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An igniter tube assembly includes an axis of symmetry extending therethrough, an igniter tube that includes 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 g

An igniter tube assembly includes an axis of symmetry extending therethrough, an igniter tube that includes 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, a ferrule coupled to the igniter tube, and a plurality of cooling air openings extending through at least one of the igniter tube and the ferrule to facilitate channeling cooling air into the gap.

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What is claimed is: 1. 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

What is claimed is: 1. 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. 2. A method in accordance with claim 1 wherein providing an igniter tube assembly further comprises providing an igniter tube that includes at least one of the first plurality of cooling air openings extending therethrough at a first angle and at least one of the first plurality of cooling air openings extending therethrough at a second angle that is different than the first angle. 3. A method in accordance with claim 2 wherein providing an igniter tube assembly further comprises providing an igniter tube that includes at least one of the first plurality of cooling air openings extending therethrough at a first compound angle and at least one of the first plurality of cooling air openings extending therethrough at a second compound angle that is different than the first compound angle. 4. A method in accordance with claim 3 further comprising coupling a retainer that is sized to seat circumferentially against the igniter tube to the combustor such that the igniter tube and the ferrule are secured to the combustor. 5. A method in accordance with claim 4 wherein the retainer includes a plurality of tabs, said method further comprising coupling the plurality of tabs to the combustor such that the igniter tube and the ferrule are secured to the combustor. 6. A method in accordance with claim 1 wherein providing an igniter tube assembly further comprises providing a ferrule that includes at least one of the second plurality of cooling air openings extending therethrough at a first angle and at least one of the second plurality of cooling air openings extending therethrough at a second angle that is different than the first angle. 7. A method in accordance with claim 6 wherein providing an igniter tube assembly further comprises providing a ferrule that includes one of the second plurality of cooling air openings extending therethrough at a first compound angle and at least one of the second plurality of cooling air openings extending therethrough at a second compound angle that is different than the first compound angle. 8. An igniter tube assembly for a gas turbine engine, the gas turbine engine including a combustor, and at least one igniter inserted at least partially into the combustor, said igniter tube assembly comprising: an axis of symmetry extending therethrough; an igniter tube comprising a first opening extending coaxially therethrough having a diameter sized to receive a portion of the igniter therethrough such that said igniter tube circumscribes the igniter and such that a gap is defined between said igniter tube and the igniter; a ferrule coupled to said igniter tube, said ferrule comprising a radially inner surface and a radially outer surface; and at least one of a first plurality of cooling air openings defined substantially by and extending through said 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 said ferrule to facilitate channeling cooling air into said gap, wherein at least one of said second plurality of cooling air openings extends through said ferrule from said radially inner surface to said radially outer surface. 9. An igniter tube assembly in accordance with claim 8 wherein at least one of said first plurality of openings extends through said igniter tube at a first angle and at least one of said first plurality of openings extends through said igniter tube at a second angle that is different than said first angle. 10. An igniter tube assembly in accordance with claim 8 wherein at least one of said first plurality of openings extends through said igniter tube at a first compound angle and at least one of said first plurality of openings extends through said igniter tube at a second compound angle that is different than said first compound angle. 11. An igniter tube assembly in accordance with claim 8 wherein at least one of said second plurality of openings extends through said ferrule at a first angle and at least one of said second plurality of openings extends through said ferrule at a second angle that is different than said first angle. 12. An igniter tube assembly in accordance with claim 8 wherein at least one of said second plurality of openings extends through said ferrule at a first compound angle and at least one of said second plurality of openings extends through said ferrule at a second compound angle that is different than said first compound angle. 13. An igniter tube assembly in accordance with claim 8 further comprising a retainer that is sized to seat circumferentially against said igniter tube to secure said igniter tube and said ferrule to the combustor. 14. An igniter tube assembly in accordance with claim 13 wherein said retainer comprises a plurality of tabs that are coupled to the combustor to secure said igniter tube and said ferrule to the combustor. 15. A gas turbine engine including a combustor comprising an annular outer liner and an annular inner liner that define a combustion chamber therebetween, and at least one igniter tube assembly coupled to said combustor, and an igniter tube assembly comprising: an axis of symmetry extending therethrough; an igniter tube comprising a first opening extending coaxially therethrough having a diameter sized to receive a portion of the igniter therethrough such that said igniter tube circumscribes the igniter and such that a gap is defined between said igniter tube and the igniter; a ferrule coupled to said igniter tube, said ferrule comprising a radially inner surface and a radially outer surface; and at least one of a first plurality of cooling air openings defined substantially by and extending through said 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 said ferrule to facilitate channeling cooling air into said gap, wherein at least one of said second plurality of cooling air openings extends through said ferrule from said radially inner surface to said radially outer surface. 16. A gas turbine engine in accordance with claim 15 wherein at least one of said first plurality of openings extends through said igniter tube at a first angle and at least one of said first plurality of openings extends through said igniter tube at a second angle that is different than said first angle. 17. A gas turbine engine in accordance with claim 15 wherein at least one of said first plurality of openings extends through said igniter tube at a first compound angle and at least one of said first plurality of openings extends through said igniter tube at a second compound angle that is different than said first compound angle. 18. A gas turbine engine in accordance with claim 15 wherein at least one of said second plurality of openings extends through said ferrule at a first angle and at least one of said second plurality of openings extends through said ferrule at a second angle that is different than said first angle. 19. A gas turbine engine in accordance with claim 15 wherein at least one of said second plurality of openings extends through said ferrule at a first compound angle and at least one of said second plurality of openings extends through said ferrule at a second compound angle that is different than said first compound angle. 20. A gas turbine engine in accordance with claim 15 further comprising: a retainer that is sized to seat circumferentially against said igniter tube, said retainer comprising a plurality of tabs to secure said igniter tube and said ferrule to said combustor.