Cooled blade for a gas turbine, method for producing such a blade, and gas turbine having such a blade
US8444375B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 27, 2011 |
| Grant date | May 21, 2013 |
| Priority date | — |
| Expiry date | May 23, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49341
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade for a gas turbine includes an airfoil extending in radial direction of the turbine or longitudinal direction of the blade, respectively, between a platform and a blade tip. The airfoil is bordered across the airfoil by a leading edge and a trailing edge and has a suction side and a pressure side. At the trailing edge a first cooling passage runs parallel to the trailing edge from the platform to the blade tip in the interior of the airfoil. The cooling passage is supplied with a cooling air flow from the platform side, and from which cooling air is discharged through a plurality of cooling holes arranged all over the blade. For such a blade the cooling is optimized by providing a first cooling passage, the passage area of which is tapered in radial direction by between 35% and 59%.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.