Computational and experimental investigation of plasma aerodynamic actuation based corner flow separation control in a compressor cascade

Plasma aerodynamic actuation based corner flow separation control in a compressor cascade was investigated computationally and experimentally. Three dimensional corner flow separation, which is formed over the suction surface and end wall corner of a compressor cascade blade passage, could cause significant total pressure loss even when the incidence is 0 deg. When the free stream velocity is 50 m/s (corresponding Reynolds number is 223000), plasma aerodynamic actuation controls the corner flow separation effectively. When the actuation voltage and frequency are 10 kV and 22 kHz respectively, the maximum relative reductions of total pressure loss coefficient at 60% and 70% blade span are 13.83% and 10.74% respectively. So, increasing the actuation voltage or the number of electrode pair can enlarge the actuation strength and then improve the control effect.