A computer implemented method of controlling a gas turbine arranged to supply a load L, the gas turbine comprising a total fuel supply means arranged to supply fuel at a fuel flow rate FF to a combustor, wherein the total fuel supply means comprises a first fuel supply means and a second fuel supply means, the method comprising: determining one or more ratios R of one or more combustor operating parameters COP respectively at the load L to respective reference combustor operating parameters COPR at a reference load LR; and controlling a proportion P of the fuel flow rate FF supplied via the first fuel supply means based, at least in part, on the determined one or more ratios R; whereby a flame stability and/or an emission is improved, characterized in that, the combustor operating parameter COP is one selected from a group comprising a combustion intensity CI of the combustor, an equivalence ratio ER of the combustor and a combustor inlet function CIF of the combustor, wherein the combustion intensity CI is determined based, at least in part, on a heat input HI to the gas turbine, a compressor exit pressure CEP of the gas turbine and/or a combustor volume CV of the combustor and wherein the method comprises: determining the combustion intensity CI; determining a first ratio R1 of the combustion intensity CI at the load L to a reference combustion intensity CIR at the reference load LR; and controlling the proportion P of the fuel flow rate FF supplied via the first fuel supply means based, at least in part, on the determined first ratio R1, and wherein the combustor inlet function CIF is determined based, at least in part, on an air flow rate FA to the combustor, a compressor exit temperature CET of the gas turbine and/or a compressor exit pressure CEP of the gas turbine and wherein the method comprises: determining the combustor inlet function CIF; determining a third ratio R3 of the combustor inlet function CIF at the load L to a reference combustor inlet function CIFR at the reference load LR; and controlling the proportion P of the fuel flow rate FF supplied via the first fuel supply means based, at least in part, on the determined third ratio R3. determining one or more ratios R of one or more combustor operating parameters COP respectively at the load L to respective reference combustor operating parameters COPR at a reference load LR; and controlling a proportion P of the fuel flow rate FF supplied via the first fuel supply means based, at least in part, on the determined one or more ratios R; whereby a flame stability and/or an emission is improved, characterized in that, the combustor operating parameter COP is one selected from a group comprising a combustion intensity CI of the combustor, an equivalence ratio ER of the combustor and a combustor inlet function CIF of the combustor, wherein the combustion intensity CI is determined based, at least in part, on a heat input HI to the gas turbine, a compressor exit pressure CEP of the gas turbine and/or a combustor volume CV of the combustor and wherein the method comprises: determining the combustion intensity CI; determining a first ratio R1 of the combustion intensity CI at the load L to a reference combustion intensity CIR at the reference load LR; and controlling the proportion P of the fuel flow rate FF supplied via the first fuel supply means based, at least in part, on the determined first ratio R1, and wherein the combustor inlet function CIF is determined based, at least in part, on an air flow rate FA to the combustor, a compressor exit temperature CET of the gas turbine and/or a compressor exit pressure CEP of the gas turbine and wherein the method comprises: determining the combustor inlet function CIF; determining a third ratio R3 of the combustor inlet function CIF at the load L to a reference combustor inlet function CIFR at the reference load LR; and controlling the proportion P of the fuel flow rate FF supplied via the first fuel supply means based, at least in part, on the determined third ratio R3. determining the combustion intensity CI; determining a first ratio R1 of the combustion intensity CI at the load L to a reference combustion intensity CIR at the reference load LR; and controlling the proportion P of the fuel flow rate FF supplied via the first fuel supply means based, at least in part, on the determined first ratio R1, and wherein the combustor inlet function CIF is determined based, at least in part, on an air flow rate FA to the combustor, a compressor exit temperature CET of the gas turbine and/or a compressor exit pressure CEP of the gas turbine and wherein the method comprises: determining the combustor inlet function CIF; determining a third ratio R3 of the combustor inlet function CIF at the load L to a reference combustor inlet function CIFR at the reference load LR; and controlling the proportion P of the fuel flow rate FF supplied via the first fuel supply means based, at least in part, on the determined third ratio R3.