Abstract: A 3D numerical solution of transonic turbulent flowfield inside a compressor rotor is analyzed with a consideration of blade tip clearance.The complex vortex system structure and shock wave system structure inside this rotor is obtained.Wall flow patterns on the blade surface and hub surface are found out.The complex vortex system structure, such as horseshoe vortex,passage vortex,corner vortex and trailing vortex,and the interaction with shock wave system are researched.Especially,the character of the tip clearance flow inside the rotor passage is revealed,and the interaction between shock wave and tip clearance flow near blade tip and the evolution of tip clearance flow are considered.