| 摘要 |
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 two frame-mounted combustion chambers with jet nozzle, regenerative cooling system, one integrated turbopump unit which comprises main turbine, oxidiser and fuel pumps and gas generator mounted below said main turbine. Note here that lower bearing plate accommodates nozzle extensions arranged concentric about jet nozzles. Said lower bearing plate can move along engine lengthwise axis over guide cylinder fitted perpendicular to upper bearing plate communicated, via drive, with combustion chambers. Aforesaid cooled nozzle extensions are made from composite and comprises cooling jackets arranged concentrically about nozzle extensions to make gaps communicated, via flexible pipelines, with fuel pump and fuel manifold. Afore mentioned drive can comprise actuating mechanism and at least two actuating mechanisms. The latter are arranged regularly along nozzle circumference. Actuating mechanism represents either pneumatic or hydraulic cylinder. ^ EFFECT: higher reliability, power output and simplified pneumohydraulic circuit. |
