Comparison of the different shapes of extruded annular nozzle on the fuel mixing of the hydrogen jet at supersonic combustion chamber.

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. • Effect of injector type on mixing performance of single annular extruded nozzle at supersonic flow is studied. • Flow analysis around the extruded nozzle is done to disclose the shock effects on mixing mechanism. • Computational modeling is applied to visualize the compressible flow near extruded nozzle. • Circulation and mixing are compared downstream of various extruded nozzles. [ABSTRACT FROM AUTHOR]