Two stage gas turbine propulsion jet unit with thrust diverting means

Claim 1

IN A TWO-STAGE GAS TURBINE JET PORPULSION UNIT, FOR PROPELLING VERTICAL TAKE-OFF AND SHORT TAKE-OFF AIRCRAFTS, WHICH INCLUDES A FIRST PORPULSION UNIT CYCLE WITH AIR COMPRESSOR MEANS, COMBUSTIOIN CHAMBER MEANS AND COMPRESSOR-DRIVE TURBINE MEANS; A CHANNEL SYSTEM INCLUDING A CHANNEL BIFURCATION OPERATIVELY CONNECTED WITH THE OUTPUT OF SAID TURBINE MEANS AND CONTINUING, ON THE ONE HAND, IN A HORIZONTAL THRUST CHANNEL AND EXTENDING SUBSTANTIALLY IN THE LONGITUDINAL AXIS OF THE PROPULSION UNIT AND, ON THE OTHER, IN LIFT CHANNEL BENT AT AN ANGLE TO SAID LONGITUDINAL AXIS, AND CONTROL MEANS IN SAID BIFURCATION OPERABLE TO SELECTIVELY CONTROL THE OPENING AND CLOSING OF SAID THRUST AND LIFT CHANNELS; AND A SECOND PROPULSION UNIT CYCLE INCLUDING LIFT COMPRESSOR ROTOR MEANS OPERABLE TO DRAW IN ATMOSPHERIC AIR FOR SAID SECOND CYCLE AND SUPPLY THE SAME TO SAID LIFT CHANNEL, AND AIR INLET MEANS FOR THE SECOND CYCLE DISPOSED ALONG THE CIRCUMFERENCE OF THE PROPULSION UNIT, THE IMPROVEMENT ESSENTIALLY CONSISTING OF BLADE MEANS CARRIED BY SAID LIFT COMPRESSORE ROTOR MEANS INCLUDING AIR COMPRESSOR BLADE MEANS DISPOSED RADIALLY OUTWARDLY THEREOF, A SET OF SPOKES RADIALLY INWARDLY THEREOF THAT ARE AERODYNAMICALLY INEFFECTUAL AND ROTATE WITHIN SAID THRUST CHANNEL MEANS, AND TURBINE BLADE MEANS INTERMEDIATE SAID AIR COMPRESSOR BLADE MEANS AND SAID SPOKES. SAID LIFT CHANNEL INCLUDING AN INITIALLY APPROXIMATELY LONGITUDINALLY DIRECTED AND SUBSEQUENTLY DOWNWARDLY BENT LIFT-CHANNEL BRANCH WHICH IS SUPPLIED WITH PROPULSION GASES OF THE FIRST PROPULSION UNIT CYCLE AND WITH AIR OF THE SECOND PROPULSION UNIT CYCLE.