Combustor with additively manufactured combustor body having impingement cooling of combustion liner near aft frame

An additively manufactured (AM) combustor body having 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 and an outer end configured to couple to a turbine inlet casing;
• 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;
• a flow sleeve integral with the plurality of circumferentially spaced ribs and defining a circumferentially extending passage with the combustion liner and the inner end of the aft frame, wherein the flow sleeve includes an aft end;
• a circumferential inlet to the circumferentially extending passage defined between the aft end of the flow sleeve and the inner end of the aft frame;
• an internal impingement cavity defined by and within material of the transition portion of the combustion liner radially inward of the circumferential inlet;
• and
• a plurality of impingement openings defined in the transition portion of the combustion liner that extend from the circumferentially extending passage to the internal impingement cavity,
• wherein the AM combustor body further includes a plurality of parallel, metallurgically bonded metal layers.

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 having a one-piece member including:
• a combustion liner having 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 and an outer end configured to couple to a turbine inlet;
• 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;
• a flow sleeve integral with the plurality of circumferentially spaced ribs and defining a circumferentially extending passage with the combustion liner and the inner end of the aft frame, wherein the flow sleeve includes an aft end;
• a circumferential inlet to the circumferentially extending passage defined between the aft end of the flow sleeve and the inner end of the aft frame;
• an internal impingement cavity defined by and within material of the transition portion of the combustion liner radially inward of the circumferential inlet;
• and
• a plurality of impingement openings defined in the transition portion of the combustion liner that extend from the circumferentially extending passage to the internal impingement cavity,
• wherein the AM combustor body further includes a plurality of parallel, metallurgically bonded metal layers.