A combustor for a turbine engine, comprising: an outer liner (28, 228) having a first group of air admission holes (250, 252) and defining a plurality of outer liner regions (202, 204), each outer liner region (202, 204) being separated from an adjacent outer liner region (202, 204) by an outer boundary line (270, 274); an inner liner (30, 330) circumscribed by the outer liner (28, 228) and forming a combustion chamber therebetween, the inner liner (30, 330) having a second group of air admission holes (350, 352) and defining a plurality of inner liner regions (302, 304), each inner liner region (302, 304) being separated from an adjacent inner liner region (302, 304) by an inner boundary line 370, 374); and a plurality of fuel injectors (44, 244, 246, 344, 346) extending into the combustion chamber and configured to deliver an air-fuel mixture to the combustion chamber, each of the plurality of fuel injectors (44, 244, 246, 344, 346) being associated with one of the outer liner regions (202, 204) and one of the inner liner regions (302, 304), wherein the first group of air admission holes (250, 252) within a respective outer liner region (202, 204) includes a first air admission hole axially aligned with the respective fuel injector and a second air admission hole approximately on the outer boundary line between the respective outer liner region and a first adjacent outer liner region, the first air admission hole being downstream of the second air admission hole, wherein the first group of air admission holes (250, 252) includes a third air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region, characterized in that the first group of air admission holes (250, 252) includes a fourth air admission hole (264, 265) downstream of the second air admission hole, upstream of the first air admission hole, and circumferentially between the first and second air admission holes (263, 266), the first group of air admission holes (250, 252) further including a fifth air admission hole (261, 262) downstream of the third air admission hole, upstream of the first air admission hole, and circumferentially between the third and first air admission holes (260, 263), and in that each of the first group of air admission holes is a combustion air admission hole configured to admit a quench jet into the combustion chamber. an outer liner (28, 228) having a first group of air admission holes (250, 252) and defining a plurality of outer liner regions (202, 204), each outer liner region (202, 204) being separated from an adjacent outer liner region (202, 204) by an outer boundary line (270, 274); an inner liner (30, 330) circumscribed by the outer liner (28, 228) and forming a combustion chamber therebetween, the inner liner (30, 330) having a second group of air admission holes (350, 352) and defining a plurality of inner liner regions (302, 304), each inner liner region (302, 304) being separated from an adjacent inner liner region (302, 304) by an inner boundary line 370, 374); and a plurality of fuel injectors (44, 244, 246, 344, 346) extending into the combustion chamber and configured to deliver an air-fuel mixture to the combustion chamber, each of the plurality of fuel injectors (44, 244, 246, 344, 346) being associated with one of the outer liner regions (202, 204) and one of the inner liner regions (302, 304), wherein the first group of air admission holes (250, 252) within a respective outer liner region (202, 204) includes a first air admission hole axially aligned with the respective fuel injector and a second air admission hole approximately on the outer boundary line between the respective outer liner region and a first adjacent outer liner region, the first air admission hole being downstream of the second air admission hole, wherein the first group of air admission holes (250, 252) includes a third air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region, characterized in that the first group of air admission holes (250, 252) includes a fourth air admission hole (264, 265) downstream of the second air admission hole, upstream of the first air admission hole, and circumferentially between the first and second air admission holes (263, 266), the first group of air admission holes (250, 252) further including a fifth air admission hole (261, 262) downstream of the third air admission hole, upstream of the first air admission hole, and circumferentially between the third and first air admission holes (260, 263), and in that each of the first group of air admission holes is a combustion air admission hole configured to admit a quench jet into the combustion chamber.