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    IMPINGEMENT INSERT FOR A GAS TURBINE ENGINE
    21.
    发明申请
    IMPINGEMENT INSERT FOR A GAS TURBINE ENGINE 有权

    公开(公告)号：US20210270141A1

    公开(公告)日：2021-09-02

    申请号：US17118792

    申请日：2020-12-11

    Applicant: General Electric Company

    Inventor： Sandip Dutta ,  Benjamin Paul Lacy ,  Gary Michael Itzel ,  Zachary John Snider

    IPC: F01D9/06 ,  F01D11/08 ,  F01D5/18 ,  F01D25/14

    Abstract: The present disclosure is directed to a turbomachine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.

    TURBINE ROTOR BLADE WITH ANGEL WING WITH COOLANT TRANSFER PASSAGE BETWEEN ADJACENT WHEEL SPACE PORTIONS BY ADDITIVE MANUFACTURE
    22.
    发明申请
    TURBINE ROTOR BLADE WITH ANGEL WING WITH COOLANT TRANSFER PASSAGE BETWEEN ADJACENT WHEEL SPACE PORTIONS BY ADDITIVE MANUFACTURE 有权

    公开(公告)号：US20210222566A1

    公开(公告)日：2021-07-22

    申请号：US16749167

    申请日：2020-01-22

    Applicant: General Electric Company

    Inventor： Zachary John Snider

    IPC: F01D5/18

    Abstract: A turbine rotor blade is additively manufactured and includes an airfoil body including a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges. A shank is at a radial inner end of the airfoil body, and at least one angel wing extends laterally from at least one side of the shank. A coolant transfer passage is defined through the at least one angel wing. The coolant transfer passage fluidly couples a first wheel space portion defined between the shank and a first adjacent shank of a first adjacent turbine rotor blade and a second wheel space portion defined between the shank and a second adjacent shank of a second adjacent turbine rotor blade. The coolant transfer passage allows coolant to pass between wheel space portions of adjacent turbine rotor blades.

    COOLANT DELIVERY VIA AN INDEPENDENT COOLING CIRCUIT
    23.
    发明申请
    COOLANT DELIVERY VIA AN INDEPENDENT COOLING CIRCUIT 有权

    公开(公告)号：US20210123348A1

    公开(公告)日：2021-04-29

    申请号：US16663941

    申请日：2019-10-25

    Applicant: General Electric Company

    Inventor： Matthew Troy Hafner ,  Lyndsay Marie Kibler ,  Brad Wilson VanTassel ,  Benjamin Paul Lacy ,  Zachary John Snider ,  Christopher Donald Porter ,  Srikanth Chandrudu Kottilingam

    IPC: F01D5/18

    Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.

    THERMAL BARRIER COATING SPALLATION DETECTION SYSTEM
    24.
    发明申请
    THERMAL BARRIER COATING SPALLATION DETECTION SYSTEM 审中-公开

    公开(公告)号：US20190107499A1

    公开(公告)日：2019-04-11

    申请号：US15726759

    申请日：2017-10-06

    Applicant: General Electric Company

    Inventor： Andrew David Ellis ,  Kurt Kramer Schleif ,  Zachary John Snider

    IPC: G01N25/72

    Abstract: The present application thus provides a thermal barrier coating spallation detection system for a gas turbine. The thermal barrier coating spallation detection system may include a hot gas path component with a phosphor layer and a thermal barrier coating, a stimulant radiation source, and an optical device such that the optical device directs stimulant radiation at the thermal barrier coating and receives emission radiation. A change in the received emission radiation indicates spallation of the thermal barrier coating.

    SYSTEM AND METHOD FOR NEAR WALL COOLING FOR TURBINE COMPONENT
    25.
    发明申请
    SYSTEM AND METHOD FOR NEAR WALL COOLING FOR TURBINE COMPONENT 审中-公开

    公开(公告)号：US20180363471A1

    公开(公告)日：2018-12-20

    申请号：US15624269

    申请日：2017-06-15

    Applicant: General Electric Company

    Inventor： Zachary John Snider ,  Allison Christine Gose ,  Daniel Burnos ,  Gregory Thomas Foster

    IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12

    Abstract: A turbine airfoil includes a turbine component that includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a near wall source cavity disposed within the turbine component, and the near wall source cavity receives cooling air, and a second near wall cooling cavity disposed within the turbine component. The turbine airfoil further includes a first circuit completion plate disposed on a first end of the turbine component, and the first circuit completion plate fluidly couples the near wall source cavity to the second near wall cooling cavity.

    System and method for dissipating thermal energy away from electronic components in a rotatable shaft
    27.
    发明授权
    System and method for dissipating thermal energy away from electronic components in a rotatable shaft 有权
    用于将热能从远离电子部件的旋转轴中散出的系统和方法

    公开(公告)号：US09320181B1

    公开(公告)日：2016-04-19

    申请号：US14541203

    申请日：2014-11-14

    Applicant: General Electric Company

    Inventor： Kurt Kramer Schleif ,  Donald W. Shaw ,  Zachary John Snider ,  Mario Joseph Arceneaux

    IPC: H05K7/20 ,  H05K7/14

    CPC classification number: F01D25/12 ,  F01D17/085 ,  F03D80/60 ,  F04D25/068 ,  F04D29/5813 ,  H02K9/22 ,  H02K11/20 ,  H02K11/35

    Abstract: A system for dissipating thermal energy from electronic components disposed within a rotatable shaft includes an annular carrier shaft having one end formed to couple to an end of a rotor shaft. The system also includes a transmitter assembly. The transmitter includes an outer casing, a daughter board and a circuit board electronically coupled to the daughter board within an inner pocket of the transmitter housing. The circuit board comprises a strip of thermally conductive material. The transmitter assembly further includes a lid that at least partially seals the inner pocket. A contact surface of the lid is in thermal communication with the thermally conductive material of the circuit board and at least a portion of a top surface of the lid is thermally coupled to an inner surface of the carrier shaft during rotation thereof. A method for dissipating thermal energy away from the circuit board is also provided.

    Abstract translation: 用于从设置在可旋转轴内的电子部件散发热能的系统包括环形载体轴，其一端形成为联接到转子轴的端部。 该系统还包括发射器组件。 发射机包括外壳，子板和电路板，电子耦合到发射器壳体的内袋内的子板。 电路板包括导热材料条。 发射器组件还包括至少部分地密封内袋的盖。 盖的接触表面与电路板的导热材料热连通，并且盖的顶表面的至少一部分在其旋转期间热耦合到载体轴的内表面。 还提供了一种用于从电路板散发热能的方法。

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