Research on the Influence of Different Installation Positions of Blade Tip Winglets on the Flow Field of a Transonic Compressor Rotor

In order to study the effect of the blade tip winglet and its installation position on the compressor performance, the transonic axial compressor rotor NASA Rotor37 was used as the research object, and the original rotor and 4 different blade tip winglet rotors with different installation positions were studied by numerical simulation method. The results show that each configuration can improve its stability margin while ensuring the efficiency of the rotor. Among them, the suction side trailing edge winglet has the best stabilization effect, and the margin improvement can reach 4.93%; the pressure side leading edge winglet has the worst stabilization effect, and the margin improvement is 4.5%; the stabilization effect of the pressure side trailing edge winglet and the suction side leading edge winglet is between the two. It is revealed that, to improve the stability margin of the rotor, the leading edge winglet inhibits the separation of the boundary layer, while the trailing edge winglet controls the accumulation of low-velocity fluid in the passage by weakening the degree of leakage vortex breakdown.