Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air
US11591960B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 22, 2020 |
| Grant date | Feb 28, 2023 |
| Priority date | — |
| Expiry date | Jan 22, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake extending circumferentially around the axis X and comprising an inner wall, which faces the axis X in order to guide an inner air flow, and an outer wall, which is opposite the inner wall, for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the internal cavity, the air intake comprising at least one disruption member of the external air flow, positioned upstream of the ventilation orifice, which extends outwardly from the outer wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.