MULTI-CHAMBER LIQUID PROPELLANT ROCKET ENGINE Russian patent published in 2021 - IPC F02K9/60 

FIELD: rocket engineering.

SUBSTANCE: multi-chamber liquid propellant rocket engine containing a turbopump aggregate common for all chambers, a gas generator, automation and adjustment aggregates, a frame and a base shield installed in the lower part of the engine compartment, with cylindrical openings, with nozzles of chambers with trunnions, configured to swing, installed method, with said trunnions interacting with the traverses connected with the frame, wherein located on the outer part of the nozzles of the chambers are annular collars with counterparts fixed thereon with gaps relative to the cylindrical openings of the base shield by spherical blisters interacting with cylindrical shells of the openings of the base shield, forming slot gaps between said shields therein, the parts of the annular collars not connected with the external parts of the nozzles of the chambers and the counterparts of the blisters are made with cylindrical flanges oriented by the free ends thereof in the direction of the traverses, configured to move telescopically along the longitudinal axes of symmetry of the nozzles of the chambers relative to each other and equipped with movements fixation units.

EFFECT: invention ensures reduction in the thermal impact of the combustion products of the chambers on the aggregates of the engine in the compartment behind the base shield during the return flow thereof from the nozzle cuts by reducing the assembly annular slotted gaps between the blisters and the cylindrical openings of the base shield.

3 cl, 10 dwg