Patent ID: 8800914

Claim:
A gas turbine engine comprising: a core nacelle defined about an engine centerline axis; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass airflow path for a fan bypass airflow; a gear train defined along an engine centerline axis, said gear train defines a gear reduction ratio of greater than or equal to about 2.3; a fan drive turbine along said engine centerline axis which drives said gear train, said fan drive turbine including three to six (3-6) stages; and a fan configured for rotation within the fan nacelle for operation at a fan pressure ratio less than about 1.45, wherein said fan is driven by said spool through said gear train. a fan variable area nozzle axially movable relative to said fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.