FIELD: engine building.
SUBSTANCE: invention relates to liquid-propellant rocket engines. Liquid-propellant engine chamber comprises a combustion chamber, a nozzle and a mixing head with a two-component centrifugal nozzle arranged along its axis, with corresponding collectors of fuel components at inlet of tangential channels of nozzles of external and internal centrifugal nozzles. According to the invention, the gas chamber of the inner centrifugal nozzle is filled with a cylindrical insert with an outer diameter equal to the diameter of the gas vortex in the zone of input tangential channels of the centrifugal nozzle to the zone of hydraulic jumping.
EFFECT: invention provides higher stability of the working process and uniformity of temperature distribution on the wall of the combustion chamber.
1 cl, 2 dwg
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