Platform cooling core for a gas turbine engine rotor blade
US10907481B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 31, 2019 |
| Grant date | Feb 2, 2021 |
| Priority date | — |
| Expiry date | May 31, 2039 |
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 radially from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform, a first cooling hole that extends circumferentially between a mate face of the platform and the second cooling core, a second cooling hole that extends between a gas path surface of the platform and the second cooling core, the second cooling core radially disposed between the gas path surface and a non-gas path surface, and the second cooling core circumferentially disposed between the first cooling core and the mate face. A method of cooling a blade is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.