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    TWIN TIP TURBINE PROPULSORS POWERED BY A SINGLE GAS TURBINE GENERATOR
    1.
    发明申请
    TWIN TIP TURBINE PROPULSORS POWERED BY A SINGLE GAS TURBINE GENERATOR 审中-公开
    单燃气轮机发电机供电的双头涡轮推进器

    公开(公告)号：WO2014109811A2

    公开(公告)日：2014-07-17

    申请号：PCT/US2013066531

    申请日：2013-10-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M ,  STAUBACH JOSEPH B ,  SUYDAM ADAM JOSEPH

    CPC classification number: B64D27/14 ,  F02C7/36 ,  F02K3/06

    Abstract: A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles, with each of the nacelles receiving a fan rotor. The fan rotor is fixed to rotate with a tip turbine mounted at a radially outer location of the fan rotor, with the tip turbine being in the path of gases from the manifold. An aircraft is also disclosed.

    Abstract translation: 燃气涡轮发动机具有并入涡轮的核心发动机和位于涡轮下游的歧管。 歧管将涡轮下游的气体输送到至少两个机舱中，每个机舱接收风扇转子。 风扇转子被固定以随着安装在风扇转子的径向外部位置处的尖端涡轮机旋转，其中尖端涡轮机处于来自歧管的气体的路径中。 还披露了一架飞机。

    CERAMIC LINER FOR A TURBINE EXHAUST CASE
    3.
    发明申请
    CERAMIC LINER FOR A TURBINE EXHAUST CASE 审中-公开
    陶瓷内胆用于涡轮机排气

    公开(公告)号：WO2015069358A3

    公开(公告)日：2015-07-16

    申请号：PCT/US2014051600

    申请日：2014-08-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M

    IPC: F02C7/20 ,  F01D9/04 ,  F01D25/24 ,  F02C7/24 ,  F02K1/04

    CPC classification number: F02C7/20 ,  F01D25/26 ,  F01D25/28 ,  F02C3/04 ,  F02C7/24 ,  F02K1/822 ,  F05D2220/32 ,  F05D2300/20 ,  F05D2300/6033 ,  F23R3/007 ,  Y02T50/672 ,  Y02T50/675

    Abstract: A gas turbine engine includes a core engine including a central engine axis and a nacelle surrounding the core engine. At least a portion of the nacelle is axially movable relative to the core engine between open and fully closed positions. A ceramic-based liner is located at an aft portion of the core engine. The ceramic-based component mechanically interfaces with the movable portion of the nacelle when the nacelle is in the fully closed position. A turbine section and a method of accommodating thermally-induced dimensional change of engine components are also disclosed.

    Abstract translation: 燃气涡轮发动机包括具有中心发动机轴线和围绕核心发动机的机舱的核心发动机。 机舱的至少一部分在开放位置和完全关闭位置之间相对于核心发动机可轴向移动。 陶瓷基衬套位于核心发动机的后部。 当机舱处于完全关闭位置时，陶瓷基部件与机舱的可移动部分机械地接合。 还公开了涡轮部分和容纳发动机部件的热致尺寸变化的方法。

    TWIN TARGET THRUST REVERSER MODULE
    4.
    发明申请
    TWIN TARGET THRUST REVERSER MODULE 审中-公开
    双目标扭转模块

    公开(公告)号：WO2014197056A3

    公开(公告)日：2015-03-05

    申请号：PCT/US2014025163

    申请日：2014-03-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M

    IPC: F02K1/60 ,  F02K1/11

    CPC classification number: F02K1/70 ,  F02K1/06 ,  F02K1/52 ,  F02K1/60 ,  F02K1/62 ,  F05D2220/323 ,  F05D2240/40

    Abstract: A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines.

    Abstract translation: 一种用于双燃气涡轮发动机推进系统的喷嘴组件，包括靠近第一燃气涡轮发动机的第一旁通通道安装的壳体和第二燃气涡轮发动机的第二旁通通道，第一和第二上部门，以及第一和第二下部 门。 第一和第二上部门以及第一和第二下部门中的每一个都枢转地安装到壳体上，以在收起位置和展开位置之间移动，在该位置中，穿过第一和第二旁路通道的气流相对于相应的中心线 第一和第二燃气涡轮发动机。

    GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR AND THERMAL MANAGEMENT
    5.
    发明申请
    GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR AND THERMAL MANAGEMENT 审中-公开
    燃气轮机与入口颗粒分离器和热管理

    公开(公告)号：WO2014078003A3

    公开(公告)日：2014-08-07

    申请号：PCT/US2013065337

    申请日：2013-10-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  EPSTEIN ALAN H ,  LORD WESLEY K ,  CHANDLER JESSE M

    IPC: F02C7/052 ,  F02C7/12

    CPC classification number: F01D25/08 ,  F02C7/052 ,  Y02T50/675

    Abstract: A gas turbine engine includes a nose cone at an inlet end, and spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. Air delivered by the inlet particle separator passes over a heat exchanger before passing to an outlet.

    Abstract translation: 燃气涡轮发动机在入口端处包括鼻锥，并且在机舱的径向内侧间隔开。 压缩机位于机头锥体的下游。 一个核心入口将空气锥形下游的空气输送到压缩机中。 入口颗粒分离器包括用于向核心入口径向向外输送空气的歧管。 由入口颗粒分离器输送的空气在通过出口之前通过热交换器。

    NACELLE VENTILATION MANIFOLD
    6.
    发明公开
    NACELLE VENTILATION MANIFOLD 审中-公开
    LÜFTUNGSVERTEILERFÜRTRIEBWERKSGONDEL

    公开(公告)号：EP3105438A4

    公开(公告)日：2017-10-04

    申请号：EP15749596

    申请日：2015-01-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M ,  PAPA FEDERICO

    IPC: F02C7/18

    CPC classification number: F01D17/145 ,  F01D25/26 ,  F02C3/04 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/608 ,  Y02T50/675

    Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

    Abstract translation: 燃气涡轮发动机包括核心发动机壳体。 发动机舱定位在核心发动机壳体的径向外侧。 外部旁路壳体定位在机舱的外部。 至少有一个待冷却的附件径向位于核心发动机壳体与机舱之间的腔室中。 歧管将冷却空气输送到腔室中，并围绕核心发动机的中心轴线周向延伸。 发动机舱在圆周范围内具有不对称的流动横截面。

    CERAMIC LINER FOR A TURBINE EXHAUST CASE
    7.
    发明公开
    CERAMIC LINER FOR A TURBINE EXHAUST CASE 审中-公开
    KERAMISCHE AUSKLEIDUNGFÜREINETURBINENABGASGEHÄUSE

    公开(公告)号：EP3044442A4

    公开(公告)日：2017-05-10

    申请号：EP14860946

    申请日：2014-08-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M

    IPC: F02C7/20 ,  F01D9/04 ,  F01D25/24 ,  F01D25/28 ,  F02K1/82

    CPC classification number: F02C7/20 ,  F01D25/26 ,  F01D25/28 ,  F02C3/04 ,  F02C7/24 ,  F02K1/822 ,  F05D2220/32 ,  F05D2300/20 ,  F05D2300/6033 ,  F23R3/007 ,  Y02T50/672 ,  Y02T50/675

    Abstract: A gas turbine engine includes a core engine including a central engine axis and a nacelle surrounding the core engine. At least a portion of the nacelle is axially movable relative to the core engine between open and fully closed positions. A ceramic-based liner is located at an aft portion of the core engine. The ceramic-based component mechanically interfaces with the movable portion of the nacelle when the nacelle is in the fully closed position. A turbine section and a method of accommodating thermally-induced dimensional change of engine components are also disclosed.

    Abstract translation: 燃气涡轮发动机包括具有中心发动机轴线和围绕核心发动机的机舱的核心发动机。 机舱的至少一部分相对于核心发动机在打开和完全关闭位置之间可轴向移动。 陶瓷基衬里位于核心发动机的后部。 当机舱处于完全关闭位置时，陶瓷基部件与机舱的可移动部分机械地连接。 还公开了一种适应发动机部件的热致尺寸变化的涡轮部分和方法。

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