CFD Analysis of Scramjet Engines with Ramp fuel Injector using Non-Premixed Combustion Model
This paper presents the supersonic combustion of hydrogen using ramp based injector with two-dimensional turbulent non-premixed combustion model. The present model is based on the standard k-epsilon (two equations) with standard wall functions which is P1 radiation model. In this process, a PDF (Probability Density Function) approach is created and this method needs solution to a high dimensional PDF transport equation. As the combustion of hydrogen fuel is injected from the ramp based injector, it is successfully used to model the turbulent reacting flow field. It is observed from the present work that, the maximum temperature occurred in the recirculation areas which is produced due to shock wave-expansion and the fuel jet losses concentration and after passing successively through such areas, temperature decreased slightly along the axis. From the maximum mass fraction of OH, it is observed that there is very little amount of OH around 0.013 were found out after combustion. By providing ramp, expansion wave is created which cause the proper mixing between the fuels and air which results in complete combustion.
