In this study, the performances of a Mach 9 oblique detonation engine fueled by hydrogen are numerically investigated by solving the multi-species reactive Reynolds-averaged Navier-Stokes (RANS) equations with a detailed combustion mechanism. The fuel is perpendicularly pre-injected into the core airflow in the engine inlet by three parallel strut-injectors. It is demonstrated that mixing can be enhanced by the baroclinic effect of oblique shock waves, the incipient expansion of fuel jets and the intensive momentum exchange of vertical jets into the crossflow, resulting in a well-mixed fuel-air core flow before entering the combustor. Analyses of the two most dangerous zones that bear potential of pre-ignition suggest that no pre-combustion occurs in the inlet. Benefiting from the floor bleed structure, the upstream movement of the shock waves stops at the combustor's entrance and they remain stabilized in the combustor thereafter. Finally, the combustor is proved to work under the stable detonation mode of combustion, and the supersonic fuel-air mixture is fast burnt through the steady detonation waves generated in the combustor. The concept of the pre-injection oblique detonation engine has been numerically demonstrated, which provides a significant reference to further experimental studies and future engineering applications.

在这项研究中，通过求解具有详细燃烧机理的多物种反应性雷诺平均Navier-Stokes（RANS）方程，对以氢为燃料的Mach 9斜爆发动机的性能进行了数值研究。燃料通过三个平行的支柱式喷射器垂直预喷射到发动机进气口的核心气流中。结果表明，斜向冲击波的斜压作用，燃料射流的初期膨胀以及垂直射流进入横流的强烈动量交换可以增强混合，从而在进入燃烧室之前使燃料-空气核心流充分混合。 。对具有预燃潜力的两个最危险区域的分析表明，进气口未发生预燃烧。受益于地板出血结构，冲击波的上游运动在燃烧器的入口处停止，此后它们在燃烧器中保持稳定。最后，证明燃烧器在稳定的燃烧爆震模式下工作，并且通过燃烧器中产生的稳定的爆燃波来快速燃烧超音速燃料-空气混合物。数值模拟表明了预喷射斜爆震引擎的概念，为进一步的实验研究和未来的工程应用提供了重要参考。