Kinetic analysis of n-decane–hydrogen blend combustion in premixed and non-premixed supersonic flows

Abstract

Numerical analysis of ignition and combustion of an n-decane–hydrogen fuel blend in a premixed supersonic flow and in a model scramjet duct is performed using a reduced reaction mechanism built especially to describe the oxidation of blended n-C₁₀H₂₂–H₂ fuel in air at the temperature T₀ > 900–1000 K in the pressure range P₀ = 0.1–13 atm. The developed kinetic mechanism involves the principal reactions responsible for chain mechanism development both for n-decane and for hydrogen oxidation. It has been shown that using blended n-C₁₀H₂₂–H₂ fuel makes it possible to enhance the ignition and combustion both in premixed and in non-premixed supersonic fuel–air flows compared to burning pure hydrogen–air and n-decane–air mixtures. This allows high combustion completeness in the scramjet duct at the distance of ∼1 m even at extremely low air temperature T₀ = 1000 K and pressure P₀ = 0.3 atm. This is due to the interaction of kinetics of the formation of highly reactive atoms and radicals, carriers of chain mechanism, in H₂–air and n-C₁₀H₂₂–air mixtures.

Keywords:

• kinetics of ignition and combustion
• n-decane–hydrogen blend
• detailed and reduced reaction mechanisms
• scramjet duct
• numerical simulation

Additional information

Funding

This work was supported by the Russian Foundation for Basic Research [grants 14-08-00743a; 13-01-00786a; 14-08-90034-Бел_а].