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    AIRFOIL WITH A TRAILING EDGE SUPPLEMENT STRUCTURE
    81.
    发明申请
    AIRFOIL WITH A TRAILING EDGE SUPPLEMENT STRUCTURE 审中-公开
    具有跟踪边缘补偿结构的气翼

    公开(公告)号：US20150041590A1

    公开(公告)日：2015-02-12

    申请号：US13963276

    申请日：2013-08-09

    Applicant: General Electric Company

    Inventor： Kevin Richard Kirtley ,  David Edward Schick ,  Aaron Ezekiel Smith

    IPC: B64C3/00

    CPC classification number: B64C3/00 ,  F01D5/187 ,  F01D5/28 ,  F05D2230/30 ,  F05D2240/122 ,  F05D2240/304

    Abstract: An airfoil includes a main portion formed of a base material and having an inner core comprising a hollow region. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising a low-melt superalloy operatively coupled to the base material proximate the trailing edge region. Yet further included is at least one cooling passage fluidly coupling the inner core of the main portion to an inner region of the trailing edge region. Also included is a trailing edge region exhaust path disposed in the inner region and configured to route a cooling airflow in a span-wise direction of the airfoil.

    Abstract translation: 机翼包括由基材形成并具有包括中空区域的内芯的主体部分。 还包括主要部分的后缘区域。 还包括后缘补充结构，其包括可操作地连接到靠近后缘区域的基底材料的低熔融超合金。 还包括至少一个冷却通道，其将主要部分的内芯流体地连接到后缘区域的内部区域。 还包括设置在内部区域中的后缘区域排气路径，其构造成在翼型的跨度方向上布置冷却气流。

    PIN-FIN ARRAY
    82.
    发明申请
    PIN-FIN ARRAY 有权
    PIN-FIN阵列

    公开(公告)号：US20140348665A1

    公开(公告)日：2014-11-27

    申请号：US14453366

    申请日：2014-08-06

    Applicant: General Electric Company

    Inventor： Aaron Ezekiel Smith

    IPC: F01D5/18

    CPC classification number: F01D5/188 ,  F05D2240/304 ,  F05D2260/2212 ,  F05D2260/2214

    Abstract: The present application provides an airfoil with a cooling flow therein. The airfoil may include an internal cooling passage, a number of cooling holes in communication with the internal cooling passage, and a number of pin-fins positioned within the internal cooling passage. The pin-fins are arranged with one or more turning openings and one or more guiding openings so as to direct the cooling flow towards the cooling holes.

    Abstract translation: 本申请提供其中具有冷却流的翼型件。 翼型件可以包括内部冷却通道，与内部冷却通道连通的多个冷却孔以及位于内部冷却通道内的多个销翅片。 销翅片布置有一个或多个转动开口和一个或多个引导开口，以便将冷却流引向冷却孔。

    Component for a gas turbine engine with a film hole
    85.
    发明授权
    Component for a gas turbine engine with a film hole 有权

    公开(公告)号：US11466575B2

    公开(公告)日：2022-10-11

    申请号：US16122536

    申请日：2018-09-05

    Applicant: General Electric Company

    Inventor： Aaron Ezekiel Smith ,  Metodi Blagoev Zlatinov ,  Thomas Earl Dyson

    IPC: F01D5/18

    Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.

    TURBINE ENGINE HANGER
    86.
    发明申请
    TURBINE ENGINE HANGER 审中-公开

    公开(公告)号：US20200300116A1

    公开(公告)日：2020-09-24

    申请号：US16356491

    申请日：2019-03-18

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Jonathan Russell Ratzlaff ,  Aaron Ezekiel Smith

    IPC: F01D25/14 ,  B04C3/06

    Abstract: A hanger for a turbine engine can include a first surface confronting a cooling airflow, a second surface facing a heated airflow, and a third surface radially outward of the first surface. The hanger can also include a cyclonic separator with a dirty air inlet and a clean air outlet, as well as a cooling air circuit extending through the cyclonic separator.

    Turbine component cooling holes
    89.
    发明授权
    Turbine component cooling holes 有权

    公开(公告)号：US10443396B2

    公开(公告)日：2019-10-15

    申请号：US15180553

    申请日：2016-06-13

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Thomas Earl Dyson ,  Aaron Ezekiel Smith

    IPC: F01D5/18

    Abstract: A turbine component includes an internal surface, an external surface and a cooling hole. The cooling hole includes an inlet disposed on the internal surface, an outlet disposed on the external surface and a flow passage in fluid communication between the inlet and outlet. The flow passage includes a metering section extending from the inlet to a metering end, a diffusion zone extending from the metering end to the outlet, and a hooded region defined by a portion of the diffusion zone covered by a hood. The cooling hole also includes a vane extending across the flow passage, wherein a portion of the vane is disposed within the hooded region.

    Airfoils with low-angle holes and methods for drilling same
    90.
    发明授权
    Airfoils with low-angle holes and methods for drilling same 有权

    公开(公告)号：US10316672B2

    公开(公告)日：2019-06-11

    申请号：US14038076

    申请日：2013-09-26

    Applicant: General Electric Company

    Inventor： Aaron Ezekiel Smith ,  John Wesley Harris, Jr.

    IPC: F01D5/00 ,  F01D5/18 ,  B23H9/14 ,  B26F1/26 ,  F01D5/14 ,  B23K26/382

    Abstract: A method for fabricating an airfoil includes forming a diffuser section in an exterior surface of the airfoil. The diffuser section is defined by at least an outer surface and an inner surface that converge at a stop surface. The method also includes positioning a drilling element of a drilling device on the stop surface. The method further includes orienting the drilling element at a first angle relative to the exterior surface. The method also includes forming, using the drilling element, a cooling channel extending through the airfoil from the stop surface to an interior surface, thereby forming the cooling channel at substantially the first angle.

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