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    GAS TURBINE ENGINE ATTACHMENT STRUCTURE AND METHOD THEREFOR
    2.
    发明申请
    GAS TURBINE ENGINE ATTACHMENT STRUCTURE AND METHOD THEREFOR 审中-公开
    燃气涡轮发动机附件结构及其方法

    公开(公告)号：WO2014130217A1

    公开(公告)日：2014-08-28

    申请号：PCT/US2014/013300

    申请日：2014-01-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SANDER, David J. ,  DUELM, Shelton O.

    IPC: F01D25/24 ,  F02C7/20

    CPC classification number: F01D25/26 ,  F01D9/041 ,  F01D25/162 ,  F02C7/20 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/14 ,  Y02T50/672 ,  Y02T50/673

    Abstract: An attachment structure for a gas turbine engine includes a frame that has a first annular case. A second annular case extends around the frame. The first annular case and the second annular case include a plurality of interlocks. Each of the interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second case. The first member is received in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.

    Abstract translation: 用于燃气涡轮发动机的附接结构包括具有第一环形壳体的框架。 第二环形壳体围绕框架延伸。 第一环形壳体和第二环形壳体包括多个互锁。 每个互锁件包括安装在第一环形壳体或第二环形壳体中的一个上的第一构件和安装在第一环形壳体或第二壳体中的另一个上的对应的第二构件。 第一构件被容纳在第二构件中，使得多个互锁件限制第一环形壳体和第二环形壳体之间的相对周向和轴向运动。

    ATTACHMENT APPARATUS FOR CERAMIC MATRIX COMPOSITE MATERIALS
    5.
    发明申请
    ATTACHMENT APPARATUS FOR CERAMIC MATRIX COMPOSITE MATERIALS 审中-公开

    公开(公告)号：WO2014035613A3

    公开(公告)日：2014-03-06

    申请号：PCT/US2013/053615

    申请日：2013-08-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SANDER, David J. ,  DUELM, Shelton O.

    IPC: F01D25/14 ,  F01D25/00 ,  F02C7/00

    Abstract: A first ceramic matrix composite structure having a first flange with a first aperture, and a second structure having a second flange with a second aperture are clamped together by a fastener and spring assembly. The second flange is in contact with the first flange and the apertures of the first and second flanges align with each other. A threaded fastener having a thermal expansion rate that is different than the thermal expansion rate of at least one of the first ceramic matrix composite structure and second structure extends through the aligned apertures. The fastener includes a bolt, a nut, and a spring assembly that maintains a constant clamping pressure irrespective of the thermal expansion differences between the bolt and the first ceramic matrix composite structure and second structure.

    LINER ASSEMBLY
    6.
    发明申请
    LINER ASSEMBLY 审中-公开
    内衬组件

    公开(公告)号：WO2014021973A2

    公开(公告)日：2014-02-06

    申请号：PCT/US2013/040232

    申请日：2013-05-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： TREAT, Christopher ,  STENMAN, Christina A. ,  DUELM, Shelton O. ,  SIMPSON, Alex J.

    IPC: F02K1/12 ,  F02K1/06 ,  F02C7/00

    CPC classification number: F02K1/1223 ,  F02K1/12 ,  F05D2300/6033 ,  F23R3/16

    Abstract: A liner assembly includes a plurality of flaps arranged about a central axis and operable to move relative to the central axis. Each of the plurality of flaps defines a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis. Each of the plurality of flaps has a thickness between the inner surface and the outer surface, and thickness varies in a lateral direction between the lateral sides.

    Abstract translation: 衬套组件包括围绕中心轴布置并可操作以相对于中心轴线移动的多个翼片。 多个翼片中的每一个限定了前端和后端，侧面以及相对于中心轴线的内表面和外表面。 多个翼片中的每一个在内表面和外表面之间具有厚度，并且厚度在横向方向之间在横向方向上变化。

    STATOR VANE PLATFORM WITH FLANGES
    8.
    发明申请
    STATOR VANE PLATFORM WITH FLANGES 审中-公开

    公开(公告)号：WO2015023324A3

    公开(公告)日：2015-02-19

    申请号：PCT/US2014/033719

    申请日：2014-04-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： DUELM, Shelton O. ,  RUGG, Kevin L.

    IPC: F01D9/02 ,  F01D25/28 ,  F02C7/20

    Abstract: Disclosed is a gas turbine engine that includes a plurality of stator vanes. Each of the stator vanes includes an airfoil section and a platform provided at an end of the airfoil section. The platforms are provided with flanges on opposed ends thereof, and the flanges are fastened to corresponding flanges of an adjacent one of the plurality of stator vanes.

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