A gas turbine engine combustor is provided. An inner liner has an upstream end and a downstream end and extends in an axial direction between the upstream and downstream ends. A dual wall outer liner has a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end. The outer liner extends in the axial direction between the upstream (224) and downstream (226) ends. A dome assembly is coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner. Effusion cooling holes (304) are disposed in the hot wall (216), including a first row (306) disposed at a tangential angle of between about 70° and about 90° and a second row (308) disposed at a tangential angle of between about 0° and about 20°.
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