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    AIR COOLED GAS TURBINE COMPONENTS AND METHODS OF MANUFACTURING AND REPAIRING SAME
    3.
    发明申请
    AIR COOLED GAS TURBINE COMPONENTS AND METHODS OF MANUFACTURING AND REPAIRING SAME 审中-公开
    空气冷却气涡轮组件及其制造和修理方法

    公开(公告)号：US20140248425A1

    公开(公告)日：2014-09-04

    申请号：US13922933

    申请日：2013-06-20

    申请人： General Electric Company

    发明人： David Bruce Patterson ,  John Howard Starkweather ,  Thomas George Holland ,  Thomas John Tomlinson

    IPC分类号： F01D25/12

    CPC分类号： F01D25/12 ,  C23C4/01 ,  C23C4/02 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  F01D5/005 ,  F01D5/288 ,  F01D9/023 ,  F23M2900/05004 ,  F23R3/007 ,  F23R3/06 ,  Y02T50/67 ,  Y02T50/675 ,  Y02T50/6765 ,  Y10T428/24322

    摘要： A method of manufacturing a component suitable for use in a gas turbine engine, comprising the steps of forming the component from a substrate having a first surface and a second surface, forming at least one aperture through the substrate from the first surface to the second surface having a first open area, applying a first coating to at least one of the first surface and the second surface adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the first coating, applying a second coating to the first coating adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the second coating, and removing the second coating from the aperture, leaving most or all of the first coating to define a second open area which is smaller than the first open area. In a further aspect, a method of repairing a component suitable for use in a gas turbine engine, the method comprising the steps of removing coatings from the component, repairing any defects in the substrate of the component, and applying coatings as described herein.

    摘要翻译： 一种制造适用于燃气涡轮发动机的部件的方法，包括以下步骤：从具有第一表面和第二表面的基底形成所述部件，从所述第一表面到所述第二表面形成穿过所述基板的至少一个孔 具有第一开放区域，将第一涂层施加到与所述至少一个孔隙相邻的所述第一表面和所述第二表面中的至少一个，所述孔口至少部分地不被所述第一涂层阻挡，将第二涂层施加到所述第一涂层 所述孔邻近所述至少一个孔，所述孔至少部分地不被所述第二涂层阻挡，并且从所述孔移除所述第二涂层，使所述第一涂层的大部分或全部限定第二开口区域，所述第二开口区域小于所述第一开口 区。 在另一方面，一种修复适用于燃气涡轮发动机的部件的方法，所述方法包括以下步骤：从组件去除涂层，修复部件的基底中的任何缺陷，以及如本文所述的涂覆涂层。

    Turbine engine, components, and methods of cooling same
    4.
    发明授权
    Turbine engine, components, and methods of cooling same 有权

    公开(公告)号：US10975731B2

    公开(公告)日：2021-04-13

    申请号：US15314341

    申请日：2015-05-28

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Robert Francis Manning ,  Timothy Deryck Stone ,  Jared Peter Buhler ,  Victor Hugo Silva Correia ,  Gregory Michael Laskowski ,  Robert Carl Murray ,  Jonathan Russell Ratzlaff ,  Robert Proctor ,  John Howard Starkweather ,  Curtis Walton Stover

    IPC分类号： B01D45/16 ,  F02C7/05 ,  F02C7/052 ,  F01D25/32 ,  B04C3/06 ,  B04C3/00 ,  B64D33/08 ,  F01D5/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  F02C9/18 ,  B64D33/02

    摘要： A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.