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    MULTI-LOBED COOLING HOLE
    11.
    发明申请
    MULTI-LOBED COOLING HOLE 有权
    多孔冷却孔

    公开(公告)号：US20140219815A1

    公开(公告)日：2014-08-07

    申请号：US13629916

    申请日：2012-09-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Atul Kohli ,  Matthew S. Gleiner

    IPC: F01D5/18

    CPC classification number: F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/73 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine component subjected to a flow of high temperature gas 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 and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe, a second lobe and a transition region. The first lobe diverges longitudinally and laterally from the metering section and has a first shape. The second lobe is generally opposite the first lobe and diverges longitudinally and laterally from the metering section and has a second shape different from the first shape. The transition region is positioned between the first and second lobes and includes a downstream end adjacent the outlet.

    Abstract translation: 经受高温气体流动的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。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括第一凸角，第二凸角和过渡区域。 第一个凸角从计量部分纵向和横向分开并具有第一形状。 第二叶片大致与第一叶片相对，并且从计量部分纵向和横向分叉并且具有不同于第一形状的第二形状。 过渡区域位于第一和第二凸角之间并且包括邻近出口的下游端。

    Component core with shaped edges
    12.
    发明授权
    Component core with shaped edges 有权

    公开(公告)号：US10677069B2

    公开(公告)日：2020-06-09

    申请号：US16199825

    申请日：2018-11-26

    Applicant: United Technologies Corporation

    Inventor： Matthew A. Devore ,  Matthew S. Gleiner ,  Douglas C. Jenne

    IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  B22C9/10

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a plurality of blade outer air seals and a plurality of airfoils, at least one of seals and airfoils including at least one cooling passage. The cooling passage includes a first wall and an opposed second wall bounding the cooling passage, a surface contour of the first wall having a plurality of first surface features and a surface contour of the second wall having a plurality of second surface features. The first surface features and the second surface features are arranged such that a width of the cooling passage varies along a length of the cooling passage defined by the first surface features and the second surface features. The first surface features have a first profile, and the second surface features have a second, different profile. A casting core for forming cooling passages in an aircraft component is also disclosed.

    COMPONENT CORE WITH SHAPED EDGES
    13.
    发明申请
    COMPONENT CORE WITH SHAPED EDGES 审中-公开

    公开(公告)号：US20200024963A1

    公开(公告)日：2020-01-23

    申请号：US16199825

    申请日：2018-11-26

    Applicant: United Technologies Corporation

    Inventor： Matthew A. Devore ,  Matthew S. Gleiner ,  Douglas C. Jenne

    IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a plurality of blade outer air seals and a plurality of airfoils, at least one of seals and airfoils including at least one cooling passage. The cooling passage includes a first wall and an opposed second wall bounding the cooling passage, a surface contour of the first wall having a plurality of first surface features and a surface contour of the second wall having a plurality of second surface features. The first surface features and the second surface features are arranged such that a width of the cooling passage varies along a length of the cooling passage defined by the first surface features and the second surface features. The first surface features have a first profile, and the second surface features have a second, different profile. A casting core for forming cooling passages in an aircraft component is also disclosed.

    COOLING HOLE WITH CURVED METERING SECTION
    20.
    发明申请
    COOLING HOLE WITH CURVED METERING SECTION 有权
    冷却孔与弯曲计量段

    公开(公告)号：US20140373549A1

    公开(公告)日：2014-12-25

    申请号：US14478630

    申请日：2014-09-05

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo ,  Matthew S. Gleiner

    IPC: F01D25/12 ,  F01D5/18

    CPC classification number: F01D25/12 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2250/71 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a cooling hole. The component includes a first wall having an inlet, a second wall having an outlet and a metering section extending downstream from the inlet and having a substantially convex first surface and a substantially concave second surface. The component also includes a diffusing section extending from the metering section to the outlet. A gas turbine engine wall includes first and second surfaces and a cooling hole extending between an inlet at the first surface and an outlet at the second surface. The cooling hole includes a metering section commencing at the inlet and a diffusing section in communication with the metering section and terminating at the outlet. The metering section includes a top portion having a first arcuate surface and a bottom portion having a second arcuate surface. The first and second arcuate surfaces have arcs extending in substantially similar directions.

    Abstract translation: 燃气涡轮发动机部件包括冷却孔。 该部件包括具有入口的第一壁，具有出口的第二壁和从入口的下游延伸并具有基本上凸起的第一表面和基本上凹入的第二表面的计量部分。 该部件还包括从计量部分延伸到出口的扩散部分。 燃气涡轮发动机壁包括第一和第二表面以及在第一表面处的入口与第二表面的出口之间延伸的冷却孔。 冷却孔包括从入口开始的计量部分和与计量部分连通并终止于出口的扩散部分。 计量部分包括具有第一弧形表面的顶部部分和具有第二弓形表面的底部部分。 第一和第二弧形表面具有基本上相似的方向延伸的弧。

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