Gas turbine engine providing simulated boundary layer thickness increase
US7870721B2 · kind B2 · utility
29Cited by
50References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 10, 2006 |
| Grant date | Jan 18, 2011 |
| Priority date | — |
| Expiry date | Nov 28, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0536
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A nacelle assembly for a gas turbine engine includes a fan cowl disposed about an axis, a core cowl within the fan cowl and a bleed passage having an inlet that receives a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The bleed airflow is selectively introduced near a boundary layer of an inlet lip section of the fan cowl.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.