Device for damping vibrations in turbomachinery blades
US5052890A · kind A · utility
23Cited by
9References
4Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Feb 20, 1990 |
| Grant date | Oct 1, 1991 |
| Priority date | — |
| Expiry date | Feb 20, 2010 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S416/50
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a gas turbine engine, a turbine blade vibration damper is located between the underside of a blade platform and a turbine disc, and comprises a member which extends axially parallel to the blade roots. The member has on its outer surface an inverted "V" shaped projection which engages a complementary shaped recess in the underside of the blade platforms. The member has two limbs of unequal length. Centrifugal forces on the longer limb rocks the member and urges the shorter limb into engagement with the disc rim.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.