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    AIRFOIL HAVING INTERNAL HYBRID COOLING CAVITIES
    21.
    发明申请
    AIRFOIL HAVING INTERNAL HYBRID COOLING CAVITIES 审中-公开

    公开(公告)号：US20190101006A1

    公开(公告)日：2019-04-04

    申请号：US15723446

    申请日：2017-10-03

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18

    Abstract: Airfoil bodies having a first core cavity and a second core cavity adjacent each other, with the second core cavity defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall. 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 with a first impingement flow flowing from the first core cavity through the at least one first cavity impingement hole to impinge upon the first exterior wall and forms a first high momentum jet of impingement air thereon.

    AIRFOIL HAVING FLUIDLY CONNECTED HYBRID CAVITIES
    22.
    发明申请
    AIRFOIL HAVING FLUIDLY CONNECTED HYBRID CAVITIES 审中-公开

    公开(公告)号：US20190101005A1

    公开(公告)日：2019-04-04

    申请号：US15723461

    申请日：2017-10-03

    Applicant: United Technologies Corporation

    Inventor： Carey Clum ,  Timothy J. Jennings

    IPC: F01D5/18 ,  F01D9/06

    CPC classification number: F01D5/186 ,  B22C9/10 ,  B22C9/22 ,  B22C9/24 ,  B22C13/10 ,  F01D5/187 ,  F01D9/065 ,  F05D2230/211 ,  F05D2260/202 ,  F05D2260/205

    Abstract: Airfoils having a leading edge and a trailing edge, with a plurality of cavities therein including a leading edge hybrid cavity extending in a radial direction between a first end and a second end of the airfoil body along the leading edge. An airfoil side hybrid cavity is located toward the trailing edge relative to the leading edge hybrid cavity and positioned adjacent a side wall of the airfoil body. The airfoil side hybrid cavity extends in a radial direction between the first end and the second end and a divider rib extends radially between the first end and the second end along the side wall of the airfoil between the airfoil side hybrid cavity and the leading edge hybrid cavity. At least one first cross-over hole is formed within the divider rib to fluidly connect the airfoil side hybrid cavity to the leading edge hybrid cavity.

    TURBINE BLADE TIP DIRT REMOVAL FEATURE
    24.
    发明申请
    TURBINE BLADE TIP DIRT REMOVAL FEATURE 有权

    公开(公告)号：US20210215063A1

    公开(公告)日：2021-07-15

    申请号：US16743435

    申请日：2020-01-15

    Applicant: United Technologies Corporation

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

    IPC: F01D25/00 ,  F02C7/12 ,  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.

    COMPONENT HAVING A DIRT TOLERANT PASSAGE TURN
    25.
    发明申请
    COMPONENT HAVING A DIRT TOLERANT PASSAGE TURN 有权

    公开(公告)号：US20210189911A1

    公开(公告)日：2021-06-24

    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

    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.

    Airfoil having improved cooling scheme
    28.
    发明授权
    Airfoil having improved cooling scheme 有权

    公开(公告)号：US10753210B2

    公开(公告)日：2020-08-25

    申请号：US15968865

    申请日：2018-05-02

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  F01D5/14

    Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil 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 shielding sidewall cavity located adjacent one of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, a second shielding sidewall cavity located adjacent the other of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, and a shielded sidewall cavity located between the first shielding sidewall cavity and the second shielding sidewall cavity, wherein the shielded sidewall cavity is not adjacent either of the pressure or suction sides proximate the root and transitions to be proximate at least one of the pressure and suction sides proximate the tip.

    Blade with inlet orifice on aft face of root
    29.
    发明授权
    Blade with inlet orifice on aft face of root 有权

    公开(公告)号：US10731475B2

    公开(公告)日：2020-08-04

    申请号：US15958056

    申请日：2018-04-20

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  F01D5/30

    Abstract: A gas turbine engine article includes a blade that has a platform, an airfoil, and a root. The platform has a gaspath side and a non-gaspath side. The airfoil extends radially from the gaspath side and defines a leading end and a trailing end. The root is configured to secure the blade. The root extends radially from the non-gaspath side of the platform. The root defines forward and aft axial faces, and a radial channel in the aft axial face. The radial channel leads to an inlet orifice in the root. A cooling passage extends in the root from the inlet orifice.

    AIRFOIL HAVING IMPROVED COOLING SCHEME
    30.
    发明申请
    AIRFOIL HAVING IMPROVED COOLING SCHEME 审中-公开

    公开(公告)号：US20190338652A1

    公开(公告)日：2019-11-07

    申请号：US15968865

    申请日：2018-05-02

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18

    Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil 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 shielding sidewall cavity located adjacent one of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, a second shielding sidewall cavity located adjacent the other of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, and a shielded sidewall cavity located between the first shielding sidewall cavity and the second shielding sidewall cavity, wherein the shielded sidewall cavity is not adjacent either of the pressure or suction sides proximate the root and transitions to be proximate at least one of the pressure and suction sides proximate the tip.

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