Patent ID: 8763359

Claim:
A system for use with a gas turbine engine, said system comprising: a combustor assembly; a plurality of first nozzles coupled to said combustor assembly, wherein each of said plurality of first nozzles comprises a nozzle tip comprising a plurality of outlet passageways coupled to a first fuel source, and wherein each of said plurality of first nozzles comprises a plurality of first vane passageways coupled to a second fuel source; a second nozzle coupled to said combustor assembly, said second nozzle includes a plurality of second vane passageways coupled to said second fuel source; and a control system coupled to said combustor assembly, said control system configured to: channel a first fuel from said first fuel source through said plurality of outlet passageways of said plurality of first nozzles; operate said combustor assembly at a first predetermined percentage of a baseload by channeling the first fuel only through said plurality of first nozzles; channel a second fuel from said second fuel source through said plurality of second vane passageways of said second nozzle when the gas turbine engine attains the first predetermined percentage of a baseload; channel said second fuel from said second fuel source through said plurality of first vane passageways of said plurality of first nozzles when the gas turbine engine is operated at a second predetermined percentage of the baseload, wherein the second predetermined percentage of the baseload being greater than the first predetermined percentage of the baseload; and reduce a flow of said first fuel entering said plurality of first nozzles when the gas turbine engine is operated at a load of greater than the second predetermined percentage of the baseload.