Patent ID: 7624577

Claim:
A gas turbine engine combustor housed in a plenum defined at least partially by a casing of the gas turbine engine and supplied with compressed air from a compressor via a plurality of diffuser pipes in fluid flow communication therewith, the combustor comprising a liner enclosing a combustion chamber therewithin, the liner including a dome portion at a first end thereof and at least one annular liner wall extending from and circumscribing said dome portion, said liner wall having a plurality of holes defined therein to form an annular cooling band extending around said liner wall proximate exits of said diffuser pipes, said annular cooling band extending at least downstream from said exits relative to compressed air flow exiting said diffuser pipes, said plurality of holes within said annular cooling band directing cooling air from the plenum into the combustion chamber, said plurality of holes including a first set of cooling holes disposed within circumferentially spaced apart regions located at least between each of said diffuser pipes 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 therethrough than similarly sized areas of said combustor liner having said second set of cooling holes therein.