Volume No. 6 Issue No.: 2 Page No.: 344-355 Oct-Dec 2011


Computational Analysis of Supersonic Combustion with Co-axial Jet flow


K. M. Pandey* and A. P. Singh

Department of Mechanical Engineering, National Institute of Technology, Silchar, Assam (INDIA)


Received on :




In this Paper study, supersonic combustion of hydrogen using S-A and K-ω Turbulence Model has been presented. The combustor has a single fuel injection parallel to the main flow from the base. Mixing, penetration and combustion characteristics of injected fuel and air in combustor are presented here. Increase in jet to free stream momentum flux ratio will result in the increase of jet penetration to free stream. The ignition delay makes the hydrogen jet mix with the airflow, producing a homogeneous reacting mixture, which does not ignite because the jet temperature is relatively low. Mixing of the cold jet with the hot flow results in an increase in hydrogen-air temperature up to 2420K in S-A model while 2500k in K-ω model, and it is also clear that K-ω model gives higher mach 2.24 than S-A model 2.22 because of the disturbance waves propagating from the flame front are reflected from the flow boundary and, interacting with each other, from a wave structure with compression and expansion zones separated by oblique shock.


Keywords : Supersonic combustion, S-A model, K-ω model, Stagnation temperature, Hydrogen, Mach number