Numerical simulation research of the stall flow field of the transonic compressor blade tip

The rotating stall of turbo machinery causes the bottleneck in the air compressor performance further improving. Based on the numerical simulation research of the transonic compressor rotor, the flow field details which cannot get from experiments were derived, and the physical mechanism of the first stall at blade tip in transonic compressor was qualitatively interpreted, then it was found that the spatial trajectory of leakage vortex center at the blade tip is almost the same in different conditions. Because of the shock wave of the blade flow field gradually moves to the upstream and intensity increases with the decrease of the flow rate. While the leakage flows of the blade tip were increasing, the rupture of the blade tip leakage vortex was getting more serious. Thus blade row channels of the rotor blade tip are jammed, which is the main reason of blade tip stall. Blade load is beyond the load capacity because of the increase of the attack angle of the rotor blade tip under the near stall condition, which is another reason of blade tip stall. These conclusions provide the useful information to reveal compressor internal stall mechanism.