Turbojet engine nacelle including a device for absorbing circumferential stresses
US8869506B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 3, 2012 |
| Grant date | Oct 28, 2014 |
| Priority date | — |
| Expiry date | Dec 3, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K1/766
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A nacelle for a turbojet engine of an aircraft is provided that includes a fan case, an internal structure positioned upstream from the fan case, and a thrust reverser positioned downstream from the fan case. The thrust reverser includes a cowl delimiting an external line (LE) and including two removable half cowls. A device for absorbing circumferential stresses are shaped so as to lock the half cowls in the closed position when it occupies a locking configuration on the one hand and for allowing the opening of the half cowls when it occupies an unlocking configuration on the other hand. The stress absorbing device is positioned under an upstream portion of a pylon and is exclusively attached to the half cowls in order to allow the opening of the two half cowls independently of the opening/closing of an external fan cowl.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.