Patent ID: 8479490

Claim:
A combustor for a gas turbine engine, comprising: an inner liner; an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner, the outer liner being a single walled liner; a fuel igniter configured to ignite an air and fuel mixture in the combustion chamber to generate combustion gases, the fuel igniter including a tip portion exposed to the combustion gases; and an igniter tube positioning the fuel igniter relative to the combustion chamber, the igniter tube having a plurality of channels configured to direct cooling air such that the cooling air impinges the tip portion of the fuel igniter at an angle generally perpendicular to a longitudinal axis of the fuel igniter, wherein the igniter tube includes an annular igniter boss mounted on the outer liner, wherein the igniter boss comprises a plurality of holes that form, at least partially, the plurality of channels, a support ring supported by the igniter boss, and a grommet arranged on the supporting ring and configured to receive the fuel igniter, and wherein the igniter tip portion terminates at a distal end, and wherein the plurality of channels directs the cooling air on a position at or approximately at the distal end.