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本文首先利用动态测试手段和非定常数值模拟手段探讨了亚音速条件下叶顶复杂流动机制触发轴流压气机内部流动失稳机制。然后利用全三维非定常数值模拟技术对二种不同处理机匣与亚音速压气机转子叶顶流场之间的耦合流动机制进行了详细的分析,对比分析了处理机匣引入前后压气机叶顶流场结构的变化,研究结果表明:顶部间隙泄漏流所导致的堆积在叶片通道相邻叶片压力面附近的阻塞是触发该压气机内部流动失稳的主要的机制,而处理机匣结构能够抑制或者吸除叶顶区域由于顶部间隙泄漏流导致的阻塞,推迟相邻叶片压力面前缘附近间隙泄漏流溢流的出现,从而提高压气机的失速裕度。
In this paper, firstly, the dynamic instability and the unsteady numerical simulation are used to investigate the mechanism of flow instability in the axial flow compressor triggered by the complicated tip flow mechanism. Then, the coupling flow mechanism between two different casing cascades and the subsonic flow field of the subsonic compressor rotor is analyzed in detail by using the full three-dimensional unsteady numerical simulation technique. The flow field around the compressor casings before and after the introduction of the casing is analyzed and compared. The results show that the obstruction caused by the leakage flow in the top gap near the pressure surface of the adjacent blade in the vane channel is the main mechanism that triggers the flow instability inside the compressor and the casing structure can be restrained Or sucking off the obstruction caused by the leakage flow at the top of the blade due to the leakage at the top of the blade, and retarding the occurrence of the overflow of the leakage flow in the gap near the front edge of the pressure surface of the adjacent blade so as to increase the stall margin of the compressor.