Turbine airfoil cooling system with high density section of endwall cooling channels
US8388304B2 · kind B2 · utility
1Cited by
9References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 3, 2011 |
| Grant date | Mar 5, 2013 |
| Priority date | — |
| Expiry date | May 12, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/81
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling region formed from endwall cooling channels having a higher density of cooling channels than other areas in order to cool the material forming the intersection between the trailing edge of the airfoil and the endwall to prevent premature cracking. The increased density of cooling channels in the endwall at the trailing edge forms a heat sink that draws heat from the airfoil, thereby lowering the temperature of the airfoil and increasing the useful life of the airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.