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    COOLING HOLE FOR A GAS TURBINE ENGINE COMPONENT
    1.
    发明申请
    COOLING HOLE FOR A GAS TURBINE ENGINE COMPONENT 审中-公开
    用于气体涡轮发动机部件的冷却孔

    公开(公告)号：US20150377033A1

    公开(公告)日：2015-12-31

    申请号：US14766475

    申请日：2014-02-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan XU

    IPC: F01D5/18 ,  F23R3/02 ,  F01D9/02 ,  F01D11/08

    CPC classification number: F01D5/186 ,  F01D5/288 ,  F01D9/023 ,  F01D9/065 ,  F01D11/08 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/02 ,  F23R2900/03042

    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface, an outer skin and a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. At least two lobes are embedded within the diffusion section of the cooling hole. At least one surface of each of the at least two lobes is at least partially cylindrical.

    Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括具有内表面，外表皮和冷却孔的壁，所述壁具有从内表面延伸并且合并到计量部分中的入口 以及在计量部分下游延伸到位于外皮的出口的扩散部分。 至少两个叶片嵌入在冷却孔的扩散部分内。 至少两个裂片中的每一个的至少一个表面至少部分是圆柱形的。

    PLATFORM WITH CURVED EDGES ADJACENT SUCTION SIDE OF AIRFOIL
    4.
    发明申请
    PLATFORM WITH CURVED EDGES ADJACENT SUCTION SIDE OF AIRFOIL 有权
    具有弯曲边缘的平台，AIRFOIL附近相邻侧

    公开(公告)号：US20150337666A1

    公开(公告)日：2015-11-26

    申请号：US14652651

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan XU

    IPC: F01D5/14 ,  F01D9/02

    CPC classification number: F01D5/147 ,  F01D5/021 ,  F01D5/143 ,  F01D5/145 ,  F01D9/02 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/80 ,  Y02T50/673

    Abstract: A gas turbine engine component includes an airfoil and a platform. The airfoil has a pressure side and an opposite suction side. The platform is connected to the airfoil and has a first curved edge adjacent the suction side and a second curved edge spaced from the pressure side such that more than half of the platform is located to the pressure side. The platform located to the pressure side has a non-axisymmetrical surface contouring.

    Abstract translation: 燃气涡轮发动机部件包括翼型件和平台。 翼型件具有压力侧和相对的吸力侧。 平台连接到翼型件，并且具有邻近吸力侧的第一弯曲边缘和与压力侧间隔开的第二弯曲边缘，使得平台的一半以上位于压力侧。 位于压力侧的平台具有非轴对称的表面轮廓。

    DOUBLE WALL AIRFOIL COOLING CONFIGURATION FOR GAS TURBINE ENGINE
    5.
    发明申请
    DOUBLE WALL AIRFOIL COOLING CONFIGURATION FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20190316472A1

    公开(公告)日：2019-10-17

    申请号：US15954879

    申请日：2018-04-17

    Applicant: United Technologies Corporation

    Inventor： JinQuan XU

    IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12

    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. An outer cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core cooling passage. The core cooling passage, the outer cooling passage and a cooling hole fluidly interconnects the core and outer cooling passages. The cold side wall has a first thickness and a protrusion that extends from the cold side wall beyond the first thickness to a second thickness. The cooling hole is arranged at least partially in the protrusion.

    GAS TURBINE ENGINE HAVING A MISTURNED STAGE
    8.
    发明申请
    GAS TURBINE ENGINE HAVING A MISTURNED STAGE 审中-公开
    气体涡轮发动机有一个雾化的阶段

    公开(公告)号：US20160017796A1

    公开(公告)日：2016-01-21

    申请号：US14767602

    申请日：2014-02-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan XU ,  Frederic Tisdall TENNEY

    IPC: F02C3/06

    CPC classification number: F02C3/06 ,  F01D5/143 ,  F01D5/16 ,  F04D29/542 ,  F04D29/547 ,  F04D29/661 ,  F04D29/666 ,  F05D2260/961 ,  Y02T50/673

    Abstract: A stage of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a row of flow directing components circumferentially disposed about a centerline axis and at least one flow directing component of the row having at least one design characteristic that is dissimilar from a corresponding design characteristic of at least one other flow directing component of the row.

    Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机的一个阶段尤其包括围绕中心线轴线周向设置的一排流动引导部件，以及具有至少一个设计特征的行的至少一个流动引导部件 其与行的至少一个其它流动指向部件的相应设计特征不同。

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