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    Purge arrangement for dual-feed airfoil
    6.
    发明授权
    Purge arrangement for dual-feed airfoil 有权

    公开(公告)号：US11773728B2

    公开(公告)日：2023-10-03

    申请号：US17538730

    申请日：2021-11-30

    Applicant: Rolls-Royce Corporation

    Inventor： Brett Barker ,  Eric Koenig

    IPC: F01D5/18 ,  F01D5/14 ,  F01D9/04 ,  F01D25/12

    CPC classification number: F01D5/186 ,  F01D5/147 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/202

    Abstract: An airfoil, such as a vane or a blade for a gas turbine engine, may be provided. The airfoil may include a platform; a spar; a fillet; and a coversheet. The spar may include a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and a spar hole configured to direct the cooling fluid from the passageway to the outer surface of the spar. The fillet may be located at the intersection of the platform and the spar, and may couple the spar to the platform. The fillet and/or the coversheet may include a protrusion extending along the edge of the coversheet. The protrusion, along with the pedestal and the outer surface of the spar, may define a purge groove. The purge groove and a purge groove outlet may form a cooling path for cooling fluid to flow onto the platform.

    Endwall cooling scheme
    8.
    发明授权
    Endwall cooling scheme 有权

    公开(公告)号：US11536143B1

    公开(公告)日：2022-12-27

    申请号：US17559803

    申请日：2021-12-22

    Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation

    Inventor： Jack Moody ,  Jerry Layne ,  Jeffrey F. Rhodes ,  Brett Barker ,  Eric Koenig

    IPC: F01D5/18 ,  F01D9/06 ,  F01D25/12

    Abstract: An endwall assembly disposed at one end of a vane assembly may comprise an endwall spar that includes an cold side, an hot side, a leading edge, a trailing edge, and an axis extending from the leading edge to the trailing edge perpendicular to the leading edge. The endwall assembly may include a coversheet on the hot side of the endwall spar and a cooling channel that includes a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The endwall assembly may include a structure protruding from the cold side of the endwall spar, wherein the structure is located between the cooling fluid inlet and the cooling fluid outlet along the axis; and a cooling fluid source cavity on the cold side of the wall, the cooling fluid source cavity in fluid communication with the cooling fluid channel via the cooling fluid inlet.

    Combustion turbine vane cooling system
    9.
    发明授权
    Combustion turbine vane cooling system 有权

    公开(公告)号：US11225873B2

    公开(公告)日：2022-01-18

    申请号：US16741609

    申请日：2020-01-13

    Applicant: Rolls-Royce Corporation

    Inventor： Eric Koenig ,  Brett Barker

    IPC: F01D5/18

    Abstract: A system includes an air foil positionable in a combustion flow path of a combustion turbine. A shank may be integrally formed with the air foil, and the platform may be integrally formed with the shank. The platform includes linear fluid passageways, access ducts penetrating a wedge face surface of the platform, and outlet apertures formed in a radially outward surface of the platform. The outlet apertures are in fluid communication with respective linear fluid passageways such that fluid flowing through the respective linear fluid passageways is discharged from the outlet apertures into the combustion flow path. The platform also includes plugs is disposed in respective access ducts to form a fluid tight seal and be positioned in at least one of the respective linear fluid passageways. Fluid flowing through the respective linear fluid passageways flows away from a respective plug for discharge from a respective outlet aperture.

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