| 张宏达1，万斌1，张成凯1，林宏军1，尚守堂1，韩省思2.高温升燃烧室综合燃烧性能超大涡模拟[J].航空发动机,2020,46(6):11-15 |
| 高温升燃烧室综合燃烧性能超大涡模拟 |
| Very Large Eddy Simulation of Comprehensive Combustion Performance in HighTemperature Rise Combustor |
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| DOI： |
| 中文关键词: 高温升燃烧室 旋流 超大涡模拟 雷诺平均模拟 综合燃烧性能 航空发动机 |
| 英文关键词:high temperature rise combustor swirling flow very large eddy simulation（VLES） Reynolds-averaged Navier-Stokes
（RANS）simulation comprehensive combustion performance 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: |
| 为了对高温升燃烧室性能进行计算分析，运用超大涡模拟方法开展数值模拟，并同步开展了雷诺平均数值模拟作为对
比。计算结果表明：旋流器设计与火焰筒开孔设计的匹配合理，Rothstein提出的射流迹线公式能够合理预测主燃孔的射流穿透。超
大涡模拟计算得到的出口径向温度分布系数的剖面曲线趋势和最大值位置均与试验结果符合较好。通过与试验结果进行定量比较
发现，在相同计算网格条件下，超大涡模拟方法预测高温升燃烧室综合燃烧性能的精度明显高于雷诺平均方法的。 |
| 英文摘要: |
| In order to calculate and analyze the performance of high temperature rise combustor，the numerical simulation was carried
out by using very large eddy simulation（VLES）method，and numerical simulation of Reynolds-averaged Navier-Stokes（RANS）was carried
out simultaneously as a comparison. The calculation results show that the matching between the swirler design and flame tube opening hole
design is reasonable，and the jet trajectory formula given by Rothstein can predict the jet penetration of main combustion hole reasonably.
The profile curve trend and maximum position of the outlet radial temperature distribution coefficient obtained from the VLES are in good
agreement with the test results. Quantitative compared with the test results，it is found that the precision of VLES method to predict the
comprehensive combustion performance of high temperature rise combustor is obviously higher than that of RANS method under the same
grid condition. |
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