Method and appliance for cooling a gas turbine combustion chamber
US5615546A · kind A · utility
7Cited by
9References
3Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 17, 1994 |
| Grant date | Apr 1, 1997 |
| Priority date | — |
| Expiry date | Oct 17, 2014 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05B2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a gas turbine combustion chamber cooled by means of impingement and convection cooling or pure convection cooling, a compensating flow of the cooling air is guided between adjacent cooling ducts (2) in such a way that the flow velocity in the cooling duct (2) always exceeds a critical limiting value even downstream of a local damage location (6) so that the temperature is less than a critical limiting value. The compensating flow is led past the combustion chamber outer wall. Connecting openings (5) are arranged between adjacent cooling ducts (2) and are respectively offset on the opposite sides of the cooling duct (2).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.