Patent ID: 7756626
Filing Date: 2010-07-13
Classification: F02C,F05D,F23N,G05B

Abstract:
1. A gas turbine output learning circuit for a gas turbine having a gas turbine body, a combustor, and a compressor, comprising: means for computing a first exhaust gas temperature corresponding to a measured pressure ratio according to a first characteristic curve representing a relation between the pressure ratio of the compressor and an exhaust gas temperature of the gas turbine body when a combustion gas temperature at an inlet of the gas turbine is adjusted to a first combustion gas temperature at the inlet of the gas turbine; means for computing a second exhaust gas temperature corresponding to a measured pressure ratio according to a second characteristic curve representing a relation between the pressure ratio and the exhaust gas temperature when the combustion gas temperature at the inlet of the gas turbine is adjusted to a second combustion gas temperature at the inlet of the gas turbine, which is higher than the first combustion gas temperature at the inlet of the gas turbine; means for computing a third combustion gas temperature at the inlet of the gas turbine corresponding to the measured pressure ratio and a measured exhaust gas temperature by linear interpolation according to the first combustion gas temperature at the inlet of the gas turbine, the second combustion gas temperature at the inlet of the gas turbine, the first exhaust gas temperature, the second exhaust gas temperature, and the measured exhaust gas temperature; means for computing a third gas turbine output corresponding to the third combustion gas temperature at the inlet of the gas turbine by linear interpolation according to a first gas turbine output corresponding to the first combustion gas temperature at the inlet of the gas turbine and a second gas turbine output corresponding to the second combustion gas temperature at the inlet of the gas turbine which are computed by gas turbine output computing means, the first combustion gas temperature at the inlet of the gas turbine, the second combustion gas temperature at the inlet of the gas turbine, and the third combustion gas temperature at the inlet of the gas turbine; and means for correcting the first gas turbine output and the second gas turbine output which are used for computation of the third gas turbine output by comparing the third gas turbine output with a measured gas turbine output so as to match the third gas turbine output with the measured gas turbine output.