Modeling Flame Stabilization in Scramjet Combustors Using a Novel Dual-Rocket Strut with Semi-Circular Trailing Edge

Flame stabilization in the scramjet combustor is important for the successful operation of the propulsion system in an air-breathing hypersonic aircraft. This study presents a novel strut design, referred to as the dual-rocket strut with a semi-circular trailing edge for enhanced combustion performance in a scramjet engine. The performance of the proposed strut is evaluated and compared against conventional fuel injection configurations, including wedge, lobed, and diamond shaped models. The study aims to comprehensively understand the role of fuel injection strut design in fuel and air mixing and its impact on engine combustion efficiency. Numerical simulations were performed using the shear stress transport (SST) k − $\omega$ turbulence model and the finite-rate eddy dissipation combustion model to accurately capture the turbulence and combustion effects. The accuracy of the current numerical predictions has been validated against experimental and computational data for both reacting and non-reacting cases. The results show that the proposed novel strut creates strong recirculation zones, enhancing combustion efficiency by $50\%$ compared to the conventional wedge-shaped strut. However, the lobed strut corresponds to weak recirculation zone and diamond strut with no recirculation zone. The total pressure loss is observed to be $20\%$ for the dual-rocket with semi-circular T.E. fuel injection design, while the wedge strut exhibited a total pressure loss of 10$\%$. Thus, the proposed strut demonstrates potential for use as an effective flame holder. This study can serve as a valuable reference for researchers and industry professionals exploring optimal fuel injection geometries for scramjet combustors.