MULTI-CHAMBER LIQUID-PROPELLANT ENGINE Russian patent published in 2019 - IPC F02K9/60 

FIELD: rocket technics.

SUBSTANCE: invention relates to rocket engineering. Multi-chamber liquid-propellant rocket engine comprises common for all chambers turbo-pump unit, gas generator, automation and control units, frame, and installed in lower part of engine compartment bottom protection from thin-walled sheet material, for example titanium, with cylindrical openings, with nozzles installed through them, made with possibility of swinging chambers with pins, interacting with crossbars connected to frame, wherein on the outer part of the nozzles of the chambers there are circular collars with mating parts fixed thereon with gaps relative to cylindrical bottom protection openings with spherical blisters interacting with cylindrical shells of the bottom protection openings with formation of slotted gaps between them, and annular band on bottom protection periphery, uniformly connected to frame by one group of rods, pairwise and symmetrically arranged relative to openings, and in central part of ring bandage of bottom protection with frame in its central part by another group of rods, wherein above the cylinder bottom openings and equidistant to the cylindrical profiles of the circular openings cutouts and their cylindrical shells, annular tubular bandages are installed, which are rigidly connected to the bottom protection wall by means of cylindrical bushings uniformly located on the tubular band surface, and lateral parts oriented to engine longitudinal axis of symmetry, using shaped U-shaped shaped rods, with installed on the last adjusting elements of vertical displacements along longitudinal axis of the engine and retainers of end positions on ends of the shaped U-shaped profile rods located to the longitudinal axis of the engine, interacting with the circular band in the central part of the bottom protection.

EFFECT: invention reduces thermal effect of combustion products of chambers on engine units.

1 cl, 8 dwg