Patent ID: 6389796
Filing Date: 2002-05-21
Classification: F01K,Y02E

Abstract:
A gas turbine system comprising:a compressor for compressing combustion air; a fuel line for supplying fuel; a combustor for receiving the fuel supplied by said fuel line, for receiving the compressed combustion air compressed by said compressor, and for burning the fuel with the compressed combustion air so as to generate a high-temperature gas; a gas turbine for receiving the high-temperature gas generated by said combustor, said gas turbine being operable to be driven by the high-temperature gas so as to generate exhaust gas, and an exhaust gas compressor for receiving at least a portion of the exhaust gas generated by said gas turbine and for pressurizing the at least a portion of the exhaust gas to generate a pressurized portion of exhaust gas, an outlet of said exhaust gas compressor being connected to said fuel line such that said fuel line receives a first portion of the pressurized portion of the exhaust gas so as to mix the first portion of the pressurized portion of the exhaust gas with the fuel upstream of said combustor, and said outlet of said exhaust gas compressor being connected to said combustor such that said combustor receives a second portion of the pressurized portion of the exhaust gas.