A burner for a combustor includes (a) a swirl generator enclosing a burner interior on an inlet side and including a tangential air inlet relative to a longitudinal center axis; (b) a mixing chamber enclosing the burner interior on an outlet side and defining a burner outlet fluidly connecting the burner interior with a combustion chamber; and (c) a lance arranged coaxially with the longitudinal center axis. The lance introduces fuel through a nozzle tip at or near the burner outlet into the combustion chamber. The nozzle tip includes a cartridge defining a center fuel passage; fuel swirl vanes within the center fuel passage at an outlet end of the nozzle tip; a first tube surrounding the center fuel passage and defining a first fluid passage; a second tube surrounding the first tube and defining a second fluid passage; and air swirl vanes in the second fluid passage.

A method and fuel supply system for supply of a combustion chamber with at least one combustible fluid are provided. The fuel supply system includes a combustion chamber, at least one supply circuit, and at least one purge circuit, the purge circuit coupled to the at least one supply circuit, the purge circuit including at least two isolation valves defining a cavity between, a source of relatively high temperature purge air coupled in flow communication to the cavity through one of the at least two isolation valves, a source of relatively low temperature ventilation air coupled in flow communication to the cavity, and a vent coupled in flow communication to the cavity, the at least one purge circuit configured to channel a flow of relatively low temperature ventilation air from the source relatively low temperature ventilation air through the cavity to the vent during operation of the combustion chamber.

A high excess air burner includes a housing including a generally tubular body enclosing an air chamber, a nozzle located in the air chamber and spaced radially inwardly of the generally tubular body, a fuel inlet configured to supply a variable volumetric flow rate of fuel, an air inlet configured to supply air to the air chamber, a first combustion cavity having a first inlet opening communicating with the fuel inlet for receiving the variable volumetric flow rate of fuel, a second combustion cavity having a second inlet opening communicating with the first combustion cavity for receiving the first fuel-air mixture, and a third combustion cavity having a third inlet opening communicating with the second combustion cavity for receiving the second fuel-air mixture. The burner including one or more components (e.g., nozzle, rear cover) to improve flame characteristics, such as flame stability or consistency, and/or one or more components or features to improve flame detection capability.

A horizontally-fired flame burner includes a flame holder positioned laterally from the burner. The flame holder includes a plurality of perforations that collectively confine a combustion reaction of the burner to the flame holder.

A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.

A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.

A fuel injection device, for a gas turbine, which enhances uniform distribution in concentration of fuel gas and water vapor in a combustion chamber with a simple structure and at low cost to effectively reduce NOx, is provided. The fuel injection device mixes fuel gas and water vapor and injects fuel gas and water vapor into a combustion chamber. The fuel injection device includes a nozzle housing having a mixing chamber, and the nozzle housing includes a first introduction passage to introduce fuel gas from an outer circumference of the nozzle housing in a circumferential direction of the mixing chamber; and a second introduction passage to introduce water vapor from the outer circumference of the nozzle housing in a circumferential direction of the mixing chamber. Fuel gas and water vapor are swirled about an axis C of the mixing chamber and mixed in the mixing chamber.

A wall-fired burner includes a fuel tip defining a fuel direction axis and a fuel tip pivot axis perpendicular thereto. A first air tip is adjacent to the fuel tip. The first air tip defines a first air direction axis and a first air tip pivot axis perpendicular thereto. A second air tip is adjacent to the fuel tip, opposite from the first air tip across the fuel tip. The second air tip defines a second air direction axis and a second air tip pivot axis perpendicular thereto. A mechanism operatively connects the fuel tip, the first air tip and the second air tip for at least one of independent and/or joint movement of the fuel tip, the first air tip and the second air tip.

Provided is an auxiliary burner for an electric furnace capable of increasing and homogenizing the heating effect of iron scrap by suitably and efficiently burning solid fuel along with gas fuel. This presently disclosed auxiliary burner 100 for an electric furnace comprises a solid fuel injection tube 1, a gas fuel injection tube 2, and a combustion-supporting gas injection tube 3 in the stated order from the center side, all arranged coaxially, and is characterized in that: a combustion-supporting gas flow path 30 of the combustion-supporting gas injection tube 3 is provided with a plurality of swirl vanes 4 for swirling the combustion-supporting gas, and the angle formed between the swirl vanes 4 and the burner axis is 5 or more and 45 or less.

Provided is an auxiliary burner for an electric furnace capable of increasing and homogenizing the heating effect of iron scrap by suitably and efficiently burning solid fuel along with gas fuel. This presently disclosed auxiliary burner 100 for an electric furnace comprises a solid fuel injection tube 1, a gas fuel injection tube 2, and a combustion-supporting gas injection tube 3 in the stated order from the center side, all arranged coaxially, and is characterized in that: a combustion-supporting gas flow path 30 of the combustion-supporting gas injection tube 3 is provided with a plurality of swirl vanes 4 for swirling the combustion-supporting gas, and the angle formed between the swirl vanes 4 and the burner axis is 5 or more and 45 or less.