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An extended flashback annulus (520) is formed between an exterior surface (506) of a shroud or casing (508) associated with a main swirler assembly inner body (500) or other fuel/air mixing device and the inner surface (514) of an annulus casting (510) which are in operational relationship with one

An extended flashback annulus (520) is formed between an exterior surface (506) of a shroud or casing (508) associated with a main swirler assembly inner body (500) or other fuel/air mixing device and the inner surface (514) of an annulus casting (510) which are in operational relationship with one another in a gas turbine combustor assembly. The extended flashback annulus (520) is capable of forming an extended protective cylindrical air barrier (550) that extends farther into the combustion zone, this barrier being more robust and providing for the reduction or prevention of flashback to the baseplate and other heat-susceptible upstream components.

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I claim as my invention: 1. In a gas turbine combustor, a main swirler assembly comprising an inner body and an annulus casting, the inner body comprising a main swirler assembly casing having an upstream front end and a downstream exhaust end defining a length and a plurality of swirler flow condi

I claim as my invention: 1. In a gas turbine combustor, a main swirler assembly comprising an inner body and an annulus casting, the inner body comprising a main swirler assembly casing having an upstream front end and a downstream exhaust end defining a length and a plurality of swirler flow conditioning members arranged within a bore defined by the casing, and the annulus casting having a length defined by a distance between an upstream end and a downstream end, the annulus casting length being significantly shorter than the swirler casing length, the downstream end adapted to contact a baseplate, the baseplate comprising high-flashback-occurrence zones adjacent an opening into which fits the downstream end, a downstream section of the casing in substantially concentric cylindrical alignment within the annulus casting to define a flashback annulus, the main swirler assembly casing exhaust end positioned between about 25 percent of the annulus casting length upstream of, and about 5 percent of the annulus casting length downstream of, the annulus casting downstream end, wherein flow through the flashback annulus is effective to reduce, in total area, regions of structural damage located in the high-flashback-occurrence zones. 2. The apparatus of claim 1, the main swirler assembly casing comprising a main swirler assembly shroud. 3. The apparatus of claim 1, the main swirler assembly inner body additionally comprising a fuel delivery member having a fuel supply passage in fluid communication with a plurality of fuel exit ports disposed in said inner body. 4. The apparatus of claim 1, the main swirler assembly casing exhaust end positioned between about 10 percent of the annulus casting length upstream of, and about 5 percent of the annulus casting length downstream of, the annulus casting downstream end. 5. The apparatus of claim 4, the main swirler assembly casing comprising a main swirler assembly shroud. 6. The apparatus of claim 1, the main swirler assembly casing exhaust end aligned with the annulus casting downstream end. 7. The apparatus of claim 6, the main swirler assembly casing comprising a main swirler assembly shroud. 8. The apparatus of claim 1, the main swirler assembly casing exhaust end positioned between alignment with the annulus casting downstream end, and about 5 percent of the annulus casting length downstream of the annulus casting downstream end. 9. The apparatus of claim 8, the main swirler assembly casing comprising a main swirler assembly shroud. 10. The apparatus of claim 8, the main swirler assembly casing exhaust end extending downstream of the downstream plane of the baseplate. 11. The apparatus of claim 10, the main swirler assembly casing comprising a main swirler assembly shroud. 12. In a gas turbine combustor comprising a main swirler assembly inner body in operational relationship with an annulus casting having a length defined by a distance between an upstream end and a downstream end, the downstream end adapted to contact a baseplate, the baseplate comprising high-flashback-occurrence zones adjacent an opening into which fits the downstream end, a main swirler assembly casing having an upstream front end and a downstream exhaust end defining a length, and a downstream section of the casing in substantially concentric cylindrical alignment within the annulus casting to define a flashback annulus, the exhaust end positioned between about 25 percent of the annulus casting length upstream of, and about 5 percent of the annulus casting length downstream of, the annulus casting downstream end, the annulus casting length being significantly shorter than the swirler casing length, wherein flow through the flashback annulus is effective to reduce, in total area, regions of structural damage located in the high-flashback-occurrence zones. 13. For a gas turbine combustor, a main swirler assembly comprising an inner body in operational relationship with an annulus casting, the main swirler assembly inner body comprising a generally cylindrical casing having an axis for air flow defined by a path between a front end disposed upstream and an exhaust end disposed downstream and defining a length, the casing enclosing a plurality of swirler flow conditioning members disposed angularly relative to the axis to create turbulence upon the air flowing through the main swirler assembly inner body, and a rod-shaped fuel delivery member attached centrally to the plurality of swirler flow conditioning members, and having outlets for the dispersal of fuel into the air flow, and the annulus casting having a length defined by a distance between an upstream end and a downstream end, the downstream end adapted to contact a baseplate, the baseplate comprising high-flashback-occurrence zones adjacent an opening into which fits the downstream end, a downstream section of the casing in substantially concentric cylindrical alignment within the annulus casting to define a flashback annulus, the exhaust end of the casing positioned between about 25 percent of the annulus casting length upstream of, and about 5 percent of the annulus casting length downstream of, the annulus casting downstream end, the annulus casting length being less than one half of the swirler casing length, wherein flow through the flashback annulus is effective to reduce, in total area, regions of structural damage located in the high-flashback-occurrence zones. 14. The apparatus of claim 13, the exhaust end of the casing positioned between about 10 percent of the annulus casting length upstream of, and about 5 percent of the annulus casting length downstream of, the annulus casting downstream end. 15. The apparatus of claim 13, the exhaust end of the casing aligned with the annulus casting downstream end. 16. The apparatus of claim 13, the exhaust end of the casing positioned between alignment with the annulus casting downstream end, and about 5 percent of the annulus casting length downstream of the annulus casting downstream end. 17. A plurality of main swirler assemblies and respective annulus castings of claim 13 arranged circumferentially in a combustor shell to which are fixedly attached the plurality of annulus castings, the combustor shell comprising structure for installation into a gas turbine combustor. 18. A gas turbine combustor comprising a plurality of main swirler assemblies of claim 13, a combustor shell surrounding the plurality of main swirler assemblies, and a baseplate disposed at a downstream end of the combustor shell and contacting the downstream end of each of the annulus castings of said plurality of main swirler assemblies. 19. An extended flashback annulus in a gas turbine combustor defined by a downstream section of a main swirler assembly casing having an upstream front end and a downstream exhaust end defining a length in operational relationship with an annulus casting, the annulus casting having a length defined by a distance between an upstream end and a downstream end, the annulus casting length being less than one half of the swirler casing length, the downstream end adapted to contact a baseplate, the baseplate comprising high-flashback-occurrence zones adjacent an opening into which fits the downstream end, the main swirler assembly casing having a front end disposed upstream and an exhaust end disposed downstream and enclosing a plurality of swirler flow conditioning members disposed angularly to create turbulence upon air flowing therethrough, the downstream section of the casing in substantially concentric cylindrical alignment within the annulus casting to define the extended flashback annulus, the exhaust end positioned between about 25 percent of the annulus casting length upstream of, and about 5 percent of the annulus casting length downstream of, the annulus casting downstream end, wherein flow through the flashback annulus is effective to reduce, in total area, regions of structural damage located in the high-flashback-occurrence zones. 20. The apparatus of claim 19, the exhaust end of the casing positioned between about 10 percent of the annulus casting length upstream of, and about 5 percent of the annulus casting length downstream of, the annulus casting downstream end. 21. The apparatus of claim 19, the exhaust end of the casing aligned with the annulus casting downstream end. 22. The apparatus of claim 19, the exhaust end of the casing positioned between alignment with the annulus casting downstream end, and about 5 percent of the annulus casting length downstream of the annulus casting downstream end. 23. The gas turbine combustor of claim 18, the baseplate comprising a plurality of high-flashback-occurrence zones adjacent to openings into which fit the downstream end of annulus castings of respective main swirler assemblies, each flashback annulus effective to reduce, in total area, regions of structural damage located in a respective high-flashback-occurrence zone.