In this study, an inclined injection system with a cavity and grooves arranged in series is developed to enhance the supersonic mixing in a scramjet combustor. Three-dimensional steady Reynolds-averaged Navier–Stokes equations, the two-equation shear stress transport k-ω model, and the finite-rate/no turbulence-chemistry interaction model are used to simulate the flow field structures with and without grooves at different inclination angles. The numerical method used in the study has been verified using experimental data from the open literature, and the static wall pressure distribution of the numerical simulation is in good agreement with the experimental data. The numerical results reveal that the grooved configuration has a significant influence on the flow field structure. The downstream streamline of the structure with grooves is more turbulent and produces more streamwise vortices because the geometry of the grooves enhances the shear effect between the vortex and the high-speed incoming flow. In the case of the grooved configuration, the mixing coefficient at the fuel orifices is slightly lower, but the fuel mixing effect in the downstream is enhanced and gradually exceeds the grooveless configuration. Moreover, the grooved configuration can obtain the best mixing coefficient at a jet angle of 30°. The grooved configuration has a greater stagnation pressure loss than the grooveless configuration.

在这项研究中，开发了一种倾斜的喷射系统，该系统的腔体和凹槽串联布置，以增强超燃冲压燃烧器中的超音速混合。使用三维稳态雷诺平均Navier-Stokes方程，两方程式剪切应力传递k-ω模型以及有限速率/无湍流-化学相互作用模型来模拟在不同位置带有和不带有凹槽的流场结构倾斜角度。该研究中使用的数值方法已经使用公开文献中的实验数据进行了验证，数值模拟的静态壁压力分布与实验数据非常吻合。数值结果表明，槽形对流场结构有重要影响。具有凹槽的结构的下游流线更湍流并且产生更多的沿流方向的涡流，因为凹槽的几何形状增强了涡流和高速进入流之间的剪切作用。在带槽构造的情况下，燃料孔口处的混合系数略低，但是下游的燃料混合效果增强并且逐渐超过无槽构造。而且，开槽构造在喷射角为30°时可以获得最佳的混合系数。沟槽构造比无沟槽构造具有更大的停滞压力损失。燃料孔的混合系数略低，但下游的混合效果增强，逐渐超过无槽结构。而且，开槽构造在喷射角为30°时可以获得最佳的混合系数。沟槽构造比无沟槽构造具有更大的停滞压力损失。燃料孔的混合系数略低，但下游的混合效果增强，逐渐超过无槽结构。而且，开槽构造在喷射角为30°时可以获得最佳的混合系数。沟槽构造比无沟槽构造具有更大的停滞压力损失。