Air inlet structure for a turbojet engine nacelle of laminar type
US9938897B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 25, 2014 |
| Grant date | Apr 10, 2018 |
| Priority date | — |
| Expiry date | Apr 28, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0536
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An air intake structure for a turbojet engine nacelle includes an inner panel to be attached to a fan casing, and an external panel capable of a translational movement in a longitudinal direction of the nacelle. The external panel incorporates a portion of an air inlet lip able to provide a junction between the inner panel and the external panel, and each of the air inlet lip portion and the inner panel is equipped, at least in the region of a joining end, with an acoustic attenuation structure. In particular, at least one of the joining ends is equipped with a radial buffer able to come into contact with a corresponding joining flange exhibited by the other joining end when the external panel is in a closed position.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.