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    MULTI-SEGMENT ADJUSTABLE STATOR VANE FOR A VARIABLE AREA VANE ARRANGEMENT
    1.
    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。

    VARIABLE AREA VANE ENDWALL TREATMENTS
    4.
    发明申请
    VARIABLE AREA VANE ENDWALL TREATMENTS 审中-公开
    可变区域VANE EndWALL治疗

    公开(公告)号：WO2015099869A2

    公开(公告)日：2015-07-02

    申请号：PCT/US2014/061333

    申请日：2014-10-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： TEIXEIRA, John, D. ,  GROVER, Eric, A. ,  SURACE, Raymond

    IPC: F01D9/02

    CPC classification number: F01D17/162 ,  F01D5/143 ,  F05D2250/241 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

    Abstract: A gas turbine engine component includes an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one body supported between the outer and inner endwalls for rotation about an axis. The body includes an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap. The outer and inner diameter surfaces and the outer and inner diameter endwalls are configured such that the first and second gaps remain generally constant in size as the body rotates about the axis.

    Abstract translation: 燃气涡轮发动机部件包括外径端壁，位于外径端壁的径向内侧的内径端壁，以及支撑在外端壁与内端壁之间的至少一个主体，用于绕轴线转动。 主体包括通过第一间隙与外径端壁隔开的外径表面，以及通过第二间隙与内径端壁隔开的内径表面。 外径和内径表面以及外径和内径端壁被构造成使得当主体围绕轴旋转时，第一和第二间隙的尺寸基本保持不变。

    VARIABLE AREA TURBINE ARRANGEMENT FOR A GAS TURBINE ENGINE
    5.
    发明申请
    VARIABLE AREA TURBINE ARRANGEMENT FOR A GAS TURBINE ENGINE 审中-公开
    燃气涡轮发动机的可变面积涡轮排列

    公开(公告)号：WO2015069334A2

    公开(公告)日：2015-05-14

    申请号：PCT/US2014/049536

    申请日：2014-08-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SURACE, Raymond

    CPC classification number: F01D17/162 ,  F01D9/041 ,  F01D9/06 ,  F02C9/20 ,  F05D2220/32

    Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a first turbine section having at least a first variable vane row and a second turbine section downstream from the first turbine section and having at least a second variable vane row. A transition duct is disposed between the first turbine section and the second turbine section.

    Abstract translation: 根据本公开的示例性方面的可变面积的涡轮机装置尤其包括第一涡轮机部分，该第一涡轮机部分具有至少第一可变叶片排和位于第一涡轮机下游的第二涡轮机部分 部分并具有至少第二可变叶片排。 过渡管道设置在第一涡轮机部分和第二涡轮机部分之间。

    VARIABLE AREA VANE ARRANGEMENT FOR A TURBINE ENGINE
    7.
    发明申请
    VARIABLE AREA VANE ARRANGEMENT FOR A TURBINE ENGINE 审中-公开
    涡轮发动机的可变区域风扇装置

    公开(公告)号：WO2014113039A1

    公开(公告)日：2014-07-24

    申请号：PCT/US2013/022411

    申请日：2013-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: F01D17/16

    CPC classification number: F01D17/162 ,  F01D5/145 ,  F01D5/187

    Abstract: An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface 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 around the inlet and the shaft, and radially from the stator vane body.

    Abstract translation: 用于涡轮发动机的可调节定子叶片包括轴，凸缘和绕可变叶片轴线枢转的定子叶片体。 定子叶片体在第一端和第二端之间轴向延伸。 定子叶片主体包括翼型件，空腔和位于第一端的主体表面。 空腔从体表中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。 凸缘围绕入口和轴周向延伸，并且从定子叶片体径向延伸。

    VANE PLATFORM COOLING STRUCTURESPLATFORM
    9.
    发明公开
    VANE PLATFORM COOLING STRUCTURESPLATFORM 审中-公开

    公开(公告)号：EP3467257A1

    公开(公告)日：2019-04-10

    申请号：EP18186880.3

    申请日：2018-08-01

    Applicant: United Technologies Corporation

    Inventor： PROPHETER-HINCKLEY, Tracy A. ,  SURACE, Raymond

    IPC: F01D5/14 ,  F01D5/18

    Abstract: A vane platform cooling system (99; 299) may comprise a combustor shell (184; 284) and a combustor panel (110b; 210). A cavity (117; 217) may be located between the combustor shell (184; 284) and the combustor panel (110b; 210). A surface of the cavity (117; 217) may be angled toward the combustor shell (184; 284). An orifice (127; 227) may be formed in a vane platform (122; 222) located aft of the combustor panel (110b; 210). A standoff (198; 234) located in the cavity (117; 217) may direct air toward the vane platform (122; 222). An aperture (118; 218) may be formed in a surface of the vane platform (122; 222). A channel (119; 219) formed through the vane platform (122; 222) may connect the orifice (127; 227) and aperture (118; 218).

    COOLED COOLING AIR FOR BLADE AIR SEAL THROUGH OUTER CHAMBER
    10.
    发明公开
    COOLED COOLING AIR FOR BLADE AIR SEAL THROUGH OUTER CHAMBER 审中-公开

    公开(公告)号：EP3382156A1

    公开(公告)日：2018-10-03

    申请号：EP18165234.8

    申请日：2018-03-29

    Applicant: United Technologies Corporation

    Inventor： ORTIZ, Jonathan ,  SURACE, Raymond ,  JUREK, Renee J. ,  PROPHETER-HINCKLEY, Tracy A.

    IPC: F01D11/24 ,  F01D9/06

    Abstract: A gas turbine engine (20) includes a compressor section (24), a combustor (56), and a turbine section (28). The combustor (56) has a radially outer surface that defines a diffuser chamber (112) radially outwardly of the combustor (56). The turbine section (28) has a high pressure turbine first stage blade (118) that has an outer tip, and a blade outer air seal (126) positioned radially outwardly of the outer tip. A tap (102) for tapping air has been compressed by the compressor (56) and is passed through a heat exchanger (104). The air downstream of the heat exchanger (104) passes through at least one pipe (120) and into a manifold (122) radially outward of the blade outer air seal (126), and then passes across the blade outer air seal (126) to cool the blade outer air seal (126).

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