The effects of shock waves on turbulent mixing layers in a supersonic combustor are investigated. An asymmetric scramjet combustor with strut designed and tested by German Aerospace Center is taken as the physical model. Then Reynolds-averaged Navier-Stokes numerical simulations of the non-reacting cold flow field are carried out. The results demonstrate that the mixing zone containing two mixing layers exhibits a complex thickness variation under the actions of multiple shock waves. In this variation, the thickness decrease at shock wave action positions can be quantitatively characterized by the relative decrease of thickness of mixing layers, while the recovery of thickness increase in the vicinities downstream of shock wave action positions can be quantitatively characterized by the slope increase of thickness variation curve of mixing layers. Both of these characterization parameters are positively correlated with the shock intensity. The physical mechanism of the thickness decrease at the shock wave action positions is that shock waves cause density increase which then lead the thickness to decrease. The physical mechanism of the recovery of thickness increase in the vicinities downstream of the shock wave action positions is that shock waves induce vorticity enhancement which then results in the thickness growth rate to increase.

研究了冲击波对超音速燃烧室湍流混合层的影响。由德国航空航天中心设计和测试的带有支柱的非对称超燃冲压燃烧器作为物理模型。然后进行非反应冷流场的雷诺兹平均Navier-Stokes数值模拟。结果表明，包含两个混合层的混合区在多次冲击波的作用下表现出复杂的厚度变化。在该变型中，可以通过混合层的厚度的相对减小来定量地表征在冲击波作用位置处的厚度减小，而通过冲击角的作用位置的斜率增大可以定量地表征在冲击波作用位置的下游附近的厚度增加的恢复。混合层的厚度变化曲线。这两个表征参数都与冲击强度呈正相关。在冲击波作用位置处厚度减小的物理机理是冲击波引起密度增加，然后导致厚度减小。冲击波作用位置下游附近厚度恢复增加的物理机制是，冲击波会引起涡度增强，从而导致厚度增长速率增加。