Systems and methods for bulk temperature variation reduction of a gas turbine through can-to-can fuel temperature modulation

A gas turbine (10) includes a plurality of combustion chambers (14); at least one fuel nozzle (16, 18, 20) for each of the combustion chambers; at least one fuel line (34, 36, 38) for each fuel nozzle in each of the combustion chambers; at least one heat exchanger (28, 30, 32) for each fuel line configured to adjust a temperature of a fuel flow to each fuel nozzle; and a controller (50) configured to control each of the heat exchangers to reduce temperature variations amongst the combustion chambers.