Combustor liner having dilution openings with swirl vanes

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

• a liner at least partially defining a combustion chamber,
• wherein the liner includes a plurality of dilution openings therethrough, each dilution opening of the plurality of dilution openings defined by (a) an outer wall defining an outer perimeter of the dilution opening and defining a dilution opening centerline axis through the dilution opening, and (b) a plurality of swirl vanes extending from the outer wall into a dilution airflow passage that extends through the dilution opening, each of the plurality of swirl vanes extending from the outer wall into the dilution airflow passage at a respective swirl vane angle with respect to the outer wall, the plurality of swirl vanes being arranged in a successive arrangement about the outer wall, and successive respective ones of the plurality of swirl vanes extend from the outer wall at a different swirl vane angle.