Numerical Simulation of Plasma Actuator Effect on Control of Tip Leakage Vortex in Low Speed Axial Compressor Rotor

Tip Leakage vortex in axial compressor is source of unsteadiness and loss in flow field, so it is very important to investigate its controlling method. The aim of this article is numerical simulation of plasma actuator effect on tip leakage vortex in low speed axial compressor rotor. By applying linear distribution of body force at upstream of rotor on casing, effects of plasma actuator on tip leakage vortex have been investigated. Numerical simulation confirm that plasma actuator at blade tip region boost the flow momentum and in addition to decreasing the size of tip leakage vortex and reduces blockage due to the flow separation from blade surface, leads to decreasing loss in tip region. In addition, Plasma actuator can eliminate leading edge spillage and Trailing edge backflow in tip clearance region. Furthermore, the results show that plasma actuator caused the stall margin of the rotor blade row to increase by 5.2%.