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    Geared architecture to protect critical hardware during fan blade out
    3.
    发明授权
    Geared architecture to protect critical hardware during fan blade out 有权

    公开(公告)号：US10107134B2

    公开(公告)日：2018-10-23

    申请号：US14773924

    申请日：2013-12-03

    Applicant: United Technologies Corporation

    Inventor： Jason Husband ,  Drew W. Lancaster

    IPC: F01D21/00 ,  F01D21/04 ,  F01D5/02 ,  F01D15/12

    Abstract: A turbofan engine including a fan section including a plurality of fan blades rotatable about an axis, a compressor including a plurality of compressor blades, a turbine including a plurality of turbine blades and a geared architecture driven by the turbine for driving the fan section at a speed and direction different than the turbine is disclosed. A rub strip proximate at least one of the compressor blades, the turbine blades and the fan blades slows rotation when engaged. The rub strip generates a torque opposing rotation when in an engaged condition that is between 2 and 6 times a torque encountered in a non-engaged condition.

    GEARED ARCHITECTURE TO PROTECT CRITICAL HARDWARE DURING FAN BLADE OUT
    4.
    发明申请
    GEARED ARCHITECTURE TO PROTECT CRITICAL HARDWARE DURING FAN BLADE OUT 审中-公开
    用于风扇叶片保护关键硬件的齿轮架构

    公开(公告)号：US20160017746A1

    公开(公告)日：2016-01-21

    申请号：US14773924

    申请日：2013-12-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jason Husband ,  Drew W. Lancaster

    IPC: F01D21/00 ,  F01D15/12 ,  F01D5/02

    CPC classification number: F01D21/006 ,  F01D5/02 ,  F01D15/12 ,  F01D21/045 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/40311 ,  F05D2260/902 ,  Y02T50/671

    Abstract: A turbofan engine including a fan section including a plurality of fan blades rotatable about an axis, a compressor including a plurality of compressor blades, a turbine including a plurality of turbine blades and a geared architecture driven by the turbine for driving the fan section at a speed and direction different than the turbine is disclosed. A rub strip proximate at least one of the compressor blades, the turbine blades and the fan blades slows rotation when engaged. The rub strip generates a torque opposing rotation when in an engaged condition that is between 2 and 6 times a torque encountered in a non-engaged condition.

    Abstract translation: 一种涡轮风扇发动机，其包括风扇部分，所述风扇部分包括可围绕轴线旋转的多个风扇叶片，包括多个压缩机叶片的压缩机，包括多个涡轮机叶片的涡轮机以及由所述涡轮机驱动的齿轮架构， 公开了与涡轮机不同的速度和方向。 接近压缩机叶片，涡轮机叶片和风扇叶片中的至少一个的摩擦带在接合时减慢旋转。 当处于非接合状态下遇到的扭矩的2至6倍的接合状态时，摩擦带产生相反的转矩。

    FBO TORQUE REDUCING FEATURE IN FAN SHAFT
    6.
    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。

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