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A turbine engine augmentor has a centerbody within a gas flowpath. A flameholder is positioned in the flowpath outboard of the centerbody. A burner within the centerbody has an outlet for expelling combustion products of a first pilot fuel. A pilot fuel conduit has an outlet positioned to introduce

A turbine engine augmentor has a centerbody within a gas flowpath. A flameholder is positioned in the flowpath outboard of the centerbody. A burner within the centerbody has an outlet for expelling combustion products of a first pilot fuel. A pilot fuel conduit has an outlet positioned to introduce a supplemental pilot fuel to the expelled combustion products.

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What is claimed is: 1. A turbine engine augmentor comprising: a gas flowpath; a flameholder positioned in the gas flowpath outboard of a centerbody; a burner having an outlet for expelling combustion products of a first pilot fuel; and a pilot fuel conduit having an outlet positioned to introduce a

What is claimed is: 1. A turbine engine augmentor comprising: a gas flowpath; a flameholder positioned in the gas flowpath outboard of a centerbody; a burner having an outlet for expelling combustion products of a first pilot fuel; and a pilot fuel conduit having an outlet positioned to introduce a supplemental pilot fuel to the expelled combustion products within the centerbody. 2. The augmenter of claim 1 wherein the flameholder is a first of a plurality of flameholders and the pilot fuel conduit is a first of a plurality pilot fuel conduits, each aligned with an associated one of the plurality of flameholders. 3. The augmenter of claim 1 wherein the outlet of the burner is a first outlet of a plurality of burner outlets circumferentially arrayed about an axis of the engine. 4. The augmentor of claim 1 wherein the centerbody has a tailcone and a recessed area upstream of the tailcone and wherein said cutlet of said burner is positioned within said recessed area. 5. The augmentor of claim 4 wherein the recessed area is a non-annular compartment. 6. The augmentor of claim 4 wherein the outlet of the pilot fuel conduit is positioned within said recessed area. 7. The augmentor of claim 1 wherein the pilot fuel conduit comprises a distal end portion of a spray bar extending within a vane associated with the flameholder. 8. A turbine engine augmentor comprising: a centerbody within a core flowpath of the engine; a flameholder positioned in the core flowpath and extending radially outboard of the centerbody; a burner within the centerbody and having: a housing; an upstream inlet for receiving oxygen-containing gas; an igniter for initiating combustion of a first pilot fuel with said oxygen-containing gas; a foraminate liner positioned within the housing to direct products of said combustion downstream; a plurality of foraminate outlet conduits extending at least partially radially outward from the liner to direct the products toward the core flowpath; and a plurality of cooling conduits, each surrounding an associated one of the outlet conduits; and a pilot fuel conduit having an outlet positioned to introduce a supplemental pilot fuel to the expelled combustion products. 9. The augmentor of claim 8 wherein the outlet of the burner is a first outlet of a plurality of burner outlets circumferentially arrayed about an axis of the centerbody. 10. A gas turbine engine comprising: a compressor compressing inlet air; a combustor receiving compressed air from the compressor and combusting a mixture of said compressed air and a fuel; a turbine extracting work from products of said combusting to drive the compressor and discharging said products as exhaust; and an augmentor within a path of said exhaust and having: a conduit receiving bypass air; a burner combusting a first portion of said bypass air with a burner fuel and discharging combustion products of said first portion of said bypass and said burner fuel into said exhaust through a burner outlet conduit; an air conduit directing a second portion of said bypass air, the burner outlet conduit passing within the air conduit; and a pilot fuel conduit directing a pilot fuel and positioned relative to said air conduit and said burner so as to permit beat from said combustion products of said first portion of said bypass and said burner fuel to ignite a mixture of said pilot fuel and said second portion of said bypass air. 11. A method for operating a turbine engine augmentor comprising: causing an exhaust gas flow from a turbine engine to an augment or; causing combustion of a first pilot fuel to produce combustion products, a flow of said combustion products joining said exhaust gas flow; introducing a supplemental pilot fuel to said flow of said combustion products; introducing a main augmentor fuel, separately from the first pilot fuel and the supplemental pilot fuel, reactive species of combustion of said supplemental pilot fuel igniting the main augmentor fuel. 12. A turbine engine augmentor comprising: a gas if flowpath; a flameholder positioned in the gas if flowpath; a burner having an outlet for expelling combustion products of a first pilot fuel; a pilot fuel conduit having an outlet positioned to introduce a supplemental pilot fuel to the expelled combustion products; and a main augmentor fuel outlet positioned to introduce a main augmentor fuel to the expelled combustion products and combustion products of said supplemental pilot fuel to, in turn, ignite the main augmentor fuel, wherein the flame holder is a first of a plurality of flameholders and the pilot fuel conduit is a first of a plurality pilot fuel conduits, each aligned with an associated one of the plurality of flameholders. 13. A turbine engine augmentor comprising: a gas flowpath; a centerbody within the gas if flowpath; a flameholder positioned in the gas if flowpath outboard of the centerbody; a burner within the centerbody and having: a housing; a liner within the housing; and a plurality of burner outlets expelling combustion products of a first pilot fuel, each comprising a liner outlet tube extending from the liner within a housing outlet tube extending from the housing; and a pilot fuel conduit having an outlet positioned to introduce a supplemental pilot fuel to the expelled combustion products. 14. The augmentor of claim 13 wherein the pilot fuel conduit is a first conduit of a plurality of pilot fuel conduits, each extending into the liner outlet tube of an associated one of the burner outlets. 15. A turbine engine augmentor comprising: a gas flowpath; a centerbody in the gas flowpath and having a tailcone and a recessed area upstream of the tailcone a flameholder positioned in the gas flowpath outboard of the centerbody; a burner having an outlet for expelling combustion products of a first pilot fuel; and a pilot fuel conduit having an outlet positioned within said recessed area to introduce a supplemental pilot fuel to the expelled combustion products. 16. The augmentor of claim 15 wherein the recessed area is a non-annular compartment. 17. The augmentor of claim 15 wherein the outlet of the pilot fuel conduit is positioned within said recessed area. 18. A method for operating a turbine engine augmentor comprising: causing an exhaust gas flow from a turbine engine to an augmentor; causing combustion of a first pilot fuel in an augmentor centerbody to produce combustion products, a flow of said combustion products exiting the centerbody and joining said exhaust gas flow, the centerbody extending generally fore-to-aft within the exhaust gas flow; and introducing a supplemental pilot fuel to said flow of said combustion products within a recess in the centerbody. 19. A gas turbine engine comprising: a compressor compressing inlet air; a combustor receiving compressed air from the compressor and combusting a mixture of said compressed air and a fuel; a turbine extracting work from products of said combusting to drive the compressor and discharging said products as exhaust; a centerbody within a path of said exhaust and an augmentor within the centerbody and having: a conduit receiving bypass air; a burner combusting a first portion of said bypass air with a burner fuel and discharging combustion products of said first portion of said bypass and said burner fuel into said exhaust; an air conduit within the centerbody and directing a second portion of said bypass air; and a pilot fuel conduit directing a pilot fuel and positioned relative to said air conduit and said burner so as to permit heat from said combustion products of said first portion of said bypass and said burner fuel to ignite a mixture of said pilot fuel and said second portion of said bypass air. 20. A method for operating a turbine engine augmentor comprising: causing an exhaust gas flow from a turbine engine to an augment or; causing combustion of a first pilot fuel in an augmentor centerbody to produce combustion products, a flow of said combustion products exiting the centerbody and joining said exhaust gas flow; introducing a supplemental pilot fuel to said flow of said combustion products; introducing a main augmentor fuel, separately from the first pilot fuel and the supplemental pilot fuel, reactive species of combustion of said supplemental pilot fuel igniting the main augmentor fuel. 21. The method of claim 20 wherein; the supplemental pilot fuel is introduced within a recess in the centerbody; and the centerbody extends generally fore-to-aft within the exhaust gas flow.