Effects of Tip Leakage Flow on the Aerodynamic Performance and Stability of an Axial-Flow Transonic Compressor Stage

To explain the effect of tip leakage flow on performance an axial-flow transonic compressor, compressors with different rotor clearances were studied numerically. The results show that as clearance increases, intensity is increased, shock wave position moved backward, and interaction between vortex intensified, while boundary layer weakened. Most all, stall mechanisms varying are different. main cause rotating under large clearance. However, form for compressor half designed caused by joint action spillage at blade leading edge whole span separation stator passage. Within investigated varied range, when size design, improved best, peak efficiency margin increased 0.2% 3.5%, respectively.