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A combustor for a turbine engine includes an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor further includes an inner liner circumscribed by the outer liner and forming a combustion chamber therebetween, the inner liner having a

A combustor for a turbine engine includes an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor further includes 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. The combustor further includes 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. The first group 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.

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1. 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

1. 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; anda 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 each outer boundary line is defined approximately equidistant between respective adjacent fuel injectors,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, the third air admission hole being upstream of the second air admission hole, andwherein each of the air admission holes is configured to admit a quench jet into the combustion chamber,wherein the second group of air admission holes within a respective inner liner region includes air admission holes that circumferentially alternate between approximately the first size and approximately the second size, and wherein the air admission holes of the first group are arranged with respect to the air admission holes of the second group such that the air admission holes of the first size are radially aligned with the air admission holes of the second size. 2. The combustor of claim 1, wherein the first air admission hole and the third air admission hole are approximately the first size and the second air admission hole is approximately the second size. 3. The combustor of claim 2, wherein the first group of air admission holes further includes a fourth air admission hole downstream of the first air admission hole, upstream of the second air admission hole, and between the first and second air admission holes, anda fifth air admission hole downstream of the fourth air admission hole, upstream of the second air admission hole, and between the fourth and second air admission hole. 4. The combustor of claim 3, wherein the fourth air admission hole is approximately the second size and the fifth air admission hole is approximately the first size. 5. The combustor of claim 4, wherein the first group of air admission holes further includes a sixth air admission hole upstream of the second air admission hole, approximately circumferentially aligned with the fifth air admission hole, and between the second and third air admission holes, anda seventh air admission hole upstream of the sixth air admission hole, approximately circumferentially aligned with the fourth air admission hole, and between the sixth and third air admission holes,the sixth air admission hole being approximately the first size and the seventh air admission hole being approximately the second size. 6. The combustor of claim 5, 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, anda 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. 7. The combustor of claim 6, wherein the first size is larger than the second size. 8. The combustor of claim 1, wherein the first group of air admission holes has a pattern that is repeated in additional groups of air admission holes in the adjacent outer regions. 9. The combustor of claim 1, wherein the first group of air admission holes includes at least portions of at least seven air admission holes. 10. The combustor of claim 1, wherein the first group of air admission holes are plunged. 11. The combustor of claim 10, wherein the plunged air admission holes of the first group are integral with the outer liner. 12. The combustor of claim 10, wherein the plunged air admission holes of the first group each includes an insert that extends into the combustion chamber. 13. The combustor of claim 10, wherein the outer liner is a dual walled liner with a first wall and a second wall. 14. The combustor of claim 13, wherein the plunged air admission holes of the first group each includes an insert that directs air through the first wall, through the second wall, and into the combustion chamber. 15. The combustor of claim 1wherein the first group of air admission holes generally forms a V-shaped pattern. 16. 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; anda 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 includesa 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, anda 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, andwherein 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, anda 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.