Turbine blade with blade tip cooling passages
US7922451B1 · kind B1 · utility
45Cited by
18References
17Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Sep 7, 2007 |
| Grant date | Apr 12, 2011 |
| Priority date | — |
| Expiry date | Feb 3, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade for use in an industrial gas turbine engine, the blade having a squealer pocket with a plurality of discrete curved cooling channels to cool the blade tip and to reduce the hot gas flow leakage across the tip. The curved cooling channels include a side wall cooling channel, a tip rail crown cooling channel and an inner tip rail wall cooling channel all discharging cooling air from a cooling supply channel within the airfoil. Both the pressure side and suction side tip rails include this arrangement of cooling channels.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.