Electrophysics of the combustion of hydrocarbon fuel in the liquid propellant rocket engine chamber

A mathematical model of the generation of an intrinsic electric field in the system high-enthalpy ionized flow–nozzle wall has been developed, and numerical calculations have been carried out in relation to the chamber of a sustainer liquid-propellant rocket engine. The electrical conductivity of a weakly ionized plasma of combustion products of oxygen $+$ kerosene fuel has been determined. Numerical calculations of the electric current to the grounded wall of the nozzle were carried out and were verified with the experimental data of other authors. It was found that the integral value of the current to the wall was $800$–$7500$ mA at a given potential of the nozzle wall of $20$–$250$ mV, depending on the outflow mode. The calculated values of the voltage and current can be used to diagnose the working process in a noncontact way and to build an algorithm for a next-generation engine-emergency protection system for tests at the stand.