Patent ID: 7926284

Claim:
A combustor for a turbine engine, comprising: an outer liner having a first row and a second row of circumferentially distributed air admission holes penetrating therethrough for admitting dilution jets of air, the air admission holes of the first and second rows of the outer liner having leading and trailing edges such that the leading edges of the second row of the outer liner are downstream of the trailing edges of the first row of the outer liner, and the air admission holes of the first row of the outer liner being larger than the air admission holes of the second row of the outer liner; an inner liner circumscribed by the outer liner and having a first row and a second row of circumferentially distributed air admission holes penetrating therethrough for admitting dilution jets of air, the air admission holes of the first and second rows of the inner liner having leading and trailing edges such that the leading edges of the second row of the inner liner are downstream of the trailing edges of the first row of the inner liner, the air admission holes of the first row of the inner liner being larger than the air admission holes of the second row of the inner liner, and the inner and outer liners forming a combustion chamber; and a plurality of fuel injectors extending into the combustion chamber and configured to deliver an air-fuel mixture to the combustion chamber, wherein the outer liner is defined by a series of outer liner regions separated by boundaries, each extending in a straight line, axially in a downstream direction, and positioned midway between adjacent fuel injectors, wherein each of the outer liner regions defines two air admission holes of the first row of the outer liner and four air admission holes of the second row of the outer liner, wherein the inner liner is defined by a series of inner liner regions separated by boundaries, each extending in a straight line, axially in a downstream direction, and positioned midway between adjacent fuel injectors, wherein each of the inner liner regions defines two air admission holes of the first row of the inner liner and two air admission holes of the second row of the inner liner, wherein the first row of air admission holes in the inner liner is generally aligned with the first row of air admission holes in the outer liner in a longitudinal direction, the second row of air admission holes in the inner liner is generally aligned with the second row of air admission holes in the outer liner in the longitudinal direction, and the first row of air admission holes in the inner liner is circumferentially offset with respect to the first row of air admission holes in the outer liner, and wherein each two of immediately adjacent air admission holes of the second row of the outer liner are circumferentially centered around a respective one of the air admission holes of the first row of the inner liner.