Numerical Analysis of Supersonic Scramjet Combustion Engine with Double Cavity Configuration at Mach 2 Fuel Injection

One of the unique growing researches in the field of aerospace is an air-breathing propulsion system SCRAMJET. Scramjet has a wide range of application at present from ballistic missile to launching vehicle and inter-orbitary space transportation in future. Scramjet (supersonic ramjet engine), which operation is simple consists of an inlet, combustion chamber, injectors and a nozzle were the combustion process is taking place in a supersonic flow region. Hence the time required for combustion is less than 0.0001s and it is a huge task which develops interest for most researches to improve efficiency of combustion with different methods. This paper is a further continuation of a double cavity region with a back ramp angle from the best performance model in the previous paper which is to be tested in a hypersonic combustion process. The design is carried out in Ansys Design Modeler with 2-dimensional hypersonic vehicle design. The ICEM fine meshing is done near the walls and inside the cavity region. Here the analysis are done in Ansys Fluent 14.5 were liquid hydrogen is used as a major fuel injected at mach 2 with the hypersonic air flow in a non-premixed combustion process and the analysis are carried out with two different viscous models to determine the better performance in terms of combustion. Finally the results are compared by taking the contours of static temperature, turbulence kinetic energy, total pressure, mass fraction of h2, mass fraction of o2, mass fraction of n2 and a comparative graph is plotted which is used to predict the best combustion efficiency between the two turbulence models.