is in fluid communication with second passage 47 premix nozzle 40 further includes a fourth tube 80 having a generally conical shape with a tapered outer surface 81 a fourth inner diameter and opposing fourth tube ends fourth tube 80 is fixed at fourth tube ends to injector assembly 49 opposite first tube 43 and second tube 44 and to third tube 46 the fourth inner diameter of fourth tube 80 is greater in diameter than the third outer diameter of third tube 46 thereby forming a fourth annular passage 82 which is in fluid communication with second passage 47 premix fuel nozzle 40 further includes a cap assembly 56 fixed to the forward end of fourth tube 80 and includes an effusion plate 57 having an end surface including a set of third injector holes 58 therein the use of a conical shaped tube as fourth tube 80 allows a smooth transition in flow path between injector assembly 49 and cap assembly 56 such that large zones of undesirable recirculation downstream of fins 50 are minimized if the recirculation zones are not minimized they can provide an opportunity for fuel and air to mix to the extent that combustion occurs and is sustainable upstream of the desired combustion zone the premix fuel nozzle 40 in the present embodiment injects fluids such as natural gas and compressed air into a combustor of a gas turbine engine for the purposes of establishing a premixed pilot flame and supporting combustion downstream of the fuel nozzle one operating embodiment for this type of fuel.