Patent ID: 8286433

Claim:
A fuel injector for a gas turbine engine comprising: an injector housing having a longitudinal axis, the injector housing including one or more fuel galleries annularly disposed about the longitudinal axis, and a compressed air inlet; a premix barrel having a proximal end and a distal end circumferentially disposed about the longitudinal axis, the premix barrel being fluidly coupled to the fuel galleries and the compressed air inlet at the proximal end and being configured to couple to a combustor of the gas turbine engine at the distal end; a substantially cylindrical pilot assembly disposed radially inwards of the premix barrel having a first end and a second end, the second end being coupled to the injector housing and the first end being proximate the distal end of the premix barrel; and a pilot liquid tube having a third end and a fourth end disposed radially inwards of the pilot assembly, the fourth end being removably coupled to the injector housing and the third end being located proximate the first end of the pilot assembly, wherein the fourth end of the pilot liquid tube includes first screw threads on an external surface of the pilot liquid tube, and the injector housing includes second screw threads on an internal surface of the injector housing, the second screw threads on the injector housing mating with the first screw threads on the pilot liquid tube, and the pilot liquid tube is removably coupled to the injector housing by engaging the first screw threads and the second screw threads.