A reduced order model for coupled mode cascade flutter analysis  

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

机构地区：[1]School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China [2]Yangtze River Delta Research Institute of Northwestern Polytechnical University,Taicang 215400,China [3]Department of Aeronautics and Astronautics,Fudan University,Shanghai 200433,China

出　　处：《Chinese Journal of Aeronautics》2022年第10期176-182,共7页中国航空学报（英文版）

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)

摘　　要：A Reduced Order Model(ROM)based analysis method for turbomachinery cascade coupled mode flutter is presented in this paper.The 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 aeroelasticity.The cascade flutter can be determined by solving the eigenvalues of the ROM.Bending-torsional coupled mode flutter analysis for the Standard Configuration Eleven(SC11)cascade is used to validate the proposed method.

关 键 词：Aerodynamic influence coefficients Chirp signal Coupled mode flutter Eigenvalue problem Reduced order model 

分 类 号：V231.92[航空宇航科学与技术—航空宇航推进理论与工程]