Abstract: 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.

Key words: Blade tip winglet；Low flow rate compressor；Transonic rotor；Tip leakage flow；Tip leakage vortex

摘要： 为了控制压气机转子叶尖泄漏流动，减少叶尖泄漏流和叶尖泄漏涡对压气机内部流场带来的不利影响，针对小流量压气机进口跨声速转子进行了叶尖小翼的数值研究，探索了叶尖小翼对小流量跨声速压气机转子性能的影响和对叶尖泄漏流的控制机理。研究表明，4倍压力面宽度的压力面叶尖小翼可以使得压气机转子的流量裕度增加24.5%；吸力面叶尖小翼和压力面叶尖小翼影响失速的主要因素不同，吸力面叶尖小翼增大了吸力面侧流体的逆压梯度，扩大了低速流体区域，压力面叶尖小翼通过降低叶尖负荷，从而减弱泄漏强度，减小了低速流体区域。

关键词: 叶尖小翼；小流量压气机；跨声速转子；叶尖泄漏流；叶尖泄漏涡