Abstract
The strut and wall injection system not only influences combustion in a scramjet combustor but is also useful to overcome the thermal chocking problem. The present work investigates the effect of strut and wall injection system with a cavity-based scramjet combustor numerically. The inflow conditions of stagnation temperature, stagnation pressure, and Mach number are 605 kPa, 1250 K, and 2.5, respectively. The SST k–ω turbulence model along with single-step reaction mechanism has been employed to simulate the fluid flow in the hydrogen-fueled scramjet. The mechanism of the formation of shock waves is analyzed. Further, the comparative analysis of combustion characteristics with strut and wall injection technique is carried out. The results show that the better combustion and probability of mixing can be achieved when the strut injection system is employed in a scramjet combustor.
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