OXYGEN-KEROSENE LIQUID-PROPELLANT ROCKET ENGINE WITH HEAT MODULE, HEAT MODULE AND METHOD OF PRODUCTION OF SOOTLESS GAS IN HEAT MODULE Russian patent published in 2004 - IPC

FIELD: rocketry.

SUBSTANCE: proposed oxygen-kerosene liquid-propellant rocket engine with heat module includes engine chamber and turbopumps set whose turbine is connected with regenerative cooling duct. Gas generator and turbine working medium heater are made in form of common heat module including housing at inlet of which mixing head is installed, reaction chamber arranged inside housing and outlet branch pipe connected with main line of oxidizer pump. Heat exchange elements connected with main line to deliver working medium to turbine of turbopumps set are installed lengthwise reaction chamber. Excess fuel afterburning belts are made lengthwise heat module housing being connected with reaction chamber and with pressure main line of oxidizer pump. Outlet of reaction chamber is connected with outlet main line of oxidizer pump. Distance between excess fuel afterburning belts is chosen to provide temperature of combustion products at end of each combustion stage being not lower than temperature of beginning of soot formation. Method of production of sootless high-temperature gas is based on combustion of hydrocarbon fuel with liquid oxygen in reaction chamber.

EFFECT: improved reliability and overall dimensions and mass characteristics of liquid propellant rocket engine.

12 cl, 4 dwg