Flattened nacelle of a turbojet engine
US9777598B2 · kind B2 · utility
1Cited by
2References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 28, 2014 |
| Grant date | Oct 3, 2017 |
| Priority date | — |
| Expiry date | Jan 24, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/14
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.