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    MULTI-SEGMENT ADJUSTABLE STATOR VANE FOR A VARIABLE AREA VANE ARRANGEMENT
    24.
    发明申请
    MULTI-SEGMENT ADJUSTABLE STATOR VANE FOR A VARIABLE AREA VANE ARRANGEMENT 审中-公开
    适用于可变区域的多分段可调节定时器阵列

    公开(公告)号：WO2014116259A1

    公开(公告)日：2014-07-31

    申请号：PCT/US2013/023440

    申请日：2013-01-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： MCCAFFREY, Michael G. ,  PROPHETER-HINCKLEY, Tracy A. ,  SURACE, Raymond ,  SPANGLER, Brandon W.

    IPC: F01D17/16

    CPC classification number: F01D17/16 ,  F01D5/147 ,  F01D9/04 ,  F01D9/065 ,  F01D17/162 ,  F02C9/22 ,  F05D2260/201 ,  F05D2260/202

    Abstract: An assembly for a turbine engine includes a plurality of vane segments. The vane segments are fastened together and form an adjustable stator vane that pivots about a variable vane axis. The adjustable stator vane includes a stator vane body, a shaft and a flange. The stator vane body extends axially between a first end and a second end, and includes an airfoil, a body surface and a cavity. The body surface is located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially at least partially around the inlet, and radially from the stator vane body. A first of the vane segments includes the flange. A second of the vane segments includes at least a portion of the airfoil.

    Abstract translation: 涡轮发动机的组件包括多个叶片段。 叶片段被紧固在一起，并形成一个可调节的定子叶片，其绕可变叶片轴线枢转。 可调节定子叶片包括定子叶片体，轴和凸缘。 定子叶片体在第一端和第二端之间轴向延伸，并且包括翼型件，主体表面和空腔。 身体表面位于第一端。 空腔从体表面的入口轴向延伸到翼型中。 轴从第一端沿着可变叶片轴线延伸。 凸缘至少部分地围绕入口周向延伸，并且从定子叶片体径向延伸。 第一叶片段包括凸缘。 叶片段中的第二个叶片包括翼型的至少一部分。

    MANUFACTURE OF FULL RING STRUT VANE PACK
    25.
    发明申请
    MANUFACTURE OF FULL RING STRUT VANE PACK 审中-公开
    全系列风箱包装的制造

    公开(公告)号：WO2014100347A1

    公开(公告)日：2014-06-26

    申请号：PCT/US2013/076415

    申请日：2013-12-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： DUELM, Shelton O. ,  MCCAFFREY, Michael G.

    IPC: F01D9/04 ,  F01D9/02 ,  F02C7/00

    CPC classification number: F01D5/284 ,  F01D9/041 ,  F01D25/162 ,  F05D2230/23 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A vane assembly for a gas turbine engine is disclosed and includes a plurality of individual vane segments forming an annular ring. Each of the plurality of vane segments is formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform. An outer wrap is disposed about an outer periphery of the annular ring and over an interface between outer platforms of adjacent ones of the plurality of vane segments.

    Abstract translation: 公开了一种用于燃气涡轮发动机的叶片组件，并且包括形成环形环的多个单独叶片段。 多个叶片段中的每一个由包括在内平台和外平台之间延伸的至少一个翼型的陶瓷基复合材料形成。 围绕环形圈的外周并且在多个叶片段中的相邻叶片段的外平台之间的界面上设置外包裹物。

    WOVEN STRUCTURE AND METHOD FOR WEAVING SAME
    26.
    发明申请
    WOVEN STRUCTURE AND METHOD FOR WEAVING SAME 审中-公开
    WOVEN结构及其制造方法

    公开(公告)号：WO2014011380A1

    公开(公告)日：2014-01-16

    申请号：PCT/US2013/047019

    申请日：2013-06-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： HASKO, Gregory H. ,  MCCAFFREY, Michael G.

    IPC: D03D13/00 ,  D03D25/00

    CPC classification number: D03D23/00 ,  D03D41/004 ,  D03D47/12

    Abstract: An exemplary weaving method includes placing a first section of a fill fiber between warp fibers, forming a pick, moving a base to reposition the warp fibers, and placing a second section of the fill fiber between the warp fibers.

    Abstract translation: 示例性的编织方法包括将填充纤维的第一部分放置在经纤维之间，形成拾取，移动基底以重新定位经纱，以及将填充纤维的第二部分放置在经纱之间。

    PRE-DIFFUSER FOR A GAS TURBINE ENGINE
    27.
    发明公开
    PRE-DIFFUSER FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3719261A1

    公开(公告)日：2020-10-07

    申请号：EP20166506.4

    申请日：2020-03-27

    Applicant: United Technologies Corporation

    Inventor： MCCAFFREY, Michael G. ,  HOUGH, Matthew Andrew ,  RIVERO, Pedro

    IPC: F01D9/04 ,  F01D9/06 ,  F01D25/24 ,  F01D25/26

    Abstract: A hot fairing structure (102) for a pre-diffuser (100) includes a ring-strut-ring structure (118) that comprises a multiple of hollow struts (200), and a multiple of diffusion passage ducts (124) attached to the ring-strut-ring structure (118). A pre-diffuser (100) for a gas turbine engine (20) includes an exit guide vane ring (104) having a multiple of exit guide vanes (108) defined around an engine longitudinal axis (A), a ring-strut-ring structure (118) adjacent to the exit guide vane ring (104) to form a multiple of diffusion passages (120) defined around the engine longitudinal axis (A), an inlet to each of the multiple of diffusion passages (120) smaller than an exit from each of the multiple diffusion passages (120) through the ring-strut-ring structure (118), and a diffusion passage duct (124) attached to the ring-strut-ring structure (118) at the exit from each of the multiple diffusion passages (120).

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