Turbomachine nacelle and anti-icing system and method therefor
US8549832B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Dec 30, 2009 |
| Grant date | Oct 8, 2013 |
| Priority date | — |
| Expiry date | Mar 12, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An anti-icing system and method for an aircraft engine nacelle. The nacelle has an inlet lip that defines a leading edge of the nacelle and has a cross-sectional shape and oppositely-disposed exterior and interior surfaces. An anti-icing system contacts at least the inlet lip of the nacelle. The anti-icing system includes at least one heating element having a cross-sectional shape that conforms to the cross-sectional shape of the inlet lip and in which carbon nanotubes are oriented and arranged to conduct electrical current through the heating element. Passing an electrical current through the heating element causes Joule heating of the heating element and heating of the inlet lip by thermal conduction.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.