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    Cast features for a turbine engine airfoil
    22.
    发明授权
    Cast features for a turbine engine airfoil 有权
    用于涡轮发动机翼型的铸件特征

    公开(公告)号：US08955576B2

    公开(公告)日：2015-02-17

    申请号：US14155545

    申请日：2014-01-15

    Applicant: United Technologies Corporation

    Inventor： Jason Edward Albert ,  Atul Kohli ,  Eric L. Couch

    IPC: B22C9/10 ,  B22C9/24 ,  B22C9/04 ,  F01D25/12 ,  F01D5/18

    CPC classification number: B22C9/24 ,  B22C9/04 ,  B22C9/108 ,  F01D5/186 ,  F01D25/12 ,  F05D2230/21 ,  F05D2260/202 ,  Y10T29/49341 ,  Y10T29/49826

    Abstract: A core assembly for a turbine engine blade includes a generally radially extending trunk interconnected to multiple generally axially extending tabs. The tabs are interconnected by a generally radially extending ligament. Multiple generally axially extending protrusions are interconnected to the ligament opposite the trunk. A mold is configured to define an exterior surface of an airfoil. The core is arranged within the mold and is configured such that the tabs and the ligament break through at the exterior surface.

    Abstract translation: 用于涡轮发动机叶片的芯组件包括与多个大致轴向延伸的突片相互连接的大致径向延伸的躯干。 翼片通过大致径向延伸的韧带相互连接。 多个大致轴向延伸的突起互连到与躯干相对的韧带。 模具构造成限定翼型件的外表面。 芯部布置在模具内并且被构造成使得突片和韧带在外表面突破。

    MULTI-LOBED COOLING HOLE
    23.
    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。

    CAST FEATURES FOR A TURBINE ENGINE AIRFOIL
    24.
    发明申请
    CAST FEATURES FOR A TURBINE ENGINE AIRFOIL 有权
    涡轮发动机气翼的特征

    公开(公告)号：US20140190654A1

    公开(公告)日：2014-07-10

    申请号：US14155545

    申请日：2014-01-15

    Applicant: United Technologies Corporation

    Inventor： Jason Edward Albert ,  Atul Kohli ,  Eric L. Couch

    IPC: B22C9/24 ,  F01D25/12

    CPC classification number: B22C9/24 ,  B22C9/04 ,  B22C9/108 ,  F01D5/186 ,  F01D25/12 ,  F05D2230/21 ,  F05D2260/202 ,  Y10T29/49341 ,  Y10T29/49826

    Abstract: A core assembly for a turbine engine blade includes a generally radially extending trunk interconnected to multiple generally axially extending tabs. The tabs are interconnected by a generally radially extending ligament. Multiple generally axially extending protrusions are interconnected to the ligament opposite the trunk. A mold is configured to define an exterior surface of an airfoil. The core is arranged within the mold and is configured such that the tabs and the ligament break through at the exterior surface.

    Abstract translation: 用于涡轮发动机叶片的芯组件包括与多个大致轴向延伸的突片相互连接的大致径向延伸的躯干。 翼片通过大致径向延伸的韧带相互连接。 多个大致轴向延伸的突起互连到与躯干相对的韧带。 模具构造成限定翼型件的外表面。 芯部布置在模具内并且被构造成使得突片和韧带在外表面突破。

    Internal cooling cavity with trip strips
    25.
    发明授权
    Internal cooling cavity with trip strips 有权

    公开(公告)号：US10947854B2

    公开(公告)日：2021-03-16

    申请号：US16793575

    申请日：2020-02-18

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

    IPC: F01D5/18

    Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

    Airfoil with varying wall thickness
    26.
    发明授权
    Airfoil with varying wall thickness 有权

    公开(公告)号：US10731474B2

    公开(公告)日：2020-08-04

    申请号：US16003755

    申请日：2018-06-08

    Applicant: United Technologies Corporation

    Inventor： Atul Kohli ,  Jaime G. Ghigliotty ,  James B. Downey

    IPC: F01D5/18 ,  F02C3/04 ,  F01D9/04

    Abstract: An airfoil includes an airfoil body that has a peripheral wall that defines an exterior side and an interior side that bounds an internal cavity in the airfoil body. The peripheral wall has first and second wall sections joined by a transition section. The first wall section is thicker than the second wall section. The transition section provides a change in thickness between the first wall section and the second wall section. The second wall section includes a cooling hole that has a first end that opens to the internal cavity at the interior side and a second end that opens to the exterior side.

    INTERNAL COOLING CAVITY WITH TRIP STRIPS
    28.
    发明申请
    INTERNAL COOLING CAVITY WITH TRIP STRIPS 审中-公开

    公开(公告)号：US20200182070A1

    公开(公告)日：2020-06-11

    申请号：US16793575

    申请日：2020-02-18

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

    IPC: F01D5/18

    Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

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