Investigation of Blade Tip Winglet Effects on Transonic Rotor of Low Flow Rate Compressor

In order to control the tip leakage flow of compressor rotor and reduce the adverse effects of tip leakage flow and tip leakage vortex on the internal flow of the compressor, a numerical simulation of blade tip winglet aimed at transonic rotor of a low flow rate compressor has been carried out, exploring the effect of blade tip winglet to the transonic rotor of low flow rate compressor and the control mechanism of tip leakage flow. Research shows that the pressure-side winglet which has four times width of thickness of pressure side can make the flow stall margin of the compressor rotor increase 24.5%.The main factors of suction-side winglet and pressure-side winglet influencing the stall of compressor stall are different. Suction-side winglet increases the adverse pressure gradient of the fluid at the suction side, expanding the low-speed fluid region and pressure-side winglet reduce the low-speed fluid region by reducing the tip load to weaken the leakage intensity.