Intensively cooled trailing edge of thin airfoils for turbine engines
US7722326B2 · kind B2 · utility
13Cited by
19References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 13, 2007 |
| Grant date | May 25, 2010 |
| Priority date | — |
| Expiry date | Sep 28, 2028 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling system designed to cool the trailing edge of a turbine blade usable in rear stages of a turbine engine. The turbine blade may have a leading edge cooling cavity and a trailing edge cooling cavity separated by an impingement rib. The cooling system may exhaust cooling fluids through the tip of the turbine blade rather than through the trailing edge of the turbine blade to prevent premature failure at the trailing edge of the turbine blade.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.