Composite reaction engine for aircraft with wide ranges of speed

Claim 1

A COMPOSITE JET ENGINE DESIGNED FOR EFFICIENT OPERATION IN THE SUBSONIC AS WELL AS HIGHLY SUPERSONIC RANGE OF AIRCRAFT SPEED, COMPRISING A FIRST JET PROPULSION CHANNEL ENDING REARWARDLY WITH AN ADJUSTABLE CONVERGENT-DIVERGENT NOZZLE, A SECOND JET PROPULSION CHANNEL ENDING REARWARDLY WITH A FURTHER AND DISTINCT ADJUSTABLE CONVERGENT-DIVERGENT NOZZLE, AT LEAST ONE ADJUSTABLE CONVERGENT-DIVERGENT RAMMING INTAKE AT THE FORE END OF SAID CHANNELS, A COMBUSTION CHAMBER WITHIN SAID SECOND CHANNEL INTERMEDIATE THE RAMMING INTAKE AND NOZZLE THEREOF WHEREBY SAID SECOND CHANNEL IS OPERABLE SUBSTANTIALLY ALONG A RAM-JET CYCLE IN SAID SUPERSONIC RANGE, A LOW-PRESSURE COMPRESSOR IN SAID SECOND CHANNEL POSITIONED UPSTREAM OF SAID COMBUSTION CHAMBER, A TURBINE DRIVINGLY CONNECTED TO SAID COMPRESSOR, A FURTHER AND SEPARATE COMBUSTION CHAMBER CONNECTED WITH THE INLET OF SAID TURBINE, A COMPRESSED-AIR GENERATOR IN SAID FIRST CHANNEL, AND AN INTERCONNECTING CONDUIT EXTENDING BETWEEN SAID CHANNELS FOR SUPPLYING SAID FURTHER COMBUSTION CHAMBER WITH COMPRESSED-AIR GENERATOR IN SAID FIRST CHANNEL, AND AN INTERCONNECTING CONDUIT EXTENDING BETWEEN SAID CHANNELS FOR SUPPLYING SAID FURTHER COMBUSTION CHAMBER WITH COMPRESSED AIR DELIVERED BY SAID GENERATOR WHEREBY SAID SECOND CHANNEL IS OPERABLE SUBSTANTIALLY ALONG A TURBOFAN CYCLE IN SAID SUBSONIC RANGE.