航空学报 > 1995, Vol. 16 Issue (1): 105-109

跨音叶栅三维激波损失的改进模型

张扬军, 陶德平, 周盛   

  1. 北京航空航天大学407 教研室, 北京, 100083
  • 收稿日期:1994-01-22 修回日期:1994-05-12 出版日期:1995-02-25 发布日期:1995-02-25

AN IMPROVED THREE DIMENSIONAL MODEL FOR THE PREDICTION OF SHOCK LOSSES IN COMPRESSOR BLADE ROWS

Zhang Yangjun, Tao Deping, Zhou Sheng   

  1. Faculty 407,Beijing University of Aeronautics and Astronautics ,Beijing,100083
  • Received:1994-01-22 Revised:1994-05-12 Online:1995-02-25 Published:1995-02-25

摘要: 在低展弦比、低轮毂比的轴流压气机中激波结构常常是三维的。叶尖区域的三维激波损失在整个流场的激波损失中占有十分重要的比例。Wennerstrom和Puterbaugh于1984年推出的三维激波损失模型忽略了激波在叶尖区域的流动结构。通过分析叶尖区域的激波结构及其与机匣附面层流动的相互作用,提出了考虑叶尖区域激波与附面层相互作用所引起的激波结构及强度变化的跨音叶栅三维激波损失的改进模型,应用改进模型计算得出的结果和实验结果符合的很好。

关键词: 跨音速涡轮, 三维流, 激波相互作用, 激波衰减

Abstract: The shock structure in a transonic compressor with the low aspect ratio of blading is three dimensional. The shock loss of the flow in close proximity to the outer casing is significant. A known weakness of the three dimensional shock loss model of Wennerstrom and Puterbaugh is its treatment of the shock surface in the vicinity of the outer casing. By studying the interaction between shock and the outer casing boundary, an improved model is presented for predicting the shock loss through a transonic or supersonic compressor blade row operating at peak efficiency, which can consider the changes of the shock structure and its strength owing to the interaction of the shock and the outer casing boundary layer. The results using the improved model agree very well with those by the experiment.

Key words: supersonic turbines, three dimensional flow, shockwave interaction, shock wave atten2uation

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