| 摘要 |
PURPOSE:To permit the correct control of the combustion gas temperature by measuring the pressure, atmospheric pressure, compressor inlet temperature, fuel flow rate, etc. before and behind the first stage nozzle of a gas turbine and calculating the inlet side temperature of the first stage nozzle according to the measured data. CONSTITUTION:A gas turbine carries-out the combustion of the fuel 5 jetted into a combustion chamber 7 under the supply of the high-pressure air 2 from a compressor 1, and introduces the generated high-temperature and high-pressure gas 3 into a turbine 8 and drives a power generator 9. In this case, the flow rate of the first nozzle of the turbine 8 is obtained from the sum of the air flow rate obtained from the pressure on the upstream and downstream of the first stage nozzle and the characteristics of the compressor 1 and the measured combustion flow rate. Further, the characteristics of combustion gas (specific-hear ratio, gas constant) are calculated. The turbine inlet combustion gas temperature is calculated from the flow-rate characteristic equation of the nozzle according to the above-described elements, and said temperature is compared with the combustion gas temperature obtained from the exhaust temperature and the compressor exhaust pressure, and fuel control is carried-out according to the smaller temperature value.
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