Gas turbine engine with noise attenuating variable area fan nozzle
US9745918B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 30, 2015 |
| Grant date | Aug 29, 2017 |
| Priority date | — |
| Expiry date | Sep 24, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/96
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.