United Technologies Corporation

Dennis Cicon

Jonathan Gilson

Oliver V Atassi

Bruce L Morin

Rudolph A Ksiazkiewicz, Jr

Jr Rudolph A Ksiazkiewicz

A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path. A variable area fan nozzle is in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section. The second fan nacelle section is axially movable relative to the 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. The second fan nacelle section includes an acoustic system that has an acoustic impedance located on a radially outer surface.

Gas turbine engine with noise attenuating variable area fan nozzle

A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.

An example liner assembly includes a backing plate that supports a cellular structure covered by a perforated face sheet including a plurality of openings. Each of the plurality of openings is of a size determined to provide desired acoustic performance.

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Coventry, CT, United States of America

Dennis Cicon