COMBUSTOR WITH MULTIPLE COMBUSTION ZONES WITH INJECTOR PLACEMENT FOR COMPONENT DURABILITY

摘要

PROBLEM TO BE SOLVED: To provide a late lean injection system for a gas turbine with a nozzle assembly designed to minimize damage to a combustor liner and a transition duct.SOLUTION: A combustion system including a combustor; a combustor liner 15 disposed within the combustor is provided. At least one primary fuel nozzle 13 is provided to provide fuel to a primary combustion zone disposed proximate to the upstream end of the combustor liner 15. A transition duct 21 is coupled to the downstream end of the combustor liner 15. A secondary nozzle assembly 27 is disposed proximate to the downstream end of the combustor to provide fuel to a secondary combustion zone at a location predetermined to reduce peak thermal loads on the surface area of the transition duct 21. By disposing the secondary nozzle assembly 27 at a proper position on an aft part 23 of the combustion linear 15, hot spots are remarkably reduced.