FIELD: rocketry.
SUBSTANCE: invention relates to liquid-propellant rocket engines operating with generator gas afterburning. Disclosed is a chamber of a liquid-propellant engine operating with the afterburning of a reducing generator gas, consisting of lines for the supply of fuel components, a mixing head with a cooling cavity of the fire bottom, a cylindrical part, subsonic and supersonic parts of the nozzle, according to the presentation, in the supersonic part of the cooling path in the high-pressure cavity, a cavity of the cooling path is made with reduced pressure, connected to the cooling cavity of the fire bottom of the head, while the connection of parts of the supersonic part of the nozzle along the inner and outer walls is made in the cavity of the low pressure cooling path.
EFFECT: invention ensures operability of the joints of the sections of the supersonic part of the chamber, which operates on the regenerative generator gas.
1 cl, 4 dwg
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