Patent ID: 7509809

Claim:
A gas turbine engine reverse-flow combustor comprising a liner enclosing a combustion chamber, the liner including a dome portion at an upstream end thereof and two annular liner walls extending downstream from and circumscribing said dome portion, the two annular liner walls being spaced apart such that the dome circumscribed thereby and disposed there between is annular, the dome portion having defined therein a plurality of openings each adapted to receive a fuel nozzle, the openings defined in said dome being positioned substantially equidistant between the two annular liner walls, at least one of said liner walls having a plurality of holes defined therein to form an annular cooling band extending around said liner wall immediately downstream of said dome portion for directing cooling air into the combustion chamber, said plurality of holes within said annular cooling band including a first set of cooling holes disposed within circumferentially spaced regions aligned with said openings and located downstream therefrom and a second set of cooling holes disposed outside said regions, wherein said regions having said first set of cooling holes provide a greater cooling air flow there through than similarly sized areas of said combustor liner having said second set of cooling holes therein.