Actuating system for a cascade type thrust reverser
US6000216A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jan 7, 1998 |
| Grant date | Dec 14, 1999 |
| Priority date | — |
| Expiry date | Jan 7, 2018 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thrust reverser is disclosed for a turbojet engine having a cowling with a longitudinal axis, the cowling having an inner surface forming an outer boundary of a gas flow duct and a reverse thrust opening. The thrust reverser has a panel movable with respect to the cowling, the panel being movable between a forward thrust position in which it covers the reverse thrust opening in the cowling and reverse thrust position wherein the opening is uncovered. Thrust reversing cascades are located in the reverse thrust opening of the cowling to direct gases passing through the opening in a reverse thrust direction. A cowling frame is connected through the cowling by a flange engaging a groove on the cowling structure, the flange and the groove having mutually engaging surfaces. A linear actuator is connected to the thrust reverser panel at a first connection and to the cowling frame at a second connection such that the linear force axis when the actuator moves the thrust reverser panel between the forward and reverse thrust positions passes through the first and second connections, as well as the engagement surfaces between the flange and the groove.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.