Nacelle rear assembly for turbojet engine
US9003770B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Mar 28, 2008 |
| Grant date | Apr 14, 2015 |
| Priority date | — |
| Expiry date | Oct 14, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/14
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention relates to a nacelle rear assembly for a turbojet engine, that comprises: a hood, an inner structure in the shape of a sheath in which at least the rear portion (15) is of the O-duct type and is capable of axial sliding between an operational position in which it covers the gas generator (3) of said turbojet engine and defines an annular cold-air jet with said hood, and a maintenance position downstream from said operational position. The downstream portion (15) is conformed so as to be capable of sliding without blocking relative to said gas generator (3), and the inner structure includes an upstream portion (13) that can be separated from the downstream portion (15) and that includes at least two doors (13a, 13b) capable of opening towards the outside.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.