Investigation of aspirated compressor cascade flow fields using numerical simulation method

To explore the application of boundary layer aspiration technology in compressor stator blade profiles of potential regions,the cascade flow fields were simulated numerically.The results indicate that:(1) for high subsonic inlet flow,the boundary layer in blade suction surface being aspirated can increase the cascade pressure rate and flow turning angle,but not always reduce flow loss;(2) for middle subsonic inlet flow,the boundary layer in blade suction surface being aspirated can increase the cascade pressure rate,flow turning angle and reduce flow loss;(3) if there is flow separation region in rear part of blade suction surface,the aspiration position located upstream far from the region can eliminate flow separation;but the separation region can not be eliminated if the aspiration position is near or within the region.