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首先回顾了近几十年来国际上在轴流压气机内部流动失稳机理方面具有代表性的研究成果,然后介绍了作者研究团队从叶顶泄漏流的视角研究压气机失稳机理所开展的主要工作,研究结果证实了叶顶泄漏流非定常性在低速亚声和高速跨声压气机转子中存在的普遍性,揭示了在节流直至失速工况过程中叶顶泄漏流的非定常波动和三维空间结构特征。主要表现为:(1)叶顶泄漏流由定常变为非定常波动,且非定常波动强度不断增强。(2)泄漏流与主流交界面的轴向位置不断向叶片前缘移动,最终溢出叶片通道,并诱发突尖失速先兆。这两方面特征的内在驱动力是节流过程中不断提高的泄漏流与主流轴向动量比。这些研究成果在发展主/被动扩稳技术和阐释扩稳机理研究中凸显出重要的应用价值。
First of all, the paper reviews the research results of the international instability mechanism of axial flow compressor in recent decades, and then introduces the main research work carried out by the author research team on the instability mechanism of the compressor from the perspective of tip leakage flow The results show that the unsteady behavior of tip leakage flow exists in low-speed subsonic and high-speed transonic compressor rotors, and the unsteady vortex leakage and three-dimensional Spatial structure characteristics. The main manifestations are as follows: (1) The tip-leakage flow changes from a steady state to an unsteady one, and the unsteady fluctuation intensity increases continuously. (2) The axial position of the leakage flow and the mainstream interface constantly moves toward the leading edge of the blade, eventually overflowing the blade passage and inducing a sharp stall. The inherent driving force of these two characteristics is the increasing leakage flow and the mainstream axial momentum ratio in throttling process. These research results have shown important application value in the development of the main / passive stabilization techniques and the study of the stabilization mechanism.