Gas turbine cooling
US5279111A · kind A · utility
21Cited by
15References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 27, 1992 |
| Grant date | Jan 18, 1994 |
| Priority date | — |
| Expiry date | Aug 27, 2012 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/288
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine having internally cooled thermal barrier coated turbine blades is disclosed. The turbine blades are made from an alloy substrate exhibiting a low coefficient of thermal expansion, an intermediate bond coating and an exterior ceramic coating. Cooling fluid is supplied from the shaft of the compressor where it flows into and out of the turbine blade. Thermal barrier coated turbine blades result in more efficient gas turbine designs.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.