United Technologies Corporation

Raytheon Technologies Corporation

Andre M Hall

Jonathan Gilson

Oliver V Atassi

Ramons Andris Reba

Gregory A Kohlenberg

A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path, and a variable area fan nozzle 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 downstream of the first fan nacelle section. The first fan nacelle section and the second fan nacelle section are axially movable relative to one another to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The auxiliary port is defined between the first fan nacelle section and the second fan nacelle section. The first fan nacelle section comprises a first acoustic system which provides an acoustic impedance configured to attenuate a noise characterized by a leading edge of the second fan nacelle section. The first acoustic system is defined at least in part within a trailing edge region of the first fan nacelle section. A method of reducing a total effective perceived noise level of a gas turbine engine with a variable area fan nozzle is also disclosed.

Variable area fan nozzle for gas turbine engine

A bypass gas turbine engine includes a variable area fan nozzle with a second fan nacelle section axially movable relative to a first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The second fan nacelle section includes a leading edge region that defines a concave external contour and the first fan nacelle section includes a trailing edge region that defines a convex internal contour.

Gas turbine engine with variable area fan nozzle

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

Variable area fan nozzle with acoustic system for a gas turbine engine

A bypass gas turbine engine includes a variable area fan nozzle with a leading edge region that defines an increased airfoil leading edge radius.

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East Hartford, CT, United States of America

Andre M Hall