Abstract: The invention relates to a plain jet radial injection fuel nozzle for a gas turbine combustor. The nozzle includes an axially elongate middle tube having a desired diameter. The middle tube is adapted for fuel flow. A fuel exit passage is located circumferentially around the middle tube near its distal end. An axially elongate inner adapted for flow of air or gaseous fuel is inside the middle tube. An axially elongate outer tube is also adapted for flow of air or gaseous fuel. The outer tube is located outisde the middle tube, so as to create a space between the middle tube and the outer tube where fuel flowing through the middle tube and air flowing through the inner and outer tubes can mix to form a fuel/air mixture. The nozzle has an endcap at the distal end of the outer tube. The endcap includes a fuel/air exit passage that permits the fuel/air mixture to exit the nozzle. The nozzle can be adapted to attach to a quarl for providing a fuel/air mixture to a gas turbine combustor.