Gas turbine engine exhaust nozzle
US7578132B2 · kind B2 · utility
30Cited by
16References
65Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Dec 17, 2004 |
| Grant date | Aug 25, 2009 |
| Priority date | — |
| Expiry date | Jun 17, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/505
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the nozzle wherein the nozzle further comprises an actuation mechanism capable of moving the tabs between a first deployed position, where the tabs interact with a gas stream to reduce exhaust noise thereof, and a second non-deployed position, where the tabs are substantially aerodynamically unobtrusive.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.