Corrugated core cowl for a gas turbine engine
US8857151B2 · kind B2 · utility
0Cited by
6References
20Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Sep 14, 2012 |
| Grant date | Oct 14, 2014 |
| Priority date | — |
| Expiry date | Sep 14, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/61
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A core nacelle for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a core cowl positioned adjacent to an inner duct boundary of a fan bypass passage having an associated cross-sectional area that radially extends between a fan exhaust nozzle and the inner duct boundary. The core cowl includes at least one groove that is selectively exposed to change the cross-sectional area at an axial location of the fan exhaust nozzle.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.