A combustion system for a gas turbine, comprising: a cylindrical combustion liner having a center axis (A-A); a flow sleeve coupled to the cylindrical combustion liner and located radially outward of the cylindrical combustion liner relative to the center axis (A-A); a main mixer coupled to the flow sleeve and located radially outward of the cylindrical combustion liner relative to the center axis (A-A), the main mixer configured to inject at least one of a gaseous and a liquid fuel into the flow sleeve; a radial inflow swirler coupled to the cylindrical combustion liner and configured to direct air from outside the cylindrical combustion liner to inside the cylindrical combustion liner, the radial inflow swirler configured to inject at least one of a gaseous and a liquid fuel into the cylindrical combustion liner; and a fuel cartridge assembly coupled to the cylindrical combustion liner and extending at least partially through the radial inflow swirler along the center axis (A-A), the fuel cartridge assembly configured to inject a liquid fuel into the combustion liner; the fuel cartridge assembly comprising a pilot fuel injector; a combustor dome located at an end of the cylindrical combustion liner; and at least one liquid fuel circuit coupled to the fuel cartridge assembly, at least one other liquid fuel circuit coupled to at least one of the main mixer, the radial inflow swirler, and the combustor dome for supplying the other liquid fuel to the cylindrical combustion liner through the at least one of the main mixer, the radial inflow swirler, and the combustor dome to which the other liquid fuel circuit is coupled; a first liquid fuel supply and a first water supply being coupled to the first fuel circuit, a second liquid fuel supply and a second water supply being coupled to the second fuel circuit, and a third fuel supply and a third water supply being coupled to the pilot fuel injector; the ratio of fuel-to-water in each of the first fuel circuit, the second fuel circuit, and the pilot fuel injector being adjustable. a cylindrical combustion liner having a center axis (A-A); a flow sleeve coupled to the cylindrical combustion liner and located radially outward of the cylindrical combustion liner relative to the center axis (A-A); a main mixer coupled to the flow sleeve and located radially outward of the cylindrical combustion liner relative to the center axis (A-A), the main mixer configured to inject at least one of a gaseous and a liquid fuel into the flow sleeve; a radial inflow swirler coupled to the cylindrical combustion liner and configured to direct air from outside the cylindrical combustion liner to inside the cylindrical combustion liner, the radial inflow swirler configured to inject at least one of a gaseous and a liquid fuel into the cylindrical combustion liner; and a fuel cartridge assembly coupled to the cylindrical combustion liner and extending at least partially through the radial inflow swirler along the center axis (A-A), the fuel cartridge assembly configured to inject a liquid fuel into the combustion liner; the fuel cartridge assembly comprising a pilot fuel injector; a combustor dome located at an end of the cylindrical combustion liner; and at least one liquid fuel circuit coupled to the fuel cartridge assembly, at least one other liquid fuel circuit coupled to at least one of the main mixer, the radial inflow swirler, and the combustor dome for supplying the other liquid fuel to the cylindrical combustion liner through the at least one of the main mixer, the radial inflow swirler, and the combustor dome to which the other liquid fuel circuit is coupled; a first liquid fuel supply and a first water supply being coupled to the first fuel circuit, a second liquid fuel supply and a second water supply being coupled to the second fuel circuit, and a third fuel supply and a third water supply being coupled to the pilot fuel injector; the ratio of fuel-to-water in each of the first fuel circuit, the second fuel circuit, and the pilot fuel injector being adjustable.