Combustion Chamber of Liquid Rocket Engine

RU patent № 2196917

The combustion chamber with regenerative cooling system includes the nozzle and nozzle extension. Nozzle extension is docked to the nozzle incorporated into the combustion chamber of liquid rocket engine without changing the initial nozzle configuration. Longitudinal contour of the nozzle extension is made on curve described by polynomial of third degree. Thickness of the nozzle extension wall is determined as d_wall=k*d_chem, where k - coefficient of material reserve in thickness at considering the magnitude of material permeability to gas, d_chem - depth of material chemical decomposition which is determined by combustion products temperature and the concept of oxygen-containing compounds in the combustion products with regard to thermal boundary layer (thermal film injector) earlier formed near the nozzle wall.
The intention allows one to increase energy characteristics of liquid rocket engines at simultaneous reduction of mass, dimensions and cost of the design.