Patent ID: 6026644
Filing Date: 2000-02-22
Classification: F02C,F05D,F23N,F23R

Abstract:
A gas turbine combuster comprising:a plurality of premixing burners, each for jetting out a premixed gas of fuel and air;a plurality of premixing fuel lines connected to said Plurality of premixing burners, respectively, each said premixing fuel line having a fuel flow adjusting device;a stabilizer for forming a circulation of combustion gas generated through combustion of said premixed gas, said stabilizer having an annular shape and a heating surface at a most downstream portion of said stabilizer, said stabilizer being disposed so that at a downstream side of said stabilizer the premixed gas jetted from each said premixing burner flows downstream of said stabilizer through inner and outer sides of said stabilizer;means for setting, before a practical operation of said combustor, a relationship between a temperature of said stabilizer and combustion conditions of a premixed gas;a plurality of thermometers arranged in said stabilizer close to said heating surface to be circumferentially distant from each other;means for adjusting a fuel flow rate to each said premixing burner according to said relationship and a detected temperature of said stabilizer at a position corresponding to each said premixing burner; andmeans for stopping fuel supply to all of said plurality of premixing burners when a temperature of said stabilizer detected by any one of said plurality of thermometers is a preset value or larger.