跨音速压气机中的涡结构与失速机理分析  

Identification of vortices in a transonic compressor flow and study on the stall process

作　　者：黄旭东[1] 陈海昕[1] 符松[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《空气动力学学报》2007年第B12期75-79,共5页Acta Aerodynamica Sinica

摘　　要：将一种新的涡识别方法应用于压气机流场的分析。该方法采用应变率张量和旋转张量的第四不变量，具有在识别流场中涡的存在的同时，分析该处涡处于拉仲（生成）或松弛（溃灭）状态的能力。通过将该方法与传统的动压头和流线、速度矢量等分析方法的结合，本文对所研究的跨音速压气机的失速过程进行了分析和讨论。A novel vortex identification method for the visualization of the flow field is used for the study of the stall process of a transonic compressor. The parameter η4 is introduced to identify the stretching and relaxation of the vortex. The new method reveals much more flow details which may advance our understanding of the compressor behaviors. With the help of DPH contour and streamlines, the detailed vortices structures and topology in a transonic compressor have been revealed. The study distinguishes different vortices structures in the compressor, as well as their development at different operating condition. From comparison of the vortices in maximum efficiency condition and near stall condition, a possible stall process has been revealed.

关 键 词：跨音速压气机 涡识别 失速过程 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]