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    Thin seal for an engine
    42.
    发明授权
    Thin seal for an engine 有权

    公开(公告)号：US10465545B2

    公开(公告)日：2019-11-05

    申请号：US15980855

    申请日：2018-05-16

    Applicant: United Technologies Corporation

    Inventor： Alan D. Cetel ,  Dilip M. Shah ,  Eric A. Hudson ,  Raymond Surace

    IPC: F01D11/00 ,  F01D25/00

    Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

    VANE COOLING STRUCTURES
    45.
    发明申请
    VANE COOLING STRUCTURES 审中-公开

    公开(公告)号：US20190107006A1

    公开(公告)日：2019-04-11

    申请号：US15727816

    申请日：2017-10-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Tracy A. Propheter-Hinckley ,  Raymond Surace

    IPC: F01D25/12 ,  F01D9/04 ,  F23R3/00 ,  F02C7/18

    Abstract: A vane platform cooling system may comprise a combustor shell and a combustor panel. A cavity may be located between the combustor shell and the combustor panel. A surface of the cavity may be angled toward the combustor shell. An orifice may be formed in a vane platform located aft of the combustor panel. A standoff located in the cavity may direct air toward the vane platform. An aperture may be formed in a surface of the vane platform. A channel formed through the vane platform may connect the orifice and aperture.

    Variable area vane arrangement for a turbine engine
    46.
    发明授权
    Variable area vane arrangement for a turbine engine 有权

    公开(公告)号：US10215048B2

    公开(公告)日：2019-02-26

    申请号：US14762302

    申请日：2013-01-21

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey ,  Raymond Surace ,  Tracy A. Propheter-Hinckley

    IPC: F01D17/16 ,  F01D5/14 ,  F01D5/18

    Abstract: An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially around the inlet and the shaft, and radially from the stator vane body.

    VARIABLE-PITCH VANE ASSEMBLY
    47.
    发明申请
    VARIABLE-PITCH VANE ASSEMBLY 审中-公开

    公开(公告)号：US20190024530A1

    公开(公告)日：2019-01-24

    申请号：US15653064

    申请日：2017-07-18

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Raymond Surace ,  Robert L. Hazzard ,  Mark Borja

    IPC: F01D17/16

    CPC classification number: F01D17/162 ,  F05D2230/60 ,  F05D2240/128 ,  F05D2260/30 ,  F05D2260/50

    Abstract: A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.

    Vane support systems
    49.
    发明授权
    Vane support systems 有权

    公开(公告)号：US10036282B2

    公开(公告)日：2018-07-31

    申请号：US14715253

    申请日：2015-05-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Loi Cheng ,  Raymond Surace

    IPC: F01D9/06 ,  F01D17/16 ,  F01D25/28 ,  F04D29/56 ,  F01D9/02 ,  F01D25/24

    CPC classification number: F01D25/28 ,  F01D9/02 ,  F01D9/065 ,  F01D17/162 ,  F01D25/24 ,  F04D29/563

    Abstract: A vane support system includes a frame and a vane. The frame has a first end configured to engage to a first platform and a second end configured to engage a second platform, so the frame can structurally support at least one of the first platform and the second platform. The first and second ends define a vane axis therebetween. The vane is mounted to the frame about the vane axis. A gas turbine engine includes a case defining a centerline axis of the engine, an inner housing and a plurality of variable vanes. The inner housing is radially inward of the case with respect to the centerline axis. At least one of the variable vanes structurally supports the case and the inner housing in response to at least one of radial, axial or tangential loads with respect to the centerline axis.

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