叶尖小翼对小流量跨声速压气机转子的影响研究  

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

作　　者：牛汗 刘波[1] 史磊[1] 那振喆[1] 张鹏[1] 茅晓晨[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710129

出　　处：《推进技术》2017年第11期2522-2531,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金面上项目(51676162);先进航空发动机协同创新中心资助

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。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. Re- search 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 pres- sure gradient of the fluid at the suction side, expanding the low-speed fluid region and pressure-side winglet re- duce the low-speed fluid region by reducing the tip load to weaken the leakage intensity.

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 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]