Patent ID: 8166763

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 inlets, one or more fuel galleries annularly disposed about the longitudinal axis, and an 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 air inlet at the proximal end and being configured to mechanically couple to a combustor of the gas turbine engine at the distal end, the premix barrel being configured to direct a first fuel stream to the combustor, the first fuel stream being a premixed air-fuel mixture; and a pilot assembly disposed radially inwards of the premix barrel and configured to direct a second fuel stream to the combustor unmixed with the first fuel stream, the pilot assembly having a first end and a second end, the second end being removably coupled to the injector housing and the first end being proximate the distal end of the premix barrel, the pilot assembly being fluidly coupled to the fuel galleries, the air inlet, and the combustor, wherein the pilot assembly further includes first screw threads on an external surface and the injector housing includes mating second screw threads on an internal surface, and the pilot assembly is removably coupled to the injector housing by engaging the first screw threads with the second screw threads.