Numerical simulation with high density grid was carried out to study blade tip clearance of a transonic axial-flow compressor rotor 37 at near-stall condition. The blade tip clearance included design clearance

half design clearance

quarter design clearance

2 times design clearance and zero clearance. The results show that stall margin is improved 4%

and adiabatic efficiency and pressure ratio don't decline obviously

when the blade tip clearance reduced from design clearance to half design clearance. Details of the flow field were analyzed based on different stall forms and vortex dynamics. The change of clearance may improve stability margin greatly and clearance plays an important role in leakage vortex and separation of boundary layer

or even induces different stall forms. This has provided necessary basic research for design of the compressor are provided

and discussed the application condition of clearance control technology in aerodynamics.