An air and gas feeder device for gas boilers, comprising an air-gas conveyance body which comprises: a boiler coupling face configured to be coupled to a boiler at an intake duct of the boiler; an air intake port connected to an air discharge opening by means of an air passage, the air discharge opening leading out from the boiler coupling face; a gas intake port, configured to be fixed to a gas dispensing duct in fluid communication with a gas discharge opening, which leads out from the boiler coupling face; wherein the air discharge opening is coaxial to, and at least partially surrounded by, the gas discharge opening; the air passage accommodates a flow diverter configured to divert an air flow in output from the air discharge opening in the direction of the gas in output from the gas discharge opening and to impart a rotation to said air flow.

A swirler apparatus for a combustor, including: primary and secondary swirlers disposed axially adjacent to each other along a swirler centerline; the primary swirler including a plurality of primary swirl vanes arrayed around the swirler centerline, each primary swirl vane including opposed sides bounded between opposed forward and aft edges and opposed leading and trailing edges; wherein the forward edge is oriented at a first vane angle with respect to a radial direction; wherein the aft edge is oriented at a second vane angle with respect to the radial direction; wherein the second vane angle is different from the first vane angle; and the secondary swirler including a plurality of secondary swirl vanes arrayed around the swirler centerline.

Disclosed are a fuel nozzle assembly, and a fuel nozzle module and gas turbine having the same. The fuel nozzle assembly includes a fuel nozzle, a shroud spaced apart from the fuel nozzle and defining a flow path between an inner wall and the fuel nozzle, a rim formed around the shroud to guide air, and a turning guide spaced apart from the rim to distribute the air. The turning guide includes a turning separator spaced apart from the rim to extend in a circumferential direction of the rim, and inner separators extending in a radial direction of the rim to interconnect opposite circumferential ends of the turning separator and an outer surface of the fuel nozzle. The fuel nozzle assembly prevents air pockets, and ensures uniform supply of air, thereby preventing a local increase in combustion temperature inside the fuel nozzle and reducing generation of NOx.

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.

The invention is directed to a method for reducing NOx emission from an industrial process furnace comprising a firebox containing a burner and a tube, which method comprises subjecting an oxidant gas and/or a fuel gas (1) to humidification, thereby obtaining a humidified gas; and pre-heating the humidified gas with an external waste heat stream (20) before feeding the gas to the burner.

A fuel nozzle assembly includes an inner fuel nozzle; a plurality of outer fuel nozzles disposed radially around the inner fuel nozzle, each outer fuel nozzle including a central body for fuel injection, a shroud spaced apart from and surrounding the central body, the shrouds forming an outer periphery of the fuel nozzle assembly, and an inlet formed at one end of the shroud; and a peripheral rim formed at the inlets and disposed to cover at least a portion of the outer periphery. The fuel nozzle assembly is connected to an end plate of a combustion chamber. The one end of a corresponding shroud is disposed at a set distance from an end plate of a combustion chamber, the set distance depending on at least one of relative positions of the inner fuel nozzle and the plurality of outer fuel nozzles and an inlet radius of the corresponding shroud.

A burner for a gas turbine engine has a combustion chamber and a swirler adapted to guide a swirler air flow to the combustion chamber, wherein the swirler has a first wall confining the swirler air flow as well as a second wall confining the swirler air flow on the same side as and downstream with respect to the swirler air flow from the first wall and being displaced with respect to the first wall in a direction away from the swirler air flow so that a step being able to cause a flow separation of the swirler air flow is formed by the first wall and the second wall, wherein the second wall has a through hole in its surface adapted to inject a liquid fuel into the swirler air flow.

A fuel supply device includes a first supply pipe, a first on-off valve, a second on-off valve, a second supply pipe, a connection pipe, a third on-off valve, and a leak check measuring device, and performs a leak check of the first supply pipe.

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 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.