A combustor for a turbine engine, comprising: an outer liner having a first group of air admission holes (750, 752) and defining a plurality of outer liner regions (702, 704), each outer liner region (702, 704) being separated from an adjacent outer liner region (702, 704) by an outer boundary line (770, 774); 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 (850, 852) and defining a plurality of inner liner regions (702, 704), each inner liner region (702, 704) being separated from an adjacent inner liner region (702,704) by an inner boundary line (870, 874); and a plurality of fuel injectors (644, 646) extending into the combustion chamber and configured to deliver an air-fuel mixture to the combustion chamber, each of the plurality of fuel injectors (644, 646) being associated with one of the outer liner regions (702, 704) and one of the inner liner regions (702, 704), wherein the first group of air admission holes (750, 752) within a respective outer liner region (702, 704) includes air admission holes that circumferentially alternate between a first size and a second size, the first size being different than the second size, wherein the second group of air admission holes (850, 852) within a respective inner liner region includes air admission holes that circumferentially alternate between the first size and the second size, characterised in that 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. an outer liner having a first group of air admission holes (750, 752) and defining a plurality of outer liner regions (702, 704), each outer liner region (702, 704) being separated from an adjacent outer liner region (702, 704) by an outer boundary line (770, 774); 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 (850, 852) and defining a plurality of inner liner regions (702, 704), each inner liner region (702, 704) being separated from an adjacent inner liner region (702,704) by an inner boundary line (870, 874); and a plurality of fuel injectors (644, 646) extending into the combustion chamber and configured to deliver an air-fuel mixture to the combustion chamber, each of the plurality of fuel injectors (644, 646) being associated with one of the outer liner regions (702, 704) and one of the inner liner regions (702, 704), wherein the first group of air admission holes (750, 752) within a respective outer liner region (702, 704) includes air admission holes that circumferentially alternate between a first size and a second size, the first size being different than the second size, wherein the second group of air admission holes (850, 852) within a respective inner liner region includes air admission holes that circumferentially alternate between the first size and the second size, characterised in that 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.