CFD Analysis of Cavity Based Combustion of Hydrogen at Mach Number 1.4

This work involves an application of computational fluid dynamics to a problem associated with the flow in the combustor region of a supersonic combustion ramjet engine (Scramjet). The CFD analysis of the combustion process of a scramjet engine having wall injector at different position on the wall of the combustion nozzle with single cavity and double cavity for L/D ratio 10. The main objective of this work is to design the combustion chamber model by using GAMBIT software, study the combustion processes of Air-Fuel (H2) mixture for the wall injector models with inlet air at Mach number 1.4 and inlet fuel at Mach number 1.4. There are several key issues that must be considered in the design of an efficient combustion chamber of a rocket engine. The main objective of this analysis is to compare the various two-dimensional cavity based models. Numerical results are obtained with the FLUENT software shows that duel cavity based combustor model is found to have good overall agreement with results obtained from literature reviews. To delineate the purely fluid dynamic effects, the flow is treated as non-reacting. The grid independent test was also carried out for better accurate results. The various profiles of static pressure, static temperature at various locations of the flow field are presented. Some discrepancies were observed for static pressure and static temperature in the vicinity of the jets due to unsteadiness in the shock system. The both, air intake and the Hydrogen injection are at same Mach speed. It is observed that a maximum temperature of 1340K can be achieved with injection of Hydrogen at mach 1.4 speed and two cavity nozzle of combustion.