航空学报 > 2009, Vol. 30 Issue (10): 1863-1870

一种基于响应信息的整体叶盘结构失谐识别方法

王帅,王建军,李其汉   

  1. 北京航空航天大学 能源与动力工程学院
  • 收稿日期:2008-09-04 修回日期:2008-12-30 出版日期:2009-10-25 发布日期:2009-10-25
  • 通讯作者: 王建军

Mistuning Identification for Integrally Bladed Disk from Measured Response Information

Wang Shuai, Wang Jianjun, Li Qihan   

  1. School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
  • Received:2008-09-04 Revised:2008-12-30 Online:2009-10-25 Published:2009-10-25
  • Contact: Wang Jianjun

摘要: 以谐调叶盘有限元模型解析模态和真实失谐结构的稳态响应作为基础信息,提出一种整体叶盘结构失谐识别方法。该方法基于公称模态子集(SNM)降阶技术,降低了识别过程的计算花费以及对基础信息量的要求;采用子矩阵型技术使得失谐参数定义更加自由,并使得该方法具有模型修正的功能;直接利用实测的稳态响应数据作为输入参数,并且不需要施加在结构上的外力信息,提高了基础数据可靠性并有效降低了实际测量的难度。最后以一个整体叶盘结构的仿真分析证明了该方法的有效性。

关键词: 动力学, 整体叶盘, 失谐, 识别, 降阶技术, 子矩阵型法, 稳态响应

Abstract: A method of mistuning identification for integrally bladed disk is presented in this article. The analytical modes obtained by the finite element model of a tuned bladed disk and the measured steady-state responses of the actual mistuned bladed disk are used as the basic information. The identification method is based on the subset of nominal modes (SNM) reduced technique, which greatly lowers the computational cost and information requirement of the identification procedure. The submatrix method enables a more free definition of mistuning parameters and allows this identification method to perform the function of model modification. The forced response experimental data is used for identification without requiring the knowledge of the applied forces. This makes the basic data more reliable and reduces measurement difficulty. Finally, numerical simulation of an integrally bladed disk is preformed to validate the effectiveness of the identification method.

Key words: dynamics, integrally bladed disk, mistuning, identification, reduced technique, submatrix method, steady-state response

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