GAS-TURBINE ENGINE Russian patent published in 1997 - IPC

FIELD: manufacture of aircraft engines. SUBSTANCE: gas-turbine engine has low-pressure compressor connected to inlet of high-pressure compressor, combustion chamber connected to outlet of high-pressure compressor, flame tube of combustion chamber connected to inlet of centripetal radial axial turbine, two-stage two-rotor centripetal radial axial turbine with opposite rotation of rotor; flame tube of combustion chamber, nozzle unit of centripetal radial axial turbine and rotor wheel of second stage of turbine are made integral; provision is made for second combustion chamber connected to outlet of low-pressure compressor, flame tube of second combustion chamber connected to outlet of centripetal radial axial turbine, jet nozzle connected to outlet of flame tube of second combustion chamber. Rich mixture of combustion products is fed to flame tube of second combustion chamber from flame of first combustion chamber through centripetal radial axial turbine where it is mixed with air fed from low-pressure compressor and burnt. EFFECT: enhanced efficiency. 6 dwg