Volume 36, Number 5, October 2018
|Page(s)||856 - 864|
|Published online||17 December 2018|
A High Efficient Fluid-Structure Interaction Method for Flutter Analysis of Mistuned
School of Aeronautic Engineering, Zhengzhou University of Aeronautics, Zhengzhou
2 CECCS Sichuan Gas Turbine Establishment, Chengdu 610500, China
3 National Key Laboratory of Aerodynamic Design and Research, Northwestern Polytechnical University, Xi’an 710072, China
The time cost is very high by direct fluid-structure interaction method for mistuned bladed disk structures, so aerodynamic loads generally are ignored or treated as small perturbations in traditional flutter analysis. In order to analyze the flutter characteristics of mistuned blade rapidly and accurately, this paper presents an efficient fluid-structure interaction method based on aerodynamic reduced order model. system identification technology and two basic assumptions are used to build the unsteady aerodynamic reduced order model. Coupled the structural equations and the aerodynamic model in the state space, the flutter stability of mistuned bladed disk can be obtained by changing the structural parameters. For the STCF 4 example, the response calculated by this method agrees well with the results obtained by the direct CFD, but the computational efficiency is improved by nearly two orders of magnitude. This method is used to study the stiffness mistuned cascade system, and the stability characteristics of the system are obtained by calculating the eigenvalues of the aeroelastic matrix. The results show that the stiffness mistuning can significantly improve the flutter stability of the system, and also lead to the localization of the mode. The mistuning mode, mistuning amplitude and fluid structure interaction can influence the flutter stability obviously.
Key words: reduced order model / fluid-structure interaction / aeroelastic / computational efficiency / flutter / mistuned
关键字 : 降阶模型 / 流固耦合 / 气动弹性 / 计算效率 / 颤振 / 失谐
© 2018 Journal of Northwestern Polytechnical University. All rights reserved.
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