Translating core cowl having aerodynamic flap sections
US8434309B2 · kind B2 · utility
5Cited by
5References
20Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Oct 12, 2006 |
| Grant date | May 7, 2013 |
| Priority date | — |
| Expiry date | Sep 17, 2029 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K1/15
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An example core nacelle for a gas turbine engine includes a core cowl positioned adjacent an inner duct boundary of a fan bypass passage having an associated discharge airflow cross-sectional area. The core cowl includes at least one translating section and at least one flap section. The translating section of the core cowl is selectively moveable to vary the discharge airflow cross-sectional area.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.