Numerical analysis of scramjet combustor with innovative strut and fuel injection techniques

In this research paper computational fluid dynamic simulations of scramjet combustor at Mach 2 with innovative strut fuel injections have been presented and discussed. In scramjet combustor fuel and air mixing not taking place at required level due to less resident time of air in the combustor for this innovative struts have been modeled such that it should improve the mixing of air and fuel by creating more shock waves and streamline vortices. The computational geometries considered in this paper are slight modification of the DLR scramjet (German Aerospace Center). The innovative computational models are defined as double strut and strut side fuel injection models. Reynolds averaged Navier-Stokes (BANS) governing equations coupled with implicit and SST k - omega turbulence model have been considered to evaluate scramjet combustor internal flow dynamics and to predict shock formation, streamline structure and combustion phenomenon inside the combustor. Numerical simulations of combustor internal flow dynamics have been carried out by using ANSYS 15-FLUENT code. Chemical reaction kinetics are modeled by global one-step reaction mechanism along with eddy dissipation and finite rate chemistry combustion model. From the numerical simulation results it is observed that ignition delay is decreases with double strut model and better mixing and increased combustion efficiency is obtained with strut side fuel injection technique. (C) 2017 Hydrogen Energy Publications LLC. Published by Elsevier Ltd. All rights reserved.