Gas turbine: seal between adjacent can annular combustors
US7870738B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 29, 2006 |
| Grant date | Jan 18, 2011 |
| Priority date | — |
| Expiry date | Feb 15, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present invention is directed to a seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for sealing pressure drops of 0.5 bar or greater. The seal includes a plate configured to extend between adjacent transition sections and the plate may have at least one perforation extending from the front surface of the plate to the rear surface of plate. The seal further includes a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix may be fixedly attached to a surface of the plate.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.