Combustor for a gas turbine and associated operating method

A method for operating a combustor for a gas turbine, wherein the combustor has a burner system with at least two burner groups, each burner group with at least one burner, the method comprising:

• determining the fuel flows which are fed to the individual burner groups with regard to their volume in dependence upon pressure pulsations, upon emissions allocated to the burner group, or upon both, so that in each burner group the pulsation values, the emission values, or both, assume, fall below, or both, predetermined threshold values.

The method as claimed in 11, further comprising:

• determining the proportional factors, the fuel flows, or both, which are to be fed to individual burner groups, so that the total fuel flow to be fed to the combustion chamber remains constant.

The method as claimed in 11, wherein at least in one burner group all the burners comprise multistage burners with at least two burner stages each, and further comprising:

• distributing the fuel flows fed within each burner group to the individual burner stages so that in the respective burner group the pulsation values, the emission values, or both, assume, fall below, or both, the predetermined threshold values.