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    Integrated squealer pocket tip and tip shelf with hybrid and tip flag core
    13.
    发明授权
    Integrated squealer pocket tip and tip shelf with hybrid and tip flag core 有权

    公开(公告)号：US10830055B2

    公开(公告)日：2020-11-10

    申请号：US15368826

    申请日：2016-12-05

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo, Jr. ,  Carey J. Clum

    IPC: F01D5/18 ,  F01D25/12 ,  F01D5/20

    Abstract: An airfoil includes an airfoil body having a first wall, a second wall, a third wall, a tip shelf, a pocket surface, and a tip surface. The tip shelf circumferentially extends between the first wall and the second wall. The pocket surface circumferentially extends between the second wall and the third wall. The first wall, the second wall, the third wall, and the pocket surface at least partially define a squealer pocket. The tip surface is spaced apart from the pocket surface and circumferentially extends between the second wall and the third wall.

    Double wall turbine gas turbine engine blade cooling configuration
    15.
    发明授权
    Double wall turbine gas turbine engine blade cooling configuration 有权

    公开(公告)号：US10590779B2

    公开(公告)日：2020-03-17

    申请号：US15832491

    申请日：2017-12-05

    Applicant: United Technologies Corporation

    Inventor： Christopher Whitfield ,  Carey Clum ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/18 ,  F02C9/18 ,  F02C3/04

    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.

    Airfoil turn caps in gas turbine engines
    16.
    发明授权
    Airfoil turn caps in gas turbine engines 有权

    公开(公告)号：US10465528B2

    公开(公告)日：2019-11-05

    申请号：US15426082

    申请日：2017-02-07

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Dominic J. Mongillo, Jr.

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

    Abstract: Turn caps for airfoils of gas turbine engines including cavity sidewalls, a first turn cap divider extending between the cavity sidewalls and defining a turning cavity between the first turn cap divider and the cavity sidewalls, and a second turn cap divider disposed radially inward within the turning cavity. A first turning path is defined between the first turn cap divider and the second turn cap divider and a second turning path is defined radially inward of the second turn cap divider and a merging chamber is formed in the turn cap wherein fluid flows through the first turning path and the second turning path are merged, the merging chamber, the first turning path, and the second turning path forming the turning cavity.

    DOUBLE WALL TURBINE GAS TURBINE ENGINE BLADE COOLING CONFIGURATION
    17.
    发明申请
    DOUBLE WALL TURBINE GAS TURBINE ENGINE BLADE COOLING CONFIGURATION 审中-公开

    公开(公告)号：US20190169997A1

    公开(公告)日：2019-06-06

    申请号：US15832478

    申请日：2017-12-05

    Applicant: United Technologies Corporation

    Inventor： Christopher Whitfield ,  Carey Clum ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/18 ,  F02C9/18

    CPC classification number: F01D5/187 ,  F02C3/04 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2250/185 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/2212

    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage. The resupply hole has an exit at the skin passage and the exit has a diffuser.

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