LIQUID-PROPELLANT ROCKET ENGINE CHAMBER Russian patent published in 2017 - IPC F02K9/64 F02K9/52 

FIELD: engines and pumps.

SUBSTANCE: invention can be used while creating gas alternator-free liquid-propellant rocket engines (LRE) operating on cryogenic fuel components. The LRE chamber comprises a regeneratively-cooled combustion chamber with the throat and the nozzle, the mixing head comprising the oxidant supply unit, the fuel supply unit, and the fire bottom unit. Coaxial aligned-jet nozzles are arranged in these units in concentric circles. In the inner cavity of the combustion chamber, heat exchange elements are arranged, made in the form of Field's tubes, whose outer tube inlet and inner tube inlet are connected to the cavities of the fire bottom unit. One of its cavities communicates with the combustion chamber cooling path; in an embodiment version, ribs are made on the outer surface of Field's tubes.

EFFECT: increased pressure in the LRE chamber due to improving the conditions of heat exchange between the fuel combustion products and a fuel component used for driving the turbines of the turbopump units.

2 cl, 3 dwg