Gas turbine engine bifurcation located fan variable area nozzle
US9885313B2 · kind B2 · utility
8Cited by
36References
31Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jan 5, 2012 |
| Grant date | Feb 6, 2018 |
| Priority date | — |
| Expiry date | Oct 10, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/327
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a core engine defined about an axis, a gear system driven by the core engine, a fan, and a variable area flow system. The gear system defines a gear reduction ratio of greater than or equal to about 2.3. The fan is driven by the gear system about the axis to generate a bypass flow. The variable area flow system operates to effect the bypass flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.