Abstract: Detailed measurements of three-dimensional turbulent flow field at the exit of an axial flow single-stage compressor rotor were made under different conditions.The flow structures were surveyed with both hot-wire probe and high frequency pressure probe.Under the design condition,substantial blockage,loss and turbulence mainly emerge in the tip mid-passage,in the wake and the corner between the suction surface and the hub,and the tip leakage vortex exists in the mid-passage at the exit.When the mass flow reduces,the flow becomes more turbulent.As a result,flow mixing is more,and the leakage vortex is far away from the suction surface,that leads to more substantial blockage,loss and turbulence in the tip region.Under the near stall condition,the radial migration of the blade suction surface boundary layer and the tangential migration of the endwall flow play a more important role in the flow field of the passage.