MULTI-CHAMBER LIQUID-PROPELLANT ROCKET ENGINE WITH AFTERBURNING WITH CONTROLLED THRUST VECTOR Russian patent published in 2019 - IPC F02K9/42 F02K9/80 

FIELD: engine building.

SUBSTANCE: invention relates to liquid-propellant rocket engines. Multichamber liquid-propellant rocket engine with afterburning with controlled thrust vector, comprising installed two engine units, each with gas generator, chambers, automatic and control units, frame arranged in central part of engine compartment by turbo pump unit with turbine and pumps, connected by their turbine cavities and cavities after pumps with branched lines of common branch pipes and diverging to chambers of bent symmetric pipelines of supplying respectively generator gas and components to corresponding cavities of mixing heads and cooling circuits of chambers arranged and attached to frames by means of traverses along periphery of engine compartment, wherein in each engine block is located crosswise and orthogonal to the other by its main corresponding longitudinal planes of symmetry and with radially symmetrical arrangement of chambers, wherein in each of engine blocks symmetrical bent pipelines of symmetrical bent pipelines of supply of generator gas and components to corresponding cavities of mixing heads and cooling circuits of chambers are made with identical diameters of cross sections and identical trajectory and are directed by bent parts at connection point with common branch pipe on first unit towards nozzle cuts, and on second side – in reverse side along longitudinal axis of symmetry of liquid-propellant engine side with formation of clearance between pipelines of first unit, and common branch pipes of one and the second motor unit are made gas-dynamically identical, for example, with identical diameters of cross sections, radii, angles, number of turns and lengths of rectilinear and curvilinear trajectories of sections between them.

EFFECT: invention provides expansion of engine functional capabilities with afterburning of generator gas and with controlled thrust vector.

1 cl, 11 dwg