LIQUID-PROPELLANT ROCKET ENGINE CHAMBER Russian patent published in 2003 - IPC

FIELD: liquid-propellant rocket engines. SUBSTANCE: liquid-propellant rocket engine chamber is provided with regenerative cooling system, propulsive jet nozzle and head which is coupled with nozzle without change in nozzle configuration. Longitudinal contour of head is made over curve described by third-degree polynomial. Thickness of wall of this head is determined as δ_wall = k•δ_chem,, where k is coefficient of margin of material in thickness taking into account amount of gas permeability of material; δ_chem is depth of chemical fracture of material determined depending on temperature of combustion products and concentration of oxygen- containing compounds in combustion products taking into account thermal boundary layer (thermal screen) which was formed near wall of nozzle. EFFECT: improved power characteristics; reduced mass and overall dimensions; low cost. 1 dwg