A turbine system , comprising: a main compressor for compressing a flow of ambient air ; a turbine ; and a combustor ; the combustor comprising a fuel nozzle , a combustion liner , an extended flow sleeve in communication with the main compressor , and an extraction port ; wherein the extended flow sleeve receives the flow of ambient air from the main compressor so as to cool the combustion liner , wherein the turbine system is a stoichiometric exhaust gas recovery turbine system and the combustor is a stoichiometric exhaust gas recovery combustor, in which the fuel nozzle is provided in the combustor, the combustion liner comprises a mixing zone and a firing zone downstream of the fuel nozzle , wherein the fuel nozzle is positioned within and extends through the mixing zone into the firing zone , the extended flow sleeve surrounds the combustion liner and defines an ambient air path therein for the flow of ambient air , and a casing surrounds the extended flow sleeve , characterized in that the extraction port is provided through the casing and in communication with the ambient air path of the extended flow sleeve and with the turbine via an extraction line , and the extended flow sleeve comprises one or more flow sleeve apertures in communication with the mixing zone so that the flow of ambient air splits into an extraction flow to the turbine via the extraction port and a combustion flow within the combustion liner via the one or more flow sleeve apertures , and in that the turbine system further comprises a low oxygen recirculation flow exiting the turbine via a recirculation loop in communication with the stoichiometric exhaust gas recovery combustor and a low oxygen recirculation inlet is in communication with the mixing zone and in communication with the low oxygen recirculation flow from the turbine . a main compressor for compressing a flow of ambient air ; a turbine ; and a combustor ; the combustor comprising a fuel nozzle , a combustion liner , an extended flow sleeve in communication with the main compressor , and an extraction port ; wherein the extended flow sleeve receives the flow of ambient air from the main compressor so as to cool the combustion liner , wherein the turbine system is a stoichiometric exhaust gas recovery turbine system and the combustor is a stoichiometric exhaust gas recovery combustor, in which the fuel nozzle is provided in the combustor, the combustion liner comprises a mixing zone and a firing zone downstream of the fuel nozzle , wherein the fuel nozzle is positioned within and extends through the mixing zone into the firing zone , the extended flow sleeve surrounds the combustion liner and defines an ambient air path therein for the flow of ambient air , and a casing surrounds the extended flow sleeve , characterized in that the extraction port is provided through the casing and in communication with the ambient air path of the extended flow sleeve and with the turbine via an extraction line , and the extended flow sleeve comprises one or more flow sleeve apertures in communication with the mixing zone so that the flow of ambient air splits into an extraction flow to the turbine via the extraction port and a combustion flow within the combustion liner via the one or more flow sleeve apertures , and in that the turbine system further comprises a low oxygen recirculation flow exiting the turbine via a recirculation loop in communication with the stoichiometric exhaust gas recovery combustor and a low oxygen recirculation inlet is in communication with the mixing zone and in communication with the low oxygen recirculation flow from the turbine . <EOS>