The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirler assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.

A fuel injection device for a gas turbine combustor includes a pilot fuel injector disposed on an axis of the fuel injection device; an annular main fuel injector encircling the pilot fuel injector; and a plurality of main fuel injection holes formed in the main fuel injector and spaced circumferentially from each other for injecting fuel axially rearward. The main fuel injector includes an annular fuel passage forming portion, an inner ring portion on an inner peripheral side of the fuel passage fowling portion, and an outer ring portion on an outer peripheral side of the fuel passage forming portion. One of a space between the fuel passage forming portion and the inner ring portion and a space between the fuel passage forming portion and the outer ring portion forms a pilot fuel supply passage, and the other one forms a main fuel supply passage.

A fuel injector for a gas turbine engine includes a monolithic nozzle body that defines within its interior one or more fuel circuits. Each fuel circuit includes an inlet, an outlet orifice, a main passage fluidly coupling the inlet with the outlet orifice, and a branch passage connected to the main passage. The branch passage connects to the main passage downstream of the inlet and upstream of the outlet orifice to form an effective metering flow area that is smaller than the flow area of the outlet orifice.

A nozzle, a combustor, and a gas turbine, which are capable of atomizing fuel efficiently, are provided. A fuel injection device for the combustor may include a plurality of guide channels connected to a pilot fuel passage through which fuel is supplied, an injection chamber connected to the plurality of guide channels, the fuel being merged in the injection chamber, and an injection hole formed at a tip of the injection chamber to inject the fuel, and the injection chamber may include a decompression space to drop a pressure therein.

The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.

A fuel supply device includes: an outer tubular member; an inner tubular member inside the outer tubular member; and a flow distribution portion on an inner surface of the outer tubular member or an outer surface of the inner tubular member, wherein the flow distribution portion includes first and second distribution wall portions arranged apart from one another in an axial direction of the inner tubular member, the first distribution wall portion includes first individual wall portions spaced apart from one another along a first circumference of the inner tubular member, the second distribution wall portion includes second individual wall portions spaced apart from one another along a second circumference of the inner tubular member, at least some of the first individual wall portions are arranged to face spaces between at least some of the second individual wall portions, respectively, in the axial direction of the inner tubular member.

A fuel swirler has a swirler housing defining an interior chamber having a fuel outlet at a downstream end. A swirler core is mounted inside the interior chamber. The swirler core has a downstream end portion with one or more fuel channels disposed thereon. The one or more fuel channels is in fluid communication with the fuel outlet. An internal bore extends longitudinally through the swirler core. The internal bore has an inlet connectable to a source of fuel. One or more exit holes fluidly connects the internal bore to the one or more fuel channels. An annular air gap is provided radially between the swirler housing and the swirler core for thermally shielding the internal bore.

A swirler assembly includes a swirler having a primary swirler with a primary swirler venturi, a swirler ferrule plate connected upstream to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an annular pressure drop cavity with oxidizer inlet orifices in fluid communication with the swirler, and at least one outlet orifice in fluid communication with the primary swirler venturi. A second flow of oxidizer to the swirler incurs a first pressure drop, a third flow of the oxidizer from the swirler to the annular pressure drop cavity incurs a second pressure drop, and a fourth flow of the oxidizer from the annular pressure drop cavity to the primary swirler venturi incurs a third pressure drop.

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector and an array of secondary plain jet fuel injectors.

A liquid fuel injector includes a cylindrical primary fuel injecting body having a central axis; an annular shroud concentrically placed radially outside; and an annular secondary fuel injecting body placed concentrically with the primary fuel injecting body and the shroud between the primary fuel injecting body and the shroud. A plurality of inner swirlers placed at equal intervals in a circumferential direction are provided in an annular inner air passage formed between the primary fuel injecting body and the secondary fuel injecting body, and a plurality of outer swirlers placed at equal intervals in the circumferential direction are provided in an annular outer air passage formed between the secondary fuel injecting body and the shroud. The primary fuel injecting body is formed as a pressure spray-type injector, and the secondary fuel injecting body and the inner and outer air passages cooperatively constitute an airblast-type injector.