki

    IPC分类号： F02K1/58

    CPC分类号： F02K1/58 ,  B64D29/06 ,  F02C7/20 ,  F02K1/64 ,  F02K1/72 ,  F05D2250/34

    摘要： An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position.

    摘要翻译： 燃气涡轮发动机的示例推力反向器被构造成根据本公开的示例性方面经由经由一个或多个相对于发动机的顶部圆周顶点定位的一个或多个推力反向器安装座经由塔架连接到飞机机翼， 事物，第一整流罩可相对于第二整流罩在收起位置和展开位置之间移动。 在展开位置的第一个整流罩配置成允许从发动机重新引导推力以减慢发动机。 第一整流罩形成发动机的大致环形的壳体的一部分。 当第一整流罩处于收起位置时，第一整流罩直接与外壳的第二整流罩接合在整流罩接口位置，该顶盖接口位置与顶部圆周顶点周向偏移大于18度。