Patent ID: 6837052

Claim:
A secondary fuel nozzle assembly for use in a dual stage—dual mode gas turbine combustor, said fuel nozzle assembly comprising: a base; a means for supplying a fuel to said base; a nozzle body comprising: an elongated tube having a first and second opposing ends, having a centerline defined therethrough, said first end of said elongated tube fixed to and in fluid communication with said base, and a tip region proximate said second end; at least one first injector extending radially away and fixed to said elongated tube, said first injector containing at least one first injector hole for injecting a fuel into a combustor such that compressed air surrounding said fuel nozzle mixes with said fuel to form a premixture; a first passage located within said elongated tube and extending from said first end to proximate said at least one first injector, wherein said first passage is in fluid communication with said at least one first injector; a plurality of second passages extending from upstream of said at least one first injector to downstream of said first passage, said plurality of second passages in fluid communication with said compressed air surrounding said fuel nozzle; a third passage in fluid communication with said plurality of second passages and extending from downstream of said first passage to said tip region; an injector plate proximate said tip region, said injector plate having an outer surface and a plurality of second injector holes that are in fluid communication with said third passage; wherein all fuel is injected into said surrounding air upstream of said third passage.