FIELD: technological processes.
SUBSTANCE: invention relates to cooling of liquid-propellant rocket engines. Disclosed is a liquid-propellant engine chamber operating with afterburning of generator gas, comprising a mixing head with mixing elements, a housing of a chamber with a fuel supply collector located thereon, toroidal gas duct in the area of minimum cross-section and uncooled metal nozzle, according to the statement between the cooling channels in the housing of the chamber in front of the coolant supply header there are holes connecting the gas duct cavity with the inner cavity of the housing of the chamber.
EFFECT: invention provides higher energy characteristics, longer service life and improved mass characteristics.
1 cl, 2 dwg
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