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以某叶尖失速型的轴流压气机转子为研究对象,开展了无叶尖喷气以及喷气量为1%边界流量情况的全通道非定常数值模拟。数值探针监测结果表明:不喷气时出现了与实验测量结果一致的突尖型失速,而喷气情况下出现的是模态型失速。对比叶尖喷气下不同工况点的瞬态流场发现:在喷气流影响的径向范围内,喷嘴右侧通道中间隙泄漏流和吸力面尾缘分离耦合作用形成的流动阻塞,随着流量的减小逆转子转动方向沿周向扩展;而喷气流影响的径向范围外,喷嘴左侧通道中吸力面尾缘分离形成的流动阻塞顺转子转动方向沿周向扩展。这种流动阻塞格局的发展演化是喷气情况下出现模态扰动的原因。
Taking a tip-stalled axial-flow compressor rotor as the research object, unscented unscented jet and full-channel unsteady numerical simulation of jet flow rate of 1% is carried out. The results of the numerical probe showed that there was a sharp-pointed stall consistent with the experimental measurement when no gas was jetted, while the modal stall occurred during the jetting. Contrasting the transient flow field under different operating conditions, it is found that the flow blockage caused by the coupling effect between the leakage flow in the right passageway and the trailing edge of the suction surface in the radial range affected by the jet flow, The rotation direction of the reverse rotor is expanded in the circumferential direction, and the flow obstructed by the trailing edge of the suction surface in the left channel of the nozzle outside the radial range affected by jet flow expands circumferentially along the rotation direction of the rotor. The evolution of this pattern of flow blockages is the cause of modal disturbances in the jet case.