Suspension for mounting a turbojet engine on an aircraft
US8104708B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 5, 2008 |
| Grant date | Jan 31, 2012 |
| Priority date | — |
| Expiry date | Jul 22, 2030 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D27/404
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The present invention relates to an isostatic suspension for mounting a turbojet engine on a pylon of an aircraft, the turbojet engine comprising a front fan, an intermediate casing downstream of the fan with an outer shell and a hub interconnected by radial arms, and an exhaust casing with an outer shell on the same axis XX, the suspension comprising a front attachment on the intermediate casing, a rear attachment with at least two rear attachment links connected to the outer shell of the exhaust casing, a pair of thrust bars being fixed at their upstream ends to the hub of the intermediate casing. It is characterized in that the plane formed by the two links of the rear attachment is inclined with respect to the plane of the exhaust casing.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.