Convectively cooled liner for a combustor
US5737922A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jan 30, 1995 |
| Grant date | Apr 14, 1998 |
| Priority date | — |
| Expiry date | Jan 30, 2015 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S165/908
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor liner (2) for convectively cooling a combustor chamber (16) in a gas turbine (4) comprises a chamber wall (30) with an array of coolant channels (60) formed therein. Supply manifolds (50) are coupled to the coolant channel inlets for directing bypass air through the channels, where the bypass air removes heat from the chamber wall, and discharge manifolds (52) are coupled to the coolant channel outlets for discharging the heated bypass air to the turbine (10). The coolant channels are spaced and distributed throughout the combustor liner so that the coolant flows through a substantial portion of the liner. The coolant channels are minute channels with relatively short flow paths to minimize both the pressure drop and the quantity of bypass air required to cool the wall. In addition, the channels are completely enclosed within the chamber wall to significantly improve the heat transfer characteristics of the combustor liner. Because the chamber wall is cooled convectively, without bleeding air directly into the combustion chamber, the combustor liner is particularly suited for fuel-rich combustors, such as the first stage of a two stage low NOx combustor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.