以某小型高速离心压气机为研究对象，采用数值方法研究了微射流对压气机性能和叶轮叶顶流场结构的影响。研究结果表明：射流为1%设计流量时，失速裕度能够提高3.12%，稳定工作范围拓宽28.17%；在设计点，原型离心压气机叶顶来流马赫数达1.8以上，叶顶存在复杂激波/间隙泄漏流干扰，工作稳定性较差，微射流改变了“λ”状的激波结构，使前缘激波的强度减弱，后掠角度减小，并且降低了叶顶的负荷水平；微射流能够抑制间隙泄漏流的周向运动，并削弱激波/间隙泄漏流之间的相互作用，间隙泄漏涡不易发生破裂、溃散，极大增强了压气机工作的稳定性。

Taking a compact highspeed centrifugal compressor as research object,the influences of micro jet on the performance of the compressor and the flow field structure of impeller tip were studied by numerical method.The results show that when the jet flow rate is 1% of the design flow rate,the stall margin can be increased by 3.12%,and the stable working range can be expanded by 28.17%.At the design point,the inlet Mach number of the blade tip of the prototype centrifugal compressor is more than 1.8,and there is complex shock wave/tip leakage flow interaction at the blade tip,so the operation stability is poor.The micro jet changes the "λ" shaped shock structure,weakens the strength of the leading edge shock wave,reduces the sweepback angle,and reduces the blade tip load level.The micro jet can suppress the circumferential motion of tip leakage flow and weaken the interaction between shock wave and tip leakage flow.The tip leakage vortex is not prone to rupture and collapse,which greatly enhances the operation stability of compressor.

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