自适应流通处理机匣喷气位置对压气机性能的影响  

Influence of the injecting position of self recirculation casing treatment on compressor performance

作　　者：张皓光[1] 吴俊[1] 王云鹏[1] 楚武利[1,2] 吴艳辉[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2016年第5期1149-1158,共10页Journal of Aerospace Power

基　　金：国家自然科学基金重点项目(51236006);国家自然科学基金(51006084);航空科学基金(2014ZB53014);中央高校基本科研业务费专项资金(3102014JCY01004)

摘　　要：采用数值模拟方法研究了跨声风扇转子Rotor 67的失速机理和3个喷气位置的自适应流通处理机匣对转子性能的影响.结果表明:叶顶间隙泄漏涡中低速团是诱发失稳的主要原因;3个喷气位置的处理机匣均增大了压气机的稳定工作范围,喷气位置居中和后移的处理机匣综合稳定裕度改进量分别为13.43%,9.47%,均大于前移的2.72%;喷气位置居中和后移有利于抑制间隙泄漏流的发展,减小低能流体泄漏范围;相比前移和居中,后移不能激励压力面前缘处的低速团和抑制低能流体从叶顶前部泄漏.A numerical investigation was carried out on the transonic axial-flow com- pressor Rotor 67 to clarify the stall mechanism and the influence of self recirculation casing treatment （with three injection positions） on its performance. The result showed that low- speed region in the tip leakage vortex played a major role in stall. Casing treatments with three different injection positions improved the aerodynamic stability of compressor, and those with forward injector gives less improvement （2.72%） on stall margin than those with center （13.43%） and backward （9.47%） injectors. Casing treatment with center or back- ward injector performed better in suppressing the tip leakage flow, thus reducing the sprea- ding of low energy fluid. Additionally, the backward injector showed no effect in accelera- ting the blockage around pressure side leading edge and suppressing the low energy leakage, so the ability of improving flow-filed of backward injector was lower than that of center injector.

关 键 词：轴流压气机 处理机匣 喷气位置 失速机理 间隙泄漏流 

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]