Platform cooling core for a gas turbine engine rotor blade
US10364682B2 · kind B2 · utility
5Cited by
12References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 28, 2014 |
| Grant date | Jul 30, 2019 |
| Priority date | — |
| Expiry date | Mar 20, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/2212
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.