压气机二维动叶栅非定常流场的大涡模拟  

Large eddy simulation of unsteady flow field in a two-dimensional moving compressor cascade

作　　者：赵龙[1,2] 耿少娟[1] 张宏武[1] 

机构地区：[1]中国科学院工程热物理研究所先进能源动力重点实验室,北京100190 [2]中国科学院大学,北京100049

出　　处：《航空动力学报》2015年第1期248-256,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(50906080)

摘　　要：对压气机二维动叶栅,采用单通道和多通道计算模型进行了大涡模拟(LES),研究了节流过程中内部流场的非定常波动特征,分析了旋涡结构和波动频率的变化规律.结果表明:大流量工况时,前缘绕流和叶片吸力面分离产生的两种非定常波动共存,波动频率随压气机节流基本保持不变,此时吸力面分离表现为小尺度旋涡结构;近失速工况时,吸力面发生大尺度的流动分离,波动频率明显下降,低于叶片通过频率.Using single-passage and multi-passage caculation models, large eddy simulations were conducted to study the unsteady oscillating features of internal flow field in a twodimensional moving compressor cascade during the throttling process. The changes of vortex structure and oscillating frequency were analyzed. The resutls show that at working conditions with larger mass flow rates, two unsteady oscillations resulted from flow around leading edge and separation on blade suction surface coexist. Both frequencies almost keep constant. Flow structures of separation on suction surface are of small scale. At working conditions near stall limit, large scale separations occur on suetion surface. The oscillating frequency decreases dramatically, lower than blade passing frequency.

关 键 词：压气机 流动分离 旋涡脱落 频率 大涡模拟 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]