Simulation of flutter suppression for a transonic fan blade based on plasma excitation

Along with the development of advanced high-performance aero-engines to higher thrust-weight ratio, further improvement stage load, adoption new materials and lightweight structures, aeroelasticity blade structure is becoming more prominent. The high cycle fatigue failure blades significantly reduces structural reliability during process using. At same time, a large number forms aero-engine experimental server can be attributed aeroelastic problems. Therefore, it urgent improve stability blade. One most important factors suppress airflow separation, but its mechanism still unclear. Based on this, this paper combines aerodynamic damping analysis energy method plasma excitation simulation references low-speed wind tunnel expansion test consider effects different exciter distributions intensities flutter. results show that stall flutter related flow separation not key factor determinates whether flutters occurs or not. Flutter suppression strongly correlated shock wave intensity, amplitude first harmonic force, work density. In addition, relative distribution field positive zone also has direct effect