【摘要】 为了探究轴流压气机单转子叶顶区域的非定常流动机理，针对某跨声速压气机开展数值模拟研究，探究了叶顶泄漏流流场非定常演化特性。研究发现：该转子叶顶非定常流动现象特征频率为1863.3 Hz。吸力面前缘形成的泄漏涡，在一个波动周期内发生破碎，并形成一个新的涡结构；该结构受到压力面吸力面之间的压差及前缘脱体激波共同作用逐渐向相邻叶片压力面前缘外沿移动，并在此跨周期演化过程中出现约1/9周期的维持现象；泄漏涡破碎后形成的涡结构消散的同时与下一个循环中破碎的涡共同作用，在通道内形成堵塞区，受激波的影响，进一步加剧“前缘溢流”现象的生成。也依此推测出，涡波干涉导致的泄漏涡破碎是诱发流场非定常性的关键因素。泄漏涡破碎后在相邻叶片前缘形成新的涡结构，其随时间变化发生的一系列演化过程是造成叶顶区域非定常流动的主要原因。更多还原

【Abstract】 In order to investigate the unsteady flow mechanism in the tip region of the axial-, a numerical simulation study was carried out to investigate the unsteady evolutionary-of the tip leakage flow field. It was discovered that the dominant frequency of the unsteady flow at the blade tip region was 1863.3 Hz, and the tip leakage vortex formed at the leading edge of the suction surface broke down in one oscillation phase and formed a new vortex structure. Due to the combined effect of the differential pressure between the suction surface and the pressure surface and the leading edge excitation shock wave, the vortex structure gradually moved to the leading edge of the adjacent blades, and during this cross-cycle evolution, the vortex structure appeared to be maintained for about 1/9th of a cycle. In the subsequent cycle, the vortex structure formed by the tip leakage vortex breakdown dissipated while interacting with the broken vortex to form a blockage region in the passage. Along with the influence of the excitation shock wave, this blockage region exacerbated the generation of the “leading edge overflow”phenomenon. It was also hypothesized that the tip leakage vortex breakdown due to vortex wave interference was the key factor in the flow unsteadiness. After the tip leakage vortex broke down, a new vortex structure was formed at the leading edge of the adjacent blade, and a series of evolutionary processes occurred over time, which was the main cause of the unsteady flow in the blade tip region.更多还原