Turbine blade with mate face cooling air flow
US8951014B2 · kind B2 · utility
6Cited by
20References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 15, 2011 |
| Grant date | Feb 10, 2015 |
| Priority date | — |
| Expiry date | Feb 22, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S416/50
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine blade comprises a dovetail, a shank extending from the dovetail, an airfoil, and a platform between the shank and the airfoil. The platform comprises a side wall extending between an upstream side and a downstream side of the platform. A first pin channel extends from the upstream side of the sidewall and a second pin channel, co-axial with the first pin channel, extends from the downstream side of the sidewall. The first channel includes a radial notch at the upstream longitudinal end of the first pin channel.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.