Method for operating a gas turbine
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United States of America Patent
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app pub date -
Jun 29, 2005
filing date -
Jan 9, 2004
priority date (Note) -
Abandoned
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Abstract
A gas turbine (10) includes a compressor (12) receiving inlet air (18) and producing compressed air, a combustor (14) receiving a combustion portion (30) of the compressed air and producing a hot combustion gas (32), and a turbine (16) receiving the hot combustion gas and producing an exhaust gas (28). The gas turbine also includes a bypass flow path (34) receiving a bypass portion (e.g. 36) of the compressed air and conducting the bypass portion into the exhaust gas to produce a cooled exhaust gas (44). In addition, the gas turbine includes a recirculation flow path (64) receiving a recirculation portion (e.g. 62) of the compressed air and conducting the recirculation portion into the inlet air upstream of the compressor to heat the inlet air.
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