LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2014 - IPC F02K9/60 

FIELD: engines and pumps.

SUBSTANCE: proposed rocket engine has four chambers secured at the frame, turbopump unit secured thereto. Said unit comprises turbine, oxidiser and fuel pumps, heat protection, lines for oxidiser and fuel feed to gas generator and combustion chamber. In compliance with this invention, said frame is an all-welded 3D structure composed by fender and bottom frames interconnected by rods. Note here that crossbars with bearings are secured to bottom frame, journals of chambers being fitted in said bearing to turn about swing axis. Besides, the engine comprises four bent oxidiser gas feed lines with their common manifold connected with turbine outlet. Other eight bends are connected to appropriate heads of the chambers. Note here that sets of flexible pipes with bellows are arranged in said lines perpendicular to said swing axis. Said bellows are connected with fixed part of the line by one butt and, by opposite one, with movable part incorporated with unit of chambers swinging in one plane.

EFFECT: more efficient control over thrust vector, higher specific thrust pulse, perfected design.

12 cl, 28 dwg