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 burner designed to be fitted in a combustion chamber, the burner including: a central nozzle configured to have an oxidizer and fuel supply; several peripheral nozzles configured to have an oxidizer and fuel supply and which each have at least one upstream fuel injector in order to pre-mix the fuel and the oxidizer in the nozzle; at least one oxidizer input connected to the said central and/or peripheral nozzles; wherein peripheral nozzles each have a flame stabilizer located at the end of the peripheral nozzle designed to exit into the combustion chamber, as well as a tip injector to inject fuel at the end of the peripheral nozzle.

A combustion head for a burner is provided with an outer sleeve, which houses, on the inside, a first feeding device to feed a gaseous fuel into an oxidizing air flow fed along the outer sleeve by means of a pneumatic ventilation device, at least one swirl device, which is configured to cause a primary flow F.sub.1 of gaseous fuel and oxidizing air flowing out of the outer sleeve to make a helical movement, and at least one feeding channel with an annular shape, which is obtained between the outer sleeve and the swirl device in order to feed a secondary flow F.sub.2 of oxidizing air around the primary flow F.sub.1; a second feeding device being mounted on the outside of the outer sleeve and being connected to a gaseous fuel source.

In a combustor including a plurality of combustion nozzles, and a gas turbine including the same, fuel can be uniformly mixed with compressed air for each combustion nozzle. The combustor includes a plurality of combustion nozzles arranged in a nozzle casing, and each combustion nozzle includes a nozzle shroud for taking in compressed air; an injection cylinder concentrically disposed in the nozzle shroud and configured to be supplied with fuel for mixing with the compressed air; and a plurality of swirlers circumferentially arranged around the injection cylinder and configured to inject the fuel from the injection cylinder into the shroud. The plurality of swirlers divide an interior space of the nozzle shroud into a plurality of fluid flow regions, and include a pair of adjacent swirlers spaced apart from each other by a circumferential distance that differs from a circumferential distance between another pair of adjacent swirlers.

Adhesion of particulate matters to the burner accompanying combustion in a lean-combustion gas turbine combustor is suppressed, and the structural reliability is improved. In a gas turbine combustor including: a tubular liner that forms a combustion chamber; and a burner including an air hole plate that is arranged at an inlet of the liner and includes a plurality of air holes for guiding compressed air to the combustion chamber, and a plurality of fuel nozzles that are arranged on a side opposite to the combustion chamber with the air hole plate being sandwiched therebetween, the plurality of fuel nozzles each injecting a fuel toward a corresponding air hole, the air holes and the fuel nozzles forming a plurality of concentric annular lines, a plurality of small holes having opening diameters smaller than those of the air holes are provided through the air hole plate such that the plurality of small holes are positioned in an inner area of an innermost annular line of the air holes.

A method for assembling a fuel distribution system for a turbomachine fuel injector includes inserting a liquid fuel distributor into an interior cavity of a shroud to create a liquid fuel distribution circuit between the liquid fuel distributor and the shroud and inserting a gas fuel distributor into the interior cavity of the shroud and into an interior cavity of the liquid fuel distributor to create a gas fuel distribution circuit between the gas fuel distributor and the liquid fuel distributor. The method includes inserting a fuel transfer tube into an outer diameter of the shroud. The method includes brazing or shrink fitting at least one of the fuel transfer tube, the gas fuel distributor, or the liquid fuel distributor to the shroud.

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 along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.

A method for assembling a fuel distribution system for a turbomachine fuel injector includes inserting a liquid fuel distributor into an interior cavity of a shroud to create a liquid fuel distribution circuit between the liquid fuel distributor and the shroud and inserting a gas fuel distributor into the interior cavity of the shroud and into an interior cavity of the liquid fuel distributor to create a gas fuel distribution circuit between the gas fuel distributor and the liquid fuel distributor. The method includes inserting a fuel transfer tube into an outer diameter of the shroud. The method includes brazing or shrink fitting at least one of the fuel transfer tube, the gas fuel distributor, or the liquid fuel distributor to the shroud.

An apparatus includes first and second mixer tubes. The first mixer tube contains a first gas flow passage having an inlet communicating with the source of fuel gas and an outlet to a combustion chamber. The second mixer tube contains a second gas flow passage having an inlet communicating with the source of combustion air and an outlet to the combustion chamber. The apparatus further includes premix control means for forming fuel gas-combustion air premix in the second passage by directing fuel gas from the first passage into the second passage, and for alternatively forming fuel gas-combustion air premix in the first passage by directing combustion air from the second passage into the first passage.

The present invention reduces the concentration of thermal stress on a burner. A gas turbine combustor receiving compressed air from a compressor, mixing the compressed air with a fuel, burning the mixture to generate a combustion gas, and supplying the combustion gas to a turbine. The combustor includes: an inner cylinder internally forming a combustion chamber; an outer cylinder covering the inner cylinder and forming a cylindrical outer circumferential flow path between the inner and outer cylinders to allow the compressed air to flow; and a burner mounted on an end of the outer cylinder, which is positioned on an opposite side to a turbine side, and facing the combustion chamber. The burner includes a cylindrical base frame including a cavity distributing the fuel, and fuel nozzles circularly arranged as viewed from the combustion chamber and connected to the cavity. When viewed from the combustion chamber, slits extending radially are formed in the base frame such that each separate the circumferentially adjacent fuel nozzles from each other.