Nacelle for an aircraft turbojet engine provided with a hydraulic roto-linear actuator of a thrust reverser and of a variable-section nozzle
US10190605B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jun 18, 2018 |
| Grant date | Jan 29, 2019 |
| Priority date | — |
| Expiry date | Jun 18, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present disclosure concerns a nacelle for an aircraft turbojet engine that includes a thrust reverser having a cowl displaceable between a deployed position and a stowed position, a fixed structure, and a secondary nozzle. The nozzle includes panels movable in rotation, and hydraulic actuators for sequenced actuation of the cowl and panels. The actuators include a body mounted on the fixed structure, and a rod mounted in the body and is linked to the cowl and panels via a device for transmitting movement of the actuator to the panel. An actuation system having a hydraulic control device controls the displacement of the rod of the actuator. The actuator further includes a device for alternately displacing the rod in translation relative to the body to cause translation of the cowl, or in rotation relative to the body to cause rotation of the nozzle panel.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.