Aeroengine nacelle afterbodies
US6516606B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 17, 2001 |
| Grant date | Feb 11, 2003 |
| Priority date | — |
| Expiry date | Jul 17, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention discloses an aeroengine nacelle afterbody of the type comprising a common nozzle for exhausting the mixed hot and cold gases originating respectively from the fan duct and from the aeroengine combustion chamber, the said nozzle having a longitudinal axis more or less coincident with the axis of the said engine. The common exhaust nozzle consists of two half-nozzles which are more or less symmetric with respect to a plane containing the said longitudinal axis, the said half-nozzles being, on the one hand, individually hinged via one of their longitudinal edges to a support structure hanging down from the wing structure or from the fuselage of the aircraft and, on the other hand, lockable together along their opposite longitudinal edges.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.