Damping device for turbojet engine fan blades
US4494909A · kind A · utility
31Cited by
5References
4Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Dec 3, 1982 |
| Grant date | Jan 22, 1985 |
| Priority date | — |
| Expiry date | Dec 3, 2002 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S416/50
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A damping device for the turbojet engine fan blades which includes a wedge placed between the platforms of the blades, the shanks of the blades, and the disc. The wedge consists of a hollow, bellows-shaped body fitted with an axial stop member, the body being inflated after mounting so that it takes up all the space between the platforms of the blades, the blade shanks and the teeth of the disc. The invention is used for damping device of turbojet engine blades.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.