Disclosed is a fuel control method for a gas turbine, in which a combustor is constituted by dividing fuel-feeding main nozzles into at least two groups. The fuel is fed (at S1) from the main nozzles of all groups at an ignition time of the combustor, and the fuel is subsequently fed (at S3) from the three main nozzles of an A-group at the speed rising time of the gas turbine. At the speed rising time, the fuel is injected from a small number of main nozzles so that the fuel flow rate per main nozzle is increased to raise the fuel/air ratio (fuel-flow-rate/air-flow-rate) in a combustion region, to thereby improve the combustibility. As a result, it is possible to reduce the productions of carbon monoxide and unburned hydrocarbons and to need no bypass valve, to thereby lower the manufacturing cost. At the ignition time, moreover, the fuel can be fed from the main nozzles of all groups and burned in the whole area of the combustor, so that flames can be easily propagated to all the remaining adjacent main nozzle groups, to thereby improve the ignitability of the whole gas turbine.