Statistical characteristics of forced response in mistuned bladed disks based on high-fidelity finite element model

被引：0

作者：

Zhang B. ^{[1
]}

Zang C. ^{[1
]}

Petrov E.P. ^{[2
]}

机构：

[1] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing

[2] College of Engineering and Design, University of Sussex, Brighton

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2019年 / 34卷 / 01期

关键词：

Extreme value theory; Maximum response; Mistuned bladed disk; Monte Carlo; Statistical characteristics;

D O I：

10.13224/j.cnki.jasp.2019.01.016

中图分类号：

学科分类号：

摘要：

The extreme value theory was used to analyze the statistical characteristics of maximum forced response of the mistuned bladed disks, and applied to a compressor disk. The mistuning bladed disk was reduced and modeled. The Monte Carlo method was used to simulate the response calculation, and the distribution characteristics for the amplification factor of the maximum response under different engine order excitations were studied. The extreme value theory was used to model the maximum response distribution, and the maximum likelihood estimation method was introduced to get the unknown parameters. The K-S(Kolmogorov-Smirnov) test was employed to test the goodness of fit of different distribution functions. The statistical characteristics of the response of a compressor disk were analyzed. The fitting results of seven kinds of distribution functions for the amplification factor of the maximum response were compared. Results showed that the fitting effects of the extreme value distribution, two-parameter Weibull distribution, normal distribution, lognormal distribution and Gamma distribution were all poor; the fitting effect of the commonly used three-parameter Weibull distribution was not as good as that of the generalized extreme value distribution. Therefore, the generalized extreme value distribution can more accurately describe the statistical characteristics of the dynamic response of mistuned bladed disks. © 2019, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：135 / 141

页数：6

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