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 swirler with a fuel manifold, and a combustor and gas turbine including the same are provided. The swirler may include a swirler body disposed between an inner surface of a fuel nozzle and an outer surface of a center body, a fuel injection hole disposed on the swirler body, a fuel manifold formed in the swirler body, the fuel manifold being connected to a fuel channel disposed in the center body while communicating with the fuel injection hole, and a turbulence alleviator formed at a fuel inlet of the fuel manifold to alleviate creation of turbulence of fuel flowing from the fuel channel to the fuel manifold.

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 combustor having an ion transport membrane therein and an adjustable swirler, which is mechanically connected at an inlet of a combustion zone of the combustor; a combustion system comprising the combustor, a feedback control system adapted to adjust swirler blades of the combustor based on a compositional variation of a fuel stream, and a plurality of feedback control systems to control operational variables within the combustor for an efficient oxy-combustion; and a process for combusting a fuel stream via the combustion system. Various embodiments of the combustor, the combustion system, and the process for combusting the fuel stream are disclosed.

A gas turbine combustor is equipped with a nozzle in which an air ejection passage extending along an axis and having an open distal end, and a fuel supply passage extending along the axis and having an open distal end are formed; swirling vanes provided around the nozzle so as to be twisted around the axis of the nozzle; an inner cylinder surrounding an outer periphery of the nozzle and the swirling vanes, and in which compressed air flows through an inside of the inner cylinder toward a downstream side; an outer cylinder which defines an inversion flow path, which inverts the compressed air on an outer periphery of the inner cylinder and introduces the compressed air to the inside of the inner cylinder, between the inner and outer cylinders; and an air introduction pipe having one end connected to a space on an upstream side of the compressed air from the inversion flow path, and the other end connected to the air ejection passage.

A combustor having an ion transport membrane therein and an adjustable swirler, which is mechanically connected at an inlet of a combustion zone of the combustor; a combustion system comprising the combustor, a feedback control system adapted to adjust swirler blades of the combustor based on a compositional variation of a fuel stream, and a plurality of feedback control systems to control operational variables within the combustor for an efficient oxy-combustion; and a process for combusting a fuel stream via the combustion system. Various embodiments of the combustor, the combustion system, and the process for combusting the fuel stream are disclosed.

A combustor includes: a nozzle main body having a shaft body and a swirl vane; a first fuel flow path which supplies fuel to a first fuel injection hole formed in the nozzle main body; a second fuel flow path which supplies fuel to a second fuel injection hole formed on a radial outer side of the first fuel injection hole in the nozzle main body; a first regulating valve provided in the first fuel flow path and configured to regulate a flow rate of the fuel flowing through the first fuel flow path; a temperature sensor-which detects a temperature on a downstream side of the swirl vane; and a control device which controls the first regulating valve so that the flow rate of the fuel flowing through the first fuel flow path is lowered when a temperature detected by the temperature sensor satisfies a predetermined condition.

Provided herein is a swirler for a gas turbine. The swirler includes a support plate including an injection part to inject a fuel supplied from the outside, a support shaft connected to the support plate, a guide part connected to the support plate and the support shaft and configured to mix a fluid introduced via a side surface of the support plate with the fuel injected from the injection part and to guide the mixture in at least one of a first direction and a second direction, the first direction being a longitudinal direction of the support shaft and the second direction being a direction swirling the support shaft, and a cover housing spaced apart from the support plate and coupled to the guide part so as to form a transfer flow path of the fluid together with the guide part.

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.

A diffusion cartridge assembly for a gas turbine engine, and methods of using the same. The diffusion cartridge assembly includes a tip plate with an array of fuel supply openings and a mounting hole radially inward of the array of fuel supply openings, an end cover, and an outer sleeve extending from the tip plate to the end cover and defining an open inner chamber. A fuel supply line is coupled to the end cover and extends within the open inner chamber toward the tip plate. A manifold is coupled to an end of the fuel supply line proximate to the tip plate, and includes an array of fuel injector tips. Each of the fuel injector tips extends through a respective one of the array of fuel supply openings in the tip plate. The manifold also includes a thermally free mounting pin extending into the mounting hole.