Axial fuel stage injector with multiple mixing chambers, and combustor and GT system including same

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

• a combustor body including a combustion liner;
• and
• a plurality of axial fuel stage (AFS) injectors directed into the combustion liner, each AFS injector including:
• a mixing member including:
• a plurality of mixing chambers defined in the mixing member, each mixing chamber including an inlet and an outlet, wherein each outlet is configured to be in fluid communication with a combustion liner of the combustor, and
• a set of fuel injectors defined in a side wall of each mixing chamber;
• a high-pressure (HP) air injection member defining a set of HP air jets spaced from the inlet of each mixing chamber;
• a filter member upstream of the set of HP air jets;
• and
• a fuel plenum defined in the mixing member, the fuel plenum configured to deliver fuel from a fuel source to each set of fuel injectors,
• wherein each set of HP air jets is configured to direct a HP air from a HP air source into the inlet of a respective mixing chamber where fuel is injected by the set of fuel injectors.

A gas turbine (GT) system, comprising:

• a compressor section;
• a combustion section operatively coupled to the compressor section;
• and
• a turbine section operatively coupled to the combustion section,
• wherein the combustion section includes at least one combustor including:
• a combustor body including a combustion liner;
• a head end fuel nozzle assembly at a forward end of the combustor body;
• a plurality of axial fuel stage (AFS) injectors directed into the combustor body downstream of the head end fuel nozzle assembly, each AFS injector including:
• a mixing member including:
• a plurality of mixing chambers defined in the mixing member, each mixing chamber extending along a linear centerline and including an inlet and an outlet, wherein each outlet is configured to be in fluid communication with a combustion liner of the combustor, and
• a set of fuel injectors defined in a side wall of each mixing chamber;
• a high-pressure (HP) air injection member defining a set of HP air jets spaced from the inlet of each mixing chamber;
• a filter member upstream of the set of HP air jets;
• and
• a fuel plenum defined in the mixing member, the fuel plenum configured to deliver fuel from a fuel source to each set of fuel injectors,
• wherein each set of HP air jets is configured to direct a HP air from a HP air source into the inlet of a respective mixing chamber where fuel is injected by the set of fuel injectors.