Patent ID: 7546739

Claim:
A method for assembling a gas turbine engine, the gas turbine engine including a combustor, and at least one igniter inserted at least partially into the combustor, said method comprising: providing an igniter tube assembly including an axis of symmetry extending therethrough, an igniter tube, and a ferrule that includes a radially inner surface and a radially outer surface, the igniter tube having a first opening extending coaxially therethrough having a diameter sized to receive a portion of the igniter therethrough such that the igniter tube circumscribes the igniter and such that a gap is defined between the igniter tube and the igniter, and at least one of a first plurality of cooling air openings defined substantially by and extending through the igniter tube and a second plurality of cooling air openings axially spaced from the at least one of a first plurality of cooling air openings which are defined substantially by and extending through the ferrule to facilitate channeling cooling air into the gap, wherein at least one of the second plurality of cooling air openings extends through the ferrule from the radially inner surface to the radially outer surface; and coupling the igniter tube and the ferrule to the combustor.