Gas turbine control device, gas turbine control method, and program

A gas turbine control method comprising:

• a step of calculating a fuel flow rate indicating the amount of a fuel flowing into a combustor of a gas turbine, based on measurement data relating to a fuel supply system for supplying the fuel to the combustor;
• a step of calculating an air flow rate indicating the amount of air suctioned by a compressor of the gas turbine, based on measurement data relating to the compressor;
• a step of calculating a turbine inlet temperature, based on the fuel flow rate, the air flow rate, and a physical model equation relating to heat energy balance relating to the combustor;
• a step of performing a computation for satisfying heat balance of the gas turbine, based on measurement data relating to energy balance of the gas turbine, and outputting a computation result;
• a step of detecting a state of the gas turbine;
• and
• a step of correcting any one or both of the fuel flow rate and the air flow rate, based on the computation result output in the step of performing the computation for satisfying the heat balance when the state of the gas turbine which is detected in the step of detecting the state is a static state, and providing the corrected flow rate to the step of calculating the turbine inlet temperature.

A non-transitory computer-readable recording medium storing a program that causes a computer to function as:

• fuel flow rate calculation means for calculating a fuel flow rate indicating the amount of a fuel flowing into a combustor of a gas turbine, based on measurement data relating to a fuel supply system for supplying the fuel to the combustor;
• air flow rate calculation means for calculating an air flow rate indicating the amount of air suctioned by a compressor of the gas turbine, based on measurement data relating to the compressor;
• turbine inlet temperature calculation means for calculating a turbine inlet temperature, based on the fuel flow rate, the air flow rate, and a physical model equation relating to heat energy balance relating to the combustor;
• heat balance computation means for performing a computation for satisfying heat balance of the gas turbine, based on measurement data relating to energy balance of the gas turbine, and outputting a computation result;
• state detection means for detecting a state of the gas turbine;
• and
• correction process means for correcting any one or both of the fuel flow rate and the air flow rate, based on the computation result output by the heat balance computation means when the state of the gas turbine which is detected by the state detection means is a static state, and providing the corrected flow rate to the turbine inlet temperature calculation means.