A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The lip generally increases in diameter as it extends downstream.

A fuel injector assembly for a combustor is provided, including a fuel nozzle having an axial inflow swirler and one or more radial inflow swirlers spaced radially outward of the downstream end of the fuel nozzle and mounted to the combustor, wherein the airstreams produced by the swirlers airblast atomize fuel films produced by the fuel nozzle.

A lean burn fuel injector comprises a fuel feed arm and a fuel injector head. The fuel feed arm has a single pilot fuel supply passage and a single main fuel supply passage extending there-through. The fuel injector head has a coaxial arrangement of an inner pilot air-blast fuel injector and a coaxially arranged outer main air-blast fuel injector. The inner pilot air-blast fuel injector comprises a coaxial arrangement of a pilot inner air swirler passage and a pilot outer air swirler passage. The outer main air-blast fuel injector comprises a coaxial arrangement of a main inner air swirler passage and a main outer air swirler passage. The single main fuel supply passage is arranged to supply main fuel to the main inner air swirler passage. The single pilot fuel supply passage is arranged to supply pilot fuel onto the pre-filming surfaces in the pilot inner and outer air swirler passages.

An injector for a multipoint combustor system includes an inner air swirler which defines an interior flow passage and a plurality of swirler inlet ports in an upstream portion thereof. The inlet ports are configured and adapted to impart swirl on flow in the interior flow passage. An outer air cap is mounted outboard of the inner swirler. A fuel passage is defined between the inner air swirler and the outer air cap, and includes a discharge outlet between downstream portions of the inner air swirler and the outer air cap for issuing fuel for combustion. The outer air cap defines an outer air circuit configured for substantially unswirled injection of compressor discharge air outboard of the interior flow passage.

A fuel injector includes a central member arranged on axis of fuel injector and a first member arranged around central member. A first swirler is arranged between central member and first member. A pilot fuel injector is arranged to supply fuel onto inner surface of first member. A second member is arranged between downstream end of first member and downstream end of shroud. A second swirler is arranged between upstream end of first member and upstream end of shroud and between downstream end of first member and upstream end of second member. A third swirler is arranged between downstream end of shroud and second member. A main fuel injector is arranged to supply fuel into an annular passage between first member and second member and a fourth swirler extends through first member.

A nozzle is provided including a nozzle body having an upstream end and a downstream end aligned about a central axis. A discharge portion is positioned adjacent the downstream end. A bore extends inwardly from the downstream end over the length of the discharge portion. An opening is formed in the nozzle body adjacent the discharge portion. The opening is fluidly connected to the bore to provide an interior air flow passage. A main fuel channel extends from the upstream end to the discharge portion. At least one fuel flow branch extends through the discharge portion between the bore and an outer surface of the nozzle body. The fuel flow branch is fluidly coupled to the main fuel conduit to provide a fuel flow passage. The outer air cap is positioned about the outer surface of the discharge portion of the nozzle body to form an exterior air flow passage.

A fuel nozzle apparatus has a centerline axis, and includes: a main fuel injector including an enclosed interior volume in fluid communication with a plurality of fuel ports configured to discharge fuel therefrom; a main fuel conduit disposed upstream of the main fuel injector and configured to supply liquid fuel to the interior volume; and a fluid lock disposed between the main fuel conduit and the main fuel injector, the fluid lock including a plurality of parallel capillary channels.

A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer elements includes: a fuel/air mixer body having an internal cavity extending axially between an air inlet and an air outlet; and a prefilmer residing within an interior cavity of the fuel/air mixer body, the prefilmer including an axial inner air flow passage extending coaxially with an axial centerline of the internal cavity of the fuel/air mixer body and a radial fuel injection port into the air flow passage. The fuel injector is arranged to direct fuel into a plurality of the fuel/air mixer elements via the fuel injection port of the prefilmer of each fuel/air mixer element.

A nozzle for a combustion chamber of an engine for providing a fuel-air mixture at a nozzle exit opening of the nozzle includes a nozzle main body including the nozzle exit opening and extends along a nozzle longitudinal axis. The nozzle main body has a first air guiding channel, a fuel guiding channel and a further, radially outwardly second air guiding channel. One end of the fuel guiding channel is positioned in front of the end of the second air guiding channel. A tapering channel portion with a shell surface inclined with respect to a nozzle longitudinal axis in the axial direction and connects to a radially outer shell surface of the fuel guiding channel is formed between the end of the fuel guiding channel and the end of the second air guiding channel at the nozzle.

A swirler, such as for swirling air in a fuel injector of a gas turbine engine, includes a swirler body with opposed inlet and outlet ends with a swirler wall extending therebetween along a longitudinal axis. The inlet end of the swirler body defines an inlet opening. A plurality of swirl slots is defined through a portion of the swirler wall that converges toward the longitudinal axis in a direction from the inlet opening toward the outlet end of the swirler body. The swirl slots are radially off-set with respect to the longitudinal axis for imparting swirl on a flow passing from the inlet opening, through the swirl slots, and past the outlet end of the swirler body.