Performance Comparison of Three Liquid Propellant Fuels, Kerosene (RP-1), Methane and Hydrogen By CFD
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Authors
1Department of Chemical Engineering, Imam Hossein Comprehensive University, Tehran, I.R.Iran
2عضو هیئت علمی
Abstract
In this research, liquid propellant rocket engine RD-108 which is designed and operated based on kerosene and liquid oxygen fuel, which was modeled and simulated. Then the possibility of using two fuels, methane, and hydrogen, was investigated in that engine. Simulations of the combustion chamber and nozzle are based on modeling of a turbulent flow with combustion reactions. In this modeling, the turbulence model k-ε (RNG) and eddy dissipation concept (EDC) were used for steady flow in two-dimensional symmetric geometry. The results of numerical modeling were validated with experimental data that show a reasonable accuracy. Fuel selection is a key parameter in rocket engine design. Equivalence ratio (oxidant to fuel), combustion chamber temperature, isentropic coefficient, specific impulse, temperature, and average molecular weight of exhaust gases are the most important parameters of fuel performance that have been studied. Their evaluation showed that kerosene fuel has the highest efficiency for the RD-108 engine and by improving the geometry of the nozzle, its efficiency can be increased. On the other hand, hydrogen fuel although has a higher specific impulse But in this engine, its full capacity has not been used and its efficiency has been reduced.
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