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    GAS TURBINE ENGINE COMPONENT WITH CONVERGING/DIVERGING COOLING PASSAGE
    1.
    发明申请
    GAS TURBINE ENGINE COMPONENT WITH CONVERGING/DIVERGING COOLING PASSAGE 审中-公开
    具有混合/分流式冷却通气的气体涡轮发动机部件

    公开(公告)号：WO2013123008A1

    公开(公告)日：2013-08-22

    申请号：PCT/US2013/025881

    申请日：2013-02-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, Jinquan ,  LEVASSERU, Glenn

    IPC: F02C7/00 ,  F02C7/12 ,  F02C9/00 ,  F01D25/08

    CPC classification number: F01D5/186 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2250/14 ,  F05D2250/20 ,  F05D2250/52 ,  F05D2250/70 ,  F05D2260/202 ,  F05D2260/2212 ,  Y02T50/676

    Abstract: A component for a gas turbine engine includes a gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an inlet portion having an inlet at the first surface, an outlet portion having an outlet at the second surface, and a transition defined between the inlet and the outlet. The inlet portion converges in a first direction from the inlet to the transition and diverges in a second direction from the inlet to the transition. The outlet portion diverges at least in one of the first and second directions from the transition to the outlet.

    Abstract translation: 用于燃气涡轮发动机的部件包括具有第一表面和第二表面的气体通道壁和从第一表面延伸穿过气体通道壁到第二表面的冷却孔。 冷却孔包括在第一表面具有入口的入口部分，在第二表面具有出口的出口部分和在入口和出口之间限定的过渡。 入口部分在从入口到过渡部的第一方向上会聚，并且在从入口到过渡的第二方向上发散。 出口部分至少在第一和第二方向中的一个方向上从过渡到出口发散。

    MULTIPLE DIFFUSING COOLING HOLE
    3.
    发明申请
    MULTIPLE DIFFUSING COOLING HOLE 审中-公开
    多个扩散式冷却孔

    公开(公告)号：WO2013122908A1

    公开(公告)日：2013-08-22

    申请号：PCT/US2013/025691

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, Jinquan

    IPC: F02C7/12 ,  F01D25/12 ,  F01D5/18

    CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet, a first diffusing section extending downstream from the metering section, and a second diffusing section extending downstream from the first diffusing section to the outlet. The second diffusing section includes first and second lobes, each lobe diverging longitudinally and laterally relative to the metering section, and a trailing edge.

    Abstract translation: 燃气涡轮发动机部件包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 所述冷却孔包括位于所述第一壁表面处的入口，位于所述第二壁表面处的出口，从所述入口下游延伸的计量部分，从所述计量部分下游延伸的第一扩散部分和从所述计量部分的下游延伸的第二扩散部分 第一个扩散段到出口。 第二扩散部分包括第一和第二凸角，每个凸起相对于计量部分纵向和横向发散，以及后缘。

    FILM COOLING CHANNEL ARRAY HAVING ANTI-VORTEX PROPERTIES
    5.
    发明申请
    FILM COOLING CHANNEL ARRAY HAVING ANTI-VORTEX PROPERTIES 审中-公开

    公开(公告)号：WO2014081489A3

    公开(公告)日：2014-05-30

    申请号：PCT/US2013/057034

    申请日：2013-08-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： XU, Jinquan

    IPC: F01D5/18

    Abstract: A cooling channel array carried by a component wall of a gas turbine engine is provided. The cooling channel array comprises a diffusion cavity and a metering section. The metering section comprises a main hole and two or more side holes. The side holes may be separate from the main hole or may branch off of the main hole. The diffusion cavity may incorporate a lobed configuration to help diffuse cooling fluid as it exits the cooling channel array.

    GAS TURBINE ENGINE COMPONENT WITH CONVERGING/DIVERGING COOLING PASSAGE
    9.
    发明授权
    GAS TURBINE ENGINE COMPONENT WITH CONVERGING/DIVERGING COOLING PASSAGE 有权
    燃气轮机部件会聚/发散冷却通道

    公开(公告)号：EP2815096B1

    公开(公告)日：2017-04-05

    申请号：EP13748460.6

    申请日：2013-02-13

    Applicant: United Technologies Corporation

    Inventor： XU, Jinquan ,  LEVASSEUR, Glenn

    IPC: F01D5/18 ,  F02C7/00 ,  F02C7/12 ,  F02C9/00 ,  F01D25/08

    Abstract: A component for a gas turbine engine includes a gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an inlet portion having an inlet at the first surface, an outlet portion having an outlet at the second surface, and a transition defined between the inlet and the outlet. The inlet portion converges in a first direction from the inlet to the transition and diverges in a second direction from the inlet to the transition. The outlet portion diverges at least in one of the first and second directions from the transition to the outlet.

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