Study of suppression boundary layer separation on the suction surface of supersonic compressor rotor

To provide a further prospective of the boundary layer separation of compressor rotor under high load and off-design working conditions, numerical method was used to study the effects of boundary layer suction of compressor rotor at different suction positions and suction flow rates on the aerodynamic performance of rotor. The results show that the suction position has great effect on the suction result. The boundary layer separation on the suction surface can be suppressed effectively through suction in proper downstream separation section. And, the dramatic change of gas flow at the separation point could be improved with lower flow loss, while the stage efficiency and pressure ratio can be improved remarkably. The effect is unsatisfactory in the event of slotted suction far away from the upstream or downstream of separation point. As suction flow rate also has a certain influence upon the suction effect, either bigger or lower suction flow rate has adverse effect on the result.