Mathematical model of the “tank – nozzle” cooling system

Abstract

The task of increasing heat transfer of hydrocarbon fuel in the channels of cooling systems of liquid rocket engines is a matter of current interest. The article discusses the results of developing a mathematical model of an engine cooling system operating on super-circulation of fuel between the tank and the nozzle. The model makes it possible to determine the conditions under which the ratio of kerosene circulation in the nozzle cooling circuit would ensure that the selected material is used as the nozzle wall material, to find the minimum amount of kerosene in the tank required for cooling the nozzle by the proposed method.

Keywords

• liquid rocket engines
• cooling system
• heat transfer
• heat exchange
• turbulence transition