Patent ID: 8291690

Claim:
A gas turbine engine comprising: a compressor section; a low spool; a fan; said fan delivering air into said compressor section and into a bypass duct having a variable area nozzle, and said compressor section compressing air and delivering it into a combustion section; the combustion section mixing air with fuel, igniting the fuel, and driving the products of the combustion across turbine rotors, said turbine rotors driving said low spool; a control for said gas turbine engine, programmed to position said variable area nozzle at startup of the engine to increase airflow across said fan; and said control including stored desired positions for said variable area nozzle to provide increased airflow into the compressor at startup at various conditions, said various conditions including the altitude of the aircraft carrying the gas turbine engine, an airspeed of the aircraft, and a speed of at least one spool associated with said gas turbine engine.