LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2010 - IPC F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry, particularly to liquid propellant rocket engines operating on cryogenic oxidiser and hydrocarbon fuel. Proposed engine comprises at least two frame-mounted combustion chambers with jet nozzles incorporating regenerative cooling system. Two, upper and lower, nozzle extensions are fixed concentrically about every jet nozzle on central and lower bearing plates to move along combustion chamber axes, driven by two pairs of drives for each combustion chamber. Said nozzle extensions have actuating mechanism, a motor coupled, via worm gear and screw gear, with central or lower bearing plate arranged on combustion chambers. Note here that screw gear screws pass through nuts fitted in central and lower bearing plates. Each pair of drives is coupled with synchronisation device. Engine incorporates control unit connected with all synchronisation devices. Two pairs of drives are arranged nearby each nozzle in mutually perpendicular planes.

EFFECT: higher reliability, power output and simplified pneumohydraulic circuit.

4 dwg