LIQUID-PROPELLANT ROCKET ENGINE CHAMBER Russian patent published in 2022 - IPC F02K9/64 F02K9/97 

FIELD: rocket technology.

SUBSTANCE: invention relates to rocket technology. A chamber of a liquid-propellant rocket engine containing a combustion chamber equipped with a cooling path with longitudinal channels with transverse bridges, an inlet manifold for supplying the missing component in the gas generator with a minimum cross section towards the nozzle exit, and an outlet manifold located at the mixing head and connected by a pipeline to the inlet manifold cooling path with longitudinal channels and transverse bridges of the nozzle, by the outlet manifold of the cooling path of the latter connected by a pipeline with a mixing head, while the sections of the transverse jumpers in the interface zone of the inlet manifolds of the nozzle and the combustion chamber are discontinuous and placed alternately between the longitudinal channels in the circumferential direction, the inlet manifold of the nozzle is located between the minimum section of the nozzle and the inlet manifold of the cooling path combustion chambers, and the longitudinal channels of the cooling paths of the combustion chamber and nozzle in the interface zone with the inlet manifolds are connected at the transverse jumpers alternately by radial channels with the same inlet manifolds. The walls of the discontinuous transverse jumpers in the zone of conjugation of the inlet manifolds in the radial direction are made of a V-shaped profile and are oriented with their vertices in the directions opposite from the radial channels.

EFFECT: invention provides a reduction in the hydraulic resistance of the cooling path by reducing the temperature of the nozzle in the area of ​​the transverse bridges and reducing the temperature unevenness of the nozzle wall and the combustion chamber, as well as reducing the inlet pressure of the fuel at the inlet to the cooling path and reducing the weight of the nozzle and chamber.

2 cl, 5 dwg