Combustor to combustor mode decoupling means of fuel splits to combustor plane

According to one aspect of the invention, a gas turbine system (100) is provided. The gas turbine system (100) may contain, in flow communication with the compressor (110), a compressor (110) is adapted to compress air (115) and furnace tubes (120), wherein the combustor cans (120) are adapted to , compressed air (115) from the compressor (110) receive, and to combust a fuel stream. The gas turbine system (100) may further include a multiple-circuit manifold (200, 300) comprise, connected to the combustion chamber tubes (120) and which is adapted to provide the furnace tubes by means of the fuel stream (120) a split fuel stream.