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    INTER-MODULE FLOW DISCOURAGER
    11.
    发明申请
    INTER-MODULE FLOW DISCOURAGER 审中-公开

    公开(公告)号：WO2014105524A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/075750

    申请日：2013-12-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CHUONG, Conway ,  BUDNICK, Matthew

    IPC: F01D11/02 ,  F01D5/20

    CPC classification number: F02C7/28 ,  F01D11/005 ,  F01D25/28 ,  F01D25/30

    Abstract: An assembly for a gas turbine engine includes a first module, a second module, and a flow discourager. The second module is connected to the first module along a joint. The flow discourager is connected to the first module and extends to be received in a notch in the second module. The flow discourager acts to direct an ingestion gas flow away from the joint between the first module and the second module.

    Abstract translation: 一种用于燃气涡轮发动机的组件，包括第一模块，第二模块和流动盘。 第二模块沿着接头连接到第一模块。 流动障碍物连接到第一模块并延伸以被接收在第二模块中的凹口中。 流动障碍物用于引导摄取气体流离开第一模块和第二模块之间的关节。

    FINGER SEAL
    12.
    发明申请
    FINGER SEAL 审中-公开
    手指密封

    公开(公告)号：WO2014105482A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/075406

    申请日：2013-12-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CHUONG, Conway ,  BUDNICK, Matthew

    IPC: F01D11/02 ,  F02C7/28

    CPC classification number: F01D11/003 ,  F01D11/005 ,  F05D2240/59 ,  F05D2250/293 ,  F05D2300/5024 ,  F16J15/0887

    Abstract: An assembly for a gas turbine engine includes a component and a finger seal. The component has a first surface and a second surface. The first surface has an elevation that differs from an elevation of the second surface. The finger seal is connected to the first surface and extends above the second surface. The disposition of the second surface relative to the finger seal creates a cavity below a curved portion of the finger seal.

    Abstract translation: 用于燃气涡轮发动机的组件包括部件和手指密封件。 该部件具有第一表面和第二表面。 第一表面具有不同于第二表面的高度的高度。 手指密封件连接到第一表面并在第二表面上方延伸。 相对于手指密封件的第二表面的设置在手指密封件的弯曲部分下方形成空腔。

    REDUCED MISALIGNMENT GEAR SYSTEM
    13.
    发明申请
    REDUCED MISALIGNMENT GEAR SYSTEM 审中-公开
    减少失调齿轮系统

    公开(公告)号：WO2015026600A1

    公开(公告)日：2015-02-26

    申请号：PCT/US2014/050873

    申请日：2014-08-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： BUDNICK, Matthew ,  CHUONG, Conway

    IPC: F01D25/18

    CPC classification number: F01D25/18 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F05D2260/40311 ,  F16H1/28 ,  F16H57/043 ,  F16H57/0471 ,  F16H57/0479 ,  F16H57/0486 ,  Y02T50/671

    Abstract: A lubrication system for a fan drive planetary gear system according to an exemplary aspect of the present disclosure includes, among other things, a stationary first bearing configured to receive a lubricant from a lubricant input, the stationary first bearing is located adjacent a fan drive shaft. A second bearing is configured to rotate with the fan drive shaft, the first bearing engages the second bearing and is configured to transfer the lubricant from the first bearing to the second bearing and into at least one fluid passage in the fan drive shaft. A conduit fluidly connects the at least one passage in the fan drive shaft with at least one component on the fan drive gear system.

    Abstract translation: 根据本公开的示例性方面的用于风扇驱动器行星齿轮系统的润滑系统包括构造成从润滑剂输入端接收润滑剂的固定第一轴承，固定第一轴承位于风扇驱动轴 。 第二轴承被构造成与风扇驱动轴一起旋转，第一轴承接合第二轴承并且构造成将润滑剂从第一轴承传递到第二轴承并进入风扇驱动轴中的至少一个流体通道。 导管将风扇驱动轴中的至少一个通道与风扇驱动齿轮系统上的至少一个部件流体连接。

    STATOR VANE ARRANGEMENT FOR A TURBINE ENGINE
    14.
    发明申请
    STATOR VANE ARRANGEMENT FOR A TURBINE ENGINE 审中-公开
    用于涡轮发动机的定子叶片装置

    公开(公告)号：WO2014165518A1

    公开(公告)日：2014-10-09

    申请号：PCT/US2014/032533

    申请日：2014-04-01

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： FARAH, Jorge I. ,  CHUONG, Conway ,  STEWART, Dana P.

    IPC: F01D9/00 ,  F01D9/02

    CPC classification number: F01D9/042 ,  F01D25/005 ,  F01D25/162 ,  F05D2240/12

    Abstract: A stator vane arrangement for a turbine engine includes a first vane platform, a second vane platform and a plurality of stator vanes extending radially between the first and the second vane platforms. The first and the second vane platforms extend circumferentially around an axis, and the first vane platform includes an aperture. The stator vanes are arranged circumferentially around the axis, and include a first stator vane that extends radially into the aperture and is fastened to the first vane platform.

    Abstract translation: 用于涡轮发动机的定子叶片装置包括第一叶片平台，第二叶片平台和在第一和第二叶片平台之间径向延伸的多个定子叶片。 第一和第二叶片平台围绕轴线周向延伸，并且第一叶片平台包括孔。 定子叶片围绕轴线周向地布置，并且包括第一定子叶片，该第一定子叶片径向延伸到孔中并且紧固到第一叶片平台。

    GAS TURBINE SEAL ASSEMBLY AND SEAL SUPPORT
    16.
    发明申请
    GAS TURBINE SEAL ASSEMBLY AND SEAL SUPPORT 审中-公开
    气体涡轮密封组件和密封支撑

    公开(公告)号：WO2014105803A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/077442

    申请日：2013-12-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CHUONG, Conway ,  BUDNICK, Matthew

    IPC: F01D11/02 ,  F01D25/24 ,  F02C7/28

    CPC classification number: F01D11/001 ,  F01D11/003 ,  F01D11/005 ,  F01D25/162 ,  F01D25/24 ,  F01D25/246 ,  F02C7/28 ,  F05D2240/55

    Abstract: A gas turbine engine assembly includes a second module connected axially to a first module along a joint, and an annular cavity defined between the first module and the second module. The seal assembly is disposed proximate the cavity, and includes a seal support ring, a first finger seal, and a second finger seal. The support ring has a backing portion secured to a radial wall of to the first module, and a first seal land extending axially into the cavity away from the first module. The first finger seal has a free end adapted to contact an inner side of the first seal land. The second finger seal is adapted to seal a radially outer portion of the annular cavity

    Abstract translation: 燃气涡轮发动机组件包括沿着接头轴向连接到第一模块的第二模块和限定在第一模块和第二模块之间的环形空腔。 密封组件设置在空腔附近，并且包括密封支撑环，第一指状密封件和第二手指密封件。 所述支撑环具有固定到所述第一模块的径向壁的背衬部分和从所述第一模块轴向延伸到所述腔体中的第一密封区域。 第一指状密封件具有适于接触第一密封区域的内侧的自由端。 第二指状密封件适于密封环形空腔的径向外部部分

    MULTI-PURPOSE GAS TURBINE SEAL SUPPORT AND ASSEMBLY
    17.
    发明申请
    MULTI-PURPOSE GAS TURBINE SEAL SUPPORT AND ASSEMBLY 审中-公开
    多用途气体涡轮机密封支撑和组件

    公开(公告)号：WO2014105780A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/077397

    申请日：2013-12-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： VO, Tuan, David ,  CHUONG, Conway ,  BUDNICK, Matthew ,  SCOTT, Jonathan, Ariel

    IPC: F01D11/02 ,  F01D25/24 ,  F02C7/28

    CPC classification number: F01D11/02 ,  F01D9/065 ,  F01D11/001 ,  F01D11/122 ,  F01D25/162 ,  F01D25/28 ,  F02C7/28

    Abstract: A gas turbine engine assembly includes a first module, a second module rotatable about a center line of the gas turbine engine and fluidly coupled with the first module, and a multi-purpose seal support. The multi-purpose seal support includes an aft end secured to the first module, and a forward end disposed proximate the second module. The forward end has a discourager portion, a seal portion, and a meshing portion.

    Abstract translation: 燃气涡轮发动机组件包括第一模块，可围绕燃气涡轮发动机的中心线旋转并与第一模块流体连接的第二模块，以及多用途密封支撑件。 多用途密封件支撑件包括固定到第一模块的后端和靠近第二模块设置的前端。 前端具有罢工部分，密封部分和啮合部分。

    GAS TURBINE ENGINE AFT SEAL PLATE GEOMETRY
    19.
    发明申请
    GAS TURBINE ENGINE AFT SEAL PLATE GEOMETRY 审中-公开
    气体涡轮发动机AFT密封板几何

    公开(公告)号：WO2015020775A1

    公开(公告)日：2015-02-12

    申请号：PCT/US2014/047144

    申请日：2014-07-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： BUDNICK, Matthew ,  CHUONG, Conway

    IPC: F01D11/00 ,  F02C7/28

    CPC classification number: F01D11/005 ,  F01D11/001 ,  F01D15/10 ,  F01D25/24 ,  F02C7/28 ,  F05D2220/30 ,  F05D2220/76 ,  F05D2240/55

    Abstract: A gas turbine engine includes an engine static structure. A fairing is supported relative to the engine static structure and configured to provide a flow path surface of a flow path extending in an axial direction. A seal plate has first and second ends radially spaced from one another with respect to the axial direction. The first end is operatively secured to the engine static structure. The second end is configured to seal relative to the fairing. The seal plate includes a portion between the first and second ends that extends substantially in the axial direction and configured to permit the second end to move away from the fairing in the axial direction relative to the first end in response to thermal growth.

    Abstract translation: 燃气涡轮发动机包括发动机静止结构。 整流罩相对于发动机静态结构被支撑并且构造成提供沿轴向延伸的流动路径的流路表面。 密封板具有相对于轴向方向彼此径向间隔开的第一和第二端。 第一端可操作地固定到发动机静态结构。 第二端被配置为相对于整流罩密封。 密封板包括在第一和第二端之间的基本上在轴向方向上延伸的部分，并且构造成允许第二端响应于热增长而相对于第一端沿轴向方向远离整流罩移动。

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