Nacelle for the jet engine of an aircraft
US8951006B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 23, 2007 |
| Grant date | Feb 10, 2015 |
| Priority date | — |
| Expiry date | Dec 14, 2029 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure (6) that defines, together with an inner concentric structure (9) for surrounding the downstream portion of the turbojet, an annular flow channel (8), characterised in that a portion at least of said inner structure (9) is mounted so as to be capable of a translation movement along the longitudinal axis of the nacelle so that it can move between a working position, in which the inner structure acts as a casing for the downstream portion of the turbojet, and a maintenance position in which the inner structure exposes said downstream portion of the turbojet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.