Method for film cooling of combustion chamber of LOW-THRUST liquid rocket engines on two-component HYPERGOLIC fuel

摘要

A method for film cooling of low-thrust combustion chamber of liquid rocket engines on two-component hypergolic fuel is based on supply of one of fuel components to the nozzle of film cooling. Supply of one of fuel components, for instance gasoline, to the nozzle of film cooling is carried out through start-shutoff valve that is hydraulically and electrically separated from valves for supply of fuel components to the nozzle head and is opened by connection to the source of electric power supply through thermo-relay of temperature control of wall at its increase to limit of admissible value.