Patent ID: 6813890
Filing Date: 2004-11-09
Classification: F23R

Abstract:
An improved premix secondary fuel nozzle for use in a gas turbine combustor comprising:an elongated tube having a first and second opposing ends having a centerline defined therethrough and a tip region proximate said second end; at least one first injector extending radially away from and fixed to said elongated tube and containing at least one first injector hole for injecting a fuel into said combustor such that air surrounding said fuel nozzle mixes with said fuel to form a premixture; a central core coaxial with said centerline and located radially within said elongated tube thereby forming a first passage between said central core and said elongated tube, said central core extending from proximate said first opposing end to proximate said second opposing end, said central core containing a second passage extending from proximate said first opposing end to proximate said first injector for supplying fuel to said first injector, said central core also containing a third passage extending from downstream of said first injector to proximate said second opposing end, each of said second and third passages coaxial with said centerline, and said central core further containing a plurality of air flow channels in fluid communication with said third passage, said air flow channels having an air flow inlet region and air flow exit region, and said first passage extending from proximate said first opposing end to upstream of said air flow inlet region of said air flow channels; a swirler fixed within said third passage for imparting a swirl to said air to cool said tip region of said fuel nozzle; a second injector containing a plurality of second injector holes located proximate said second opposing end of said elongated tube for injecting a fluid medium into said combustor; means for transferring said fluid medium from said first passage to said second injector; wherein all fuel is injected radially outward of and upstream of said swirler so as to not directly initiate a pilot flame.