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.

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.

A combustion burner includes a nozzle and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle. The swirl vane includes a tip portion for swirling gas, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle, the root portion having a cutout on a side of a trailing edge. The radially-outer region and a radially-inner region of the axial flow path communicate with each other, at least in a range in the axial direction in which the swirl vane is disposed. The swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge.

A burner includes a pilot burner, a combustion chamber, and a swirler located radially outwardly of the combustion chamber and being adapted to impose a swirling motion on a fuel/air mixture about an axial centerline of the combustion chamber. The pilot burner has a pilot burner face located radially inwardly of the swirler and forms an axially upstream wall of the combustion chamber, the pilot burner face incorporating a pilot fuel injector and an ignitor, both being positioned radially offset from the axial centerline. A recess is positioned radially offset from the axial centerline within the pilot burner face.

A swirler for mixing fuel with air in a combustion engine includes a central axis, a swirler base with an upper surface, a central portion, a number of main swirler elements and a number of obstruction elements. The main swirler elements and the obstruction elements are located at the upper surface of the swirler base and are arranged around the central portion. The main swirler elements form a number of swirler slots configured for directing a fluid towards the central portion. Each swirler slot has a slot inlet and a slot outlet, wherein the slot outlet is located at a smaller radial distance from the central axis than the swirler inlet. Each obstruction element is located at a slot inlet and configured for forming a plurality of flow channels into the swirler slot.

A fuel injector for a combustion engine includes an injector head including a nozzle, a premixer, and a distributor structured to distribute a plurality of different fuels to different sets of fueling orifices in the premixer. A pilot assembly of the fuel injector is coupled to the premixer and includes a first fueling passage for a first fuel and a second fueling passage for a second fuel. Multiple sets of fueling orifices are positioned within the fuel injector, the fueling orifice sets being selectively connectable to a plurality of different fuel supplies, and both located and sized so as to accommodate a wide range of flow rates to enable a combustion engine coupled with the fuel injector to operate on fuels having a range of Wobbe numbers and compositions.

The burner of a gas turbine has a duct, a vortex generator extending in the duct and including a leading edge and a trailing edge. The trailing edge has a first order lobed shape. The first order lobed shape is defined by a second order lobed shape. Preferably a nozzle for fuel injection is connected to the vortex generator and the second order lobed shape is only provided at the nozzles.

A combustion system for a gas turbine includes a combustion chamber having an end section and a pre-combustion section extending from the end section, a swirler device, an optional pilot burner device and a light emitting arrangement. Main fuel is injectable by the swirler device into an inner volume of the pre-combustion section. The main flame using main fuel is producible inside the inner volume. The pilot burner device is mounted to the end section of the combustion chamber such that a pilot fuel is injectable by the pilot burner device into the inner volume of the pre-combustion section, wherein a pilot flame using the pilot fuel is producible inside the inner volume for stabilizing the main flame. The light emitting arrangement emits an electromagnetic radiation into the inner volume, such that an energy input is generatable by the electromagnetic radiation for stabilizing the pilot flame and/or the main flame.

A combustor for a gas turbine, having a pre-combustion chamber having a peripheral wall around a center axis of the pre-combustion chamber, the peripheral wall has an inner panel and an outer panel and a passage provided between the inner and the outer panels, a swirler which is connected to the pre-combustion chamber for providing pre-combustion chamber with a flow of an oxidant gas, at least a pilot fuel injector, wherein the swirler is connected to the peripheral wall in such a way that a portion of the oxidant gas from the swirler is channeled to the passage, and the pilot fuel injector is connected to the passage for injecting a flow of pilot fuel into the passage.

A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a premixing chamber formed between an outer annular shroud and an inner annular hub, a number of swirler vanes disposed about the premixing chamber between the outer annular shroud and the inner annular hub, one or more liquid fuel injectors positioned about the swirler vanes, and a flow of liquid fuel in communication with the one or more liquid fuel injectors.