A REVIEW ON VARIOUS FUEL INJECTION SYSTEMS IN SCRAMJET COMBUSTOR

Abstract

The scramjet appears to be among the most promising propulsion solutions for the future, attracting attention of many researchers and experts. The major concern is the complicated mixing of air and fuel phenomena within the combustor. The supersonic flow inside combustor causes improper air and fuel mixing in scramjet engines. The flame in stabilizes due to less air resident time, affecting output efficiency and resulting in fuel energy loss. The primary purpose of previous researches is to increase the performance of scramjet engines by improving supersonic mixing and combustion. Furthermore, beyond previous research endeavors investigating diverse fuel injection techniques within the supersonic combustor, this paper will delve into multiple fuel injection designs aimed at enhancing the combination of air and fuel.
Additionally, it will demonstrate the reacting flow attributes associated with various ramp positions in a scramjet combustor featuring strut injection. Reduced fuel consumption in the combustor also exerts a considerable influence on efficient use of fuel energy in aviation field. A strut-based injector appears as an excellent design solution for a supersonic combustor. Conversely, a complex aero-thermodynamic system incorporating high-speed flow, compression waves, and thermochemical reactions represented by the scramjet combustor. The performance of a supersonic combustor is affected by numerous factors, such as the input Mach number, the type of fuel used, combustor pressure, and temperature.