System of fuel combustion, gas turbine, a method of controlling the distribution profile of the heat load on the crossover passage and method of making Subsystem COMBUSTION CHAMBER FOR A GAS TURBINE

摘要

A combustion system including a combustor; a combustor liner disposed within the combustor is provided. At least one primary fuel nozzle is provided to provide fuel to a primary combustion zone disposed proximate to the upstream end of the combustor liner. A transition duct is coupled to the downstream end of the combustor liner. A secondary nozzle assembly is disposed proximate to the downstream end of the combustor to provide fuel to a secondary combustion zone at locations predetermined to reduce peak thermal loads on the surface area of the transition duct.