Combustor with additively manufactured combustor body having aft frame with heat transfer augmentation

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:
• an additively manufactured (AM) combustor body including a one-piece member including:
• a combustion liner including a transition portion;
• an aft frame at an aft end of the transition portion, the aft frame including an inner end integral with the combustion liner, an outer end configured to couple to a turbine inlet, and a circumferentially extending passage defined within the inner end;
• a plurality of circumferentially spaced ribs extending forward from the inner end of the aft frame on an exterior surface of the transition portion of the combustion liner;
• and
• a first flow sleeve integral with the plurality of circumferentially spaced ribs, wherein the first flow sleeve extends circumferentially around the transition portion at a location forward of the aft frame and includes an aft end axially spaced from the aft frame,
• wherein the aft frame includes an intermediate portion between the inner end and the outer end thereof, and further comprising a plurality of circumferentially spaced openings defined circumferentially between the plurality of circumferentially spaced ribs aft of the aft end of the first flow sleeve and defined axially between the intermediate portion and the aft end of the first flow sleeve, wherein the plurality of circumferentially spaced openings are in fluid communication with the circumferentially extending passage in the inner end of the aft frame, and
• wherein the AM combustor body further includes a plurality of parallel, sintered metal layers.