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    Airfoil having non-leading edge stagnation line cooling scheme
    162.
    发明授权
    Airfoil having non-leading edge stagnation line cooling scheme 有权

    公开(公告)号：US10443406B2

    公开(公告)日：2019-10-15

    申请号：US15884447

    申请日：2018-01-31

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/18 ,  F01D5/14

    Abstract: Components for gas turbine engines are provided. The components include an airfoil extending between a first end and a second end and from a leading edge to a trailing edge. The airfoil has a pressure side and a suction side. The airfoil has a non-leading edge stagnation line that transitions from a location along a leading edge surface of the airfoil at the first end to a location on the airfoil on the pressure side of the airfoil at the second end. A leading edge feed cavity is located in the leading edge of the airfoil and extending between the first end and the second end of the airfoil. A stagnation impingement cavity is formed extending along a surface of the airfoil that aligns with the non-leading edge stagnation line.

    Article having ceramic wall with flow turbulators
    163.
    发明授权
    Article having ceramic wall with flow turbulators 有权

    公开(公告)号：US10436062B2

    公开(公告)日：2019-10-08

    申请号：US15354083

    申请日：2016-11-17

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley

    IPC: B32B18/00 ,  F01D5/28 ,  F01D25/00 ,  F01D9/04 ,  F02C3/04 ,  C04B35/80

    Abstract: An article includes a ceramic wall that defines at least a side of a passage. The ceramic wall includes a flow turbulator that projects into the passage. The flow turbulator is formed of ceramic matrix composite. A gas turbine engine is also disclosed. The gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. At least one of the turbine section or the compressor section including the article.

    AIRFOIL HAVING IMPINGEMENT LEADING EDGE
    168.
    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
    169.
    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
    170.
    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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