Retractable damping device for blades of a turbojet
US4516910A · kind A · utility
34Cited by
9References
4Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 18, 1983 |
| Grant date | May 14, 1985 |
| Priority date | — |
| Expiry date | May 18, 2003 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S416/50
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A retractable damping device for the blades of a turbojet, located between two consecutive blades against the lower face of the platforms of said blades. The damping element, mounted to rotate by one of its ends in the middle part of the space formed between the blades and a rotor disk positioned along an axis perpendicular to a radial axis of the disk, exhibits an upper part which constitutes a projecting dihedral that takes the form of the protruding dihedral consisting of the platforms of the two consecutive blades under the action of centrifugal force.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.