Gas turbine engine fan variable area nozzle with swivalable insert system
US8272202B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Oct 12, 2006 |
| Grant date | Sep 25, 2012 |
| Priority date | — |
| Expiry date | Nov 27, 2028 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/36
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbofan engine (10) includes a fan variable area nozzle (FVAN) (50) which effectively changes the physical area and geometry within a fan bypass flow path (40) to manipulate the pressure ratio of the bypass flow. The FVAN generally includes a multitude of aerodynamically shaped inserts (52) circumferentially located about the core nacelle (12). The FVAN at a fully stowed position (takeoff/landing) takes up a minimum of area within the fan bypass flow path to effectively maximize the fan nozzle exit area (44) while in the fully deployed position (cruise) takes up a maximum of area within the bypass flow path to effectively minimize the fan nozzle exit area. By separately adjusting each of the multiple of inserts relative the other inserts the FVAN provides an asymmetrical fan nozzle exit area to selectively vector the fan bypass flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.