Patent ID: 6327861
Filing Date: 2001-12-11
Classification: F23C,F23D,F23L,F23R

Abstract:
A gas turbine combustor for a gas turbine, comprising:an inner tube connected at a downstream side thereof to a tail tube;a pilot fuel nozzle having a pilot air supply passage there around in a central portion of said inner tube, said pilot air passage having a pilot air swirler therein;a plurality of main fuel nozzles having main air supply passages therearound and arranged around said pilot fuel nozzle and said pilot air supply passage in said inner tube, said plurality of main air supply passages having respective main swirlers therein, to form a main combustion premixture from main fuel from said main fuel nozzles and main air from said main swirlers being mixed together, anda combustion-inert shield gas supply to supply shield gas between the pilot air from said pilot air swirler and the main combustion premixture.