Axial fuel stage immersed injectors with internal cooling

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

• a combustion liner;
• a plurality of axial fuel stage (AFS) immersed injectors extending radially into the combustion liner, each AFS immersed injector including an injector body including:
• an outer wall defining a hollow interior and having a plurality of film cooling holes extending from the hollow interior to an outside of the outer wall;
• an inner wall spaced from an inside of the outer wall along at least part of a length of the outer wall, the inner wall defining an air plenum therein;
• a first plurality of impingement cooling holes extending through the inner wall along at least a first portion of the inner wall, the first plurality of impingement cooling holes in fluid communication with the air plenum;
• a fuel passage extending at least partially along the hollow interior of the outer wall;
• and
• a plurality of fuel nozzles extending through at least one of the inner wall and the outer wall to the outside of the outer wall, each fuel nozzle in fluid communication with the fuel passage.

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 combustion liner and a plurality of axial fuel stage (AFS) immersed injectors extending radially into the combustion liner, each AFS immersed injector including an injector body including:
• an outer wall defining a hollow interior and having a plurality of film cooling holes extending from the hollow interior to an outside of the outer wall;
• an inner wall spaced from an inside of the outer wall along at least part of a length of the outer wall, the inner wall defining an air plenum therein;
• a first plurality of impingement cooling holes extending through the inner wall along at least a first portion of the inner wall, the first plurality of impingement cooling holes in fluid communication with the air plenum;
• a fuel passage extending at least partially along the hollow interior of the outer wall;
• and
• a plurality of fuel nozzles extending through at least one of the inner wall and the outer wall to the outside of the outer wall, each fuel nozzle in fluid communication with the fuel passage.