Fuel nozzle assembly for gas turbine system

A fuel nozzle assembly, the fuel nozzle assembly comprising:

• an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween;
• a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus;
• an air injection feature having at least one inlet outward of the swirler assembly and at least one outlet downstream of the swirler assembly to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube;
• and
• a plurality of radially extending feed passages, each of the feed passages defined in one of the plurality of swirler vanes.

A fuel nozzle assembly, the fuel nozzle assembly comprising:

• an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween;
• a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus;
• an air injection feature having at least one inlet outward of the swirler assembly and at least one outlet downstream of the swirler assembly to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube;
• a cartridge extending through at least a portion of the inner burner tube and configured to flow a secondary fuel therethrough;
• and
• at least one radially extending injection bore defined in the inner burner tube and in fluid communication with the cartridge, the at least one injection bore configured to flow at least a portion of the secondary fuel from the cartridge into the pre-mixing annulus,
• wherein the secondary air interacts with secondary fuel disposed on the at least one of the outer burner tube and the inner burner tube.

A combustor for a gas turbine system, the combustor comprising:

• at least one fuel nozzle assembly, the at least one fuel nozzle assembly comprising:
• an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween;
• a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus;
• an air injection feature having at least one inlet outward of the swirler assembly and at least one outlet downstream of the swirler assembly to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube;
• and
• a sleeve associated with the one of the outer burner tube and the inner burner tube, the sleeve defining a plurality of bore holes configured to exhaust the secondary air adjacent the one of the outer burner tube and the inner burner tube.

A combustor for a gas turbine system, the combustor comprising:

• at least one fuel nozzle assembly, the at least one fuel nozzle assembly comprising:
• an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween;
• a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus;
• a plurality of radially extending feed passages, each of the feed passages defined in one of the plurality of swirler vanes;
• and
• an air injection feature having at least one inlet outward of the swirler assembly and at least one outlet downstream of the swirler assembly to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube.