Vortex evolution and flame propagation of supersonic reactive mixing layer with the interaction of single/double oblique shock waves are researched by employing direct numerical simulation methods. The vortex dynamics are found to be modulated by oblique shock waves, resulting in mixing enhancement of vorticity values. Notably, wider range of vortex scale distribution induced by double oblique shock waves leads to intense entrainment and nibbling process of large and small scale structures, which can remarkably increase the mixing level of hydrogen and airstreams. The analysis of vorticity transport equation indicates that compressing effects induced by shock waves are responsible for the increase of vortex strength. By tracking the vortex braid dynamical evolution process, it is revealed that local auto-ignition induced by double shock waves can accelerate the consumption of hydrogen and finally lead to high efficiency combustion. Since complex background waves are inherently present in confined space of Rocket-based Combined Cycle (RBCC) engine, the newly observed mixing enhancement mechanism for double shocked-reactive mixing layer can provide a guidance for the future design of mixing strategy using the inherent wave structures in RBCC combustor chambers.

采用直接数值模拟方法研究了单/双斜激波相互作用下超音速反应混合层的涡流演化和火焰传播。涡流动力学被发现受到斜激波的调制，导致涡度值的混合增强。值得注意的是，双斜激波引起的涡尺度分布范围更广，导致大小结构的强烈夹带和蚕食过程，可以显着提高氢气和气流的混合水平。涡度输运方程分析表明，激波引起的压缩效应是涡流强度增加的原因。通过跟踪涡流辫动力学演化过程，结果表明，双激波引起的局部自燃可以加速氢气的消耗，最终实现高效燃烧。由于复杂的背景波固有地存在于基于火箭的联合循环（RBCC）发动机的有限空间中，新观察到的双激波反应混合层的混合增强机制可以为未来使用固有波结构的混合策略设计提供指导在 RBCC 燃烧室中。