中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

101 records (took 0.027 seconds)

    LINK FOR AIRCRAFT COMPONENT MOUNTING
    93.
    发明申请
    LINK FOR AIRCRAFT COMPONENT MOUNTING 审中-公开
    关于航空器组件安装的链接

    公开(公告)号：US20170057651A1

    公开(公告)日：2017-03-02

    申请号：US14842907

    申请日：2015-09-02

    Applicant: United Technologies Corporation

    Inventor： Jason Husband

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

    CPC classification number: B64D27/26 ,  B64D27/12 ,  B64D27/14 ,  B64D2027/262 ,  B64D2027/266

    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.

    Abstract translation: 一种用于飞行器机翼的燃气涡轮发动机支架，其包括具有第一接头，第二接头和将第一接头连接到第二接头的连接结构的连接体。 连接结构至少包括弯曲部分和弹性部分。 弯曲部分构造成在预期载荷窗口外部的载荷期间弯曲。

    FBO TORQUE REDUCING FEATURE IN FAN SHAFT
    94.
    发明申请
    FBO TORQUE REDUCING FEATURE IN FAN SHAFT 有权
    FBO扭矩减少风扇风扇功能

    公开(公告)号：US20170009661A1

    公开(公告)日：2017-01-12

    申请号：US14792927

    申请日：2015-07-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jason Husband ,  Drew W. Lancaster

    IPC: F02C7/36 ,  F02C3/04

    CPC classification number: F02C7/36 ,  F01D5/02 ,  F01D21/045 ,  F02C3/04 ,  F04D29/043 ,  F04D29/053 ,  F05D2220/36

    Abstract: A fan shaft includes a first end, a second end, and an axis, the fan shaft and configured to be coupled to a gear assembly of a gas turbine engine at the first end and to a fan more proximal to the second end than the first end such that in response to being coupled, the fan shaft can transfer torque from the gear assembly to the fan. At least one axial portion of the fan shaft satisfies the relationship 0.55 ≤ T * C J * τ ≤ 0.95 , where T represents peak torque during fan blade off, C represents a distance from a centerline of the gas turbine engine to an outer fiber of the fan shaft, J represents a polar moment of inertia of the fan shaft, and τ represents yield stress in shear of the fan shaft.

    Abstract translation: 其中T表示风扇叶片关闭时的峰值扭矩，C表示从燃气涡轮发动机的中心线到风扇轴的外径的距离，J表示风扇轴的极坐标惯量，τ表示剪切中的屈服应力 的风扇轴。

    Flexible support structure for a geared architecture gas turbine engine
    95.
    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：US09523422B2

    公开(公告)日：2016-12-20

    申请号：US13938476

    申请日：2013-07-10

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Jason Husband

    IPC: F16H57/028 ,  F02C7/36 ,  F01D25/16

    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。

    FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE
    96.
    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：US20160319829A1

    公开(公告)日：2016-11-03

    申请号：US15185292

    申请日：2016-06-17

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Jason Husband

    IPC: F04D29/056 ,  F16H1/28 ,  F02K3/06 ,  F16H57/028 ,  F04D29/053 ,  F04D25/02

    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 includes a fan shaft and a frame which supports said fan shaft. The frame defines a frame stiffness. A plurality of gears drives the fan shaft and includes a gear mesh that defines a gear mesh stiffness. A stiffness of a ring gear of the plurality of gears is less than about 20% of the gear mesh stiffness. A flexible support supports the geared architecture and defines a flexible support stiffness. An input coupling to the plurality of gears defines an input coupling stiffness. The flexible support stiffness and the input coupling stiffness are each less than about 11% of the frame stiffness.

    Abstract translation: 用于燃气涡轮发动机的齿轮架构包括风扇轴和支撑所述风扇轴的框架。 框架定义框架刚度。 多个齿轮驱动风扇轴并且包括限定齿轮啮合刚度的齿轮啮合。 多个齿轮的齿圈的刚度小于齿轮啮合刚度的约20％。 灵活的支撑支持齿轮架构，并且定义了柔性支撑刚度。 耦合到多个齿轮的输入限定输入耦合刚度。 柔性支撑刚度和输入耦合刚度均小于框架刚度的约11％。

    Flexible Support Structure For A Geared Architecture Gas Turbine Engine
    99.
    发明申请
    Flexible Support Structure For A Geared Architecture Gas Turbine Engine 有权
    用于齿轮架构燃气轮机发动机的灵活支撑结构

    公开(公告)号：US20140140819A1

    公开(公告)日：2014-05-22

    申请号：US14164364

    申请日：2014-01-27

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael E. McCune ,  Jason Husband

    IPC: 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。

    Flexible Support Structure For A Geared Architecture Gas Turbine Engine
    100.
    发明申请
    Flexible Support Structure For A Geared Architecture Gas Turbine Engine 有权
    用于齿轮架构燃气轮机发动机的灵活支撑结构

    公开(公告)号：US20140133958A1

    公开(公告)日：2014-05-15

    申请号：US14160601

    申请日：2014-01-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael E. McCune ,  Jason Husband

    IPC: F02C7/36

    CPC classification number: F02C7/36 ,  F01D25/164 ,  F05D2260/96 ,  Y02T50/671

    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。

Patent Agency Ranking