Aircraft engine rear suspension with thrust recovery
US7108224B2 · kind B2 · utility
19Cited by
0References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 6, 2004 |
| Grant date | Sep 19, 2006 |
| Priority date | — |
| Expiry date | May 6, 2024 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D27/406
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A suspension of the turbo fan engine to an aircraft pylon, includes a fitting arranged to be attached to a pylon, a lever fastened in its central portion to the fitting via a linking device with a pivot pin. Two thrust rods are each connected by an end to the lever and including at the other end of the fastening device to the engine. The linking device is composed on the central portion of the lever, of two parallel branches apart from one another, and on the fitting, of a central fastening tab, whereas the fastening tab and both branches are held together by dint of the pivot pin.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.