Numerical exploration of mixing and, combustion in a dual-mode combustor with backward-facing steps
Numerical exploration of mixing and, combustion in a dual-mode combustor with backward-facing steps
复制标题
向后台阶双模式燃烧室混合与燃烧的数值探索
DOI：
10.1016/j.actaastro.2016.06.043
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发表时间：
2016-10-01
影响因子：
3.5
通讯作者：
Liao, Lei
中科院分区：
文献类型：
--
作者：
Huang, Wei;Li, Lang-quan;Liao, Lei
双模超燃冲压发动机燃烧室是航天飞行器联合循环发动机的关键部件。采用雷诺平均N-S方程、Spalart-Allmaras湍流模型和有限速率反应模型对后台阶双模式燃烧室的混合和燃烧进行了数值模拟，并利用湍流扩散燃烧问题的组分分布和马赫数分布对数值方法进行了验证。此外，还探讨了喷油策略和燃料当量比布置对其混合和燃烧流场的影响。结果表明，垂直注入有利于模式转换，垂直注入策略可产生明显的高压区。相应地，它的质量加权平均马赫数下降得更快。较低的总当量比有利于混合增强，燃料当量比偏差也较小。然而，较大的总等效比有利于模式转变。(C)2016年IAA。爱思唯尔有限公司出版。保留所有权利。
Dual-mode scramjet combustor is the crucial component for the combined cycle engine of space mission vehicles. The Reynolds Averaged Navier-Stokes (RANS) equations, Spalart-Allmaras turbulence model and the finite-rate reaction model have been utilized to investigate the mixing and combustion in a dual mode combustor with backward-facing steps, and the species distributions and the Mach number profile of a turbulent diffusion combustion problem have been employed to validate the numerical approach. Moreover, the influences of the injection strategy and the fuel equivalence ratio arrangement on its mixing and combustion flow fields have been explored. The obtained results show that the vertical injection is beneficial for mode transition, and an obvious high pressure region is generated with the vertical injection strategy. Accordingly, its mass-weighted average Mach number drops more sharply. The lower total equivalence ratio is beneficial for the mixing augmentation, as well the smaller fuel equivalence ratio discrepancy. However, the larger total equivalence ratio is beneficial for the mode transition. (C) 2016 IAA. Published by Elsevier Ltd. All rights reserved.