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    ENGINE COMPONENT WALL WITH A COOLING CIRCUIT
    51.
    发明申请
    ENGINE COMPONENT WALL WITH A COOLING CIRCUIT 审中-公开

    公开(公告)号：US20170328212A1

    公开(公告)日：2017-11-16

    申请号：US15152850

    申请日：2016-05-12

    Applicant: General Electric Company

    Inventor： Ronald Scott Bunker

    IPC: F01D5/18 ,  F01D5/14

    Abstract: An apparatus and method for cooling an engine component includes a wall. The wall can include multiple layers. The layers can be different materials and define an interior for the engine component. The layers can include shaped features to define a serial cooling air flow path for providing a flow from the interior to an exterior of the engine.

    Flowpath Contouring
    52.
    发明申请
    Flowpath Contouring 审中-公开

    公开(公告)号：US20170234161A1

    公开(公告)日：2017-08-17

    申请号：US15042568

    申请日：2016-02-12

    Applicant: General Electric Company

    Inventor： Ronald Scott Bunker

    IPC: F01D25/24 ,  F02C3/04

    Abstract: A gas turbine engine includes a compressor section, combustion section, and turbine section. The turbine section includes a turbine component stage, the turbine component stage including a plurality of turbine components together including a flowpath surface along a circumferential direction of the gas turbine engine. The flowpath surface defines in part a core air flowpath of the gas turbine engine and further defines a contour along the circumferential direction. The contour repeats less frequently than once per turbine component to accommodate a hot gas streak through the turbine section.

    ENGINE COMPONENT WITH FILM COOLING
    55.
    发明申请
    ENGINE COMPONENT WITH FILM COOLING 审中-公开

    公开(公告)号：US20170167268A1

    公开(公告)日：2017-06-15

    申请号：US14966030

    申请日：2015-12-11

    Applicant: General Electric Company

    Inventor： Ronald Scott Bunker

    IPC: F01D5/18 ,  F01D25/12

    Abstract: An engine component can comprise a cooled surface adjacent to a cooling flow and a hot surface adjacent to a hot flow of fluid. The component can comprise a wall separating the hot and cooling flows, defining the cooled surface and the hot surface, and having a plurality of film holes disposed in the wall. At least one turbulator and at least one film hole inlet can be disposed on the cooled surface. The turbulator and the inlet can be arranged to provide a steady flow of cooling fluid to the film hole. One arrangement can comprise spacing the film hole inlet at least two turbulator heights from the turbulator.

    NOZZLE FOR A GAS TURBINE ENGINE
    59.
    发明申请
    NOZZLE FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20170107834A1

    公开(公告)日：2017-04-20

    申请号：US14884134

    申请日：2015-10-15

    Applicant: General Electric Company

    Inventor： Hojjat Nasr ,  Ronald Scott Bunker ,  Gregory Michael Laskowski ,  Erich Alois Krammer

    IPC: F01D9/04 ,  F01D25/08 ,  F02C3/04

    Abstract: A nozzle assembly for a gas turbine engine includes at least one pair of fixed vanes to define a nozzle between the pair of fixed vanes. The vanes can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator, which can comprise a virtual impactor, can have an accelerator for accelerating fluid moving through the virtual impactor such that the flow path is divided into a major flow moving into the interior chamber and a minor flow moving into a particle collector defined within the virtual impactor. The accelerator accelerates the fluid such that particles within the fluid are carried by their momentum into the particle collector with the minor flow, removing the particles from the major flow of fluid moving into the interior chamber.

    COMPONENTS WITH MICROCHANNEL COOLING
    60.
    发明申请
    COMPONENTS WITH MICROCHANNEL COOLING 有权
    组件与微通道冷却

    公开(公告)号：US20170044904A1

    公开(公告)日：2017-02-16

    申请号：US15171270

    申请日：2016-06-02

    Applicant: General Electric Company

    Inventor： Ronald Scott Bunker

    IPC: F01D5/14 ,  B23P15/04 ,  F01D5/18

    CPC classification number: F01D5/147 ,  B23P15/04 ,  F01D5/186 ,  F01D5/189 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2260/204 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49229

    Abstract: A component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one hollow, interior space. The outer surface of the substrate defines a pressure side wall and a suction side wall. The pressure and suction side walls are joined together at a leading edge and at a trailing edge of the component. The outer surface defines one or more grooves that extend at least partially along the pressure or suction side walls in a vicinity of the trailing edge of the component. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer surface of the substrate. The coating comprises at least a structural coating, where the structural coating extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the trailing edge of the component. A method of forming cooling channels in the vicinity of the trailing edge of a component is also provided.

    Abstract translation: 组件包括具有外表面和内表面的基底，其中内表面限定至少一个中空的内部空间。 衬底的外表面限定了压力侧壁和吸力侧壁。 压力和吸力侧壁在部件的前缘和后缘处连接在一起。 外表面限定一个或多个凹槽，其至少部分地沿着部件后缘附近的压力或吸力侧壁延伸。 每个槽与相应的中空的内部空间流体连通。 所述部件还包括设置在所述基板的外表面的至少一部分上的涂层。 涂层至少包括结构涂层，其中结构涂层在凹槽上延伸，使得凹槽和结构涂层一起限定一个或多个通道以冷却部件的后缘。 还提供了在部件的后缘附近形成冷却通道的方法。

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