Numerical simulation intra-chamber of unsteady turbulent flows stimulate. Part 2

The flow of gas in a solid-fuel rocket engine is determined by the peculiarities of the physico-chemical processes occurring in the combustion chamber and the process of gas outflow from the nozzle. The paper proposes a method for modeling internal unsteady turbulent flows in a rocket engine with a solid fuel charge of a telescopic type. A system of defining equations written in a cylindrical coordinate system describing the flow of a compressible viscous gas is given. A computational algorithm is proposed that belongs to the class of methods using the Godunov approach, developed on the basis of a modified flow vector splitting scheme. The obtained results of a numerical study of the flow in a model rocket engine show the dependence of the gas temperature on the engine wall on the combustion rate of a low-temperature external charge of a telescopic charge.