CHAMBER OF LIQUID-PRPELLANT ROCKET ENGINE Russian patent published in 2001 - IPC

FIELD: rocketry. SUBSTANCE: proposed combustion chamber of liquid-propellant rocket engine with regenerative and transpiration cooling has mixing head with fire plate and nozzles, inner and outer shells and transpiratively-cooled porous insert. Nozzles connect spaces of components with space of combustion chamber being made coaxial, with coaxial-jet injection, including bushing enclosing the tip with ring clearance. Inner and outer shells are arranged in initial part of combustion chamber. Porous insert is located at a distance equal to 15 - 20 inner diameters of bushing from fire plate. Initial section of porous insert has permeability 1.1 - 2.5 times greater than that of other part of insert. EFFECT: provision of reliable cooling of chamber walls at minimum losses of economy and minimum mass of chamber. 4 cl, 2 dwg