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    Flexible support structure for a geared architecture gas turbine engine
    54.
    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：US08814503B2

    公开(公告)日：2014-08-26

    申请号：US14164364

    申请日：2014-01-27

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Jason Husband

    IPC: F01D15/12 ,  F01D25/16

    CPC classification number: F01D25/164 ,  F01D15/12 ,  F01D25/34 ,  F02C7/36 ,  F05D2260/40311 ,  F05D2260/53 ,  Y02T50/671 ,  Y10T29/49229

    Abstract: A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines a flexible support lateral stiffness with respect to the support lateral stiffness. An input to the gear system defines an input lateral stiffness with respect to 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。 支撑件限定了支撑横向刚度。 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刚度限定柔性支撑横向刚度。 齿轮系统的输入限定了相对于支撑横向刚度的输入横向刚度。 还公开了一种设计燃气涡轮发动机的方法。

    FUNDAMENTAL GEAR SYSTEM ARCHITECTURE
    55.
    发明申请
    FUNDAMENTAL GEAR SYSTEM ARCHITECTURE 有权
    基础系统架构

    公开(公告)号：US20140020404A1

    公开(公告)日：2014-01-23

    申请号：US14034720

    申请日：2013-09-24

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan ,  Michael E. McCune ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann ,  Jason Husband

    IPC: F02C7/06

    CPC classification number: F02C7/06 ,  F01D25/18 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  Y02T50/671

    Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system.

    Abstract translation: 用于燃气涡轮发动机的风扇驱动齿轮系统包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统和齿轮系统的柔性支撑部分的安装件。 支持风扇驱动齿轮系统的润滑系统为齿轮系统提供润滑剂，并去除由齿轮系产生的热能。 润滑系统包括能量消除等于输入到齿轮系统中的能量的小于约2％的能量。

    FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE
    56.
    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：US20130331224A1

    公开(公告)日：2013-12-12

    申请号：US13938476

    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 and a frame which supports the fan shaft, the frame defines a frame stiffness. A plurality of gears drives the fan shaft. A flexible support at least partially supports the plurality of gears, the flexible support defines a flexible support stiffness that is less than the frame stiffness. 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和支撑风扇轴的框架，框架限定框架刚度。 多个齿轮驱动风扇轴。 柔性支撑件至少部分地支撑多个齿轮，柔性支撑件限定小于框架刚度的柔性支撑刚度。 输入耦合到多个齿轮的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
    57.
    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
    58.
    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
    59.
    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.

    GEARED ARCHITECTURE FOR GAS TURBINE ENGINE
    60.
    发明申请
    GEARED ARCHITECTURE FOR GAS TURBINE ENGINE 有权

    公开(公告)号：US20210148286A1

    公开(公告)日：2021-05-20

    申请号：US16689656

    申请日：2019-11-20

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan ,  Jason Husband

    IPC: F02C7/36 ,  F02C7/06

    Abstract: A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a planetary gear system. The planetary gear system includes a plurality of planet gears surrounding a sun gear. A carrier supports the plurality of planet gears and includes a first carrier bearing flange. A ring gear surrounds the plurality of planet gears and includes a ring gear bearing flange. At least one ring gear carrier bearing engages the carrier bearing flange and the ring gear bearing flange. A speed change mechanism for a gas turbine is also disclosed.

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