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    Turbine airfoil trailing edge coolant passage created by cover
    11.
    发明授权
    Turbine airfoil trailing edge coolant passage created by cover 有权

    公开(公告)号：US10233761B2

    公开(公告)日：2019-03-19

    申请号：US15334450

    申请日：2016-10-26

    Applicant: General Electric Company

    Inventor： Zachary John Snider ,  Gregory Thomas Foster ,  Joseph Anthony Weber ,  James Fredric Wiedenhoefer

    IPC: F01D9/06 ,  F01D5/18 ,  F01D25/08 ,  F01D5/14 ,  F01D9/04

    Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.

    Impingement system for an airfoil
    12.
    发明授权
    Impingement system for an airfoil 有权

    公开(公告)号：US10408062B2

    公开(公告)日：2019-09-10

    申请号：US15235986

    申请日：2016-08-12

    Applicant: General Electric Company

    Inventor： Brian Gene Brzek ,  James Fredric Wiedenhoefer

    IPC: F01D5/18 ,  F01D25/12 ,  F01D9/02 ,  F01D9/06 ,  F02C3/04

    Abstract: An airfoil includes an exterior wall, a triple trailing edge pin bank, and an impingement system. The exterior wall defines a first interior space. The exterior wall also includes a pressure sidewall and a suction sidewall. The impingement system is disposed within the first interior space. The impingement system includes an interior wall which defines a second interior space a plurality of impingement holes configured to channel a flow of coolant from the second interior space to the first interior space. The interior wall has an impingement hole density with a varying hole density pattern. The impingement system also includes dividing walls extending from the interior wall to the exterior wall. The interior wall, exterior wall, and dividing walls define a first and second zone coupled in flow communication. The impingement hole density is configured to separately meter flow to the first and second zones.

    SYSTEM FOR REMOVING HEAT FROM TURBOMACHINERY COMPONENTS
    14.
    发明申请
    SYSTEM FOR REMOVING HEAT FROM TURBOMACHINERY COMPONENTS 审中-公开

    公开(公告)号：US20180045073A1

    公开(公告)日：2018-02-15

    申请号：US15234588

    申请日：2016-08-11

    Applicant: General Electric Company

    Inventor： James Fredric Wiedenhoefer ,  James Albert Tallman ,  Brian Gene Brzek

    IPC: F01D25/12 ,  F01D9/04 ,  F04D29/58 ,  F01D25/14 ,  F04D29/52 ,  F04D29/54 ,  F02C3/04 ,  F01D25/24

    Abstract: A turbomachinery component for a turbomachine includes feed manifold, a return manifold and a sidewall. The feed manifold is configured to receive a coolant stream therein and includes a plurality of feed plenums. The return manifold includes a plurality of return plenums. The sidewall defines a plurality of feed channels and a plurality of return channels therein. The sidewall further includes an inner surface and an outer surface opposite the inner surface. Each feed channel is in fluid communication with at least one of the feed plenums. Each return channel is in fluid communication with at least one of the return plenums. The sidewall further at least partially defines a plurality of microchannels. Each microchannel is in fluid communication with one of the feed channels and one of the return channels.

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