Nacelle for an aircraft turbojet engine with an extended front lip
US9969499B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Oct 16, 2015 |
| Grant date | May 15, 2018 |
| Priority date | — |
| Expiry date | Jun 24, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A nacelle for an aircraft turbojet engine includes: a substantially cylindrical internal envelope, a substantially cylindrical external envelope, a downstream partition wall and an upstream partition wall secured to the cylindrical internal envelope and a front lip disposed forward of the upstream partition wall. The cylindrical internal envelope includes an upstream portion including an acoustic shroud connected, by an attachment flange, to a downstream portion including a fan casing. In particular, the front lip is extended and disposed over the upstream partition wall by presenting a downstream edge between the upstream and downstream partition walls in order to be secured to a homologous edge of the cylindrical external envelope so as to arrange a maintenance access to the attachment flange.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.