Catalytic arrangement for gas turbine combustor
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United States of America Patent
Stats
-
Mar 27, 2001
Grant Date -
N/A
app pub date -
May 5, 1999
filing date -
May 5, 1999
priority date (Note) -
Expired
status (Latency Note)
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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.
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