Patent ID: 6460346
Filing Date: 2002-10-08
Classification: F01D,F02C,F05D,F23N

Abstract:
A method of identifying an abnormal combustion temperature in an operating gas turbine comprising the steps of:a. operating a gas turbine having a compressor, a combustion section, and a turbine, such that hot combustion gases generated in the combustion section flow through the turbine and exit the turbine as exhaust gases; b. measuring temperatures of the exhaust gases at a plurality of positions arranged downstream of the turbine; c. identifying at least one of the measured exhaust gas temperatures as an abnormal exhaust gas temperature; d. correlating the at least one abnormal exhaust gas temperature with a corresponding location in the combustion section, wherein the correlation of the exhaust gas temperature with the combustion section is based on at least one linear function of a power output of the gas turbine and an ambient temperature bias, and e. identifying the corresponding location in the combustion section having the abnormal combustion gas temperature.