An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.

A reactor for a mixture of fluids that can react with each other exothermically, the reactor combining the properties of heat transfer and porosity, and having a first chamber wherein reacted fluids are maintained above the reaction temperature threshold, a second chamber disposed adjacent to the first chamber, wherein unreacted fluids enter the second chamber at a temperature that is below a reaction temperature threshold that is necessary for reaction of the fluids to occur, the fluids flowing in a second direction, opposite the first direction and a porous wall disposed between the first chamber and a second chamber, allowing portions of the unreacted fluids from the second chamber to seep into the reacted fluids of the first chamber, thereby heating the seeped fluids, causing the seeped fluids to react, the reaction increasing the temperature of the reacted fluid.

A fuel gas nozzle used in a microturbine includes a first chamber, a second chamber connected to the first chamber, a pilot fuel gas pipe, a main fuel gas pipe and an intake pipe. An intake zone and a mixing zone are respectively formed in the first chamber and the second chamber and are communicated with each other. The pilot fuel gas pipe is for introducing a first fuel gas into a downstream of the second chamber. The main fuel gas pipe is for introducing a second fuel gas into the mixing zone via the intake zone. The intake pipe is for introducing an air into the mixing zone. A centerline of the intake pipe is not intersected with a centerline of the second chamber, so as to induce a vortex flow field of the air flowing into the mixing zone for mixing the air and the second fuel gas.

Provided is a combustor that includes a plurality of main burners disposed at intervals in a circumferential direction. The main burners include first main burners (16A) and second main burners (16B) that separately generate fuel-air mixtures. The second main burners (16B) generate fuel-air mixtures that have less evenness in concentration of fuel than the fuel-air mixtures generated by the first main burners (16A).

The present disclosure is directed to a dual-fuel fuel nozzle that includes a center body having a tube shape and a gas fuel plenum defined within the center body. The duel-fuel fuel nozzle also includes a ring manifold defining a liquid fuel plenum disposed within the center body. The duel-fuel fuel nozzle further includes a plurality of radially oriented fuel injectors in fluid communication with the liquid fuel plenum. Additionally, the duel-fuel fuel nozzle includes an inner fuel tube extending axially within the center body. A portion of the inner fuel tube extends helically about an axial centerline of the center body. The inner fuel tube is in fluid communication with an axially oriented fuel injector. Furthermore, the duel-fuel fuel nozzle includes first fuel tube extending helically around a portion of the inner fuel tube within the center body. The first fuel tube is fluidly coupled to the fuel plenum.

A combustor for a gas turbine engine includes an annular combustor shell, the annular combustor shell defining a combustion chamber, and a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion. The fuel injector includes a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis. A swirler for a gas turbine engine includes a swirler entrance and a swirler exit. The swirler exit has a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis.

A combustor of an embodiment includes: a cylindrical combustor liner; and a fuel nozzle which is provided at one end of the combustor liner and jets a fuel and an oxidant into the combustor liner. The fuel nozzle includes: a plurality of fuel supply passages which each supply the fuel; and a plurality of oxidant supply passages which each supply the oxidant. Flow rates of the fuel supplied to the respective fuel supply passages and flow rates of the oxidant supplied to the respective oxidant supply passages are each individually regulated.

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.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a monolithic body. The monolithic body includes a splash plate and a fuel nozzle. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface.

A fuel injector for a turbomachine includes an inner heat shield having an air cavity wall defining an air cavity for allowing air to flow therethrough. The inner heat shield includes an integral air swirler forming a downstream end thereof. The integral air swirler extends in an axially downstream direction at least as far as a fuel distribution channel defined on or in a fuel distributor of the injector to direct airflow at an outlet of the fuel distributor.