Effect of inner strut on mass diffusion and mixing efficiency of cross fuel jet inside the scramjet combustor

Injection and mass diffusion of fuel jet released in the combustor of scramjet are the primary processes that improve scramjet engine performance. In this work, the presence of the strut fin inner the nozzle injector on the distribution and penetration mechanism of fuel jet at supersonic cross air stream is broadly investigated. The main novelty of this work is to disclose the fuel mixing mechanism inside combustion chamber with strut. Computational fluid dynamic is applied for the simulation of different nozzle types with an inner fin at high -compressible airflow. The type of injectors (3-lobe, circular and 4-lobe injector) and height of strut fin (h = 2 mm and 4 mm) are also investigated in the present research to unveil the impacts of the proposed configuration on the mixing mechanism of fuel jet. Obtained findings show that the use of the inner fin improves the mixing fuel when the strength of the produced vortex is not so high. Comparison of fuel mixing indicates that the 3-lobe injector has higher efficiency (35%) than 4-lobe and circular nozzles.

Automated summary

This study extensively investigates the effects of the inner strut fin in the nozzle injector on the distribution and penetration mechanism of fuel jet in supersonic cross air stream, and reveals the improvement of fuel mixing mechanism with the presence of the strut. Computational fluid dynamic simulations are conducted to examine different nozzle types and strut fin heights on the fuel mixing mechanism. The findings show that the use of the inner fin enhances fuel mixing, with the 3-lobe injector achieving a higher efficiency (35%) compared to the 4-lobe and circular nozzles.