Patent ID: 7117662

Claim:
A gas turbine control system for controlling a gas turbine unit including an air compressor for producing compressed air, said compressor having inlet guide vanes or blades for adjusting an air flow rate into the compressor, a combustor for combusting a fuel mixed with the compressed air from the compressor to produce a combustion gas, a gas turbine receiving the combustion gas from the combustor and driven by the combustion gas to drive the compressor; and an electric generator driven by gas turbine unit and connected to an electric power system: said gas turbine control system comprising: inlet guide blade control means that controls the inlet guide vanes or blades to change the air flow rate into the compressor, said inlet guide blade control means being changeable between a normal inlet guide blade control mode and an emergency inlet guide blade control mode; a fuel control valve provided to control flow rate of the fuel into the combustor; speed-load control means including a speed control means and a load control means, said speed-load control means operating on said fuel control valve to control the flow rate of the fuel so that the gas turbine has a rotational speed coinciding with a set speed value; combustion gas temperature control means that controls the flow rate of the fuel so that the combustion gas temperature does not exceed a combustion gas temperature limit value; a system frequency abnormality sensor that operates to detect such a variation of frequency of the electric power system as to cause the power system to go out of normal operation; and changeover means that operates in response to operation of said system frequency abnormality sensor to change over the inlet guide blade control means from said normal inlet guide blade control mode to said emergency inlet guide blade control mode, whereby output of the gas turbine is controlled to stabilize a system frequency.