Sensitivity analysis method for forced response of mistuned bladed discs

被引：0
|
作者：
Tan Y. [1 ]
Zang C. [1 ]
Zhou B. [1 ]
Duan Y. [1 ]
Petrov E.P. [2 ]
机构：
[1] Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] School of Engineering and Informatics, University of Sussex, Brighton
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2017年 / 38卷 / 12期
基金：
中国国家自然科学基金;
关键词：
Bladed disc; High-fidelity; Mathematical expression; Mistuning; Sensitivity analysis;
D O I：
10.7527/S1000-6893.2017.221305
中图分类号：
学科分类号：
摘要：
The forced response of bladed discs is very sensitive to random blade mistuning. This paper proposes an effective sensitivity analysis method to explore the impact of blade mistuning parameters on the maximum vibrational amplitude of mistuned bladed discs. This method is constructed based on the reduced-order model and a subsequent forced response analysis of mistuned bladed discs. Mathematical expressions of the first and second order sensitivity coefficients for the maximum blade vibrational amplitude with respect to blade frequency mistuning parameters and mistuning nodal mass are derived from the equations for motion of mistuned bladed discs, without any hypothesis or numerical simplification. The method proposed can be used to perform effective sensitivity analysis for bladed discs with any random blade mistuning pattern vibrating in different frequency bands under an engine order excitation. The method is numerically validated in a high-fidelity mistuned bladed disc model. It is shown that the proposed method has the advantages of high accuracy and computational efficiency over the method of finite difference approximation of the sensitivity coefficients. Benefiting from its versatility, the method proposed is expected to further contribute to the forced response analysis of mistuned bladed discs. © 2017, Press of Chinese Journal of Aeronautics. All right reserved.
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