论文部分内容阅读
为了探究近失速工况下,跨声速压气机转子中非定常流动及相关流动机制,采用多通道全三维数值模拟方法对跨声速转子其内部流场进行了数值模拟,并利用已有的实验数据对计算结果进行了校核。对近失速工况探针监测结果的分析表明:流场中出现了非定常扰动,且扰动最活跃的区域位于近叶尖通道靠近叶片前缘的压力面侧;随着流量的降低,非定常扰动的幅值增大,波动周期变长。对近叶尖瞬态流场的分析表明:流场中的一个不同于泄漏涡的涡结构(命名为叶尖二次涡)的出现及其沿流向的发展诱发了非定常静压扰动,而且其强度随着流量的降低而增强,由此导致了非定常扰动的周期变长,振幅增加。伴随着叶尖二次涡强度的增加,叶顶通道的阻塞以及由叶尖二次涡诱发的“前缘溢流”也随之增强。因此,叶尖二次涡的出现及其强度的变化是影响该跨声速转子流动稳定性的主要因素之一。
In order to explore the unsteady flow and related flow mechanism in a transonic compressor rotor at near stall conditions, a multi-channel three-dimensional numerical simulation method was used to simulate the internal flow field of the transonic rotor. Based on the existing experimental data The calculation results were checked. Analysis of monitoring results of near-stall condition probes shows that unsteady perturbation occurs in the flow field and the most disturbed area is located on the pressure side of the near-apex channel near the leading edge of the blade. As the flow rate decreases, the unsteady The magnitude of disturbance increases and the period of fluctuation becomes longer. The analysis of the transient tip flow field shows that the appearance of a vortex structure (named secondary vortex) different from the leakage vortex in the flow field and its development along the flow direction induce unsteady static pressure disturbances, and Its intensity increases with the decrease of the flow rate, which leads to a longer period of unsteady disturbance and an increase of amplitude. With the increase of blade secondary vortex intensity, the obstruction of the tip channel and the “leading edge overflow” caused by the secondary vortex of tip are also enhanced. Therefore, the emergence of secondary vortex tip and the change of its intensity are one of the main factors that affect the flow stability of the transonic rotor.