Patent ID: 8307657

Claim:
A system comprising: a turbine engine comprising: a combustor comprising a hollow wall having a sleeve disposed about a combustor liner, wherein the combustor liner comprises an inner surface facing inwardly toward a combustion chamber and a plurality of axial cooling channels arranged circumferentially about a downstream end portion, wherein the plurality of axial cooling channels are defined by alternating axial grooves and axial protrusions about a circumference of the combustor liner; a first air flow path in a first direction through the hollow wall, wherein the first air flow path comprises a bypass opening extending through the combustor liner to the inner surface; and a second air flow path in a second direction opposite the first direction through the hollow wall, wherein the second air flow path comprises one or more film holes extending radially through the alternating axial grooves of the combustor liner to the inner surface, the one or more film holes are arranged in a series of groups wherein the one or more film holes of each group of the series of groups is spaced together along each of the alternating axial grooves closer than spacing between each group, and the one or more film holes are configured to supply a cooling film to a downstream end portion of the combustor liner.