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    Radially diffused tip flag
    2.
    发明授权
    Radially diffused tip flag 有权

    公开(公告)号：US10815800B2

    公开(公告)日：2020-10-27

    申请号：US15368829

    申请日：2016-12-05

    Applicant: United Technologies Corporation

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

    IPC: F01D5/20 ,  F01D9/04 ,  F01D5/18

    Abstract: An airfoil includes an airfoil body having a first wall, a second wall, a third wall, a tip surface, and a rib. The first wall radially extends between a root region and a tip region and axially extends between a leading edge and a trailing edge. The second wall radially extends from the tip region towards the root region and axially extends between the leading edge and the trailing edge. The third wall radially extends between the root region and the tip region and axially extends between the leading edge and the trailing edge. The tip surface circumferentially extends between the second wall and the third wall. The rib is radially spaced apart from the tip surface and circumferentially extends between the first wall and the third wall.

    Cored airfoil platform with outlet slots
    3.
    发明授权
    Cored airfoil platform with outlet slots 有权

    公开(公告)号：US10808549B2

    公开(公告)日：2020-10-20

    申请号：US16049987

    申请日：2018-07-31

    Applicant: United Technologies Corporation

    Inventor： Benjamin F. Hagan ,  Ryan Alan Waite ,  Bryan P. Dube ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/18 ,  F01D5/14 ,  F01D9/04 ,  F01D25/12 ,  F01D9/06 ,  F01D5/22

    Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.

    Double wall turbine gas turbine engine blade cooling configuration
    4.
    发明授权
    Double wall turbine gas turbine engine blade cooling configuration 有权

    公开(公告)号：US10648345B2

    公开(公告)日：2020-05-12

    申请号：US15832467

    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 fluidly interconnects the core and skin passages. The resupply hole has a single inlet that is fluidly connected to multiple discrete outlet apertures. A centerline of the single inlet is arranged at an angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.

    Gas turbine engine components having internal cooling features
    5.
    发明授权
    Gas turbine engine components having internal cooling features 有权

    公开(公告)号：US10584596B2

    公开(公告)日：2020-03-10

    申请号：US15852400

    申请日：2017-12-22

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo, Jr. ,  Allan N. Arisi

    IPC: F01D5/18 ,  F01D25/12 ,  F23R3/00 ,  F23M5/08 ,  F01D9/06

    Abstract: Components for gas turbine engines are provided. The components include a hybrid skin core cooling cavity defined by a cold wall and a hot wall, wherein the hot wall is exposed to an exterior environment of the component, a hybrid resupply hole formed in the cold wall and fluidly connecting a cold cavity and the hybrid skin core cooling cavity, and a resupply cover located on the cold wall and within the hybrid skin core cooling cavity and positioned relative to the hybrid resupply hole to shield resupply air injected from the cold cavity into the hybrid skin core cooling cavity to minimize losses as the resupply air mixes with air flowing within the hybrid skin core cooling cavity.

    Airfoil having non-leading edge stagnation line cooling scheme
    8.
    发明授权
    Airfoil having non-leading edge stagnation line cooling scheme 有权

    公开(公告)号：US10443406B2

    公开(公告)日：2019-10-15

    申请号：US15884447

    申请日：2018-01-31

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, Jr.

    IPC: F01D5/18 ,  F01D5/14

    Abstract: Components for gas turbine engines are provided. The components include an airfoil extending between a first end and a second end and from a leading edge to a trailing edge. The airfoil has a pressure side and a suction side. The airfoil has a non-leading edge stagnation line that transitions from a location along a leading edge surface of the airfoil at the first end to a location on the airfoil on the pressure side of the airfoil at the second end. A leading edge feed cavity is located in the leading edge of the airfoil and extending between the first end and the second end of the airfoil. A stagnation impingement cavity is formed extending along a surface of the airfoil that aligns with the non-leading edge stagnation line.

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