Catalytic arrangement for gas turbine combustor
US6205768A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | May 5, 1999 |
| Grant date | Mar 27, 2001 |
| Priority date | — |
| Expiry date | May 5, 2019 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02E20/34
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine system includes a compressor side for compressing an air/fuel mixture, and a turbine side for driving the compressor side. A heat exchanger transfers heat from turbine exhaust gases to the air/fuel mixture from the compressor side. A main catalytic combustor is disposed between the heat exchanger and the turbine side for combusting the air/fuel mixture and supplying the resultant products of combustion to the turbine side. The main catalytic combustor has a volume which is sufficient for oxidizing enough fuel to achieve a predetermined turbine inlet temperature, but insufficient for oxidizing all of the fuel. A secondary catalytic combustor is disposed downstream of the turbine side for combusting at least some of the fuel that was not combusted by the main catalytic combustor. The second catalytic combustor typically operates at a lower temperature than the main catalytic combustor. The secondary catalytic combustor may constitute a separate unit, or it may be integrated with the heat exchanger.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.