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    Airfoil and method of making
    11.
    发明授权
    Airfoil and method of making 有权
    机翼和制作方法

    公开(公告)号：US09551228B2

    公开(公告)日：2017-01-24

    申请号：US13737200

    申请日：2013-01-09

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  San Quach ,  Matthew A. Devore

    IPC: F01D5/18 ,  B23P15/04 ,  B22C9/10

    CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/103 ,  F01D5/186 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  Y10T29/49337

    Abstract: An airfoil includes leading and trailing edges, a first exterior wall extending from the leading edge to the trailing edge and having inner and outer surfaces, a second exterior wall extending from the leading edge to the trailing edge generally opposite the first exterior wall and having inner and outer surfaces, and cavities within the airfoil. A first cavity extends along the inner surface of the first exterior wall and a first inner wall and has an upstream end and a downstream end, and a feed cavity is located between the first inner wall and the second exterior wall.

    Abstract translation: 机翼包括前缘和后缘，从前缘延伸到后缘并具有内表面和外表面的第一外壁，从前缘延伸到后缘的第二外壁，大体与第一外壁相对，并且具有内 和外表面以及翼型内的空腔。 第一腔沿着第一外壁的内表面延伸并且具有第一内壁，并且具有上游端和下游端，并且进料腔位于第一内壁和第二外壁之间。

    FLARED CROSSOVERS FOR AIRFOILS
    12.
    发明申请
    FLARED CROSSOVERS FOR AIRFOILS 审中-公开
    用于航空货架的绞肉机

    公开(公告)号：US20160230565A1

    公开(公告)日：2016-08-11

    申请号：US14618912

    申请日：2015-02-10

    Applicant: United Technologies Corporation

    Inventor： Christopher King ,  San Quach ,  Steven Bruce Gautschi

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

    CPC classification number: F01D5/187 ,  B22C9/103 ,  F01D5/18 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

    Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a reference plane extending in a spanwise direction along a surface of the internal wall, a first cavity and a second cavity separated by the internal wall, and a plurality of crossover passages within the internal wall and connecting the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The passage axis of each of the plurality of crossover passages is arranged at a radial angle relative to a localized region of the reference plane such that the radial angle of at least some of the plurality of crossover passages differs in the spanwise direction.

    Abstract translation: 根据本公开的示例的翼型件尤其包括具有外壁和内壁的翼型部分。 内壁限定沿着内壁的表面沿翼展方向延伸的参考平面，由内壁分隔的第一腔和第二腔，以及在内壁内的多个交叉通道，并将第一腔连接到 第二腔。 多个交叉通道中的每一个限定通道轴线。 多个交叉通道中的每一个的通道轴线相对于参考平面的局部区域以径向角度布置，使得多个交叉通道中的至少一些的径向角在翼展方向上不同。

    DISK LUG IMPINGEMENT FOR GAS TURBINE ENGINE AIRFOIL
    14.
    发明申请
    DISK LUG IMPINGEMENT FOR GAS TURBINE ENGINE AIRFOIL 审中-公开
    用于气体涡轮发动机气动盘的盘式油封

    公开(公告)号：US20160040534A1

    公开(公告)日：2016-02-11

    申请号：US14683408

    申请日：2015-04-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Steven Bruce Gautschi ,  San Quach ,  Tracy A. Propheter-Hinckley

    IPC: F01D5/18 ,  F01D5/02 ,  F01D5/30

    Abstract: A component for a gas turbine engine includes a root with a neck that extends into a fir tree with at least one tooth, the root includes a feed passage in communication with a multiple of cooling passages that extend through the neck and fir tree.

    Abstract translation: 用于燃气涡轮发动机的部件包括具有延伸到具有至少一个齿的枞树的颈部的根部，根部包括与延伸穿过颈部和枞树的多个冷却通道连通的进料通道。

    Blade outer air seal including cooling trench
    17.
    发明授权
    Blade outer air seal including cooling trench 有权

    公开(公告)号：US11098612B2

    公开(公告)日：2021-08-24

    申请号：US16686609

    申请日：2019-11-18

    Applicant: United Technologies Corporation

    Inventor： Winston Gregory Smiddy ,  San Quach ,  Matthew D. Parekh ,  Jeffrey T. Morton

    IPC: F01D25/12 ,  F01D11/00

    Abstract: A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a core flowpath, and a turbine fluidly connected to the combustor via the core flowpath. The turbine includes at least one stage having a plurality of rotors and a plurality of vanes. An outer diameter of the core flowpath at at least one stage is at least partially defined by a set of circumferentially arranged blade outer air seals. Each blade outer air seal includes a platform. An internal cooling cavity is defined within the platform. At least one mateface of the platform includes a cooling trench, and a first set of cooling holes connecting the internal cavity to the cooling trench.

    Panel surface pockets for coating retention
    20.
    发明授权
    Panel surface pockets for coating retention 有权

    公开(公告)号：US10823412B2

    公开(公告)日：2020-11-03

    申请号：US15477518

    申请日：2017-04-03

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Andreas Sadil ,  Donald W. Peters

    IPC: F23R3/00 ,  F01D25/14 ,  F02K1/82 ,  F02K9/97 ,  C23C2/00 ,  C23C4/02 ,  B32B3/30

    Abstract: A coated panel for a gas turbine engine includes a panel having a panel inner surface and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is disposed within the pocket to enhance coating retention to the panel. A gas turbine engine includes a turbine, a combustor to supply hot combustion gases to the turbine along a gas path, and one or more coated panels located along the gas path. The one or more panels includes a panel having a panel inner surface, and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is located within the pocket to enhance coating retention to the panel.

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