Numerical evaluation of the effect of using plasma actuators on the performance of low speed axial compressor rotor subjected to swirl inlet distortion

This paper investigated a numerical simulation of the undesirable effects of swirl inlet distortion on a low-speed axial compressor rotor and the effect of plasma actuators as an active flow control method on reducing these flow instabilities. Initially, the effect of co and counter-rotating inlet swirl distortion at angles of ±5 and ±10° on the rotor's performance and efficiency was evaluated. Then, using simulations of plasma actuators' fluid dynamics effects, the effect of this method on mitigating the destructive effects of this type of bulk swirl distortion was examined. Co-rotation swirl distortion reduces the rotor's total pressure rise coefficient, whereas counter-rotation swirl distortion reduces the stall margin. Applying plasma actuators by modifying the rotor inlet flow angle, leading to stall margin improvement. Furthermore, in the 5 degree counter rotation swirl distortion case, plasma actuators, in addition to compensating the adverse effects of swirl distortion, increased the stall margin by 1.3%