| 魏婷，胡骏.马赫数对压气机失稳静压升系数影响的数值模拟[J].航空发动机,2020,46(4):20-23 |
| 马赫数对压气机失稳静压升系数影响的数值模拟 |
| Numerical Simulation of the Influence of Mach Number on Stalling Pressure Rise Coefficient ofCompressor |
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| DOI： |
| 中文关键词: 压气机 失稳边界预测 数值模拟 马赫数 失稳静压升系数 航空发动机 |
| 英文关键词:compressor stall margin prediction numerical simulation Mach number stalling pressure rise coefficient aeroengine |
| 基金项目:航空动力基础研究项目资助 |
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| 中文摘要: |
| 为了提高压气机失稳边界预测的准确性，将压气机级压升类比于二元扩压器扩压，在不同长宽比和附面层堵塞程度下，
开展了马赫数对压气机失稳静压升系数影响的数值研究。结果表明：马赫数对失稳静压升系数的影响与静压升系数定义方式有关。
若静压升定义考虑了流体可压缩性，马赫数对失稳静压升系数的影响可忽略，此时在大范围马赫数下都能运用同一条失稳静压升
系数与无量纲长度关联曲线进行压气机失稳边界的预测。 |
| 英文摘要: |
| In order to improve the accuracy of compressor stall margin prediction，the compressor stage pressure rise was compared to
the pressure expansion of a binary diffuser. The numerical study on the influence of Mach number on the stalling pressure rise coefficient
was carried out under different length-width ratio and boundary layer blockage. The results show that the influence of Mach number on the
stalling pressure rise coefficient is related to the definition of pressure rise coefficient. If the definition of pressure rise takes into account the compressibility of fluid，the influence of Mach number on the stalling pressure rise coefficient is negligible. At this time，the compressor stall margin can be predicted by using a same correlation curve of the stalling pressure rise coefficient and the dimensionless length in a wide
range of Mach number. |
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