Abstract
We introduce a mathematical model of the nonequilibrium process of thermal decomposition of hydrocarbon fuel in heated channels of a ramjet combustion chamber cooling system. This mathematical model is based on describing the process using intermediate asymptotics formed when taking into account the equilibrium gas composition, which is determined using open source software for calculating the equilibrium state of the chemical reaction products. A procedure was introduced allowing at different stages of the process of thermal decomposition of fuel to separate kinetically irreversible and reversible chemical reactions and to exclude from consideration chemical reactions which remained incomplete in a limited size engine. We present the features of the process of thermal decomposition of liquid and solid fuels which can be used in high-speed aircraft engines.
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