Annular combustor dilution with swirl vanes for lower emissions

A combustor liner for a combustor of a gas turbine engine, the combustor including a combustion chamber, the combustor liner defining an axial direction, a radial direction, and a circumferential direction about a combustor centerline, the combustor liner comprising:

• an outer liner extending circumferentially about the combustor centerline, and extending in the axial direction from an outer liner upstream end to an outer liner downstream end, an outer liner dilution zone defined between the outer liner upstream end and the outer liner downstream end, the outer liner having an outer liner cold surface side and an outer liner hot surface side, and defining an outer liner flow direction extending in the axial direction from the outer liner upstream end to the outer liner downstream end, the outer liner including an annular outer liner radial wall located at the outer liner dilution zone, the annular outer liner radial wall extending from the outer liner at least partially in the radial direction into the combustion chamber, the annular outer liner radial wall and the outer liner defining an annular outer liner slot dilution opening therebetween, the annular outer liner slot dilution opening extending through the outer liner, the annular outer liner radial wall and the annular outer liner slot dilution opening extending continuously in the circumferential direction about the combustor centerline, the annular outer liner slot dilution opening including a plurality of outer liner swirl vanes therewithin;
• and
• an inner liner extending circumferentially about the combustor centerline, and extending in the axial direction from an inner liner upstream end to an inner liner downstream end, an inner liner dilution zone defined between the inner liner upstream end and the inner liner downstream end, the inner liner having an inner liner cold surface side and an inner liner hot surface side, and defining an inner liner flow direction extending in the axial direction from the inner liner upstream end to the inner liner downstream end, the inner liner including an annular inner liner radial wall located at the inner liner dilution zone, the annular inner liner radial wall extending from the inner liner at least partially in the radial direction into the combustion chamber, the annular inner liner radial wall and the inner liner defining an annular inner liner slot dilution opening therebetween, the annular inner liner slot dilution opening extending through the inner liner, the annular inner liner radial wall and the annular inner liner slot dilution opening extending continuously in the circumferential direction about the combustor centerline, the annular inner liner slot dilution opening including a plurality of inner liner swirl vanes therewithin,
• wherein the combustion chamber is defined between the outer liner hot surface side of the outer liner and the inner liner hot surface side of the inner liner.