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A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough includes: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section

A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough includes: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of the openings includes a cooling trough formed therein; and, a free floating swirler located upstream of the dome plate in substantial alignment with each of the openings in the dome plate, the swirler including a forward portion and an aft portion. The aft portion of each swirler is configured so as to permit air flow to the cooling trough during operation of the gas turbine engine. In particular, the swirler aft portion includes a substantially annular flange extending adjacent to the forward surface of the dome plate, wherein opposing portions of a circumference for the flange adjacent the radial sections of the dome plate are substantially linear.

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1. A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising:(a) an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial

1. A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising:(a) an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of said openings includes a cooling trough formed therein; and,(b) a free floating swirler located upstream of said dome plate in substantial alignment with each of said openings in said dome plate, said swirler including a forward portion and an aft portion;wherein said aft portion of each said swirler is configured so as to permit air flow to said cooling trough during operation of the gas turbine engine.2. The combustor dome assembly of claim 1, said swirler aft portion further comprising a substantially annular flange extending adjacent to said forward surface of said dome plate, wherein opposing portions of a circumference for said flange adjacent said radial sections of said dome plate are substantially linear.3. The combustor dome assembly of claim 2, wherein the circumference of said swirler flange has a variable radius between said opposing portions.4. The combustor dome assembly of claim 2, said swirler flange including an undercut along a portion of an aft surface thereof so as to form a recessed area.5. The combustor dome assembly of claim 4, said swirler flange including a plurality of circumferentially spaced purge holes formed therein in flow communication with said recessed area.6. The combustor dome assembly of claim 4, said aft surface of said swirler flange including a layer of thermal barrier coating along said recessed area.7. The combustor dome assembly of claim 1, wherein each opening in said dome plate has at least a predetermined diameter.8. The combustor dome assembly of claim 1, wherein a circumferential distance between adjacent openings in said dome plate is no greater than a predetermined amount.9. The combustor dome assembly of claim 1, said swirler aft portion further comprising a lip connected to said flange and oriented substantially parallel to a centerline axis through a dome plate opening.10. The combustor dome assembly of claim 9, further comprising a deflector plate connected to and positioned within each opening in said dome plate, wherein a cavity is formed between an inner surface of each deflector plate and said swirler aft lip.11. The combustor dome assembly of claim 2, wherein said swirler aft portion is contoured to limit stress on said flange to a predetermined amount.12. The combustor dome assembly of claim 5, wherein at least a portion of said purge holes in said swirler flange are angled in a first direction.13. The combustor dome assembly of claim 12, wherein at least a portion of said purge holes in said swirler flange are angled in a second direction.14. The combustor dome assembly of claim 5, wherein at least a portion of said purge holes in said swirler flange are oriented straight through said swirler flange.15. The combustor dome assembly of claim 5, wherein said purge holes have a varying diameter.16. The combustor dome assembly of claim 1, said swirler forward portion including a pair of anti-rotation tabs associated therewith.