1Department of Mechanical Engineering, Sri Ramakrishna Engineering College, Coimbatore, India. E-mail:
2Dr. N.G.P. Institute of Technology, Coimbatore, India. E-mail:
A computational investigation on effect of fuel injection angle on mixing in a staged transverse injection of H2 fuel into supersonic airstream is presented. Numerical results are obtained with the FLUENT code solving SST-KZ turbulence model. The variation of important parameters such as mole fraction of H2, penetration distance of fuel, velocity vectors, stagnation pressure loss and percent area of combustion are taken into consideration and analysed for the injection angles θ = 30°, 60°, 90°, 120° and 135°. Contour plots of mole fraction of H2 and velocity vector plots at various cross sections of the combustion chamber are obtained to qualitatively investigate the mixing process and to quantitatively investigate the same, x-y plots of all the important parameters are obtained from the computational results. Among these angles 120° angle of injection configuration is found to give better results due to the pressure gradients created in the near field regions.
Supersonic flow-jet-mixing-K-ω, turbulence model-backward facing, step-scramjet- bow, shock-Mach disk- convection, diffusion mechanisms
