A reduced order model for coupled mode cascade flutter analysis

作     者：Huang HUANG Xinkai JIA Jia REN Bochao CAO Dingxi WANG Xiuquan HUANG Huang HUANG;Xinkai JIA;Jia REN;Bochao CAO;Dingxi WANG;Xiuquan HUANG

作者机构：School of Power and EnergyNorthwestern Polytechnical UniversityXi'an 710072China Yangtze River Delta Research Institute of Northwestern Polytechnical UniversityTaicang 215400China Department of Aeronautics and AstronauticsFudan UniversityShanghai 200433China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2022年第35卷第10期

页      面：176-182页

核心收录：

学科分类：082502[工学-航空宇航推进理论与工程] 08[工学] 0825[工学-航空宇航科学与技术] 

基　　金：supported by the National Science and Technology Major Project, China (No. 2017-II-0009-0023) the Aeronautical Science Foundation of China(No. 2020Z039053004) the Fundamental Research Funds for the Central Universities, China (No. 3102019OQD701) 

主　　题：Aerodynamic influence coefficients Chirp signal Coupled mode flutter Eigenvalue problem Reduced order model 

摘      要：A Reduced Order Model(ROM)based analysis method for turbomachinery cascade coupled mode flutter is presented in this *** unsteady aerodynamic model is established by a system identification technique combined with a set of Aerodynamic Influence Coefficients(AIC).Subsequently,the aerodynamic model is encoded into the state space and then coupled with the structural dynamic equations,resulting in a ROM of the cascade *** cascade flutter can be determined by solving the eigenvalues of the ***-torsional coupled mode flutter analysis for the Standard Configuration Eleven(SC11)cascade is used to validate the proposed method.