Patent ID: 8584466

Claim:
A combustor for a turbine engine, comprising: a first liner; a second liner positioned relative to the first liner to form a combustion chamber therebetween, the combustion chamber configured to receive a fuel-air mixture; an igniter positioned relative to the combustion chamber and configured to ignite the fuel-air mixture; air admission holes positioned in the first liner and configured to admit combustion air into the combustion chamber; a plurality of injectors configured to generate the fuel-air mixture for the combustion chamber, wherein each injector defines a region of the first liner, and wherein at least one of the regions is circumferentially associated with the igniter to form at least one igniter region and a plurality of non-igniter regions, wherein the air admission holes have a regular circumferential pattern around the first liner in each of the non-igniter regions and an interrupted circumferential pattern in the at least one igniter region, different from the regular circumferential pattern, wherein the air admission holes in the at least one igniter region are positioned axially downstream of the air admission holes in the non-igniter regions.