Blade feature to support segmented coverplate
US10563525B2 · kind B2 · utility
0Cited by
4References
29Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 5, 2014 |
| Grant date | Feb 18, 2020 |
| Priority date | — |
| Expiry date | Nov 27, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component comprises a blade having a leading edge and a trailing edge. The blade is mounted to a disc and configured for rotation about an axis. A platform supports the blade, and has a fore edge portion at the leading edge and an aft edge portion at the trailing edge. At least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing. At least one coverplate is retained against the disc by the inner wing. A gas turbine engine is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.