Two-stage turbine unit

Claim 1

IN COMBINATION WITH A DOUBLE-STAGE GAS TURBINE JET POWER PLANT, ESPECIALLY FOR THE PROPULSION OF AIRCRAFT, WITH A FIRST POWER PLANT STAGE HAVING AT LEAST ONE COMPRESSOR, AT LEAST ONE COMBUSTION CHAMBER, AT LEAST ONE COMPRESSOR-DRIVING TURBINE, ONLY TWO SEPARATE THRUST DUCTS EACH HAVING A DISCHARGE NOZZLE AND EXTENDING FROM AND CONNECTED TO AN ANNULAR TURBINE EXIT, AND WITH A SECOND POWER PLANT STAGE HAVING A THRUST BLOWER THAT IS DRIVEN THROUGH A SHAFT BY A TURBINE OF THE FIRST POWER PLANT STAGE AND IS ARRANGED IN BACK OF AND COAXIALLY TO SAID TURBINES FOR DRAWING IN AND COMPRESSING AIR THROUGH TWO SEPARATE INTAKE DUCTS WHICH UNITE IN FRONT OF THE STAGE TO FORM AN ANNULAR AIR ENTRY PIPE FOR CONDUCTING THE GAS OUT THROUGH A SINGLE CENTRAL PROPULSIVE DUCT HAVING A DISCHARGE NOZZLE ARRANGED CONCENTRICALLY TO THE LONGITUDINAL AXIS OF THE POWER PLANT, THE IMPROVEMENT COMPRISING: SAID TWO AIR INLET DUCTS OF THE SECOND POWER PLANT STAGE BEING DIAMETRICALLY SYMMETRICAL AND ALIGNED; SAID TWO THRUST DUCTS OF THE FIRST POWER PLANT STAGE AND SAID TWO DISCHARGE NOZZLES OF THE FIRST POWER PLANT STAGE AND BEING DIAMETRICALLY SYMMETRICAL AND ALIGNED WITH THEIR DIAMETRIC LINE OF SYMMETRY BEING SUBSTANTIALLY PERPENDICULAR TO THE DIAMETRIC LINE OF SYMMETRY OF SAID TWO AIR INLET DUCTS OF THE SECOND POWER PLANT STAGE; SAID THRUST DUCTS AND SAID DISCHARGE NOZZLES OF SAID FIRST POWER PLANT STAGE HAVING A NODULAR PROFILE OF SAID FIRST POWER PLANT THE SIDES OF AND PARTIALLY ENVELOPING SAID CENTRAL PROPULSIVE DUCT OF THE SECOND POWER PLANT STAGE AND BEING COUPLED TO IT BY SHAPE.