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    CERAMIC LINER FOR A TURBINE EXHAUST CASE
    1.
    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。

    TURBOFAN ENGINE BEARING AND GEARBOX ARRANGEMENT
    2.
    发明申请
    TURBOFAN ENGINE BEARING AND GEARBOX ARRANGEMENT 审中-公开
    涡轮发动机轴承和齿轮架布置

    公开(公告)号：WO2014197155A1

    公开(公告)日：2014-12-11

    申请号：PCT/US2014/036941

    申请日：2014-05-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SHERIDAN, William G. ,  SCHWARZ, Frederick M. ,  SUCIU, Gabriel L.

    IPC: F02C7/06 ,  F01D25/16 ,  F16C35/06

    CPC classification number: F02C3/107 ,  F01D25/162 ,  F02C3/06 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/52 ,  F05D2240/55 ,  F05D2240/60 ,  F05D2250/312 ,  F05D2260/40311 ,  F16C19/26 ,  F16C19/545 ,  F16C19/55 ,  F16C35/06 ,  F16C2360/23

    Abstract: A turbofan engine (20) comprises a fan (28). A fan drive gear system (60) is configured to drive the fan. A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. An intermediate spool comprises an intermediate pressure turbine (48), a compressor (42), and an intermediate spool shaft (54) coupling the intermediate pressure turbine to the intermediate spool compressor. A combustor (45) is between a core spool compressor (44) and a high pressure turbine (46). A first (160) main bearing engages a static support (164; 164') and a forward hub (236) of the intermediate spool. A second (162) main bearing engages the low shaft and the forward hub.

    Abstract translation: 涡扇发动机（20）包括风扇（28）。 风扇驱动齿轮系统（60）被配置为驱动风扇。 低阀芯包括将低压涡轮机联接到风扇驱动齿轮系统的低压涡轮机（50）和低轴（56）。 中间阀芯包括中间压力涡轮机（48），压缩机（42）和将中压涡轮机联接到中间阀芯压缩机的中间阀芯轴（54）。 燃烧器（45）位于核心卷轴压缩机（44）和高压涡轮机（46）之间。 第一（160）主轴承接合中间卷轴的静态支撑件（164; 164'）和前轮毂（236）。 第二（162）主轴承接合低轴和前轮毂。

    TWO SPOOL GAS GENERATOR TO CREATE FAMILY OF GAS TURBINE ENGINES
    5.
    发明申请
    TWO SPOOL GAS GENERATOR TO CREATE FAMILY OF GAS TURBINE ENGINES 审中-公开
    两台气体发生器创造气体涡轮发动机系列

    公开(公告)号：WO2014098962A1

    公开(公告)日：2014-06-26

    申请号：PCT/US2013/043039

    申请日：2013-05-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D.

    IPC: F02C6/00 ,  F02C6/02 ,  F02C9/00 ,  F02C7/00

    CPC classification number: F02C6/02 ,  F02C3/10 ,  F02C7/06 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/324 ,  F05D2220/326 ,  F05D2250/31 ,  F05D2260/4031

    Abstract: A method of configuring a plurality of gas turbine engines includes the steps of configuring each of the engines with respective ones of a plurality of propulsors. Each propulsor includes a propulsor turbine and one of a fan and a propeller. Each of the engines is configured with respective ones of a plurality of substantially mutually alike gas generators, with the respective propulsor turbine driven by products of combustion downstream of the gas generator.

    Abstract translation: 配置多个燃气涡轮发动机的方法包括以下步骤：用多个推进器中的相应的发动机配置每个发动机。 每个推进器包括推进涡轮机和风扇和螺旋桨之一。 每个发动机配置有多个基本上相互相似的气体发生器中的相应的发动机，相应的推进涡轮机由气体发生器下游的燃烧产物驱动。

    GAS TURBINE ENGINE WITH A LOW SPEED SPOOL DRIVEN PUMP ARRANGEMENT
    6.
    发明申请
    GAS TURBINE ENGINE WITH A LOW SPEED SPOOL DRIVEN PUMP ARRANGEMENT 审中-公开
    气体涡轮发动机与低速驱动泵配置

    公开(公告)号：WO2014088925A1

    公开(公告)日：2014-06-12

    申请号：PCT/US2013/072547

    申请日：2013-12-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  DYE, Christopher M.

    IPC: F02C7/236 ,  F02C7/36

    CPC classification number: F02C7/236 ,  F02C7/32

    Abstract: A gas turbine engine includes, among other things, a propulsion assembly situated to rotate about an engine central axis. Operation of the propulsion assembly requires a first amount of fluid during a first operating condition and a second, greater amount of the fluid during a second operating condition. A first pump is operatively associated with a low speed spool that rotates with a low pressure turbine. The first pump has a first fluid delivering capacity corresponding to at least the first amount. A second pump has a second fluid delivering capacity configured to correspond to at least a difference between the first amount and the second amount. The first pump provides the fluid for propulsion assembly during the first and second operating conditions and the second pump provides the fluid for propulsion assembly operation only during the second operating condition.

    Abstract translation: 燃气涡轮发动机尤其包括位于围绕发动机中心轴线旋转的推进组件。 推进组件的操作在第一操作条件期间需要第一量的流体，并且在第二操作条件期间需要第二较大量的流体。 第一泵与低速涡轮机一起旋转的低速滑阀可操作地连接。 第一泵具有对应于至少第一量的第一流体输送能力。 第二泵具有被配置为对应于第一量和第二量之间的至少差异的第二流体输送能力。 第一泵在第一和第二操作条件期间提供用于推进组件的流体，并且第二泵仅在第二操作条件期间提供用于推进组装操作的流体。

    GAS TURBINE ENGINE BUFFER COOLING SYSTEM
    9.
    发明申请
    GAS TURBINE ENGINE BUFFER COOLING SYSTEM 审中-公开
    气体涡轮发动机缓冲器冷却系统

    公开(公告)号：WO2013130246A1

    公开(公告)日：2013-09-06

    申请号：PCT/US2013/025507

    申请日：2013-02-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  ALVANOS, Ioannis

    IPC: F01D9/02 ,  F01D25/12 ,  F02C7/12

    CPC classification number: F02C7/185 ,  F01D5/081 ,  F01D25/125 ,  F02C6/08 ,  F02C7/06 ,  F05D2220/32 ,  F05D2260/232

    Abstract: A gas turbine engine includes a heat exchanger, a bearing compartment, and a nozzle assembly in fluid communication with the bearing compartment. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The bearing compartment is in fluid communication with the heat exchanger. A first passageway communicates the conditioned airflow from the heat exchanger to the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment to the nozzle assembly.

    Abstract translation: 燃气涡轮发动机包括热交换器，轴承室和与轴承室流体连通的喷嘴组件。 热交换器与放气气流交换热量以提供调节气流。 轴承室与热交换器流体连通。 第一通道将经调节的气流从热交换器传递到轴承室。 第二通道将经调节的气流从轴承室传送到喷嘴组件。

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