Direct numerical simulation of supersonic internal flow in a model scramjet combustor under a non-reactive condition
Direct numerical simulation of supersonic internal flow in a model scramjet combustor under a non-reactive condition
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DOI：
10.1063/5.0137884
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发表时间：
2023-02
影响因子：
4.6
通讯作者：
J. Fang;Xi Deng;Zhi X. Chen
中科院分区：
文献类型：
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作者：
J. Fang;Xi Deng;Zhi X. Chen
采用直接数值模拟的方法，对模型超燃冲压发动机空腔稳定燃烧室内马赫数为1.5的非反应性流动进行了研究，重点分析了边界层、空腔上方自由剪切层和激波之间的相互作用。结果表明，自由剪切层对凹腔后壁的冲击导致了强的湍流动能、高的局部压力和压缩波扇。压缩波演变成斜激波，在上下壁之间反射，并与附在两壁上的边界层相互作用。对湍流产生的分析表明，剪切层核心区和再附着点附近的湍流放大主要是由于剪切产生，而减速度产生机制对空腔后壁以上区域和激波干扰点附近的湍流放大有重要影响。在激波/边界层干扰中通常观察到的非常低的频率在本研究中没有观察到，这可能是由于所研究的情况下的低雷诺数。
A Mach 1.5 non-reactive flow in a cavity-stabilized combustor of a model scramjet is studied via a direct-numerical simulation approach, and the analysis is focused on the interaction among boundary layer, free shear-layer above the cavity and shock wave. It is found that the impingement of the free shear-layer on the aft wall of the cavity leads to strong turbulence kinetic energy, high local pressure, and a fan of compression waves. The compression waves evolve into an oblique shock, which reflects between the upper and lower walls and interacts with the boundary layers attached to the two walls. The analysis of the turbulence production reveals that the amplification of turbulence in the core of the shear-layer and around the reattachment point is mainly due to the shear production, but the deceleration production mechanism presents a significant impact in the regions above the aft wall of the cavity and around the shock interaction points. The very low frequency commonly observed in shock wave/boundary layer interactions is not observed in the present research, which might be due to the low Reynolds number of the studied case.