Patent ID: 9745918
Date: 2017-08-29
CPC Classifications: F02K,F05D

Claim:
1. A nacelle assembly for a high-bypass 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 flow path; and a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan nozzle having a first fan nacelle section and a second fan nacelle section, said second fan nacelle section axially movable relative said first fan nacelle section to define an auxiliary port at a non-closed position to vary a fan nozzle exit area and adjust fan bypass airflow, said second fan nacelle section including an acoustic system having an acoustic impedance located on a radially outer surface, wherein the acoustic system is located on a fore portion of the radially outer surface, an aft portion of the radially outer surface lacking the acoustic system.