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    Gas turbine engine front center body architecture
    61.
    发明授权
    Gas turbine engine front center body architecture 有权

    公开(公告)号：US10605167B2

    公开(公告)日：2020-03-31

    申请号：US13860774

    申请日：2013-04-11

    Applicant: United Technologies Corporation

    Inventor： Todd A. Davis ,  Brian P. Cigal

    IPC: F02C7/06 ,  F01D25/28 ,  F01D25/16 ,  F01D15/12 ,  F02K3/06 ,  F02C7/20 ,  F02C7/36

    Abstract: Disclosed is a gas turbine engine configured to include a propulsor section having a fan drive geared architecture. The gas turbine engine includes a gas generator section that includes a compressor section having a first rotor rotationally mounted to a first spool. The engine further includes a bearing package adapted for rotationally supporting the first spool. The bearing package is configured for supporting the first rotor during at least one of (1) a period prior to installation of the fan drive geared architecture into the engine and (2) a period after removal of the fan drive geared architecture from the engine.

    BEARING SUPPORT ASSEMBLY
    62.
    发明申请
    BEARING SUPPORT ASSEMBLY 审中-公开

    公开(公告)号：US20190293293A1

    公开(公告)日：2019-09-26

    申请号：US15927285

    申请日：2018-03-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Todd A. Davis ,  Christopher M. Valva ,  Daniel Rosen ,  Armando Amador ,  Aneil S. Hegde ,  Ramin M. Rafatpanah

    IPC: F23R3/60 ,  F23R3/00 ,  F02C7/28 ,  F01D25/16

    Abstract: A bearing support may include a central shaft, a flange shaft, and a tube boss. The central shaft may include a central longitudinal axis extending between a first end and a second end of the bearing support. The flange shaft may extend radially outward of the central shaft at an acute angle, relative to the central longitudinal axis from the first end to the second end, and the flange shaft may include a rim defining an aperture. The tube boss extends from the central shaft radially outward through the aperture, according to various embodiments. An annular channel may be between the rim and the tube boss.

    Aircraft engine case shock mount
    63.
    发明授权
    Aircraft engine case shock mount 有权

    公开(公告)号：US10293950B2

    公开(公告)日：2019-05-21

    申请号：US14951674

    申请日：2015-11-25

    Applicant: United Technologies Corporation

    Inventor： Mark Ronski ,  Todd A. Davis ,  Ernest Boratgis

    IPC: F02C7/32 ,  B64D27/26 ,  F16F9/10 ,  F02C7/36 ,  F16F9/19

    Abstract: The present disclosure relates to shock mounts for turbine engine components. A shock mount may be used to mount an accessory gearbox to an engine case. The shock mount may allow free thermal expansion, while providing damping and stiffness in response to vibrations. The shock mount may include a cylinder filled with fluid, and a piston telescopically moveable within the cylinder. The piston may be coupled to an orifice plate. The orifice plate may include orifices through which the fluid may flow in response to compression or extension of the shock mount. The interaction of the fluid and the orifice plate may resist rapid compression or extension of the shock mount while allowing relatively slow compression or extension of the shock mount.

    Phonic seal seat
    64.
    发明授权
    Phonic seal seat 有权

    公开(公告)号：US10174629B1

    公开(公告)日：2019-01-08

    申请号：US15700922

    申请日：2017-09-11

    Applicant: United Technologies Corporation

    Inventor： Christopher M. Valva ,  Todd A. Davis ,  Joseph D. Walker

    IPC: F01D25/16 ,  F02C7/06 ,  F16C37/00 ,  F16C33/66 ,  F01D11/00 ,  F16J15/34

    Abstract: A sealing assembly for a bearing compartment of a gas turbine engine includes a shaft and a seal plate mounted to the shaft. The shaft is configured to rotate about a longitudinal axis of the gas turbine engine. The seal plate includes an annular body, scoop, sealing surface, plurality of teeth, and channel. The scoop is connected to and extends radially from the annular body. The scoop defines a lip and an annulus surrounding the shaft and is disposed on a first axial end of the annular body. The sealing surface is disposed on a second axial end of the annular body opposite from the scoop. The plurality of teeth are disposed into and along an outer perimeter of a portion of the annular body. The channel extends through a portion of the annular body and is fluidly connected to the scoop and to the sealing surface.

    INTERSHAFT COMPARTMENT BUFFERING ARRANGEMENT
    65.
    发明申请
    INTERSHAFT COMPARTMENT BUFFERING ARRANGEMENT 审中-公开

    公开(公告)号：US20180306044A1

    公开(公告)日：2018-10-25

    申请号：US15496399

    申请日：2017-04-25

    Applicant: United Technologies Corporation

    Inventor： Russell B. Witlicki ,  Todd A. Davis ,  Francis Parnin

    IPC: F01D11/00 ,  F01D25/16 ,  F04D27/00 ,  F04D29/054

    Abstract: Aspects of the disclosure are directed to a system associated with an engine having a central longitudinal axis, including a first shaft axially extending along the central longitudinal axis, a second shaft coaxial with the first shaft, a first air seal that seals between the first shaft and the second shaft at a first axial location, a second air seal that seals between the first shaft and the second shaft at a second axial location, a first oil seal that provides intershaft sealing between the first shaft and the second shaft at a third axial location, a second oil seal that provides intershaft sealing between the first shaft and the second shaft at a fourth axial location axially adjacent to the third axial location, and a high pressure compressor that provides pressurized air to a first radially exterior side of the first air seal and to a second radially exterior side the second air seal.

    OIL TANK MOUNT ARRANGEMENT ON A GEARED TURBOFAN ENGINE
    66.
    发明申请
    OIL TANK MOUNT ARRANGEMENT ON A GEARED TURBOFAN ENGINE 审中-公开

    公开(公告)号：US20180245484A1

    公开(公告)日：2018-08-30

    申请号：US15958527

    申请日：2018-04-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Todd A. Davis ,  Mark Ronski ,  David Allen Stachowiak

    IPC: F01D25/28 ,  F16M13/02 ,  F01D25/18 ,  F02C7/32 ,  F02C7/06

    Abstract: An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the oil tank in one degree of freedom, a second mount may fix the oil tank in two degrees of freedom, and a third mount may fix the oil tank in three degrees of freedom. This allows limited rotational and expansion movement while coupling the oil tank to the engine. The mount attachments may be embodied in rubber, with pins, or with spherical joints in a variety of configurations. Frangible pins may be used to absorb energy but still retain the oil tank in the event of a high energy event.

    GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE
    70.
    发明申请
    GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE 审中-公开
    气体涡轮发动机前中心体系结构

    公开(公告)号：US20140079546A1

    公开(公告)日：2014-03-20

    申请号：US13860774

    申请日：2013-04-11

    Applicant: United Technologies Corporation

    Inventor： Todd A. Davis ,  Brian P. Cigal

    IPC: F02C7/06

    CPC classification number: F02C7/06 ,  F01D15/12 ,  F01D25/162 ,  F01D25/285 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2230/80 ,  Y02T50/671 ,  Y10T29/49245

    Abstract: Disclosed is a gas turbine engine configured to include a propulsor section having a fan drive geared architecture. The gas turbine engine includes a gas generator section that includes a compressor section having a first rotor rotationally mounted to a first spool. The engine further includes a bearing package adapted for rotationally supporting the first spool. The bearing package is configured for supporting the first rotor during at least one of (1) a period prior to installation of the fan drive geared architecture into the engine and (2) a period after removal of the fan drive geared architecture from the engine.

    Abstract translation: 公开了一种燃气涡轮发动机，其构造成包括具有风扇驱动齿轮架构的推进部分。 燃气涡轮发动机包括气体发生器部分，其包括具有旋转地安装到第一线轴的第一转子的压缩机部分。 发动机还包括适于旋转地支撑第一线轴的轴承组件。 所述轴承组件被配置用于在（1）在将所述风扇驱动齿轮架构安装到所述发动机之前的期间中的至少一个中支撑所述第一转子;以及（2）从所述发动机移除所述风扇驱动齿轮架构之后的期间。

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