靳楠,胡骏,李骏.压气机稳定边界的数值预测研究[J].航空发动机,2017,43(4):48-55
压气机稳定边界的数值预测研究
Numerical Predicting 47Study on Compressor Surge Margin
  
DOI:
中文关键词:  轴流压气机  稳定边界  数值模拟  最大静压升  航空发动机
英文关键词:axial compressor  surge margin  numerical simulation  maximum pressure rise method  aeroengine
基金项目:
作者单位E-mail
靳楠,胡骏,李骏 南京航空航天大学能源与动力学院南京210016 jinnan666@foxmail.com 
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中文摘要:
      为研究不同压气机稳定性预测方法的准确性,采用最大静压升系数法与商用CFD软件,对某4级低速压气机的稳定边 界进行了数值模拟,并与试验结果对比。计算结果表明:最大静压升系数法在预测压气机稳定边界上有一定的准确性。使用商用 CFD软件NUMECA对某4级压气机进行模拟计算,考虑了不同的网格划分方案、使用不同的湍流模型和差分格式等因素,以出现数 值发散作为压气机失稳的标准,结果表明:主流区的网格对计算结果影响较大。不同差分格式的结果显示,中心差分格式的结果最 好。
英文摘要:
      In order to evaluate the accuracy of different method in predicting surge margin of axial compressor, a fourth-stage lowspeed model compressor was numerically simulated by maximum pressure rise method and commercial CFD software MUNECA, and the result was compared to experiment data. The calculation result shows that the maximum pressure rise method has certain accuracy according to experiment data. The simulation calculation of a fourth stage compressor was performed using NUMECA software, considering the influence of meshing means, different turbulence models and different scheme on surge margin, and taking numerical divergence as the instability standard of compressor. The results show that the factors in consideration all influence the accuracy of the simulation results, especially grid percentage of mid-flow cells, and the result of central difference scheme is the best in three schemes.
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