Dual fuel injectors and methods of use in gas turbine combustor

A fuel injector for a gas turbine combustor, the fuel injector comprising:

• a body comprising a frame defining an inlet portion and an outlet member extending downstream from the frame and defining an outlet portion, the body defining an air flow path from the inlet portion through the outlet portion, and the outlet member defining therein a mixing chamber, wherein
• the frame defines a leading end wall and a trailing end wall opposite the leading end wall, relative to a flow of combustion products through the gas turbine combustor, the frame further defining a pair of side walls between the leading end wall and the trailing end wall;
• a first fuel injection vane extending across the frame from the leading end wall to the trailing end wall, such that the air flow path extends between the vane and the pair of side walls of the frame;
• a fuel chamber defined within the first fuel injection vane, the fuel chamber being in flow communication with the air flow path via a vane fuel injection aperture defined in the first fuel injection vane;
• a gaseous fuel supply conduit in flow communication between a source of gaseous fuel and the vane fuel injection aperture, via the fuel chamber;
• a fuel plenum defined within the outlet member;
• a fuel injection port defined through the outlet member and in flow communication with the fuel plenum;
• and
• a liquid fuel supply conduit fixed to the body, wherein the liquid fuel supply conduit is in flow communication between a source of liquid fuel and the fuel injection port, via the fuel plenum.