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    Cooled airfoil and method of making
    12.
    发明授权
    Cooled airfoil and method of making 有权

    公开(公告)号：US11499434B2

    公开(公告)日：2022-11-15

    申请号：US17262399

    申请日：2018-07-31

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Thomas Earl Dyson ,  Brian Brzek ,  Fred Willett, Jr. ,  Paul Dimascio

    IPC: F01D5/18 ,  B33Y80/00

    Abstract: In one embodiment, an airfoil includes an airfoil body portion, an airfoil tip portion disposed radially outward of the airfoil body portion, an airfoil root portion, and a plurality of radial cooling passages extending through the airfoil body portion from the root portion to the tip airfoil portion. The airfoil body portion and the airfoil tip portion are joined at a braze interface or a weld interface. The airfoil tip portion includes at least one manifold fluidly connecting at least one radial cooling passage to at least one other radial cooling passage.

    Ceramic matrix composite component including counterflow channels and method of producing
    13.
    发明授权
    Ceramic matrix composite component including counterflow channels and method of producing 有权

    公开(公告)号：US11326470B2

    公开(公告)日：2022-05-10

    申请号：US16722980

    申请日：2019-12-20

    Applicant: General Electric Company

    Inventor： Thomas Earl Dyson ,  Douglas Glenn Decesare ,  Changjie Sun

    IPC: F01D25/00 ,  C04B35/80 ,  C04B38/06 ,  F01D5/14 ,  F01D9/02 ,  F01D25/24

    Abstract: A ceramic matrix composite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of elongated functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration.

    COOLING ASSEMBLY FOR A TURBINE ASSEMBLY
    14.
    发明申请
    COOLING ASSEMBLY FOR A TURBINE ASSEMBLY 有权

    公开(公告)号：US20210156265A1

    公开(公告)日：2021-05-27

    申请号：US16697242

    申请日：2019-11-27

    Applicant: General Electric Company

    Inventor： Nicholas William Rathay ,  Thomas Earl Dyson ,  Brian Brzek

    IPC: F01D5/18

    Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.

    PROTECTIVE SHIELDS FOR IMPROVED COATING OF TURBINE COMPONENT COOLING FEATURES
    15.
    发明申请
    PROTECTIVE SHIELDS FOR IMPROVED COATING OF TURBINE COMPONENT COOLING FEATURES 有权

    公开(公告)号：US20210047718A1

    公开(公告)日：2021-02-18

    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 ,  B33Y80/00 ,  B33Y10/00 ,  F01D5/28 ,  F01D5/18

    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.

    COOLING ASSEMBLY FOR A TURBINE ASSEMBLY
    18.
    发明申请
    COOLING ASSEMBLY FOR A TURBINE ASSEMBLY 审中-公开

    公开(公告)号：US20180171872A1

    公开(公告)日：2018-06-21

    申请号：US15379988

    申请日：2016-12-15

    Applicant: General Electric Company

    Inventor： Thomas Earl Dyson ,  Daniel Robinson Getsinger ,  Nicholas William Rathay

    IPC: F02C7/18 ,  F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F23R3/06

    CPC classification number: F02C7/18 ,  F01D5/18 ,  F01D5/186 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/202 ,  F23R3/06

    Abstract: A cooling assembly comprises a cooling chamber disposed inside a turbine assembly. The cooling chamber is configured to direct cooling air inside one or more of a combustion chamber or an airfoil of the turbine assembly. An orthogonally converging diffusing (OCD) conduit is fluidly coupled with the cooling chamber. The OCD conduit is configured to direct at least some of the cooling air out of the cooling chamber outside of an exterior surface of the one or more of the combustion chamber or the airfoil. The OCD conduit is elongated along and encompasses an intersection between a constricting plane and a diffusing plane that are traverse to each other. The OCD conduit has an interior surface with a first distance between opposing first portions of the interior surface. The first distance increases in the diffusing plane at increasing distances along the intersection from the cooling chamber toward the exterior surface. The interior surface of the OCD conduit has a second distance between opposing second portions of the interior surface of the OCD conduit. The second distance between opposing second portions decreases in the constricting plane at the increasing distances along the intersection from the cooling chamber toward the exterior surface.

    Cooling assembly for a turbine assembly
    19.
    发明授权
    Cooling assembly for a turbine assembly 有权

    公开(公告)号：US11732594B2

    公开(公告)日：2023-08-22

    申请号：US16697242

    申请日：2019-11-27

    Applicant: General Electric Company

    Inventor： Nicholas William Rathay ,  Thomas Earl Dyson ,  Brian Brzek

    IPC: F01D5/18

    CPC classification number: F01D5/189 ,  F01D5/186 ,  F05D2240/121 ,  F05D2240/304 ,  F05D2250/711 ,  F05D2260/202 ,  F05D2260/2212

    Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.

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