Patent ID: 7107772
Filing Date: 2006-09-19
Classification: F23C,F23D,F23N,F23R

Abstract:
1. A multi-point fuel injector for use in a combustor stage of a gas turbine engine comprising: a plurality of nozzles arranged in a first outermost array; a plurality of nozzles arranged in a second array, said second array being adjacent said first outermost array; a first circuit for supplying fuel to said nozzles in said first outermost array, said first circuit having a first valve for controlling the supply of fuel to said nozzles; a second circuit for supplying fuel to said nozzles in said second array, said second circuit having a second valve for controlling the supply of fuel to said nozzles in said second array, and said second circuit being independent of said first circuit; each of said nozzles including a fluid channel formed by an outer body and an inner body spaced from said outer body; and means for creating a swirling flow within the fluid channel, said swirling flow creating means extending between said outer body and said inner body, wherein each nozzle in said first and second arrays has a swirling means which comprises a plurality of vanes within a central portion of said fluid channel, and wherein said central portion is spaced from an inlet and an outlet of said fluid channel.