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    CERAMIC LINER FOR A TURBINE EXHAUST CASE
    2.
    发明申请
    CERAMIC LINER FOR A TURBINE EXHAUST CASE 审中-公开
    汽轮机排气装置用陶瓷衬里

    公开(公告)号：WO2015069358A2

    公开(公告)日：2015-05-14

    申请号：PCT/US2014/051600

    申请日：2014-08-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

    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核心发动机，该核心发动机包括中心发动机轴线和围绕核心发动机的机舱。 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。 还公开了一种涡轮部分和适应发动机部件的热致尺寸变化的方法。

    TWIN TIP TURBINE PROPULSORS POWERED BY A SINGLE GAS TURBINE GENERATOR
    4.
    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：WO2014109811A3

    公开(公告)日：2014-07-17

    申请号：PCT/US2013/066531

    申请日：2013-10-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  STAUBACH, Joseph B. ,  SUYDAM, Adam Joseph

    IPC: F02K3/062 ,  F02C7/36 ,  F02C7/32 ,  B64D27/14 ,  B64D29/04 ,  B64D33/04

    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包含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。

    TWO SPOOL GAS GENERATOR WITH MOUNT RING
    5.
    发明申请
    TWO SPOOL GAS GENERATOR WITH MOUNT RING 审中-公开
    两个SPOOL气体发生器与安装环

    公开(公告)号：WO2014109787A1

    公开(公告)日：2014-07-17

    申请号：PCT/US2013/044022

    申请日：2013-06-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

    IPC: F02C7/36 ,  F02C7/32

    CPC classification number: F02C7/36 ,  B64D27/10 ,  B64D2027/005 ,  F02C7/06 ,  F02C7/20 ,  F02C7/32 ,  F02K3/072 ,  F05D2240/90 ,  Y02T50/66

    Abstract: A gas turbine engine has a first shaft including a first turbine rotor, and a second shaft including a second turbine rotor disposed downstream of the first turbine rotor. A third shaft includes a propulsor turbine positioned downstream of the second turbine rotor for driving a propeller. A mount ring is secured between the second turbine rotor and the propeller.

    Abstract translation: 燃气涡轮发动机具有包括第一涡轮转子的第一轴和包括设置在第一涡轮转子下游的第二涡轮转子的第二轴。 第三轴包括位于第二涡轮转子下游的推进涡轮机，用于驱动螺旋桨。 安装环固定在第二涡轮转子和螺旋桨之间。

    GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR AND THERMAL MANAGEMENT
    7.
    发明申请
    GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR AND THERMAL MANAGEMENT 审中-公开
    具有入口颗粒分离器和热管理的气体涡轮发动机

    公开(公告)号：WO2014078003A2

    公开(公告)日：2014-05-22

    申请号：PCT/US2013/065337

    申请日：2013-10-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    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: 燃气涡轮发动机包括在入口端处的鼻锥体，并且在机舱的径向内侧间隔开。 压缩机在鼻锥的下游。 核心入口将鼻锥下游的空气输送到压缩机中。 入口颗粒分离器包括用于沿芯入口径向向外输送空气的歧管。 通过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
    8.
    发明申请
    NACELLE VENTILATION MANIFOLD 审中-公开
    通风通风口

    公开(公告)号：WO2015122992A1

    公开(公告)日：2015-08-20

    申请号：PCT/US2015/011944

    申请日：2015-01-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  PAPA, Federico

    IPC: F02C7/18 ,  F02C7/32

    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。 机舱位于核心发动机壳体的径向外侧。 外部旁路外壳位于机舱的外侧。 至少有一个待冷却的附件定位在径向位于核心发动机壳体和机舱之间的腔室中。 歧管将冷却空气提供到腔室中，并且围绕核心发动机的中心轴线周向延伸。 机舱在圆周范围内具有不对称的流动横截面。

    BELOW WING REVERSE CORE GAS TURBINE ENGINE WITH THRUST REVERSER
    9.
    发明申请
    BELOW WING REVERSE CORE GAS TURBINE ENGINE WITH THRUST REVERSER 审中-公开
    下面的逆向核心燃气涡轮发动机与扭矩反转器

    公开(公告)号：WO2014109785A1

    公开(公告)日：2014-07-17

    申请号：PCT/US2013/040487

    申请日：2013-05-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

    IPC: F02K1/56 ,  F02K1/54 ,  F02K3/02

    CPC classification number: F02C3/107 ,  F02K1/60 ,  F02K1/70 ,  F02K3/00

    Abstract: A core engine includes a compressor section, a combustor and a turbine section, with the turbine section being closest to a fan, the combustor section and then the compressor section being positioned further away from the fan relative to the turbine section. A downstream end of a nozzle has at least one pivoting shell and an actuator pivots the shell between a stowed position and a deployed position. A mount bracket is mounted at one circumferential location of the engine. The shell moves in a direction having at least a component perpendicular to a vertical direction defined perpendicular to a top surface of the mount bracket.

    Abstract translation: 核心发动机包括压缩机部分，燃烧器和涡轮机部分，其中涡轮部分最靠近风扇，燃烧器部分然后压缩机部分相对于涡轮部分定位成更远离风扇。 喷嘴的下游端具有至少一个枢转壳体，并且致动器在收起位置和展开位置之间枢转壳体。 安装支架安装在发动机的一个圆周位置。 壳体沿着至少垂直于垂直于安装支架的顶表面限定的垂直方向的分量的方向移动。

    ASYMMETRIC THRUST REVERSERS
    10.
    发明申请
    ASYMMETRIC THRUST REVERSERS 审中-公开
    不对称扭矩反转器

    公开(公告)号：WO2014092757A1

    公开(公告)日：2014-06-19

    申请号：PCT/US2013/031844

    申请日：2013-03-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CHANDLER, Jesse M. ,  SUCIU, Gabriel L.

    IPC: B24C5/02 ,  B64D33/04

    CPC classification number: B64D33/04 ,  B64C5/02 ,  B64D27/14 ,  B64D27/20 ,  F02K1/60

    Abstract: An aircraft includes a propulsion supported within an aft portion of a fuselage A thrust reverser is mounted in the aft portion of the fuselage proximate the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser includes an upper blocker door movable about a first pivot axis to a deployed position and a lower blocker door movable about a second pivot axis not parallel to the first pivot axis.

    Abstract translation: 飞行器包括支撑在机身的后部的推进器。推力反向器安装在靠近推进系统的机身的后部，用于引导推进以减缓飞行器的方向。 推力反向器包括可围绕第一枢转轴线移动到展开位置的上部阻挡门，以及可围绕不平行于第一枢转轴线的第二枢转轴线移动的下部阻挡门。

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