Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface
US8096133B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 13, 2008 |
| Grant date | Jan 17, 2012 |
| Priority date | — |
| Expiry date | Jun 16, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03042
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor liner includes a forward end and an aft end, the aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing a cooling plenum therebetween. A plurality of cooling and dilution air entry holes are formed in the cooling and dilution sleeve and a plurality of cooling and dilution air exit holes formed adjacent an aft edge of the liner such that, in use, cooling and dilution air flows through the cooling and dilution air entry holes, and through the plenum, exiting the cooling and dilution air exit holes, thereby cooling and dilution tuning the aft end of the combustor liner without having to remove the transition piece.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.