A novel strut with sawtooth grooves arranged at the trailing edge of a normal strut was developed to improve the performance of a scramjet combustor. Through numerical simulations, the cold and hot flow fields of scramjet combustors with normal and novel struts were presented at an inlet Mach number of 2.0. The comparison of numerical results with experimental results has proven the accuracy of the numerical method for cold flow and hot combustion fields. The effects of sawtooth grooves on the performance and mechanism of a scramjet combustor were investigated. The results show that streamwise vortices induced by sawtooth grooves promote the macro-transport process, which promotes the diffusion of fuel to both sides of the strut and the mixing of fuel and air. Compared to the normal strut, the novel strut can reduce the distance by 24% for fuel being completely mixed and cut the length by 45.9 and 42.7% for combustion efficiency reaching 95 and 100%, respectively. The cost of this improvement is the increase in the total pressure loss by only 1%. The combustion and heat release processes were significantly enhanced by the sawtooth grooves. Therefore, the arrangement of sawtooth grooves at the trailing edge of the strut can effectively improve the performance of the scramjet combustor, which is promising for further research and optimization.

为了提高超燃冲压发动机燃烧室的性能，开发了一种在普通支柱后缘布置锯齿槽的新型支柱。通过数值模拟，在入口马赫数为 2.0 时，呈现了具有普通和新型支柱的超燃冲压发动机燃烧器的冷热流场。数值结果与实验结果的比较证明了数值方法对冷流和热燃烧场的准确性。研究了锯齿槽对超燃冲压发动机燃烧室性能和机理的影响。结果表明，由锯齿槽引起的流向涡促进了宏观输运过程，从而促进了燃料向支柱两侧的扩散以及燃料与空气的混合。与普通的支柱相比，新型支柱可使燃料完全混合的距离缩短24%，燃烧效率分别缩短45.9%和42.7%，燃烧效率达到95%和100%。这种改进的代价是总压力损失仅增加 1%。锯齿槽显着增强了燃烧和放热过程。因此，在支柱后缘设置锯齿槽可以有效提高超燃冲压发动机燃烧室的性能，有利于进一步研究和优化。