Blade platform with damper restraint
US10724386B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 18, 2017 |
| Grant date | Jul 28, 2020 |
| Priority date | — |
| Expiry date | Oct 20, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine, having: a disk; a plurality of blades secured to the disk, each of the plurality of blades having a platform located between a root portion and an airfoil portion of the blade, wherein the platform of one of the plurality of blades is configured to define a cavity with a platform of an adjacent blade that is secured to the disk; a damper seal located in the cavity and positioned adjacent to a gap defined by edges of the platforms of the blades; and a damper restraint located on an interior surface of each platform, wherein the damper restraint extends into the cavity and is a raised feature configured to contact a peripheral edge portion of a damper seal when it is adjacent to the gap defined by the platforms of the blades.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.