Experimental determination of the suitable rang of injectors used in the vortex combustion chamber in liquid rocket engine

Vortex combustion chamber which is a new generation of liquid fuel engine with different arrangements of injectors generated a vortex flow into the combustion chamber. This vortex contributed to increased cooling and mixing the components of the propellant in the combustion chamber and can be generated a complete combustion in a small volume chamber. In this chamber several type of injector used in various locations including, centrifugal, flow and vortex injectors. In this study, the design of these injectors and then experimental test to investigate the effect of geometrical parameters on their hydrodynamic characteristics is done using water flow. Spry forming process, flow measurement, pressure drop and injector spray angle including hydrodynamic characteristics that have been studied. The results show acceptable agreement of the predicted design with performance of injectors. Accordingly, centrifugal and flow injectors that injected the fuel and oxidizer into the chamber were selected and shown that increasing the number of tangential vortex injectors to 6, generated more uniformity in the rising vortex flow in the chamber but the entry angle to 5 degrees no significant effect on rising flow.