A gas turbine combustor liner comprising: an outer surface and an inner surface , the outer surface being exposed to a cooling airflow and the inner surface being exposed to hot combustion gases; a plurality of film cooling holes through a thickness of the gas turbine combustor liner , the film cooling holes extending circumferentially around the gas turbine combustor liner , wherein the film cooling holes comprise: a first set of holes having a first axial row spacing X , the first set of holes being defined by a first plurality of rows of holes extending in a circumferential direction; and a second set of holes having a second axial row spacing X ', the second set of holes being defined by a second plurality of rows of holes extending in a circumferential direction, wherein the second set of holes is formed in the gas turbine combustor liner in a downstream direction relative to the first set of holes , the second axial row spacing X ' being greater than the first axial row spacing X ; and a plurality of resonator boxes affixed to the outer surface of the gas turbine combustor liner , characterized in that the resonator boxes further comprise a plurality of impingement holes configured to introduce at least a portion of the cooling airflow into the resonator boxes , and in that the resonator boxes further comprise an upstream wall and a downstream wall , an upstream wall height being less than a downstream wall height. an outer surface and an inner surface , the outer surface being exposed to a cooling airflow and the inner surface being exposed to hot combustion gases; a plurality of film cooling holes through a thickness of the gas turbine combustor liner , the film cooling holes extending circumferentially around the gas turbine combustor liner , wherein the film cooling holes comprise: a first set of holes having a first axial row spacing X , the first set of holes being defined by a first plurality of rows of holes extending in a circumferential direction; and a second set of holes having a second axial row spacing X ', the second set of holes being defined by a second plurality of rows of holes extending in a circumferential direction, wherein the second set of holes is formed in the gas turbine combustor liner in a downstream direction relative to the first set of holes , the second axial row spacing X ' being greater than the first axial row spacing X ; and a plurality of resonator boxes affixed to the outer surface of the gas turbine combustor liner , characterized in that the resonator boxes further comprise a plurality of impingement holes configured to introduce at least a portion of the cooling airflow into the resonator boxes , and in that the resonator boxes further comprise an upstream wall and a downstream wall , an upstream wall height being less than a downstream wall height. a first set of holes having a first axial row spacing X , the first set of holes being defined by a first plurality of rows of holes extending in a circumferential direction; and a second set of holes having a second axial row spacing X ', the second set of holes being defined by a second plurality of rows of holes extending in a circumferential direction, wherein the second set of holes is formed in the gas turbine combustor liner in a downstream direction relative to the first set of holes , the second axial row spacing X ' being greater than the first axial row spacing X ; and a plurality of resonator boxes affixed to the outer surface of the gas turbine combustor liner , characterized in that the resonator boxes further comprise a plurality of impingement holes configured to introduce at least a portion of the cooling airflow into the resonator boxes , and in that the resonator boxes further comprise an upstream wall and a downstream wall , an upstream wall height being less than a downstream wall height. <EOS>