Turbomachine nacelle and anti-icing system and method therefor
US8382039B2 · kind B2 · utility
6Cited by
16References
19Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Dec 30, 2009 |
| Grant date | Feb 26, 2013 |
| Priority date | — |
| Expiry date | May 6, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An anti-icing system for a nacelle of an aircraft engine. The nacelle has an inlet lip that defines a leading edge of the nacelle, and further has an annular-shaped cavity adjacent and delimited in part by an interior surface of the inlet lip. An anti-icing system is located within the cavity and includes a manifold with a cross-sectional shape that conforms to the interior surface of the inlet lip. A wall of the manifold faces the interior surface of the inlet lip, and air is conducted to the manifold to cause heating of the inlet lip via the manifold wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.