A combustion burner for a boiler includes: an inner cylinder defining a fuel supply passage for supplying fuel; an outer cylinder surrounding the inner cylinder and defining an air supply passage between the inner cylinder and the outer cylinder; and a swirler in the air supply passage, the swirler being configured to swirl air in the air supply passage. The swirler includes a plurality of blades radially disposed between the inner cylinder and the outer cylinder, the plurality of blades extending from an air-supply side toward a combustion-space side of the air supply passage, and each of the plurality of blades having, at least on an inner cylinder side of the blade, a section with a thickness varied in a burner axial direction, the thickness being smaller at an edge portion on the combustion-space side than at a maximum-thickness section of the blade.

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.

A combustor for a gas turbine engine includes an annular combustor shell, the annular combustor shell defining a combustion chamber, and a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion. The fuel injector includes a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis. A swirler for a gas turbine engine includes a swirler entrance and a swirler exit. The swirler exit has a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis.

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.

A rotation-suspension smelting method, in which a powdered sulfide concentrate and an oxygen-containing gas are sprayed into a high-temperature reaction tower. The oxygen-containing gas is divided into two parts: the second oxygen-containing gas is sprayed in the form of an annular direct flow into the reaction tower and forms a bell-shaped wind curtain; and the first oxygen-containing gas is transformed into a rotation-jet and jetted into the center of the wind curtain. In the space between the gas flows, the concentrate entering in a direction deviated towards the center is drawn in the rotation-jet, and a high-temperature off-gas is sucked in, forming a gas-particle mixed two-phase rotation-jet. The sulfide concentrate is ignited, at the same time, a melt containing matte (or metal) and slag is formed; and the matte (or metal) is separated from the slag at the bottom of the reaction tower, completing the metallurgical process.

A biomass-mixed, pulverized coal-fired burner is provided, capable of burning biomass fuel as auxiliary fuel in large quantities and burning only pulverized coal when the biomass fuel is not sufficiently available. The biomass-mixed, pulverized coal-fired burner includes a biomass fuel jet nozzle that extends axially along the biomass-mixed, pulverized coal-fired burner, a fuel jet nozzle that is open midway in the biomass fuel jet nozzle, a secondary air nozzle that surrounds the fuel jet nozzle, and a tertiary air nozzle that surrounds the secondary air nozzle. A pulverized coal component in a fuel stream as a mixture of the pulverized coal fuel stream and the biomass fuel stream is distributed with a higher concentration on an outer circumferential wall side and a biomass fuel component in the fuel stream is distributed inside of the pulverized coal fuel component.

In order to create a safe and simply designed fire column, the flame of which is fed from a fuel tank, in particular for bioethanol, and is surrounded by an outer casing (4), wherein supply air flows in largely axially in the lower region of the outer casing via a plurality of guide elements (3) and is preferably set in helical rotation to form a swirling flame, according to the invention the outer casing (4) is placed over the guide elements (3). The outer casing (4) is preferably centered in an upright position by outer edges (3a) of the guide elements (3).

An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.

The present disclosure includes air spinners for use in duct burners, and duct burners and duct burner kits including a plurality of air spinners. Air spinners may include a plurality of blades extending radially outward from a fuel path and configured to impart rotation to air flowing between the blades, where the air spinner is configured to be coupled to a fuel runner of a duct burner such that the air spinner encircles a fuel outlet of the fuel runner with the axis of the fuel path extending at a non-parallel angle from an axis of the fuel runner. Duct burners can comprise a plurality of air spinners coupled to a plurality of fuel runners. Duct burner kits can comprise a plurality of air spinners configured to be coupled (e.g., without welding) to a plurality of fuel runners.