Patent attributes
One embodiment of the present invention is a turbine nozzle segment for a turbine section of a gas turbine. The turbine nozzle segment includes an inner platform, an outer platform and an airfoil that extends therebetween. The airfoil includes a forward portion and an aft portion that is disposed downstream from the forward portion. The turbine nozzle segment further includes a fuel injection insert that extends between the inner platform and the outer platform downstream from the aft portion of the airfoil. The fuel injection insert includes a fuel circuit that extends within the fuel injection insert, and a plurality of fuel injection ports disposed within the fuel injection insert. The plurality of fuel injection ports provide for fluid communication with the fuel circuit.
