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    Actively cooled component
    3.
    发明授权
    Actively cooled component 有权

    公开(公告)号：US11162370B2

    公开(公告)日：2021-11-02

    申请号：US15432599

    申请日：2017-02-14

    Applicant: Rolls-Royce Corporation

    Inventor： Jim Sellhorn ,  Brett Barker ,  Jeff Rhodes

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

    Abstract: An actively cooled component can be an airfoil, such as an air foil in a jet turbine engine. The component may have a body comprising at least one internal channel adapted for a flow of a cooling media therein. The channel may have two side walls separating a cold inner surface and a hot inner surface. The cold inner surface may have two impingement holes in fluid communication with a cooling media source, allowing for ingress of the cooling media into the internal channel. The hot inner surface may have one angled film hole in fluid communication with a hot outer surface, allowing for egress of the cooling media out of the internal channel. The first and second side walls may enclose a length of the internal channel along which the angled film hole is located between the two impingement holes.

    Coolant transfer system and method for a dual-wall airfoil
    5.
    发明授权
    Coolant transfer system and method for a dual-wall airfoil 有权

    公开(公告)号：US11834961B2

    公开(公告)日：2023-12-05

    申请号：US18162108

    申请日：2023-01-31

    Applicant: Rolls-Royce Corporation

    Inventor： Brett Barker

    IPC: F01D5/18

    CPC classification number: F01D5/181 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/20

    Abstract: A dual-wall airfoil configured for coolant transfer includes a spar having a pressure side wall and a suction side wall each including raised features on an outer surface thereof. An interior of the spar includes coolant cavities. An inner surface of a pressure side coversheet is in contact with the raised features on the outer surface of the pressure side wall so as to define pressure side flow pathways between the pressure side wall and the pressure side coversheet, and an inner surface of a suction side coversheet is in contact with the raised features on the outer surface of the suction side wall so as to define suction side flow pathways between the suction side wall and the suction side coversheet. The pressure side flow pathways and/or the suction side flow pathways include cooling circuit(s) configured to transfer coolant between the coolant cavities.

    Endwall directional cooling
    6.
    发明授权
    Endwall directional cooling 有权

    公开(公告)号：US11635000B1

    公开(公告)日：2023-04-25

    申请号：US17560697

    申请日：2021-12-23

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

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

    IPC: F01D9/00 ,  F01D25/12 ,  F01D9/04

    Abstract: An endwall may be disposed at one end of a vane assembly. The endwall may comprise an endwall spar and a coversheet on the hot surface of the endwall spar. The endwall may further comprise a cooling fluid channel between the hot surface of the endwall spar and the cold surface of the coversheet. The cooling fluid channel may include a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The cooling fluid outlet may be formed at an angle with the axis of the endwall spar. A plurality of pedestals may be disposed on the hot surface of the endwall spar extending into the cooling channel. The pedestals may be formed at an angle with the axis of the endwall spar to direct a cooling fluid.

    Airfoil with dual-wall cooling and angled cooling channels
    7.
    发明授权
    Airfoil with dual-wall cooling and angled cooling channels 有权

    公开(公告)号：US11459901B1

    公开(公告)日：2022-10-04

    申请号：US17481006

    申请日：2021-09-21

    Applicant: Rolls-Royce Corporation

    Inventor： Brett Barker ,  Eric Koenig ,  Bruce Varney ,  Kyle Uhlenhake

    IPC: F01D9/04 ,  F01D9/06

    Abstract: An airfoil with dual-wall cooling for a gas turbine engine comprises a spar having a pressure side wall and a suction side wall meeting at a leading edge and a trailing edge of the airfoil. An interior of the spar comprises a coolant cavity. The suction side wall includes an arrangement of rails on an outer surface thereof, where each rail extends along a non-chordal direction and terminates at or near the trailing edge. The airfoil also comprises a suction side coversheet overlying the suction side wall, where an inner surface of the suction side coversheet is in contact with the arrangement of rails so as to define a plurality of angled channels between the suction side wall and the suction side coversheet. The suction side wall also comprises inlet holes in fluid communication with the coolant cavity for feeding coolant to the angled channels, and the arrangement of rails is configured to direct the coolant through the angled channels and toward the trailing edge of the airfoil.

    HOT SECTION DUAL WALL COMPONENT ANTI-BLOCKAGE SYSTEM
    9.
    发明申请
    HOT SECTION DUAL WALL COMPONENT ANTI-BLOCKAGE SYSTEM 审中-公开

    公开(公告)号：US20200011199A1

    公开(公告)日：2020-01-09

    申请号：US16028623

    申请日：2018-07-06

    Applicant: Rolls-Royce Corporation

    Inventor： Bruce E. Varney ,  Brett Barker

    IPC: F01D25/12

    Abstract: A system for a hot section dual wall component in a gas turbine engine is used to avoid blockage by minimizing particulate deposits. The system includes impingement apertures formed in first wall of a cooling passageway of the dual wall component, and posts included on a second wall of the cooling passageway. The impingement apertures and the posts are respectively aligned opposite each other in the cooling passageway in operative cooperation so that working fluid exhausting into the cooling passageway from the impingement apertures in a first direction is directed to flow in a second direction along the cooling passageway to provide a laminar flow of the working fluid through the cooling passageway in order to minimize deposition of particles.

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