Nacelle drag reduction device for a turbofan gas turbine engine
US7604201B2 · kind B2 · utility
4Cited by
6References
10Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Nov 17, 2006 |
| Grant date | Oct 20, 2009 |
| Priority date | — |
| Expiry date | Nov 24, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/14
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The nacelle drag reduction device comprises a substantially circular and axis symmetrical external airfoil concentric with a aft section of the nacelle and located outside a propulsive jet zone defined behind the engine when operating, the airfoil being positioned at a location providing a maximum streamline angle with reference to the main axis of the engine and a highest streamline curvature.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.