论文部分内容阅读
Considering the substantial ability increasing the stage performance as well as the difficult of the bleed air system design in the rotating part by boundary layer suction (BLS),a new aerodynamic design method has been proposed for high loaded subsonic axial flow compressors.By this method,the rotor outlet axial velocity is greatly enhanced to ensure the rotor efficiency,and moreover,BLS is used to solve the internal flow problems of the downstream stator.A preliminary verification stage has been designed.The three-dimensional viscous numericalsimulation results show that the verification stage has achieved a stage pressure ratio 1.5 with efficiency 92.5% at tip tangential speed 213m/s,which demonstrates the possibility increasing the pressure ratio of a compressor stage at a given tip tangential speed by means of this aerodynamic design method.