Turbojet engine nacelle
US8820344B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 1, 2010 |
| Grant date | Sep 2, 2014 |
| Priority date | — |
| Expiry date | Oct 23, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0645
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside. In addition, the outer structure is equipped with at least one reinforcing beam (10) designed to transmit loads between the annular lip (7) and the cowl (9), said beam (10) extending in the radial plane (P) of the air inlet from the outer structure towards the inner structure and comprising guide means (17) capable of co-operating with complementary guide means (23) belonging to the inner structure. The guide means (17) of the beam (10) and the complementary guide means (23) of the inner structure are offset with r…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.