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    CORIOLIS OPTIMIZED U-CHANNEL WITH ROOT FLAG
    61.
    发明申请
    CORIOLIS OPTIMIZED U-CHANNEL WITH ROOT FLAG 审中-公开

    公开(公告)号：US20190338646A1

    公开(公告)日：2019-11-07

    申请号：US15967950

    申请日：2018-05-01

    Applicant: United Technologies Corporation

    Inventor： Timothy J. Jennings ,  Carey Clum

    IPC: F01D5/18

    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between a leading edge and a trailing edge. The pressure and suction side walls extend in a radial direction between a platform and a tip to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction side walls and has a first passage along the pressure side wall and a second passage along the suction side wall. The first passage is configured to receive cooling air from a cooling air source radially inward of the platform. The second passage is configured to receive cooling air from the first passage near the tip. A root flag passage is configured to purge the cooling air from the second passage near the trailing edge.

    AIRFOIL COOLING CIRCUIT
    62.
    发明申请
    AIRFOIL COOLING CIRCUIT 审中-公开

    公开(公告)号：US20190120067A1

    公开(公告)日：2019-04-25

    申请号：US15791784

    申请日：2017-10-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Timothy J. Jennings ,  Carey Clum

    IPC: F01D5/18 ,  F01D9/04

    CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/18 ,  F01D5/186 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/221

    Abstract: An airfoil may include an airfoil body that defines a central chamber, a skin chamber, and an impingement hole extending between the central chamber and the skin chamber. The central chamber may be in fluidic communication with the skin chamber via the impingement hole. In various embodiments, a first cross-sectional area of the impingement hole is greater than about 25% of a second cross-sectional area of the skin chamber. In various embodiments, the impingement hole is positioned and configured to deliver cooling circuit air to a predicted position of a hotspot on a surface of the airfoil. In various embodiments, the airfoil body further defines at least one structural hole formed from at least one structural core tie, wherein a first cross-sectional area of the impingement hole is at least twice a second cross-sectional area of the at least one structural hole.

    AIRFOIL COOLING CIRCUIT
    63.
    发明申请
    AIRFOIL COOLING CIRCUIT 审中-公开

    公开(公告)号：US20190120064A1

    公开(公告)日：2019-04-25

    申请号：US15791745

    申请日：2017-10-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Timothy J. Jennings ,  Carey Clum

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

    Abstract: An airfoil may include an airfoil body that defines a skin chamber, a skin chamber outlet opening, and a tip flag chamber. In various embodiments, the skin chamber is in fluidic communication with the tip flag chamber via the skin chamber outlet opening. In various embodiments, the airfoil body further defines an outlet hole disposed on at least one of a trailing edge and a pressure side of the airfoil. The tip flag chamber may be in fluidic communication with the outlet hole (e.g., cooling circuit air in the tip flag chamber may exit the airfoil via the outlet hole). In various embodiments, the tip flag chamber extends parallel and directly adjacent to the outermost tip of the airfoil.

    AIRFOIL HAVING IMPINGEMENT LEADING EDGE
    64.
    发明申请
    AIRFOIL HAVING IMPINGEMENT LEADING EDGE 审中-公开

    公开(公告)号：US20190120063A1

    公开(公告)日：2019-04-25

    申请号：US15791464

    申请日：2017-10-24

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Carey Clum ,  Timothy J. Jennings

    IPC: F01D5/18 ,  F01D5/14

    CPC classification number: F01D5/186 ,  F01D5/141 ,  F01D5/187 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/201 ,  F05D2260/202

    Abstract: Airfoils bodies having a first end, a second end, a leading edge, and a trailing edge with a leading edge channel having a first channel wall and a second channel wall that join at a channel base to define the leading edge channel. The leading edge channel extends in a radial direction along the leading edge. A first leading edge impingement cavity is located proximate the leading edge and the first channel wall defines a portion of the first leading edge impingement cavity and a second leading edge impingement cavity with the second channel wall forming a portion of the second leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled such that air flowing from the first leading edge impingement cavity and through the first leading edge impingement hole impinges upon a portion of the second channel wall.

    AIRFOIL HAVING INTERNAL HYBRID COOLING CAVITIES
    65.
    发明申请
    AIRFOIL HAVING INTERNAL HYBRID COOLING CAVITIES 审中-公开

    公开(公告)号：US20190101008A1

    公开(公告)日：2019-04-04

    申请号：US15723486

    申请日：2017-10-03

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Carey Clum ,  Timothy J. Jennings

    IPC: F01D5/18

    Abstract: Airfoil bodies having a first core cavity and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the first and second core cavities. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface. At least one circuit exit is located in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall.

    AIRFOIL HAVING INTERNAL HYBRID COOLING CAVITIES
    66.
    发明申请
    AIRFOIL HAVING INTERNAL HYBRID COOLING CAVITIES 审中-公开

    公开(公告)号：US20190101007A1

    公开(公告)日：2019-04-04

    申请号：US15723473

    申请日：2017-10-03

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Carey Clum ,  Timothy J. Jennings

    IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  B22C9/10 ,  B22C9/24

    Abstract: Airfoils bodies having a first core cavity and a second core cavity located within the airfoil body that is adjacent the first core cavity. The second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface and a central ridge extends into the second core cavity from at least one of the first cavity wall and the second wall and divides the second core cavity into a two-vortex chamber.

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