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A method for fabricating an augmentor includes fabricating an outer casing having at least one channel defined therein, fabricating a centerbody having at least one channel defined therein, fabricating a plurality of turbine frame vanes, wherein each turbine frame vane includes a first sidewall havi

A method for fabricating an augmentor includes fabricating an outer casing having at least one channel defined therein, fabricating a centerbody having at least one channel defined therein, fabricating a plurality of turbine frame vanes, wherein each turbine frame vane includes a first sidewall having a first channel defined therein, a second sidewall having a second channel defined therein, and at least one cross-fire tube extending between the first sidewall and the second sidewall, and coupling the plurality of turbine frame vanes to the augmentor outer casing and to the centerbody such that the first sidewall first channel formed on a first turbine frame vane, the second sidewall second channel formed on a second turbine frame vane, the augmentor channel, and the centerbody channel define a substantially contiguous trapped vortex chamber.

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What is claimed is: 1. A method for fabricating a gas turbine engine augmentor system, said method comprising: fabricating an augmentor outer casing having at least one channel defined therein; fabricating a centerbody having at least one channel defined therein; fabricating a plurality of turbine

What is claimed is: 1. A method for fabricating a gas turbine engine augmentor system, said method comprising: fabricating an augmentor outer casing having at least one channel defined therein; fabricating a centerbody having at least one channel defined therein; fabricating a plurality of turbine frame vanes, wherein each turbine frame vane includes a first sidewall having a first channel defined therein, a second sidewall having a second channel defined therein, and at least one cross-fire tube extending between the first sidewall and the second sidewall; and coupling the plurality of turbine frame vanes to the augmentor outer casing and to the centerbody such that the first sidewall first channel formed on a first turbine frame vane, the second sidewall second channel formed on a second turbine frame vane, the augmentor channel, and the centerbody channel define a substantially contiguous trapped vortex chamber. 2. A method in accordance with claim 1 further comprising fabricating at least one turbine frame vane that includes a fuel inlet that extends at least partially through the at least one turbine frame vane to facilitate channeling a predetermined quantity of fuel through the fuel inlet and into the contiguous trapped vortex chamber. 3. A method in accordance with claim 1 wherein providing a plurality of turbine frame vanes comprises providing a plurality of turbine frame vanes wherein each turbine frame vane includes a first sidewall having a first channel defined therein, and a second sidewall having a second channel defined therein, the second channel formed aft of the first channel with respect to an engine axis of symmetry. 4. A method in accordance with claim 1 further comprising coupling at least one igniter to the gas turbine engine augmentor to facilitate igniting fuel within the trapped vortex chamber. 5. A method in accordance with claim 1 further comprising coupling the plurality of turbine frame vanes to the augmentor outer casing and the centerbody such that the plurality of turbine frame vanes form a plurality of contiguous trapped vortex chambers that are coupled in flow communication around an inner periphery of the gas turbine engine. 6. An augmentor for a gas turbine engine, said augmentor comprising: an augmentor outer casing comprising at least one channel defined therein; a centerbody comprising at least one channel defined therein; and a plurality of turbine frame vanes comprising at least a first turbine frame vane and a second turbine frame vane, each said turbine frame vane comprising a first sidewall comprising a first channel defined therein; a second sidewall comprising a second channel defined therein; and a cross-fire tube extending between said first sidewall and said second sidewall; said plurality of turbine frame vanes coupled to said augmentor outer casing and said centerbody such that said first sidewall first channel formed on said first turbine frame vane, said second sidewall second channel formed on said second turbine frame vane, said augmentor channel, and said centerbody channel define a substantially contiguous trapped vortex chamber. 7. An augmentor in accordance with claim 6 wherein at least one said turbine frame vane comprises a fuel inlet that extends between an upper surface of said turbine frame vane and at least partially through an interior of said turbine frame vane to facilitate channeling a predetermined quantity of fuel into said trapped vortex chamber. 8. An augmentor in accordance with claim 7 wherein said augmentor further comprises a first tube and a second tube in flow communication with said fuel inlet to facilitate channeling a predetermined quantity of fuel into said trapped vortex chamber. 9. An augmentor in accordance with claim 7 wherein each said turbine frame vane comprises a first fuel tube in flow communication with said fuel inlet and a second fuel tube in flow communication with said fuel inlet, said first fuel tube configured to channel fuel into a first trapped vortex chamber and said second fuel tube configured to channel fuel into a second trapped vortex chamber different than said first trapped vortex chamber. 10. An augmentor in accordance with claim 9 wherein said first fuel tube comprises a first length and said second fuel tube comprises a second length that is greater than said first length. 11. An augmentor in accordance with claim 9 wherein said first fuel tube comprises a first length and said second fuel tube comprises a second length that is substantially equal to said first length. 12. An augmentor in accordance with claim 8 wherein said augmentor comprises at least one igniter configured to ignite the fuel channeled from said first fuel tube and said second fuel tube. 13. An augmentor in accordance with claim 6 wherein said first sidewall comprises an outer surface that is approximately convex and said second sidewall comprises an outer surface that is approximately convex. 14. A gas turbine engine comprising: an augmentor comprising: an augmentor outer casing comprising at least one channel defined therein; a centerbody comprising at least one channel defined therein; and a plurality of turbine frame vanes comprising at least a first turbine frame vane and a second turbine frame vane, each said turbine frame vane comprising a first sidewall comprising a first channel defined therein; a second sidewall comprising a second channel defined therein; and said plurality of turbine frame vanes coupled to said augmentor outer casing and said centerbody such that said first sidewall first channel formed on said first turbine frame vane, said second sidewall second channel formed on said second turbine frame vane, said augmentor channel, and said centerbody channel define a substantially contiguous trapped vortex chamber. 15. A gas turbine engine in accordance with claim 14 wherein each said turbine frame vane comprises a fuel inlet that extends between an upper surface of said turbine frame vane and at least partially through an interior of said turbine frame vane. 16. A gas turbine engine in accordance with claim 15 wherein each said turbine frame vane comprises a cross-fire tube. 17. A gas turbine engine in accordance with claim 15 wherein each said turbine frame vane comprises a first fuel tube coupled to said fuel inlet and a second fuel tube coupled to said fuel inlet, said first fuel tube and said second fuel tube configured to channel fuel into a first trapped vortex chamber and a second trapped vortex chamber. 18. A gas turbine engine in accordance with claim 17 wherein said first fuel tube comprises a first length and said second fuel tube comprises a second length that is greater than said first length. 19. A gas turbine engine in accordance with claim 17 wherein said augmentor comprises at least one igniter configured to ignite the fuel channeled from said first fuel tube and said second fuel tube. 20. A gas turbine engine in accordance with claim 14 wherein said first sidewall comprises an outer surface that is approximately convex and said second sidewall comprises an outer surface that is approximately convex.