In this study, the combustion of a fuel jet with supersonic air flow has been studiednumerically.The injected gas was a preburned mixture of hydrogen and air with equivalence ratio of 4.5. The flow field was investigated with and without incident oblique shock wave. The simulations have been performed using openFoam software in a three-dimensional field. A two-equation turbulence model, SST-kw, and the PaSR combustion model were used. The aim of this study was to examine the impact of the shock wave on flame stabilization. According to the results, the reaction occurs at low rates without the oblique shock. However, when the incident shock hits the bottom surface downstream of the injection slot, reaction rate increases, indicating the flame stabilization in this case. These findings are in good agreement with experimental results.
Shekarian, A. A., & تابع جماعت, Ø. (2015). Numericalstudy of the effect of an incident shock wave on the combustion of transversalhydrogenjetina supersonic flow. Fuel and Combustion, 8(2), 1-12.
MLA
Ali Akbar Shekarian; صادق تابع جماعت. "Numericalstudy of the effect of an incident shock wave on the combustion of transversalhydrogenjetina supersonic flow". Fuel and Combustion, 8, 2, 2015, 1-12.
HARVARD
Shekarian, A. A., تابع جماعت, Ø. (2015). 'Numericalstudy of the effect of an incident shock wave on the combustion of transversalhydrogenjetina supersonic flow', Fuel and Combustion, 8(2), pp. 1-12.
VANCOUVER
Shekarian, A. A., تابع جماعت, Ø. Numericalstudy of the effect of an incident shock wave on the combustion of transversalhydrogenjetina supersonic flow. Fuel and Combustion, 2015; 8(2): 1-12.
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