Anterior part of a nacelle of an aircraft propulsion assembly having a thermal transition region
US11673681B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 11, 2020 |
| Grant date | Jun 13, 2023 |
| Priority date | — |
| Expiry date | Apr 13, 2041 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An anterior part of a nacelle of a propulsion assembly of an aircraft, having an air intake lip and a front frame disposed at the rear of the air intake lip that connects an outer part to an inner part of the air intake lip. A de-icing duct is formed in front of the front frame. The front frame is shaped so that the de-icing duct has a main cavity and a thermal transition region formed behind the main cavity between an internal face of the outer part of the air intake lip and the front frame. The thermal transition region extends over a longitudinal dimension greater than its average radial dimension, the front frame forming, with respect to the internal face of the outer part of the air intake lip, an angle, measured longitudinally, of between −20° and +10° over the majority of the thermal transition region.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.