Cowl and Cavity Effects on Mixing and Combustion in Scramjet Engines
Copyright policy )Cowl and Cavity Effects on Mixing and Combustion in Scramjet Engines
To investigate the supersonic combustion patterns in scramjet engines, a model scramjet engine was tested in the T4 free-piston shock tunnel. The test model had a rectangular intake, which compressed the freestream flow through a series of four shock waves upstream of the combustor entrance. A cavity flame holder was installed in the supersonic combustor to improve ignition. The freestream test condition was fixed at Mach 7.6, at an altitude of 31 km. This experimental study investigated the effects of varying fuel equivalence ratios, the influence of the cavity flame holder, and the effects of cowl shape. As a result, supersonic combustion was observed at equivalence ratios between 0.11 and 0.18. Measurements indicated that the engine thermally choked at a fuel equivalence ratio of 0.40. Furthermore, the cavity flame holder and the W-shaped cowl showed improved pressure distribution due to greater reaction intensity. With the aid of numerical analysis, the cavity and the W-shaped cowl are shown to be effective in fuel–air mixing.
- University of Queensland Australia
- Korea Aerospace Research Institute Korea (Republic of)
- University of Queensland Australia
2210 Mechanical Engineering, 621, ENGINEERING, AEROSPACE, 2103 Fuel Technology, Engineering, 1912 Space and Planetary Science, 2202 Aerospace Engineering, Engineering, Aerospace, Aerospace
2210 Mechanical Engineering, 621, ENGINEERING, AEROSPACE, 2103 Fuel Technology, Engineering, 1912 Space and Planetary Science, 2202 Aerospace Engineering, Engineering, Aerospace, Aerospace
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