Turbojet architecture with two fans at the front
US7412819B2 · kind B2 · utility
25Cited by
4References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 26, 2005 |
| Grant date | Aug 19, 2008 |
| Priority date | — |
| Expiry date | Sep 8, 2026 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.