Gas turbine rotor blade
US7497661B2 · kind B2 · utility
8Cited by
8References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 25, 2005 |
| Grant date | Mar 3, 2009 |
| Priority date | — |
| Expiry date | Mar 1, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/81
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade for a gas turbine, in particular a turbojet, the blade comprising an airfoil, a platform connecting the airfoil to a blade root and having at least one stiffener extending under the downstream portion of the platform, together with means for cooling the blade by a flow of cooling fluid in ducts formed in the blade and in a cavity formed in the stiffener substantially in register with the trailing edge of the blade, and including outlet orifices facing downstream.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.