Abstract
The performance of the engine highly depends on the fuel mixing process as a significant process to achieve efficient supersonic flight. Current article has attempted to release the effects of different annular lobe-injectors on fuel mixing when Ma>1. Three various annular jet nozzles are expansively investigated for injection of the sonic hydrogen jet at supersonic air crossflow with Mach-4. Comprehensive comparison of the jet structure of these models are performed through the evaluation of Mach and fuel concentration downstream of these lobe-injectors. Comparison of mixing efficiency also indicates that the nozzle with 3-lobe configuration has 25% more fuel mixing performance than other configurations. Our findings also show that mixing performance of annular lobe-injector is about 15% more than simple one for cases with 2-lobe and 4-lobe injectors.
•Influence of annular lobe-injector on the fuel mixing of hydrogen jet at supersonic flow is studied.•The mixing performance of the air/fuel jets in various jet conditions is investigated.•Effect of various profiles of shock generator on flame distribution is entirely investigated.•CFD approach is applied for the simulation of the co-jets with sinusoidal shock generator.