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A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing having a longitudinal axis. The injector housing includes one or more fuel galleries annularly disposed about the longitudinal axis, and a compressed air inlet. The fuel injector also includes a pre

A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing having a longitudinal axis. The injector housing includes one or more fuel galleries annularly disposed about the longitudinal axis, and a compressed air inlet. The fuel injector also includes a premix barrel having a proximal end and a distal end circumferentially disposed about the longitudinal axis. The premix barrel is fluidly coupled to the fuel galleries and the compressed air inlet at the proximal end and is configured to couple to a combustor of the gas turbine engine at the distal end. The fuel injector also includes a substantially cylindrical pilot assembly disposed radially inwards of the premix barrel having a first end and a second end. The second end is coupled to the injector housing and the first end is located proximate the distal end of the premix barrel. The fuel injector further includes a pilot liquid tube having a third end and a fourth end disposed radially inwards of the pilot assembly. The fourth end is removably coupled to the injector housing and the third end is located proximate the first end of the pilot assembly.

대표청구항 ▼

1. 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 circumfe

1. 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; anda 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. 2. The fuel injector of claim 1, wherein the pilot liquid tube includes, an elongate section extending between the third end and the fourth end;a fuel line coupled to the fourth end, the fuel line being configured to deliver liquid fuel to the pilot liquid tube; anda nozzle coupled to the third end, the nozzle being configured to spray liquid fuel from the pilot liquid tube. 3. The fuel injector of claim 2, wherein the nozzle includes swirl features on an external surface. 4. The fuel injector of claim 3, wherein the swirl features include helical grooves annularly arranged about the longitudinal axis. 5. The fuel injector of claim 2, wherein the elongate section includes two or more tubes coupled together using one or more fluid couplings. 6. The fuel injector of claim 5, wherein the fluid couplings include at least one fluid coupling having a plurality of spokes extending radially outwards from an external surface. 7. The fuel injector of claim 2, wherein the elongate section includes a tube fitting at the fourth end, the tube fitting being attached to the fuel line at one end and being attached to the elongate section at an opposite end, the tube fitting also including screw threads on an external surface. 8. The fuel injector of claim 1, wherein the pilot liquid tube and the pilot assembly form an annular channel between them. 9. A gas turbine engine: a compressor;a combustor fluidly coupled to the compressor;a fuel injector having a longitudinal axis coupled to the combustor, the fuel injector including; a housing having a front end and a back end, the housing also including a first cavity disposed about the longitudinal axis and extending from the front end to the back end;a substantially cylindrical premix barrel disposed circumferentially about the longitudinal axis, the premix barrel being coupled to the housing at one end and coupled to the combustor at an opposite end;a substantially cylindrical pilot assembly disposed radially inwards of the premix barrel, the pilot assembly having a second cavity disposed about the longitudinal axis and passing longitudinally through the pilot assembly; andan elongate pilot liquid tube disposed about the longitudinal axis, the pilot liquid tube being removably coupled to the housing and extending through the first cavity and the second cavity to a location proximate the combustor, wherein the pilot liquid tube includes screw threads on an external surface of the pilot liquid tube which mate with screw threads on an internal surface of the housing; anda turbine fluidly coupled to the combustor. 10. The gas turbine engine of claim 9, wherein the pilot liquid tube includes; an elongate section having a first end and a second end;a nozzle coupled to the first end;a tube fitting at the second end, wherein the screw threads of the pilot liquid tube are on an external surface of the tube fitting, the tube fitting being fluidly coupled to a source of liquid fuel. 11. The gas turbine engine of claim 10, wherein an external surface of the pilot liquid tube and a surface of the second cavity form an annular duct disposed about the longitudinal axis. 12. A fuel injector for a gas turbine engine comprising: an injector housing including one or more fuel galleries and a compressed air inlet;a hollow premix barrel extending along a longitudinal axis from a proximal end to a distal end, the proximal end being coupled to the injector housing and the distal end being configured to be fluidly coupled to a combustor of the gas turbine engine;a hollow pilot assembly extending from a first end to a second end along the longitudinal axis to define a first annular cavity between an inner surface of the premix barrel and an outer surface of the pilot assembly and a inner cavity within the pilot assembly, the first end being coupled to the injector housing and the second end being positioned proximate the distal end of the premix barrel; andan elongate pilot tube extending through the inner cavity from a third end to a fourth end to define a second annular cavity between an inner surface of the pilot assembly and an outer surface of the pilot tube and a central cavity within the pilot tube, the third end including screw threads on an external surface of the pilot tube that engage with screw threads on a mating internal surface of the injector housing, and the fourth end being positioned proximate the second end of the pilot assembly, wherein the fourth end of the pilot tube include swirl features configured to induce a swirl to a fluid passing through the second annular cavity. 13. The fuel injector of claim 12, wherein the screw threads of the pilot tube removably couple the pilot tube to the injector housing. 14. The fuel injector of claim 12, wherein the swirl features include helical grooves on the outer surface of the pilot tube. 15. The fuel injector of claim 12, wherein a portion of the outer surface of the pilot tube between the third end and the fourth end includes one or more spokes that extend radially into the second annular cavity. 16. The fuel injector of claim 12, wherein the elongate pilot tube includes one or more elongate tubes that are coupled together. 17. The fuel injector of claim 12, wherein the third end of the pilot tube includes a coupling that is configured to couple with a fuel line. 18. The fuel injector of claim 17, wherein the elongate pilot tube is configured to be slid out of the hollow pilot assembly from the first end of the pilot assembly. 19. The fuel injector of claim 1, wherein the pilot liquid tube is configured to be slid out of the pilot assembly from the second end of the pilot assembly. 20. The gas turbine engine of claim 9, wherein the elongate pilot tube is configured to be slid out of the pilot assembly from the back end of the housing. 21. The gas turbine engine of claim 10, wherein the nozzle includes swirl features on an external surface.