基于大涡模拟数值方法,文中研究了具有双燃烧室冲压发动机超声速燃烧室工程背景的二维超声速混合层与激波相互作用的情况。强激波入射在混合层上,使当地混合层增长加快,但在下游位置,拟序结构对平均流湍动能的吸收达到饱和,阻碍了混合层增长;超声速气流绕楔流动产生的激波角越大,更大强度的激波入射到混合层上,使其向上偏折更厉害;激波与有反应超声速混合层作用的流场,相对于无激波的燃烧流场,化学反应强度要大很多。

Large eddy simulation was carried out on the interaction between strong shock wave and supersonic mixing layer in DCR's supersonic combustor. The results show that the incidence of strong shock wave in mixing layer induces acceleration of local mixing layer development, while it blocks mixing in the backward sect because of the saturation of eddy absorbing turbulence kinetic energy of the average flow. The bigger shock wave angle induced by supersonic flow round wedge brings the more intense shock and the more deflected mixing layer. There is larger combustion intensity in the reacting supersonic mixing layer flow field with strong shock wave compared to the one without shock wave.