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.