Numerical analysis of combustion thermodynamic and kinetic of liquid propellant based on hydrogen and methane

Document Type : Research Article


1 chemical engineering, Imam Hosein comprehensive university.tehran

2 Chemical Engineering- IHU (Imam Hossein University. Tehran.Tehran


The adequate understanding of sustained combustion and performance control in liquid propulsion engines requires sufficient knowledge about combustion chamber conditions, a series of chemical reactions that occur in the combustion chamber, and the thermo-physical variables based on it. For this purpose, after studying the governing equations and simulating the combustion chamber in different equivalence ratios, how the distribution of temperature, chemical reaction rate, and mass fraction of chemical species are presented as the foundation for the challenges of the combustion chamber and related systems design. The simulation results desirably predict and justify many properties related to hydrogen-oxygen and methane-oxygen propellants. For propellant (methane-oxygen) due to the production of carbon monoxide at high ratios of fuel to oxidizer, a decrease in specific impulse, temperature, and chemical reaction rate of propellant in the combustion chamber is observed. The temperature limitation in the "combustion chamber" and the areas near the injectors for this propellant at the equivalence ratio equal to one is much higher than the hydrogen-oxygen propellant. Higher temperatures can cause serious harm to the combustion chamber wall, propellant transmission system, and injectors. Improving the nozzle design can also convert the thermal energy of the combustion gases into kinetic energy and velocity and can increase the specific impulse.


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