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    CMC gas turbine engine component with separated fiber plies
    3.
    发明授权
    CMC gas turbine engine component with separated fiber plies 有权

    公开(公告)号：US12104496B2

    公开(公告)日：2024-10-01

    申请号：US17883937

    申请日：2022-08-09

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Russell Kim

    IPC: F01D5/28 ,  F01D9/02 ,  F01D25/00

    CPC classification number: F01D25/005 ,  F01D5/282 ,  F01D9/02 ,  F05D2220/32 ,  F05D2300/6033

    Abstract: A gas turbine engine component includes a component wall that has an exterior core gaspath side and an opposed interior side. The component wall is formed of a ceramic matrix composite that includes a plurality of fiber plies disposed in a ceramic matrix. The component wall includes a corner that connects first and second wall sections. The fiber plies extend continuously through the first wall section, the corner, and the second wall section. The fiber plies are in a stacked contiguous arrangement in the first and second wall sections and at least some of the fiber plies separate from one another in the corner to define one or more void pockets there between.

    CMC laminate airfoil with ply drops
    4.
    发明授权
    CMC laminate airfoil with ply drops 有权

    公开(公告)号：US12044145B2

    公开(公告)日：2024-07-23

    申请号：US18319586

    申请日：2023-05-18

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Russell Kim ,  Howard J. Liles ,  Kathryn S. Read

    IPC: F01D5/28 ,  F01D5/14

    CPC classification number: F01D5/282 ,  F01D5/147 ,  F01D5/284 ,  F05D2300/6012 ,  F05D2300/6033 ,  F05D2300/6034

    Abstract: An airfoil includes an airfoil section that has an airfoil wall that circumscribes an internal airfoil cavity and defines leading and trailing ends and pressure and suction sides. The airfoil wall is formed of a ceramic matrix composite (CMC) laminate comprised of fiber plies disposed in a ceramic matrix. The fiber plies include a skin fiber ply that defines an exterior of the airfoil section and at least one inner fiber ply that lines the skin fiber ply. At least one inner fiber ply locally terminates at one of the leading end or the trailing end such that the airfoil wall has fewer of the fiber plies in the leading end or the trailing end than in each of the pressure side and the suction side.

    Seal arc segment with CMC ply cutouts for cooling channels
    5.
    发明授权
    Seal arc segment with CMC ply cutouts for cooling channels 有权

    公开(公告)号：US12044132B1

    公开(公告)日：2024-07-23

    申请号：US18195159

    申请日：2023-05-09

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Jonas Banhos ,  James T. Roach ,  Russell Kim

    IPC: F01D11/08 ,  F01D25/14

    CPC classification number: F01D11/08 ,  F01D25/14 ,  F05D2240/55 ,  F05D2260/2214 ,  F05D2300/6033

    Abstract: A seal arc segment includes a wall that defines radially inner and outer sides, forward and aft ends, and first and second circumferential sides. The wall includes a CMC ply lay-up of a radially inner-most CMC ply on the inner side, a radially outer-most CMC ply on the radially outer side, and radially intermediate CMC plies therebetween. At least one of the radially intermediate CMC plies has cutout voids that define cooling channels in the wall. The cooling channels are bound on lateral channel sides by the at least one of the radially intermediate CMC plies, bound on a radially inner channel side by a first adjacent one of the CMC plies, and bound on a radially outer channel side by a second, different adjacent one of the CMC plies. The radially outer-most CMC ply includes at least one inlet hole connected to the cooling channels for providing cooling air.

    Airfoil with CMC ply cutouts for cooling channels
    9.
    发明授权
    Airfoil with CMC ply cutouts for cooling channels 有权

    公开(公告)号：US12078081B1

    公开(公告)日：2024-09-03

    申请号：US18195149

    申请日：2023-05-09

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Jonas Banhos ,  Russell Kim ,  James T. Roach

    IPC: F01D5/28 ,  F01D5/18 ,  C04B35/80

    CPC classification number: F01D5/284 ,  F01D5/187 ,  F01D5/282 ,  C04B35/80 ,  F05D2300/6033

    Abstract: An airfoil includes an airfoil wall that circumscribes a main cavity and defines radially inner and outer ends, leading and trailing edges, and pressure and suction sides. The airfoil wall includes a lay-up of ceramic matrix composite (CMC) plies that span the radially inner and outer ends and have an inner-most CMC ply bounding at least a portion of the main cavity, an exterior skin CMC ply, and intermediate CMC plies between the inner-most CMC ply and the exterior skin CMC ply. At least one of the intermediate CMC plies has cutout voids that define cooling channels in the airfoil wall. The cooling channels are bound on lateral sides by the at least one of the intermediate CMC plies, bound on an inner side by a first adjacent one of the CMC plies, and bound on an outer side by a second, different adjacent one of the CMC plies.

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