Computational study of transverse oblique injectors for improvement of fuel mixing in scramjet engine of supersonic vehicles

The efficient injection of fuel in the combustion chamber is significant for the advancement of the current supersonic vehicles. This study has focused on the role of non-alignment injector configuration on the fuel mixing of the hydrogen jet inside the combustion chamber of the scramjet engine. The fuel distribution and vortex generation behind both annular and coaxial jets are modeled and compared to disclose the mechanism of fuel diffusion in the combustion chamber. A three-dimensional model of two nozzle angles is produced to visualize the complicated flow interaction of four non-aligned circular jets at supersonic cross-flow. Our results indicate that the strength of the vortex pair produced by the core of the fuel jet is extended more when the angle of the nozzles is increased. The flow visualization of the jet also confirms that the flow becomes more complex in nonalignment jet configurations and fuel mixing is improved by the addition of the internal air jet in the suggested injection model.