1
Bruce L Morin, Rudolph A Ksiazkiewicz Jr, Dennis Cicon: Micro-perforated acoustic liner. United Technologies Corporation, Carlson Gaskey & Olds, June 2, 2009: US07540354 (15 worldwide citation)

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.


2
Jonathan Gilson, Dennis Cicon, Oliver V Atassi: Gas turbine engine with noise attenuating variable area fan nozzle. UNITED TECHNOLOGIES CORPORATION, Carlson Gaskey & Olds P C, August 29, 2017: US09745918

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. ...


3
Jonathan Gilson, Dennis Cicon, Oliver V Atassi: Gas turbine engine with noise attenuating variable area fan nozzle. United Technologies Corporation, Carlson Gaskey & Olds P C, March 10, 2015: US08973364

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


4
Bruce L Morin, Rudolph A Ksiazkiewicz, Dennis Cicon: Micro-perforated acoustic liner. Carlson Gaskey & Olds Pratt & Whitney, November 29, 2007: US20070272483-A1

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.


5
Jonathan Gilson, Dennis Cicon, Oliver V Atassi: Gas turbine engine with noise attenuating variable area fan nozzle. Carlson Gaskey & Olds Pratt & Whitney, December 31, 2009: US20090320488-A1

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