Thrust reverser for an aircraft bypass turbojet engine nacelle
US12049853B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 17, 2021 |
| Grant date | Jul 30, 2024 |
| Priority date | — |
| Expiry date | May 17, 2041 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thrust reverser for an aircraft bypass turbojet engine nacelle has a generally annular shape around an axis and includes an annular frame for securing deflection grids. The frame has a first frusto-conical wall widening in the downstream direction and including an upstream peripheral edge configured to be attached to a casing of the turbojet engine. A downstream peripheral edge of the wall extends in the continuation of the wall and secures the upstream ends of the grids. A second annular wall extends radially outwards from an outer frusto-conical face of the first wall. The first and second walls are integrally formed and the second wall has axial openings through which actuators pass.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.