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    GAS TURBINE ENGINE FLOWPATH COMPONENT INCLUDING VECTORED COOLING FLOW HOLES
    11.
    发明申请
    GAS TURBINE ENGINE FLOWPATH COMPONENT INCLUDING VECTORED COOLING FLOW HOLES 有权

    公开(公告)号：US20210172335A1

    公开(公告)日：2021-06-10

    申请号：US16702887

    申请日：2019-12-04

    Applicant: United Technologies Corporation

    Inventor： Ky H. Vu ,  Brian R. Pelletier

    IPC: F01D25/12 ,  F01D11/24

    Abstract: A gas turbine engine includes a primary flowpath connecting a compressor section, a combustor section and a turbine section. The turbine section includes a stage vane having a radially outward platform and a vane extending into the primary flowpath. The platform includes a cooling plenum. At least one retaining feature extends radially outward from the platform. At least one vectored cooling hole is disposed in the retaining feature and is configured to direct cooling air from the plenum to an adjacent gaspath component.

    SERPENTINE TURN COVER FOR GAS TURBINE STATOR VANE ASSEMBLY
    12.
    发明申请
    SERPENTINE TURN COVER FOR GAS TURBINE STATOR VANE ASSEMBLY 审中-公开

    公开(公告)号：US20200088038A1

    公开(公告)日：2020-03-19

    申请号：US16159149

    申请日：2018-10-12

    Applicant: United Technologies Corporation

    Inventor： Ky H. Vu ,  Dominic J. Mongillo

    IPC: F01D5/08 ,  F01D5/14 ,  F01D5/18

    Abstract: A stator vane assembly including an inner diameter platform. The assembly also includes an outer diameter platform defining an air inlet orifice extending radially therethrough. Further included is an airfoil extending between the inner diameter platform and the outer diameter platform, the airfoil having a hollow portion therein defining a serpentine cooling airflow path fluidly coupled to the air inlet orifice. Yet further included is a collar extending radially outwardly from the outer diameter platform and positioned adjacent the air inlet orifice, the collar extending to a non-uniform radial distance. The assembly also includes a turn cover operatively coupled to the collar.

    GAS TURBINE ENGINE COOLING COMPONENT
    13.
    发明申请
    GAS TURBINE ENGINE COOLING COMPONENT 审中-公开

    公开(公告)号：US20190170014A1

    公开(公告)日：2019-06-06

    申请号：US15832925

    申请日：2017-12-06

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Adam P. Generale ,  Ky H. Vu

    IPC: F01D25/12 ,  F01D9/04

    Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn.

    GAS TURBINE ENGINE COOLING COMPONENT
    14.
    发明申请
    GAS TURBINE ENGINE COOLING COMPONENT 审中-公开

    公开(公告)号：US20190170002A1

    公开(公告)日：2019-06-06

    申请号：US15832948

    申请日：2017-12-06

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Adam P. Generale ,  Ky H. Vu

    IPC: F01D9/02 ,  F01D9/04 ,  F02C3/04 ,  F02C7/141

    Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes an internal cavity that has an inlet on the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge is at least partially aligned with the inlet.

    Serpentine turn cover for gas turbine stator vane assembly
    15.
    发明授权
    Serpentine turn cover for gas turbine stator vane assembly 有权

    公开(公告)号：US10968746B2

    公开(公告)日：2021-04-06

    申请号：US16159149

    申请日：2018-10-12

    Applicant: United Technologies Corporation

    Inventor： Ky H. Vu ,  Dominic J. Mongillo

    IPC: F01D5/18 ,  F01D5/08 ,  F01D5/14

    Abstract: A stator vane assembly including an inner diameter platform. The assembly also includes an outer diameter platform defining an air inlet orifice extending radially therethrough. Further included is an airfoil extending between the inner diameter platform and the outer diameter platform, the airfoil having a hollow portion therein defining a serpentine cooling airflow path fluidly coupled to the air inlet orifice. Yet further included is a collar extending radially outwardly from the outer diameter platform and positioned adjacent the air inlet orifice, the collar extending to a non-uniform radial distance. The assembly also includes a turn cover operatively coupled to the collar.

    Gas turbine engine airfoil platform edge geometry
    17.
    发明授权
    Gas turbine engine airfoil platform edge geometry 有权

    公开(公告)号：US10047617B2

    公开(公告)日：2018-08-14

    申请号：US14780573

    申请日：2014-04-07

    Applicant: United Technologies Corporation

    Inventor： Ky H. Vu ,  Lisa P. O'Neill ,  Takao Fukuda ,  Gerald M. Mace, Jr. ,  Andy Turko ,  Andrew P. Boursy ,  Lynn M. Boy

    IPC: F01D9/04 ,  F01D5/14

    Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.

    TOLERANCE RESISTANCE COVERPLATES
    19.
    发明申请
    TOLERANCE RESISTANCE COVERPLATES 有权
    耐受性覆盖

    公开(公告)号：US20160265372A1

    公开(公告)日：2016-09-15

    申请号：US14641470

    申请日：2015-03-09

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Ky H. Vu ,  Jeffrey J. DeGray ,  Ryan Alan Waite ,  Gina Cavallo ,  Thomas P. Dziuba

    IPC: F01D9/04 ,  F01D5/02 ,  F04D29/32 ,  F01D25/12

    CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/186 ,  F01D5/189 ,  F01D9/065 ,  F01D25/12 ,  F04D29/321 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/642 ,  F05D2240/126 ,  F05D2240/80 ,  F05D2260/20 ,  F05D2260/30 ,  Y02T50/676

    Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.

    Abstract translation: 燃气涡轮发动机部件组件包括相对于发动机中心轴线与第一部件周向间隔开的第一部件和第二部件。 第一挡板与第一部件相关联。 第二挡板与第二部件相关联。 第一和第二挡板中的每一个包括至少一个径向挡板。 在第一和第二挡板之间形成间隙以限定冷却空气入口。 第一盖板与第一挡板相关联以覆盖间隙的第一部分。 第二盖板与第二挡板相关联以覆盖间隙的第二部分。 第一和第二盖板彼此分开，并且包括至少一个盖板径向突片，其与相关联的至少一个挡板径向突片配合，以防止第一和第二挡板与第一和第二盖板之间的泄漏间隙。

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