MULTI-CHAMBERED LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2017 - IPC F02K9/60 F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: multi-chamber liquid-propellant rocket engine containing a turbopump unit common for all the chambers, a gas generator, automation and control units, a frame and bottom protection with cylindrical openings, mounted at the bottom of the engine compartment, with nozzles installed through the openings, adapted for pumping the chambers, with trunnions interacting with the cross-members connected to the frame, wherein on the exterior of chambers nozzles the annular clamps are formed, with mates with gaps fixed thereon relative to the cylindrical bottom protection openings, spherical blisters interacting with cylindrical shells of the bottom protection openings to form gap clearances between them. Between the annular clamps in the outer parts of the nozzles and the blisters mates, eccentric joints are mounted, cylindrical inner surfaces thereof are mounted with annular clamps nozzle and the outer cylindrical surfaces of which, formed eccentrically with respect to their cylindrical inner surfaces, are mounted by the cylindrical surfaces of spherical blisters formed eccentrically to the outer edges of the spherical blisters.

EFFECT: reduction of heat exposure of chambers combustion products to the engine units in the compartment behind the bottom protection during their return flow from the nozzle sections by reducing the mounting annular slit gaps between the blisters and the cylindrical openings of the bottom protection.

2 cl, 9 dwg