GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO

摘要

A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a fan pressure ratio of the fan bypass airflow during engine operation, the fan pressure ratio less than about 1.45. In a further embodiment of any of the foregoing nacelle assembly for a gas turbine engine embodiment, the assembly further includes a controller operable to control the fan variable area nozzle.