Gas turbine with noise attenuating variable area fan nozzle

摘要

A bypass gas turbine engine includes a variable area fan nozzle (40) with a first and second nacelle sections (52,54). The second nacelle section (54) is movable relative to the first nacelle section (52) to define an auxiliary port (60) which varies the fan nozzle exit area (44). The second nacelle section has a leading edge region (62) that defines an increased airfoil leading edge radius (54LR).