Supersonic Combustor with Parallel Injection

The present study aims to inspect the reacting field characteristics of a parallel injection combustor and identify the Lewis number's influence in modeling a highly turbulent supersonic environment. For this purpose, a two-dimensional Reynolds-averaged Navier–Stokes analysis of a hydrogen jet injected parallelly into a vitiated supersonic air is carried out in which the hydrogen is injected under sonic conditions into incoming air with a Mach number of 2.4. The comparison of predicted temperature at the exit of the combustor shows excellent agreement with the experiment. Analysis of species mass fraction at injector exit denotes a diffusion flame mode of supersonic combustion. The negligible effect of differential diffusion on flame field was identified, concluding that the unity Lewis number assumption is adequate for modeling the present combustor.