Gas turbine combustion apparatus
US4872312A · kind A · utility
58Cited by
3References
1Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 19, 1987 |
| Grant date | Oct 10, 1989 |
| Priority date | — |
| Expiry date | Mar 19, 2007 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03044
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine cooling apparatus is disclosed in which a flow sleeve is provided to surround a combustor liner and a tail pipe substantially over their full length. A group of small holes for impinge-cooling an outer wall of the tail pipe are formed in a region of the flow sleeve close to a turbine. Further, opening portion for introducing cooling air are provided closer to the combustor liner than the small holes. Thus, the outer wall of the tail pipe and the wall of the combustor liner are cooled by the cooling air flowing between the tail pipe, the combustor liner and the flow sleeve.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.