Patent ID: 8171740

Claim:
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, 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 a first plunged air admission hole approximately axially aligned with the respective fuel injector, a second plunged 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, a third plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region, fourth and fifth plunged air admission holes arranged on a line between the first and second plunged air admission holes, and sixth and seventh plunged air admission holes arranged on a line between the second and third plunged air admission holes.