Computational Analysis of Effect of Injection Angles in Strut Based Scramjet Combustor

The present study is to investigate the reacting flow properties of supersonic flow in a strut-based scramjet combustor, with specific emphasis on the utilization of different injection strategies. In order to investigate the effects on the system, a three-dimensional DLR Scramjet combustor with multiple injections and varying injection angles on the triangular wedge is considered. Three numbers of injectors with parallel, upward and downward injections at angles of 15° and 30° are analyzed. The numerical analysis was conducted under the constant total pressure of 7.82 bar, 340 K of temperature and with the air speed as Mach 2 at the inlet. The findings indicate that the positioning of injector location and the shape has an influence on promoting flame stabilization. Additionally, the injection angles play a crucial part to reduce the intensity of the shockwave. The numerical analysis involves steady state RANS equation with the SST k-ω turbulence model. The obtained results were analyzed by examining the critical variables such as wall and centerline static pressure and density contours across the combustor length. The observed results demonstrate that angled injection exhibits more effective mixing compared to the parallel injection of all the struts, with the evidence of wall static pressure.