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为了研究处理机匣对压气机稳定性的影响并探讨其中的流动机理,采用数值模拟方法研究了一系列深度不同的周向槽处理机匣结构对跨音压气机转子Rotor37性能的影响。结果表明:叶尖泄漏涡与激波干涉后形成的堵塞区是诱发失速的主要原因。采用周向槽机匣处理可以显著增加转子的稳定裕度,且裕度增量与槽深度呈“双峰”关系;尺寸最优的浅周向槽和深周向槽可分别获得6.7%和7.3%的稳定裕度增加,而前者的效率损失更小。该处理机匣的扩稳机理在于减弱甚至移除了泄漏涡破碎形成的堵塞区。最后从动量方程的角度对深浅槽的扩稳机理分别进行了分析。
In order to study the influence of casing on compressor stability and to explore its flow mechanism, a series of deep circumferential casing geometry with different depths on the performance of transonic compressor rotor Rotor37 was studied by numerical simulation. The results show that the main cause of stalling is the clogging zone formed by tip leakage vortex and shock wave interference. The use of circumferential groove casing treatment can significantly increase the stability margin of the rotor, and the margin increment is “double peak” relationship with the groove depth; the optimal size of the shallow circumferential groove and the circumferential groove can be 6.7 The stability margins of% and 7.3% increase, while the former have less efficiency loss. The stabilizing mechanism of the casing is to reduce or even eliminate the blockage caused by the crushing of the leakage vortex. Finally, from the point of momentum equation, the stability mechanism of deep and shallow grooves are analyzed respectively.