A turbine engine can utilize a combustor to combust fuel to drive the turbine, which drives 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. Increasing efficiency and carbon-containing emission needs benefit from the use of alternative fuels, which combust at higher temperatures than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

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 inventive concept relates to a swirler. According to an aspect of the inventive concept, there is provided a swirler including a casing, a pilot body disposed in the casing, and a plurality of vanes arranged along a circumference of the pilot body, wherein at least a part of the vane protrudes further to a downstream than an end portion of the pilot body.

The inventive concept relates to a swirler. According to an aspect of the inventive concept, there is provided a swirler including a casing, a pilot body disposed in the casing, and a plurality of vanes arranged along a circumference of the pilot body, wherein at least a part of the vane protrudes further to a downstream than an end portion of the pilot body.

A fuel injector for injecting alternate fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) may be fluidly coupled to a radial passage (22) in a plurality of vanes (20) that branches into passages (24) (e.g., axial passages) to inject a first fuel without jet in cross-flow injection. This may be effective to reduce flashback in fuels having a relatively high flame speed. A mixer (30) with lobes (32) for injection of a second fuel may be arranged at the downstream end of a fuel delivery tube (12). A fuel-routing structure (38) may be configured to route the second fuel within a respective lobe so that fuel injection of the second fuel takes place radially outwardly relative to a central region of the mixer. This may be conducive to an improved (e.g., a relatively more uniform) mixing of air and fuel.

A fuel injector for injecting alternate fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) may be fluidly coupled to a radial passage (22) in a plurality of vanes (20) that branches into passages (24) (e.g., axial passages) to inject a first fuel without jet in cross-flow injection. This may be effective to reduce flashback in fuels having a relatively high flame speed. A mixer (30) with lobes (32) for injection of a second fuel may be arranged at the downstream end of a fuel delivery tube (12). A fuel-routing structure (38) may be configured to route the second fuel within a respective lobe so that fuel injection of the second fuel takes place radially outwardly relative to a central region of the mixer. This may be conducive to an improved (e.g., a relatively more uniform) mixing of air and fuel.

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.

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.

A combustion gas supply system and method includes: a cyclonic air filter (or separator), a blower having an inlet and an outlet, and a combustible gas inlet, wherein the cyclonic air filter, the blower, and the combustible gas inlet are in fluid communication.

A combustion gas supply system and method includes: a cyclonic air filter (or separator), a blower having an inlet and an outlet, and a combustible gas inlet, wherein the cyclonic air filter, the blower, and the combustible gas inlet are in fluid communication.