Abstract: The invention relates to a method for controlling a gas turbine group including, a first combustion chamber, a first turbine connected, a second combustion chamber, a second turbine, and a load. The method includes: measuring a temperature TAT1 at an outlet of the first turbine; determining a ratio S1R of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature TAT1 in accordance with a predetermined mapping table between ratio S1R and temperature TAT1; adopting the larger one between the determined ratio S1R and a predetermined booster ratio S1R to be used in the controlling fuel flow feeding the first combustion chamber of the gas turbine group. Pulsation behavior of the gas turbine group may be improved. High pulsation during fast de-loading of the gas turbine group is substantially is decreased, avoiding potential damage to the parts of the gas turbine group.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the opening of the row of variable compressor inlet guide vanes is controlled depending on the temperatures of the operative burners of the second combustor and simultaneously the number of operative burners is kept at a minimum. This leads to low CO emissions at partial load of the gas turbine.

Abstract: A method of controlling the fuel distribution among different stages of a gas turbine combustion chamber is disclosed. The combustion chamber has at least two stages for fuel supply, and the fuel distribution between the stages is determined according to the load or one or more parameters indicative of the load. In reply to a fast load change being faster than a load change during a regular transient operation, the fuel distribution is determined according to an adjusted load or one or more parameters indicative of an adjusted load.

Abstract: The invention relates to a method for controlling a gas turbine group including, a first combustion chamber, a first turbine connected, a second combustion chamber, a second turbine, and a load. The method includes: measuring a temperature TAT1 at an outlet of the first turbine; determining a ratio S1R of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature TAT1 in accordance with a predetermined mapping table between ratio S1R and temperature TAT1; adopting the larger one between the determined ratio S1R and a predetermined booster ratio S1R to be used in the controlling fuel flow feeding the first combustion chamber of the gas turbine group. Pulsation behavior of the gas turbine group may be improved. High pulsation during fast de-loading of the gas turbine group is substantially is decreased, avoiding potential damage to the parts of the gas turbine group.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the opening of the row of variable compressor inlet guide vanes is controlled depending on the temperatures of the operative burners of the second combustor and simultaneously the number of operative burners is kept at a minimum. This leads to low CO emissions at partial load of the gas turbine.