TURBINE BLADE FATIGUE LIFE ANALYSIS USING NON-CONTACT MEASUREMENT AND DYNAMICAL RESPONSE RECONSTRUCTION TECHNIQUES
    78.
    发明申请
    TURBINE BLADE FATIGUE LIFE ANALYSIS USING NON-CONTACT MEASUREMENT AND DYNAMICAL RESPONSE RECONSTRUCTION TECHNIQUES 审中-公开
    使用非接触式测量和动态响应重构技术的涡轮叶片疲劳寿命分析

    公开(公告)号:US20140100798A1

    公开(公告)日:2014-04-10

    申请号:US14028594

    申请日:2013-09-17

    IPC分类号: G01L5/00

    摘要: A method dynamically reconstructing a stress and strain field of a turbine blade includes providing a set of response measurements from at least one location on a turbine blade, band-pass filtering the set of response measurements based on an upper frequency limit and a lower frequency limit, determining an upper envelope and a lower envelope of the set of response measurements from local minima and local maxima of the set of response measurements, calculating a candidate intrinsic mode function (IMF) from the upper envelope and the lower envelope of the set of response measurements, providing an N×N mode shape matrix for the turbine blade, where N is the number of degrees of freedom of the turbine blade, when the candidate IMF is an actual IMF, and calculating a response for another location on the turbine blade from the actual IMF and mode shapes in the mode shape matrix.

    摘要翻译: 动态重建涡轮叶片的应力和应变场的方法包括从涡轮叶片上的至少一个位置提供一组响应测量值,基于上限频率和较低频率限制对该组响应测量值进行带通滤波 从响应测量集合的局部最小值和局部最大值确定响应测量集合的上包络和下包络,从该响应集合的上包络和下包络计算候选固有模函数(IMF) 提供用于涡轮叶片的N×N模式形状矩阵,其中N是涡轮叶片的自由度的数量,当候选IMF是实际IMF时,以及计算涡轮机叶片上另一位置的响应 模式形状矩阵中的实际IMF和模式形状。