Quench jet arrangement for annular rich-quench-lean gas turbine combustors

A combustor for a turbine engine, comprising:

• an outer liner having a first group of air admission holes and defining a plurality of outer liner regions, each outer liner region being separated from an adjacent outer liner region by an outer boundary line;
• an inner liner circumscribed by the outer liner and forming a combustion chamber therebetween, the inner liner having a second group of air admission holes and defining a plurality of inner liner regions, each inner liner region being separated from an adjacent inner liner region by an inner boundary line;
• and
• a plurality of fuel injectors extending into the combustion chamber and configured to deliver an air-fuel mixture to the combustion chamber, each of the plurality of fuel injectors being associated with one of the outer liner regions and one of the inner liner regions, wherein the first group of air admission holes within a respective outer liner region includes air admission holes that circumferentially alternate between approximately a first size and approximately a second size, the first size being different than the second size,
• wherein the first group of air admission holes includes
• a first air admission hole approximately on the outer boundary line between the respective outer liner region and a first adjacent outer liner region,
• a second air admission hole downstream of the first air admission hole and approximately axially aligned with one of the plurality of fuel injectors, and
• a third air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region,
• a fourth air admission hole downstream of the first air admission hole, upstream of the second air admission hole, and circumferentially between the first and second air admission holes,
• a fifth air admission hole downstream of the fourth air admission hole, upstream of the second air admission hole, and circumferentially between the fourth and second air admission hole,
• a sixth air admission hole upstream of the second air admission hole and approximately circumferentially aligned with the fifth air admission hole and circumferentially between the second and third air admission holes,
• a seventh air admission hole upstream of the sixth air admission hole, downstream of the third air admission hole, and circumferentially between the sixth and third air admission holes,
• wherein the first, third, fifth, and sixth air admission holes are the first size, and the second, fourth, and seventh air admission holes are the second size, and
• wherein the second group of air admission holes within a respective inner liner region includes an eighth air admission hole radially aligned with the first air admission hole of the first group, the eighth air admission hole being the second size,
• a ninth air admission hole radially aligned with the fourth air admission hole of the first group, the ninth air admission hole being the first size,
• a tenth air admission hole radially aligned with the fifth air admission hole of the first group, the tenth air admission hole being the second size,
• an eleventh air admission hole radially aligned with the second air admission hole of the first group, the eleventh air admission hole being the first size,
• an twelfth air admission hole radially aligned with the sixth air admission hole of the first group, the twelfth air admission hole being the second size,
• a thirteenth air admission hole radially aligned with the seventh air admission hole of the first group, the thirteenth air admission hole being the first size, and
• a fourteenth air admission hole radially aligned with the third air admission hole of the first group, the fourteenth air admission hole being the second size,
• wherein each of the air admission holes is configured to admit a quench jet into the combustion chamber.