FIELD: rocketry, applicable in designing of burner plates of combustion chambers of liquid-propellant rocket engines, as well as in branches of engineering, where burner plates of different kinds are used. SUBSTANCE: injector of the combustion chamber has central fuel nozzles forming the flow core, and peripheral single-component nozzles surrounding the central ones. The peripheral single-component nozzles located at least on one of the circumferences of the injector, whose diameter equals 0.8-1 diameter of the combustion chamber, with a pitch of 0.15 to 0.40 of the diameter of the combustion chamber, have a carrying capacity of 5 to 50% of the total flow rate through all the single-component peripheral nozzles. EFFECT: expanded field of stable operation of combustion chamber with preservation of its economical efficiency determined only by the loss of specific thrust for wall cooling, and by combustion completeness of fuel components in the flow core. 2 dwg
