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    Turbine blade tip dirt removal feature
    55.
    发明授权
    Turbine blade tip dirt removal feature 有权

    公开(公告)号：US11274559B2

    公开(公告)日：2022-03-15

    申请号：US16743435

    申请日：2020-01-15

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  F02C7/30

    Abstract: A gaspath component for a gas turbine engine includes a platform. A body extends outward from the platform and includes at least one internal cooling passage. The internal cooling passage includes at least one particulate redirection feature defined at an end of the body opposite the platform. The at least one particulate redirection feature includes a first face oblique to and facing an expected flow of fluid through the internal cooling passage and defines at least one corresponding opening.

    Airfoils and core assemblies for gas turbine engines and methods of manufacture
    56.
    发明授权
    Airfoils and core assemblies for gas turbine engines and methods of manufacture 有权

    公开(公告)号：US11053803B2

    公开(公告)日：2021-07-06

    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: F01D9/06 ,  F01D25/08 ,  F04D29/64 ,  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.

    Airfoil having improved leading edge cooling scheme and damage resistance
    57.
    发明授权
    Airfoil having improved leading edge cooling scheme and damage resistance 有权

    公开(公告)号：US10941663B2

    公开(公告)日：2021-03-09

    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
    58.
    发明授权
    Coriolis optimized u-channel with platform core 有权

    公开(公告)号：US10890074B2

    公开(公告)日：2021-01-12

    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.

    AIRFOIL HAVING INTERNAL HYBRID COOLING CAVITIES
    59.
    发明申请
    AIRFOIL HAVING INTERNAL HYBRID COOLING CAVITIES 审中-公开

    公开(公告)号：US20200291791A1

    公开(公告)日：2020-09-17

    申请号：US16811249

    申请日：2020-03-06

    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 ,  F01D9/06

    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.

    AIRFOIL HAVING DEAD-END TIP FLAG CAVITY
    60.
    发明申请
    AIRFOIL HAVING DEAD-END TIP FLAG CAVITY 审中-公开

    公开(公告)号：US20200256196A1

    公开(公告)日：2020-08-13

    申请号：US16745930

    申请日：2020-01-17

    Applicant: United Technologies Corporation

    Inventor： David A. Niezelski ,  Timothy J. Jennings ,  Bret M. Teller ,  John McBrien ,  Thomas N. Slavens

    IPC: F01D5/18 ,  F01D25/12

    Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.

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