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 fuel nozzle assembly and a gas turbine having the fuel nozzle assembly includes a fuel nozzle guide disposed in a compressed air channel formed between a body and a housing of a gas turbine and includes a nozzle body disposed in the housing, a shroud mounted on an outer side of the nozzle body, and two or more flow guides arranged at predetermined distances from each other between the shroud and the outer side of the nozzle body and formed to correspond to the shape of an end of the shroud and the shape of the outer surface of the nozzle body.

A gas-fired burner for a drying drum of an asphalt mixing plant, such that the burner preferably has a central primary air duct (6), which opens into a combustion zone (4) via a swirl body (2). The burner has gas supply openings (9) in the area of the circumferential boundaries of the swirl body (2) for supplying fuel gas to the primary air for firing the burner. It has been shown that a stable and well-developed flame can be produced over a very large load range with such burners according to the disclosure.

Disclosed herein are methods and systems for burning gaseous ammonia, including receiving a oxidizer gas into a chamber body such that the oxidizer gas generally flows in direction that extends along a longitudinal axis of the chamber body; introducing gaseous ammonia into the chamber body such that swirl is introduced into the gaseous ammonia; mixing the oxidizer gas and the gaseous ammonia to form a combustion mixture; igniting the combustion mixture; and combusting the combustion mixture for a duration such that the gaseous ammonia is converted to combustion products.

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 swirler includes a swirler body and a plurality of axial swirl vanes extending radially outward from the swirler body. At least one of the swirler body or vanes includes a spring channel defined therethrough. A fuel injector for a gas turbine engine can include an inner air swirler and/or outer air swirler as described above.

A burner comprises a tubular diffuser wall and an inlet passage a flow of a mixture of gas within the diffuser wall, as well as a first diaphragm arranged in the inlet passage, said diaphragm forming a plurality of through openings and a plurality of guide surfaces delimiting the through openings on a radially outer side thereof so that, when introducing the mixture, said guide surfaces and said through openings direct the mixture towards the inside of the burner and in a radial direction towards the longitudinal axis.

A swirler includes a swirler body and a plurality of axial swirl vanes extending radially outward from the swirler body. At least one of the swirler body or vanes includes a spring channel defined therethrough. A fuel injector for a gas turbine engine can include an inner air swirler and/or outer air swirler as described above.

A burner having a combustion space and a multiplicity of swirl channels. each having a fuel nozzle for introducing fuel into the respective swirl channel. and The swirl channels extend from an inflow side to an outflow side leading into the fuel space. The swirl channels can each be flowed through by a fuel-air mixture consisting of the fuel and air flowing into the swirl channel. The burner has a centre axis running through the combustion space and the swirl channels, emanating from the outflow side, are helically wound about the centre axis in portions, so that the fuel-air mixture flowing from the inflow side along the flow path to the outflow side flows through the swirl channels in each case is subjected to a swirl and flows into the combustion space in a swirl-subjected manner.

Gas burner, particularly for household cooking appliances, with an horizontal or vertical gas supply conduit (1), a burner body with one more flame crowns, an horizontal or vertical Venturi (4), a nozzle (5) to inject the gas flow from said gas conduit into said Venturi pipe and, means to provide the primary air flow which include a tubular conduit which is coaxial and placed outside said gas conduit, and an opening to allow the gas flow, placed between said nozzle and the inlet of the Venturi pipe. The coaxial conduit draws the respective air flow from a zone inside the body of said cooking appliance, and said opening allows the passage of the respective primary air flow sucked and coming from over the appliance top surface (12). In order to stir the primary air flow passing through said coaxial conduit, a plurality of radial wings (10A) is arranged, said wings being shaped either planar or helical, and being connected on the outer surface of said gas supply conduit.