Reduced take-off field length using variable nozzle
US8935073B2 · kind B2 · utility
4Cited by
21References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 12, 2006 |
| Grant date | Jan 13, 2015 |
| Priority date | — |
| Expiry date | Mar 6, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbofan engine control system and method includes a core nacelle housing (12), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan nacelle (34). A bypass flow path (39) is arranged downstream from the turbofan between the core and fan nacelles. The bypass flow path includes a nozzle exit area (40). A controller (50) detects at least one of a take-off condition and a landing condition. The controller changes effectively the nozzle exit area to achieve a thrust vector in response to the take-off and landing conditions.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.