Gas turbine engine with low stage count low pressure turbine

A gas turbine engine (10) comprising: a core nacelle defined about an engine centerline axis; a fan nacelle mounted at least partially around core nacelle to define a fan bypass airflow path for a fan bypass airflow; a gear train (22, 25) defined along an engine centerline axis, said gear train defines a gear reduction ratio of greater than or equal to about 2.3; a spool along said engine centerline axis which drives said gear train, said spool includes a three to six (3-6) stage low pressure turbine; and a fan variable area nozzle axially movable relative to said fan nacelle to vary a fan nozzle exit area (44) and adjust a pressure ratio of the fan bypass airflow during engine operation.