Abstract: A gas turbine performance analysis system includes a performance computation module for receiving an actual measured value of an inlet air temperature introduced to a compressor, a compressor pressure ratio, and a flow rate of fuel supplied to the gas turbine, and for calculating and outputting values of the gas turbine's power output and exhaust temperature based on these actual measured values. A performance estimation module evaluates the performance of the gas turbine based on the deviation between the values of power output and exhaust temperature outputted from the performance computation module and the actual measured values of power output and exhaust temperature. An adjustment module calculates a corrected value of the fuel flow rate based on the actual measured values of inlet air temperature, compressor pressure ratio and fuel flow rate, and inputs the corrected fuel flow rate value into the performance computation module.

Abstract: A gas turbine performance analysis system comprising: a performance computation module for receiving each of actual measured value of an inlet air temperature introduced to compressor, a compressor pressure ratio and a fuel flow rate supplied to a gas turbine in the actual gas turbine and calculating and outputting values of a gas turbine's power output and exhaust temperature exhausted from the gas turbine based on these actual measured values; and a performance estimation module for evaluating performance of the gas turbine based on the deviation between the values of power output and exhaust temperature outputted from the performance computation module and the actual measured values of power output and exhaust temperature; wherein the gas turbine performance analysis system further comprising: an adjustment module for calculating a corrected value of the fuel flow rate based on the actual measured values of inlet air temperature, compressor pressure ratio and fuel flow rate, and inputting the corrected