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    Flexible support structure for a geared architecture gas turbine engine
    33.
    发明授权
    Flexible support structure for a geared architecture gas turbine engine 有权
    适用于齿轮架构燃气涡轮发动机的柔性支撑结构

    公开(公告)号：US09239012B2

    公开(公告)日：2016-01-19

    申请号：US14604811

    申请日：2015-01-26

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Jason Husband

    IPC: F01D25/16 ,  F02C7/32 ,  F02C7/36

    CPC classification number: F01D25/164 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/28 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/045 ,  F04D29/053 ,  F04D29/056 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/671 ,  Y10T29/49321

    Abstract: A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机包括风扇轴和支撑风扇轴的支撑件。 支撑件限定支撑横向和支撑横向刚度中的至少一个。 齿轮系驱动风扇轴。 柔性支撑件至少部分地支撑齿轮系统，并且相对于支撑横向和支撑横向刚度中的至少一个限定柔性支撑横向和柔性支撑横向刚度中的至少一个。 相对于支撑横向和支撑横向刚度中的至少一个，齿轮系统的输入限定了输入横向刚度和输入横向刚度中的至少一个。 还公开了一种设计燃气涡轮发动机的方法。

    FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE
    37.
    发明申请
    FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE 审中-公开
    用于齿轮式建筑燃气涡轮发动机的灵活支撑结构

    公开(公告)号：US20130331223A1

    公开(公告)日：2013-12-12

    申请号：US13938466

    申请日：2013-07-10

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Jason Husband

    IPC: F16H57/028

    CPC classification number: F16H57/028 ,  F01D25/164 ,  F02C7/36 ,  F02K3/06 ,  F04D25/028 ,  F04D29/053 ,  F04D29/056 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2300/501 ,  F16H1/28

    Abstract: A geared architecture for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan shaft, a frame which supports the fan shaft, the frame defines a frame stiffness and a plurality of gears which drives the fan shaft. A flexible support defines a flexible support stiffness that is less than the frame stiffness. The plurality of gears are supported by at least one of a carrier and the flexible support and an input coupling to the plurality of gears, the input coupling defines an input coupling stiffness with respect to the frame stiffness.

    Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的齿轮架构包括风扇轴，支撑风扇轴的框架，框架限定框架刚度和驱动风扇的多个齿轮 轴。 柔性支撑件限定了小于框架刚度的柔性支撑刚度。 多个齿轮由载体和柔性支撑件中的至少一个支撑，以及与多个齿轮的输入联接，输入联接器限定相对于框架刚度的输入联接刚度。

    Pinned airfoil for gas turbine engines
    38.
    发明授权
    Pinned airfoil for gas turbine engines 有权

    公开(公告)号：US11306601B2

    公开(公告)日：2022-04-19

    申请号：US16163610

    申请日：2018-10-18

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  James Glaspey

    IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction, and the airfoil section defines a pressure side and a suction side separated in a thickness direction. The airfoil section includes a metallic sheath that receives a composite core, and the core includes first and second ligaments received in respective internal channels defined by the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction. The first and second ligaments define respective sets of bores, and the respective sets of bores are aligned to receive a common set of retention pins.

    Shear wave resistant flange assembly
    39.
    发明授权
    Shear wave resistant flange assembly 有权

    公开(公告)号：US10895170B2

    公开(公告)日：2021-01-19

    申请号：US16166737

    申请日：2018-10-22

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  Canio M. Hoffarth

    IPC: F01D25/24 ,  F16L23/028 ,  F16L23/032 ,  G01N29/04 ,  F02K1/80 ,  F02C7/20

    Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first annular case that has a first body extending from a first end portion and a second annular case that has a second body extending along a longitudinal axis from a second end portion. The first end portion has a first flange. The first flange has at least one mounting assembly. The at least one mounting assembly has a first aperture dimensioned to receive a fastener and a first ramped surface that extends axially from the first aperture. The second end portion includes at least one flange that defines a receptacle dimensioned to receive the first end portion and a second aperture dimensioned to receive the fastener and a second ramped surface. The first annular case is moveable in an axial direction relative to the longitudinal axis through an axial opening of the receptacle such that the first end portion is received in the receptacle, and is rotatable about the longitudinal axis to define an interface between the first and second ramped surfaces to interlock the first end portion in the receptacle and limit movement of the first annular case relative to the longitudinal axis. A method of assembly for a gas turbine engine is also disclosed.

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