A new tip cascade structure

consisting of some small blades on top of the conventional blades

was proposed to reduce the tip clearance flow loss in compressor. The numerical simulation was carried out to investigate influence of the tip clearance on the three-dimensional flow field in compressor cascades with moving end-wall. The simulation results show that the structure can improve the tip clearance flow condition. The leakage flow from pressure side to suction side on top of the blade is suppressed in terms of pressure relief and diversion. The strength of the leakage vortices is weakened effectively

and the diffusion loss of leakage vortices is reduced

so the aerodynamic performance of compressor will be improved

and the total pressure loss coefficient decreases by 1.158% compared with conventional blade in cascade exit.