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.
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)
