Turbine blade with radial cooling channels
US7413406B2 · kind B2 · utility
14Cited by
2References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 15, 2006 |
| Grant date | Aug 19, 2008 |
| Priority date | — |
| Expiry date | Aug 27, 2026 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade is cooled by cooling air that flows through a radial cooling channel. The turbine blade includes a root and an airfoil. The flow of cooling air into the cooling channel is limited by a pre-meter orifice to provide a reduced pressure within the cooling channel. The pressure drop results from the cross-sectional area of the pre-meter orifice being less than the cross-sectional area of the adjacent cooling channel. After flowing through the cooling channel, the cooling air exits the cooling channel through a film hole to form a film layer over the airfoil to cool and insulate the turbine blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.