Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors
US10100780B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 30, 2016 |
| Grant date | Oct 16, 2018 |
| Priority date | — |
| Expiry date | Nov 30, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/42
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. The nacelle is notable in that it includes a shaped device for activation of the door, during their activation from a closed position to an open position of the door, to drive the door in a combined movement that is translational in the direction running upstream from the nacelle and rotary towards the exterior of the nacelle.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.