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    AIRFOIL HAVING IMPROVED LEADING EDGE COOLING SCHEME AND DAMAGE RESISTANCE
    31.
    发明申请
    AIRFOIL HAVING IMPROVED LEADING EDGE COOLING SCHEME AND DAMAGE RESISTANCE 审中-公开

    公开(公告)号：US20190338648A1

    公开(公告)日：2019-11-07

    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.

    AIRFOILS, CORES, AND METHODS OF MANUFACTURE FOR FORMING AIRFOILS HAVING FLUIDLY CONNECTED PLATFORM COOLING CIRCUITS
    32.
    发明申请
    AIRFOILS, CORES, AND METHODS OF MANUFACTURE FOR FORMING AIRFOILS HAVING FLUIDLY CONNECTED PLATFORM COOLING CIRCUITS 审中-公开

    公开(公告)号：US20190316471A1

    公开(公告)日：2019-10-17

    申请号：US15954857

    申请日：2018-04-17

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  B22D25/02 ,  B22C9/10 ,  B22C9/24

    Abstract: Methods for manufacturing airfoils of gas turbine engines are provided. The methods include forming a main body core, the main body core including a feed cavity core portion, the main body core configured to form at least a part of an airfoil including an airfoil body, a platform, and an attachment element, forming a platform circuit core having a platform core extension, wherein the platform circuit core is configured to form a cooling circuit in the platform, wherein at least one of the feed cavity core portion and the platform core extension comprises a notch, assembling the platform circuit core to the main body core such that the platform core extension engages with the feed cavity core portion at the notch, casting an airfoil using the assembled platform circuit core and main body core, and removing a platform core extension element that is formed at the location of the notch.

    Component having a dirt tolerant passage turn
    37.
    发明授权
    Component having a dirt tolerant passage turn 有权

    公开(公告)号：US11319839B2

    公开(公告)日：2022-05-03

    申请号：US16722226

    申请日：2019-12-20

    Applicant: United Technologies Corporation

    Inventor： Robin Prenter ,  Timothy J. Jennings ,  Carey Clum

    IPC: F01D25/32 ,  F01D5/18 ,  F01D9/06

    Abstract: A component includes a component body. The component further includes a first passage disposed in the component body. The first passage includes a first end and a second end opposite the first end. The component further includes a second passage. The second passage extends from the second end of the first passage. The second passage includes a turn. The component further includes a third passage. The third passage extends from the second end of the first passage. The component further includes a first projection extending from a passage surface of the component body within the first passage. The first projection is disposed between the first and the second end of the first passage and is configured to direct debris transiting the first passage away from the second passage and into the third passage.

    AIRFOILS AND CORE ASSEMBLIES FOR GAS TURBINE ENGINES AND METHODS OF MANUFACTURE
    40.
    发明申请
    AIRFOILS AND CORE ASSEMBLIES FOR GAS TURBINE ENGINES AND METHODS OF MANUFACTURE 有权

    公开(公告)号：US20210062658A1

    公开(公告)日：2021-03-04

    申请号：US16593076

    申请日：2019-10-04

    Applicant: United Technologies Corporation

    Inventor： Emma J. Place ,  Jeremy B. Fredette ,  Timothy J. Jennings

    IPC: F01D5/18

    Abstract: Methods for forming airfoil, cores for forming airfoil, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly, the core assembly comprising at least one core structure having a radially extending purge slot protrusion extending from a portion of the at least one core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket. The radially extending protrusion has a radial height that is equal to or less than five times a width thereof.

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