Abstract: A pilot liquid tube having a pilot liquid fuel inlet, a pilot liquid fuel conduit, a pilot liquid fuel nozzle, and a shroud configured to shield the pilot liquid fuel nozzle. The pilot liquid tube may be installed and/or removed from an injector of a gas turbine engine while the shroud remains fixed to pilot liquid fuel conduit.

Abstract: An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection portion extending radially inward and axially from the annular disk portion. The transition end also includes a plurality of wipe passages extending through the transition end. The tip end includes a cylindrical portion with a hollow right circular cylinder shape. The premix tube inner surface is a radially outer surface including the redirection portion outer surface and the cylindrical portion outer surface.

Abstract: A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet.

Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing extending from a first end to a second end along a longitudinal axis. The second end of the housing is fluidly coupled to a combustor of the turbine engine and the housing includes a liquid fuel gallery annularly disposed about the longitudinal axis. The fuel injector also includes a stem extending longitudinally from the first end of the housing to a third end. The stem includes a liquid tube configured to deliver liquid fuel to the fuel injector. The fuel injector also includes an annular shell extending along the longitudinal axis from the first end to the third end and circumferentially disposed about the stem. The fuel injector further includes an insulating air shroud formed inside the shell. The air shroud includes a layer of air between the shell and the stem.

Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing extending from a first end to a second end along a longitudinal axis. The second end of the housing is fluidly coupled to a combustor of the turbine engine and the housing includes a liquid fuel gallery annularly disposed about the longitudinal axis. The fuel injector also includes a stem extending longitudinally from the first end of the housing to a third end. The stem includes a liquid tube configured to deliver liquid fuel to the fuel injector. The fuel injector also includes an annular shell extending along the longitudinal axis from the first end to the third end and circumferentially disposed about the stem. The fuel injector further includes an insulating air shroud formed inside the shell. The air shroud includes a layer of air between the shell and the stem.

Abstract: 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.

Abstract: 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 inlets, one or more fuel galleries annularly disposed about the longitudinal axis, and an 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 air inlet at the proximal end, and configured to mechanically couple to a combustor of the gas turbine engine at the distal end. The fuel injector also includes a pilot assembly disposed radially inwards of the premix barrel. The pilot assembly may include a first end and a second end. The second end is removably coupled to the injector housing, and the first end is proximate the distal end of the premix barrel. The pilot assembly is fluidly coupled to the fuel galleries, the air inlet, and the combustor.

Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing extending from a first end to a second end along a longitudinal axis. The second end of the housing is fluidly coupled to a combustor of the turbine engine and the housing includes a liquid fuel gallery annularly disposed about the longitudinal axis. The fuel injector also includes a stem extending longitudinally from the first end of the housing to a third end. The stem includes a liquid tube configured to deliver liquid fuel to the fuel injector. The fuel injector also includes an annular shell extending along the longitudinal axis from the first end to the third end and circumferentially disposed about the stem. The fuel injector further includes an insulating air shroud formed inside the shell. The air shroud includes a layer of air between the shell and the stem.

Abstract: 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.

Abstract: 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 inlets, one or more fuel galleries annularly disposed about the longitudinal axis, and an 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 air inlet at the proximal end, and configured to mechanically couple to a combustor of the gas turbine engine at the distal end. The fuel injector also includes a pilot assembly disposed radially inwards of the premix barrel. The pilot assembly may include a first end and a second end. The second end is removably coupled to the injector housing, and the first end is proximate the distal end of the premix barrel. The pilot assembly is fluidly coupled to the fuel galleries, the air inlet, and the combustor.