Aircraft propulsion assembly comprising a cold bleed air intake device with variable aerodynamic profile
US11066992B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 25, 2019 |
| Grant date | Jul 20, 2021 |
| Priority date | — |
| Expiry date | Dec 3, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A propulsion assembly for an aircraft comprising a pylon and a bypass turbomachine having a fan duct in which an air flow flows. The turbomachine further comprises an air intake system with a cold bleed air device for bleeding some of the air flow from the fan duct, the device comprising a sliding scoop comprising an upstream face that is open to allow the air to pass and a lower side that has an air outlet opening connected to an exchanger. The scoop is able to slide between an open position in which the scoop extends at least in part into the fan duct and in which part of the air flow in the fan duct rushes into the scoop via the upstream face thereof, and a closed position in which the scoop does not extend into the fan duct and has its upper side closing off the cutout.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.