Turbojet engine nacelle with a cascade thrust reverser comprising a flap control sector
US11891965B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 18, 2021 |
| Grant date | Feb 6, 2024 |
| Priority date | — |
| Expiry date | Mar 23, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/051
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbofan engine nacelle includes a thrust reverser system provided with at least one movable cowl retracting towards a rear reverse-jet position, tilting pivoting flaps which at least partially close an annular flow duct, and opening lateral openings of this annular flow duct equipped with reverser grids. Each movable cowl includes a control sector that slides in a transverse plane, a deflection device linking a fixed part of the nacelle to this control sector in order to make it slide towards a reversal position when the movable cowl retracts, and flap connecting rods linking this control sector to the pivoting flaps, which tilt these flaps, closing the annular flow duct, when the control sector slides towards its reversal position.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.