A combustor (20) for a gas turbine engine includes a forward bulkhead (22), an inner radial combustor wall (26) and an outer radial combustor wall (28). The forward bulkhead has a plurality of circumferentially disposed injector apertures (34). The inner radial combustor wall is attached to and extends axially out from the forward bulkhead. The outer radial combustor wall is attached to and extends axially out from the forward bulkhead. At least one of the inner radial combustor wall and the outer radial combustor wall includes a plurality of quench aperture sets. Each quench aperture set includes a plurality of quench apertures. Adjacent quench apertures included within each quench aperture set are separated by an intraset distance. Adjacent quench aperture sets are separated by an interset distance. The intraset distance is different than the interset distance. The outer radial combustor wall is disposed radially outside the inner radial combustor wall, thereby defining an annular combustion region therebetween.