NUMERICAL ANALYSIS OF DIFFERENT TYPES OF FUEL INJECTOR IN SCRAMJET ENGINE BY USING FLUENT

At present the foremost promising propulsive systems; the scramjet engine has drawn the attention of the many researchers. The two-dimensional coupled implicit NS equations, the standard k-ε turbulence model and therefore the finite-rate/eddydissipation reaction model is applied to numerically simulate the flow field of the hydrogen fuel scramjet combustor with a unique kind of fuel injectors like single wall, double wall, and Pylon structure is compare with the basis of Temperature, Pressure and velocity variation, Mass fraction of H2, O2 and total energy. The results obtained by CFD simulation shows that the numerical methodology employed in this study is appropriate to simulate the flow field of the scramjet combustor. Finally, we tend to analyze the pylon kind fuel injector and conclude that this kind of injector provides the most effective results as compare to other. Temperature is enhanced by nearly 35th as compared to previous one. Pylon injector provides a higher admixture of air-fuel and complete combustion in an economical manner because of this energy is magnified and emission is reduced. From this study, we are able to conclude that Pylon kind of injector could solve the recent drawback of scramjet combustor in use and this analysis shows the answer relating to stabilized flow. From flow phenomenon, we are able to see the stability of flow that is the major drawback with planer strut injector as which offer limitation in mach no of the engine, however, could give continuous flow and combustion through the flight. The eddy generated within the pylon acts as a flame holder within the combustor, and it will prolong the duration of the mixture within the supersonic flow.