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为了探索叶顶微喷气对轴流压气机的稳定性影响,本文以西北工业大学某高负荷亚音速轴流压气机的孤立转子为研究对象,采用实验和数值模拟相结合的方法,研究了叶顶微喷气对压气机的扩稳效果和作用机理.研究结果表明,高速喷气降低了转子叶顶载荷,将压气机的流量裕度拓宽了5.6个百分点。相对于原实壁工况,喷气之后在原失稳边界流量上,削弱了由叶尖二次涡所诱导出的流场非定常脉动,而该非定常脉动与突尖形失速先兆的形成密切相关,由此推迟了压气机失稳。且存在临界攻角,随着节流程度增加,当叶顶攻角达到与原实壁工况相对应的失稳攻角后,压气机再度失稳。
In order to explore the effect of tip micro jet on the stability of axial flow compressor, this paper takes the isolated rotor of a high-load subsonic aerodynamic compressor of Northwestern Polytechnical University as the research object. By means of the combination of experiment and numerical simulation, The results show that the high-speed jet reduces the rotor blade tip load and broadens the flow margin of the compressor by 5.6%. Compared with the original real wall condition, the unsteady flow field induced by the secondary vortex tip induced by the instability of the original flow at jet instability can be weakened, which is closely related to the formation of sudden apex , Thus postponing the compressor instability. And there is a critical angle of attack. With the increase of throttling, the compressor again loses its stability after the angle of attack of the blade reaches the angle of attack of attack corresponding to the actual condition of the solid wall.