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    Airfoil with CMC ply cutouts for cooling channels
    1.
    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.

    Seal arc segment with CMC ply cutouts for cooling channels
    2.
    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 flange formed of wishbone-shaped fiber layer structure
    9.
    发明授权
    Airfoil with flange formed of wishbone-shaped fiber layer structure 有权

    公开(公告)号：US11346228B1

    公开(公告)日：2022-05-31

    申请号：US17182389

    申请日：2021-02-23

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Alyson T. Burdette ,  Bryan P. Dube ,  Howard J. Liles ,  James T. Roach

    IPC: F01D5/14 ,  F01D9/04 ,  B29B11/16 ,  D03D25/00

    Abstract: A vane arc segment includes an airfoil fairing that has a fairing platform and an airfoil section that extends there from. The fairing platform defines a gaspath side and a non-gaspath side and includes a flange that projects from the non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite that includes a wishbone-shaped fiber layer structure that has first and second arms that converge and merge into a single leg. The first and second arms are formed of fiber plies comprised of a network of fiber tows. The single leg comprises fiber tows from each of the fiber plies of the first and second arms. The fiber tows of the first arm are interwoven in the single leg with the fiber tows of the second arm. The first arm, the second arm, or the single leg forms at least a portion of the flange.

    AIRFOIL WITH SANDWICH COMPOSITE FLANGE
    10.
    发明申请
    AIRFOIL WITH SANDWICH COMPOSITE FLANGE 有权

    公开(公告)号：US20240401485A1

    公开(公告)日：2024-12-05

    申请号：US18328217

    申请日：2023-06-02

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

    IPC: F01D5/28 ,  F02C3/04

    Abstract: An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side, a flange that extends from the non-gaspath side, and a gaspath side from which the airfoil section extends. The flange is comprised of a sandwich composite that includes first and second ceramic matrix composite (CMC) skins that each have at least one 2-D ceramic fiber ply, and a cellular core disposed between the first and second CMC skins.

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