Patent ID: 7216488

Claim:
A method for assembling a gas turbine engine, said method comprising: coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combustor; providing an ignition device that includes a body and a shroud that extends circumferentially around at least a portion of the body and extends axially from a first end to a tip end, wherein a gap is defined between the shroud and the body; inserting the ignition device at least partially through a tower assembly coupled to the combustor such that a tip portion of the device is positioned upstream from the tip end, and downstream from a body portion that extends between the first end and the tip portion; and securing the ignition device within the tower assembly such that a plurality of metering openings formed within the shroud body portion are in flow communication with a cooling source for channeling cooling air into the gap, and such that a portion of the cooling air is discharged from the gap through a plurality of first cooling openings formed within the body portion, and such that a portion of the cooling air is channeled from the gap through a plurality of discharge openings formed within the shroud tip portion.