Aircraft engine nacelle provided with an icing protection system and associated protection method
US11702213B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 8, 2019 |
| Grant date | Jul 18, 2023 |
| Priority date | — |
| Expiry date | Sep 11, 2041 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft engine nacelle comprising an icing protection system and an icing protection method for such an aircraft engine nacelle. The aircraft engine nacelle comprises an air inlet comprising a lip, a tubular air inlet piece and an icing protection system. The icing protection system comprises an icing prevention means powered continuously by a first electrical energy source and wholly or partly covering the lip, a de-icing means powered by a second electrical energy source covering the tubular air inlet piece and a controller configured to acquire a current total air temperature value, and control the second electrical energy source as a function of the current total air temperature value.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.