Tabbed nozzle for jet noise suppression
US6314721A · kind A · utility
118Cited by
22References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 4, 1998 |
| Grant date | Nov 13, 2001 |
| Priority date | — |
| Expiry date | Sep 4, 2018 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present invention relates to a gas turbine engine exhaust nozzle for suppressing jet noise. The nozzle has an arrangement of tabs that extend in radially inward and outward directions. The tabs cause the formation of vortices which pull into mixing engagement the exhaust gas streams from the core and fan ducts and the ambient air. In addition, various construction details are developed for the tab arrangement including tabs that are directed radially inwardly and outwardly, and tabs that are continuous with the nozzle duct therebetween.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.