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    Airfoil having pedestals in trailing edge cavity
    22.
    发明授权
    Airfoil having pedestals in trailing edge cavity 有权

    公开(公告)号：US10337332B2

    公开(公告)日：2019-07-02

    申请号：US15053682

    申请日：2016-02-25

    Applicant: United Technologies Corporation

    Inventor： James Tilsley Auxier ,  Bret M. Teller

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

    Abstract: An airfoil of a gas turbine engine includes an airfoil body having a leading edge and a trailing edge extending in a radial direction, a trailing edge cavity formed within the airfoil and proximate to the trailing edge of the airfoil, the trailing edge cavity extending from the trailing edge in a forward direction toward the leading edge, at least one set of blocking pedestals located within the trailing edge cavity, a set of circular pedestals located aftward from the at least one blocking set of pedestals, and a set of spear pedestals located aftward from the set of circular pedestals and closest to the trailing edge of the airfoil body.

    DETECTION OF BLOCKAGE IN INTERNAL PASSAGES OF GAS TURBINE ENGINE COMPONENTS
    24.
    发明申请
    DETECTION OF BLOCKAGE IN INTERNAL PASSAGES OF GAS TURBINE ENGINE COMPONENTS 审中-公开

    公开(公告)号：US20180214941A1

    公开(公告)日：2018-08-02

    申请号：US15421502

    申请日：2017-02-01

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Lea Kennard Castle ,  Steven Bruce Gautschi ,  James Tilsley Auxier

    IPC: B22D29/00 ,  B22D25/02 ,  B22C9/24 ,  B22C9/10 ,  B22C9/04 ,  G01N23/04

    Abstract: A method of forming a component includes the steps of placing a core into a mold and pouring a component material around the core. The component material is allowed to solidify. The core is then removed from within the material, leaving a component having at least a first and a second cavity formed by the core. A first filler material is moved into the first cavity, and a second filler material is moved into the second cavity. The component is inspected for the presence of an apparent residual core within the first cavity and the second cavity. The location is identified of the apparent residual core from the core based upon an identification of whether the location of the apparent residual core is in the first or second filler materials. A method of inspecting a component formed by investment casting is also disclosed.

    Method and apparatus to enhance laminar flow for gas turbine engine components
    30.
    发明授权
    Method and apparatus to enhance laminar flow for gas turbine engine components 有权

    公开(公告)号：US10731469B2

    公开(公告)日：2020-08-04

    申请号：US15696307

    申请日：2017-09-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： JinQuan Xu ,  James Tilsley Auxier

    IPC: F01D5/14 ,  F01D5/18 ,  F01D9/04 ,  F02C3/04 ,  F01D5/28 ,  F01D9/02

    Abstract: A gas turbine engine component has a component body configured to be positioned within a flow path of a gas turbine engine having an external pressure, and wherein the component body includes at least one internal cavity having an internal pressure. At least one inlet opening is formed in an outer surface of the component body to direct hot exhaust gas flow into the at least one internal cavity, and there is at least one outlet from the internal cavity. The internal pressure is less than an inlet external pressure at the inlet opening and the internal pressure is greater than an outlet external pressure at the outlet opening to controllably ingest hot exhaust gas via the inlet opening and expel the hot exhaust gas via the outlet opening to maintain a laminar boundary layer along the outer surface of the component body.

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