Afterbody for a turbojet engine comprising a nozzle provided with a thrust reverser system that incorporates a crown of noise-reducing chevrons
US10036349B2 · kind B2 · utility
Assignees
Inventors
Key dates
| Filing date | Sep 5, 2014 |
| Grant date | Jul 31, 2018 |
| Priority date | — |
| Expiry date | Nov 14, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/182
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An afterbody for a turbojet engine having a central axis, provided with a nozzle comprising two doors facing each other between two lateral beams. The doors pivot around axes defining a pivot direction, between a retracted position, in which a middle portion of the downstream edge of the doors forms the edge of the outlet section of the nozzle combined with the downstream edges of the two lateral beams, and a deployed position, in which the middle portions of the downstream edges of the pivoting doors come together so as to block the channel between the two lateral beams in order to reverse the thrust of the turbojet engine gases. The edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons alternating with indentations and the afterbody.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.