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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。

    Rotor assembly with active damping for gas turbine engines
    38.
    发明授权
    Rotor assembly with active damping for gas turbine engines 有权

    公开(公告)号：US11136888B2

    公开(公告)日：2021-10-05

    申请号：US16163690

    申请日：2018-10-18

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  James Glaspey ,  David A. Welch

    IPC: F01D5/14 ,  F01D5/16 ,  F01D5/02

    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. The airfoil section defines a pressure side and a suction side separated in a thickness direction, and the airfoil section includes a metallic sheath that defines an internal cavity receiving a composite core. The root section defines at least one bore dimensioned to receive a retention pin. At least one damping element is received in the internal cavity and that selectively causes the airfoil section to stiffen.

    Link for aircraft component mounting
    39.
    发明授权
    Link for aircraft component mounting 有权

    公开(公告)号：US11066178B2

    公开(公告)日：2021-07-20

    申请号：US14842907

    申请日：2015-09-02

    Applicant: United Technologies Corporation

    Inventor： Jason Husband

    IPC: B64D27/26 ,  B64D27/12 ,  B64D27/14

    Abstract: A gas turbine engine mount for an aircraft wing including a link body having a first joint, a second joint and a linking structure connecting the first joint to the second joint. The linking structure includes at least a flexing portion and an elastic portion. The flexing portion is configured to flex during a load outside of an expected load window.

    GEARED ARCHITECTURE FOR GAS TURBINE ENGINE
    40.
    发明申请
    GEARED ARCHITECTURE FOR GAS TURBINE ENGINE 有权

    公开(公告)号：US20210148287A1

    公开(公告)日：2021-05-20

    申请号：US16689690

    申请日：2019-11-20

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  William G. Sheridan

    IPC: F02C7/36 ,  F16H57/00 ,  F16H57/08

    Abstract: A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a geared architecture. A flexible support supports the geared architecture relative to an engine static structure. A deflection limiter includes at least one of an axially extending branch or a radially extending branch. A flexible output shaft is in driving engagement with the fan section and driven by the geared architecture. A speed change mechanism for a gas turbine engine is also disclosed.

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