Rear assembly of an aircraft turbojet engine nacelle comprising a thrust reverser with sliding cascades
US11767808B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 20, 2020 |
| Grant date | Sep 26, 2023 |
| Priority date | — |
| Expiry date | Nov 8, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/129
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A nacelle rear assembly of a nacelle of a turbojet engine of an aircraft extends along a longitudinal central axis (A) and includes a sliding cascade thrust reverser. The cascade thrust reverser includes at least one sliding cowl, a deflection cascade including a plurality of rows of vanes that each extend around the longitudinal central axis (A) and that are longitudinally arranged from a first front row of vanes up to a last rear row of vanes, each row of vanes including at least one deflection vane for deflecting the airflow toward the outside of the rear assembly of the nacelle, the deflection cascade being movably integral with the sliding cowl, wherein the deflection cascade includes at least one additional neutral row of vanes that is interposed between the last row of vanes and the sliding cowl and that includes at least one neutral vane.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.