Abstract Numerical simulations are performed for full scale scramjet combustor of a hypersonic airbreathing vehicle with ethylene fuel at ground test conditions corresponding to flight Mach number, altitude and stagnation enthalpy of 6.0, 30km and 1.61MJ/kg respectively. Three dimensional RANS equations are solved along with species transport equations and SST-kω turbulence model using Commercial CFD software CFX-11. Both nonreacting (with fuel injection) and reacting flow simulations [using a single step global reaction of ethylene-air with combined combustion model (CCM)] are carried out. The computational methodology is first validated against experimental results available in the literature and the performance parameters of full scale combustor in terms of thrust, combustion efficiency and total pressure loss are estimated from the simulation results. Parametric studies are conducted to study the effect of fuel equivalence ratio on the mixing and combustion behavior of the combustor.
Highlights Flight sized ethylene fueled scramjet combustor is numerically simulated. 3D RANS equation with k-ε turbulence model and EDM combustion model is used. Methodology is validated against reported results in literature. Combustor performance estimated for different equivalence ratios.
Numerical exploration of mixing and combustion in ethylene fueled scramjet combustor
Acta Astronautica ; 117 ; 305-318
2015-08-25
14 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Scramjet , Mixing , Combustion , Ethylene fuel , CFD
Numerical exploration of mixing and combustion in ethylene fueled scramjet combustor
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