Abstract
The fuel mixing mechanism is a critical aspect of the propulsion system of hypersonic vehicles. This study aimed to comprehensively investigate a novel jet configuration that enhances fuel mixing in the combustion chamber. The primary objective was to analyze the significance of vortexes in fuel distribution within the combustion chamber. Computational fluid dynamics was used to investigate the three-dimensional structure of the transverse fuel jet released from an extruded nozzle in a supersonic free stream. The influence of jet type (circular and lobe structure nozzles) and nozzle height was fully explored in this research. The free stream air jet was supersonic (Mach = 4), and the hydrogen jet was injected using various annular nozzles in sonic condition. The results obtained show that the use of an annular circular nozzle is efficient in fuel mixing behind the extruded nozzle. Additionally, fuel mixing improves by approximately 90% when the height of the extruded 3-lobe injector is increased by twice its original length.
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