Patent ID: 6874323
Filing Date: 2005-04-05
Classification: F05D,F23C,F23R

Abstract:
1. A method of operating a gas turbine combustor comprising: providing a combustor having upstream and downstream combustion chambers and a combustor centerline; providing a secondary fuel nozzle along said combustor centerline for introducing fuel into said downstream combustion chamber; providing a plurality of primary fuel nozzles in an annular array about said secondary fuel nozzle and upstream from said upstream combustion chamber for introducing a fuel into said upstream combustion chamber, each of said plurality of primary fuel nozzles including a primary swirler for introducing pressurized air into said upstream combustion chamber for creating a combustible fuel air mixture; supplying a mixture of fuel to said downstream combustion chamber through said secondary fuel nozzle, said mixture comprising natural gas and hydrogen gas, wherein said mixture contains localized concentrations of hydrogen gas in which the hydrogen gas in said mixture is greater than 0.1% by mass of said mixture, and less than 20% by mass of said mixture; and, combusting said mixture in said downstream combustion chamber.