Gas turbine engine bifurcation located fan variable area nozzle
US11391240B2 · kind B2 · utility
0Cited by
96References
30Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Mar 30, 2021 |
| Grant date | Jul 19, 2022 |
| Priority date | — |
| Expiry date | Mar 30, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/327
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbofan gas turbine engine includes a core engine within a core nacelle, a fan nacelle at least partially surrounding the core nacelle to define a bypass flow path and a variable fan nozzle exit area for bypass flow, and a pylon variable area flow system which operates to effect the bypass flow. A method of operating a turbofan gas turbine engine is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.