Patent ID: 7162859

Claim:
A method of operating a variable cycle propulsion system for a supersonic aircraft, the method comprising: providing at least two engines, each engine being configured to produce exhaust gas and provided with a nozzle for generating thrust for supersonic flight speeds, providing at least one separate propulsion assembly dissociated from said at least two engines, said propulsion assembly being configured to generate thrust for takeoff, landing, and subsonic flight speeds and comprising a turbine having a hub with blades and a fan having a hub with blades, the fan connected to said turbine; tapping off, at least during takeoff and landing, at least a fraction of the exhaust gas produced by said at least two engines; feeding said fraction of the exhaust gas to said propulsion assembly; driving said turbine of said propulsion assembly with said fraction of the exhaust gas thereby slowing down said exhaust gas; driving said fan with said turbine; and exhausting air with said fan thereby generating additional thrust from said fan for takeoff and landing.