Turbomachine nacelle and anti-icing system and method therefor
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Oct 8, 2013
Grant Date -
Jul 14, 2011
app pub date -
Dec 30, 2009
filing date -
Dec 30, 2009
priority date (Note) -
In Force
status (Latency Note)
Importance
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.
First Claim
Family
International Classification(s)
Cited Art Landscape
Patent Citation Ranking
Recipient Email Address
Recipient Email Address
Comment
Recipient Email Address
Add to Portfolio(s)
To add this patent to one, or more, of your portfolios, simply click the add button.
This Patent is in these Portfolios:
Add to additional portfolios:
Last Refreshed On:
Changes done successfully