Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air
US11655760B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 5, 2020 |
| Grant date | May 23, 2023 |
| Priority date | — |
| Expiry date | Feb 5, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- 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 comprising an inner wall and an outer wall which are connected by a leading edge and an inner partition so as to delimit an annular cavity, the air intake comprising 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 inner cavity, the air intake comprising at least one acoustic member positioned in the inner cavity facing the ventilation orifice so as to modify the acoustic resonance frequencies and/or to attenuate the acoustic waves formed in the inner cavity via the ventilation orifice.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.