圆截面超声速燃烧室乙烯燃料喷注火焰结构和模式分析
收稿日期: 2023-04-17
修回日期: 2023-05-06
录用日期: 2023-06-16
网络出版日期: 2023-06-21
基金资助
国家自然科学基金(11925207)
Analysis of structure and regime of ethylene fuel injection flame in circular⁃section supersonic combustor
Received date: 2023-04-17
Revised date: 2023-05-06
Accepted date: 2023-06-16
Online published: 2023-06-21
Supported by
National Natural Science Foundation of China(11925207)
采用耦合了火焰面/进度变量模型的混合RANS/LES方法对高马赫数下的乙烯燃料圆截面超燃冲压发动机燃烧流场开展了数值研究，计算结果显示出与试验高度一致的燃烧结构和释热特征。在此基础上，分析结果表明：流场的混合过程由大尺度流动结构主导，流道中心的激波系是促进涡量产生、燃料掺混以及下游反应区褶皱的直接原因。凹腔在此构型和工况中没有直接参与释热，而是起到了诱导激波产生从而促进混合和燃烧的作用。整体上，燃烧呈现时空多尺度特征，火焰在向下游传播的过程中逐渐向近平衡状态发展。超燃模态和扩散燃烧主导了整个反应区，并且大部分快反应区燃烧处于波纹板式火焰面模式。
关键词： 超燃冲压发动机; 混合RANS/LES; 火焰面模型; 超声速; 燃烧模式
汤涛 , 于江飞 , 黄玉辉 , 汪洪波 , 孙明波 , 赵国焱 , 熊大鹏 , 王振国 . 圆截面超声速燃烧室乙烯燃料喷注火焰结构和模式分析[J]. 航空学报, 2024 , 45(11) : 528880 -528880 . DOI: 10.7527/S1000-6893.2023.28880
In this study， a hybrid Reynolds-Averaged Navier-Stokes/Large Eddy Simulation （RANS/LES） approach coupled with an improved Flamelet/Progress Variable model is used to numerically investigate the combustion flow field of an ethylene-fueled circular-section model scramjet at high Mach numbers. The computational results show highly consistent combustion structure and heat release characteristics with those from the experiments. On this basis， the analysis results indicate that the mixing process of the flow field is dominated by the large-scale flow structures， and the shock train at the center of the channel is the direct cause of promoting vorticity generation， fuel mixing， and downstream reaction zone wrinkling. In this case， the cavity does not directly participate in the heat release process， but rather plays a role in inducing shock waves and promoting mixing and combustion. Overall， combustion exhibits spatiotemporal multi-scale characteristics， and flames gradually develop towards a near equilibrium state as they propagate downstream. The scramjet mode and diffusion combustion dominate the entire reaction zone， and most of the fast-chemistry combustion is in the corrugated flamelets regime.
Key words： scramjet; hybrid RANS/LES; flamelet model; supersonic; combustion regime
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