Patent ID: 8910481

Claim:
A combustor for a gas turbine engine, comprising: a forward bulkhead having a plurality of injector apertures circumferentially disposed around the forward bulkhead; an inner radial combustor wall attached to and extending axially out from the forward bulkhead, which inner radial combustor wall includes a plurality of inner quench aperture sets, each inner quench aperture set including a first inner quench aperture and a second inner quench aperture separated from each other by an inner intraset distance, wherein each inner quench aperture set is separated from an adjacent inner quench aperture set by an inner interset distance, and wherein the inner interset distance is greater than the inner intraset distance; an outer radial combustor wall attached to and extending axially out from the forward bulkhead, which outer wall includes a plurality of circumferentially disposed outer quench apertures; and a plurality of air swirlers, wherein each air swirler is mounted with a respective one of the injector apertures; wherein the outer radial combustor wall is disposed radially outside the inner radial combustor wall defining an annular combustion region therebetween; wherein a first quantity of quench air passing through the first inner quench apertures and the second inner quench apertures is greater than a second quantity of air passing through the air swirlers; and wherein each injector aperture is circumferentially aligned between the first inner quench aperture and the second inner quench aperture of a respective one of the plurality of inner quench aperture sets.