Abstract
Plasma assisted combustion is a promising technology in reducing the emissions and stabilizing the flame propagation and it increases the combustion efficiency. The plasma assisted combustion is used in different applications like detonation engines, ramjet engines and scramjet engines etc. for the plasma discharge we have lot of techniques (dielectric barrier discharge, gliding arc discharge, laser induced …etc.). The supersonic ramjet is a scramjet. In this review, combustion in scramjet engine was discussed with different design parameters like strut design Mach number, air inflow velocity etc. we need to study about the wall pressure, velocity contours and temperature contours in a scramjet engine with plasma assisted combustion. By using the plasma combustion, the variation of combustion characteristics also to be calculated. for the prediction of the flow field in a combustion chamber in scramjet combustor the Reynolds averaged Navier stokes simulation for solving this we used ANSYS FLUENT code.
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