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    CERAMIC MATRIX COMPOSITE COMPONENT INCLUDING COOLING CHANNELS AND METHOD OF PRODUCING
    1.
    发明公开
    CERAMIC MATRIX COMPOSITE COMPONENT INCLUDING COOLING CHANNELS AND METHOD OF PRODUCING 审中-公开

    公开(公告)号：US20230313689A1

    公开(公告)日：2023-10-05

    申请号：US18322856

    申请日：2023-05-24

    Applicant: General Electric Company

    Inventor： Thomas Earl Dyson ,  Matthew Harper Hockemeyer

    IPC: F01D5/18 ,  F01D25/12 ,  C04B35/71

    CPC classification number: F01D5/18 ,  F01D25/12 ,  C04B35/71 ,  F05D2260/221 ,  F05D2300/6033

    Abstract: A ceramic matrix composite component and method of fabrication including a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration forming a densified body and one or more elongate functional features formed therein and in alignment with the plurality of longitudinally extending ceramic matrix composite plies. Each of the elongate functional features includes an inlet configured to be in fluid communication with a flow of cooling fluid from a fluid source. One or more bores cut through the plurality of ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite component. One or more film cooling throughholes cut through the ceramic matrix composite plies from an inner surface of the ceramic matrix composite component to an outlet proximate to the outer surface of the ceramic matrix composite component.

    Protective shields for improved coating of turbine component cooling features
    2.
    发明授权
    Protective shields for improved coating of turbine component cooling features 有权

    公开(公告)号：US11225707B2

    公开(公告)日：2022-01-18

    申请号：US16539803

    申请日：2019-08-13

    Applicant: General Electric Company

    Inventor： Thomas Earl Dyson ,  Lyndsay Marie Kibler ,  Brendon James Leary ,  David Vincent Bucci

    IPC: C23C4/01 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/18 ,  F01D5/28 ,  B23P15/02 ,  B23P15/04

    Abstract: A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component. A protective shield is formed on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture. During a coating process, the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture. Subsequent to coating, at least a portion of the protective shield is removed to provide for passage of a cooling fluid flow in the at least one cooling flow passage. The cooling fluid flow exits the turbine component through the aperture. A turbine component employing user of the protective shield is also disclosed.

    System for Rotating Detonation Combustion
    4.
    发明申请
    System for Rotating Detonation Combustion 有权

    公开(公告)号：US20210108801A1

    公开(公告)日：2021-04-15

    申请号：US16601012

    申请日：2019-10-14

    Applicant: General Electric Company

    Inventor： Kapil Kumar Singh ,  Thomas Michael Lavertu ,  Thomas Earl Dyson ,  Sarah Marie Monahan ,  Venkat Eswarlu Tangirala ,  Joel Meier Haynes

    IPC: F23R7/00 ,  F23R3/00 ,  F23R3/28

    Abstract: Systems for rotating detonation combustion are provided herein. The system includes an inner wall and an outer wall each extended around a centerline axis, wherein a detonation chamber is defined between the inner wall and the outer wall, and an iterative structure positioned at one or both of the inner wall or the outer wall. The iterative structure includes a first threshold structure corresponding to a first pressure wave attenuation and a second threshold structure corresponding to a second pressure wave attenuation. The iterative structure provides for pressure wave strengthening along a first circumferential direction in the detonation chamber or pressure wave weakening along a second circumferential direction opposite of the first circumferential direction. The first circumferential direction corresponds to a desired direction of pressure wave propagation in the detonation chamber.

    Turbine component with rail coolant directing chamber
    7.
    发明授权
    Turbine component with rail coolant directing chamber 有权

    公开(公告)号：US10408065B2

    公开(公告)日：2019-09-10

    申请号：US15833441

    申请日：2017-12-06

    Applicant: General Electric Company

    Inventor： Nicholas William Rathay ,  Thomas Earl Dyson ,  Jay Matthew Lang ,  Anthony William Mott

    IPC: F01D5/18

    Abstract: A turbine component includes a rail coolant directing chamber radially outward from an airfoil chamber and radially inward from a tip plate. The chamber includes an inlet fluidly coupled to the airfoil chamber to receive a coolant flow therefrom. A plurality of outlets from the rail coolant directing chamber direct the coolant flow to the at least one rail cooling passage in the rail. At least one directing wall is within the rail coolant directing chamber to direct the coolant flow towards one or more of the plurality of outlets located along at least one of the pressure side wall and an aft region of the suction side wall prior to other outlets.

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