跨声速轴流压气机非定常流动机理研究  

The Investigation of Unsteady Flow Mechanism in a Transonic Axial Compressor

作　　者：郎进花 康嘉诚 安光耀 张磊 LANG Jinhua;KANG Jiacheng;AN Guangyao;ZHANG Lei(Hebei Key Laboratory of Low Carbon and High Efficiency Power Generation Technology,North China Electric Power University,Baoding 071003,China)

机构地区：[1]华北电力大学(保定)河北省低碳高效发电技术重点实验室,保定071003

出　　处：《工程热物理学报》2025年第1期72-82,共11页Journal of Engineering Thermophysics

基　　金：国家自然科学基金面上项目(No.52076079);河北省自然科学基金项目(No.E2020502013,No.E2022502048);中央高校基本科研业务费专项资金(No.2022MS082,No.2022MS085);河北省教育厅在读研究生创新能力培养资助项目(No.CXZZSS2024162)。

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。In order to investigate the unsteady flow mechanism in the tip region of the axial compressor,a numerical simulation study was carried out to investigate the unsteady evolutionary characteristics 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.

关 键 词：轴流压气机 数值模拟 泄漏涡 涡波干涉 非定常流动 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]