TWO-LOOP GAS-TURBINE FAN ENGINE Russian patent published in 2008 - IPC F02K3/04 

FIELD: mechanical engineering.

SUBSTANCE: proposed two-loop gas-turbine fan engine has fan, high-head speed compressor, step-up gear, steam-water heater (steam generator), afterburner and turboexpander with heat mass exchange device. It has also three-stage active-reactive turbine with radial-axial third stage whose flow path changes into critical supersound section of de Laval nozzle surrounded by steam accumulator. High-head speed compressor is of combination design with pressure rise degree equal to engine is designed for thrust not less than 150 tons at air flow rate through first loop of 600 kg/s, through second loop of 1200 kg/s and gas temperature before turbine equal to 2000 K. Outer diameter of blades of first row of fan is 4000 mm. Nozzles installed inside body of de Laval nozzle are designed to feed atomic hydrogen to afterburn noncombusted oxidizer. Disks of hinge-head speed compressor are of combination design, provided with delivery centrifugal stages in addition to axial stages. De Laval nozzle has central body through holes in which steam-air mixture is delivered creating outer elastic envelope-pad to change area of passage throat section of de Laval nozzle.

EFFECT: increased reliability and economy of engine.

14 cl, 8 dwg