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    Double wall turbine gas turbine engine vane platform cooling configuration with main core resupply
    31.
    发明授权
    Double wall turbine gas turbine engine vane platform cooling configuration with main core resupply 有权

    公开(公告)号：US10648343B2

    公开(公告)日：2020-05-12

    申请号：US15886054

    申请日：2018-02-01

    Applicant: United Technologies Corporation

    Inventor： Nicholas M. LoRicco ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/18 ,  F01D9/06 ,  F01D9/04 ,  F01D25/12 ,  F02C3/04

    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. An airfoil skin cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The airfoil skin cooling passage extends to a platform skin cooling passage arranged in the platform. A resupply hole fluidly connects the main-body core cooling passage and at least one of the airfoil skin cooling passage and the platform skin cooling passage.

    Aft flowing serpentine cavities and cores for airfoils of gas turbine engines
    32.
    发明授权
    Aft flowing serpentine cavities and cores for airfoils of gas turbine engines 有权

    公开(公告)号：US10563521B2

    公开(公告)日：2020-02-18

    申请号：US15368746

    申请日：2016-12-05

    Applicant: United Technologies Corporation

    Inventor： Carey Clum ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/18 ,  F01D5/14 ,  F01D5/20

    Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom having an aft flowing serpentine hybrid skin core positioned relative to a plurality of core bodies and configured to define at least one serpentine cavity within the manufactured airfoil. The aft flowing serpentine hybrid skin core extends from a root region toward a tip region in a radial direction of the manufactured airfoil and the plurality of core bodies are positioned about the aft flowing serpentine hybrid skin core to form a shielding structure to thermally shield the aft flowing serpentine hybrid skin core in the manufactured airfoil.

    Double wall turbine gas turbine engine blade cooling configuration
    33.
    发明授权
    Double wall turbine gas turbine engine blade cooling configuration 有权

    公开(公告)号：US10508555B2

    公开(公告)日：2019-12-17

    申请号：US15832407

    申请日：2017-12-05

    Applicant: United Technologies Corporation

    Inventor： Christopher Whitfield ,  Carey Clum ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/18 ,  F02C9/18 ,  F02C3/04

    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole cluster includes first and second resupply holes that each fluidly interconnect the core and skin passages. The first and second resupply holes intersect one another and terminate in an exit at the skin passage.

    Gas turbine engine airfoil with large thickness properties
    34.
    发明授权
    Gas turbine engine airfoil with large thickness properties 有权

    公开(公告)号：US10508549B2

    公开(公告)日：2019-12-17

    申请号：US14728514

    申请日：2015-06-02

    Applicant: United Technologies Corporation

    Inventor： Wolfgang Balzer ,  Thomas J. Praisner ,  Atul Kohil ,  Mark F. Zelesky ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/14 ,  F01D5/02 ,  F01D5/18

    Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.

    Seal arrangement for turbine engine component
    35.
    发明授权
    Seal arrangement for turbine engine component 有权

    公开(公告)号：US10458264B2

    公开(公告)日：2019-10-29

    申请号：US14704278

    申请日：2015-05-05

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo, Jr. ,  Brandon W. Spangler ,  Lane Thornton

    IPC: F01D11/00 ,  F01D25/24

    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.

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