Air intake of an aircraft turbojet engine nacelle comprising ventilation orifices for a de-icing flow of hot air
US11608781B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 22, 2020 |
| Grant date | Mar 21, 2023 |
| Priority date | — |
| Expiry date | Jan 22, 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 facing the axis X and an outer 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 to allow the hot air flow to escape after heating the inner cavity, the ventilation orifice comprising an upstream edge, the circumferential profile of which is discontinuous in order to generate turbulences, and a downstream edge, the radial profile of which is aerodynamic in order to limit the formation of pressure fluctuations.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.