航空学および航空宇宙工学ジャーナル
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概要

A Numerical Study on the effect of Strut on Scramjet Combustion Intensity at various Mach Numbers

Mayur Anvekar*, Venkatesh R Kusnur, Harshit B Kulkarni

A strut based injector is found to be one of the most promising designs for supersonic combustor. However, scramjet combustor is a complex aero-thermodynamic system having high speed flow with compression waves and thermochemical process. The performance of a supersonic combustor is influenced by various parameters like the inlet Mach number, type of fuel, combustor pressure and temperature. Combustor basically makes use of single and double strut fuel injectors. In the present study, numerical investigation on the effect of using number of struts on combustion is investigated. Also, the influence of the type of fuel used at various equivalence ratios on combustor performance is analyzed. From the investigation it was found that the combustion intensity is single strut is more than the double strut at high pressure with low fuel consumption. The concluding remarks state that hydrogen scramjet combustor is superior to methane scramjet combustor. With increase in equivalence ratio and air stream Mach number, the combustion intensity and fuel consumption rate increases.