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    Airfoil having improved leading edge cooling scheme and damage resistance
    41.
    发明授权
    Airfoil having improved leading edge cooling scheme and damage resistance 有权

    公开(公告)号：US10907479B2

    公开(公告)日：2021-02-02

    申请号：US15972429

    申请日：2018-05-07

    Applicant: United Technologies Corporation

    Inventor： Timothy J. Jennings ,  Tracy A. Propheter-Hinckley ,  Kyle C. Lana

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

    Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a leading edge and a trailing edge in an axial direction, between a pressure side and a suction side in a circumferential direction, and between a root and a tip in a radial direction, a first transitioning leading edge cavity located proximate the leading edge proximate the root of the airfoil body and transitioning axially toward the trailing edge as the first transitioning leading edge cavity extends radially toward the tip, and a second transitioning leading edge cavity located aft of the first transitioning leading edge cavity proximate the root of the airfoil body and transitioning axially toward the leading edge as the second transitioning leading edge cavity extends radially toward the tip. The second transitioning leading edge cavity includes an impingement sub-cavity and a film sub-cavity along the leading edge and proximate the tip.

    Cooling arrangement with purge partition
    42.
    发明授权
    Cooling arrangement with purge partition 有权

    公开(公告)号：US10801334B2

    公开(公告)日：2020-10-13

    申请号：US16129070

    申请日：2018-09-12

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo ,  Timothy J. Jennings

    IPC: F01D5/18 ,  F01D5/20

    Abstract: An airfoil includes an airfoil section that extends in a radial direction from a platform to a tip, and extends in a thickness direction between a pressure side and a suction side that meet together at both a leading edge and a trailing edge. A purge partition radially divides the airfoil section. A perimeter of the purge partition follows along external walls of the airfoil section. The tip defines a tip pocket that extends radially inwardly from the tip to a floor. The airfoil section includes at least one internal cooling circuit and a purge cavity opposed to the at least one internal cooling circuit along the purge partition, with the purge partition bounded by the floor. The purge partition defines a first set of apertures that fluidly couple the at least one internal cooling circuit and the purge partition. A method of cooling a gas turbine engine component is also disclosed.

    Airfoil having internal hybrid cooling cavities
    43.
    发明授权
    Airfoil having internal hybrid cooling cavities 有权

    公开(公告)号：US10704398B2

    公开(公告)日：2020-07-07

    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: F01D5/08 ,  F01D5/18 ,  B22C13/10 ,  F01D9/06 ,  B22C9/24 ,  B22C9/10 ,  B22C9/22

    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 IMPROVED LEADING EDGE COOLING SCHEME AND DAMAGE RESISTANCE
    44.
    发明申请
    AIRFOIL HAVING IMPROVED LEADING EDGE COOLING SCHEME AND DAMAGE RESISTANCE 审中-公开

    公开(公告)号：US20190338649A1

    公开(公告)日：2019-11-07

    申请号：US15972637

    申请日：2018-05-07

    Applicant: United Technologies Corporation

    Inventor： Timothy J. Jennings ,  Tracy A. Propheter-Hinckley ,  Kyle C. Lana

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

    Abstract: Airfoils for gas turbine engines are provided. The airfoils include a body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction. A first transitioning leading edge cavity is located adjacent one of the sides proximate the root of the body and transitions axially toward the leading edge as the first transitioning leading edge cavity extends radially toward the tip. A second transitioning leading edge cavity is adjacent the other side and adjacent the leading edge proximate the root of the body and transitions axially toward the trailing edge as the second transitioning leading edge cavity extends radially toward the tip. A portion of the second transitioning leading edge cavity shields a portion of the first transitioning leading edge cavity proximate the root of the body.

    CORIOLIS OPTIMIZED U-CHANNEL WITH PLATFORM CORE
    45.
    发明申请
    CORIOLIS OPTIMIZED U-CHANNEL WITH PLATFORM CORE 审中-公开

    公开(公告)号：US20190338647A1

    公开(公告)日：2019-11-07

    申请号：US15968043

    申请日：2018-05-01

    Applicant: United Technologies Corporation

    Inventor： Timothy J. Jennings ,  Carey Clum

    IPC: F01D5/18

    Abstract: A gas turbine engine component includes an airfoil that has 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. The second passage is configured to receive cooling air from the first passage near the tip. A platform passage is arranged in the platform and is configured to purge the cooling air from the second passage near the trailing edge.

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