Combustion system and method for attenuation of combustion dynamics in a gas turbine engine

A combustion system for a gas turbine engine, the combustion system comprising:

• a liner and a dome assembly together defining a combustion chamber that is configured to receive compressed air from a compressor section of the gas turbine engine;
• a first set of fuel nozzles and a second set of fuel nozzles disposed in an alternating arrangement along a circumferential direction around a longitudinal centerline of the combustion system such that each fuel nozzle of the first set of fuel nozzles is adjacent to two fuel nozzles of the second set of fuel nozzles along the circumferential direction;
• and
• a fuel supply system that provides an overall supply of fuel to the first set of fuel nozzles and the second set of fuel nozzles, the fuel supply system comprising:
• a first fuel manifold extending along the circumferential direction and around each fuel nozzle of the first set of fuel nozzles and the second set of fuel nozzles, the first set of fuel nozzles being coupled only to the first fuel manifold such that the fuel supply system provides a first supply of fuel of the overall supply of fuel to the first set of fuel nozzles through the first fuel manifold;
• and
• a second fuel manifold extending along the circumferential direction and around each fuel nozzle of the first set of fuel nozzles and the second set of fuel nozzles, the second set of fuel nozzles being coupled only to the second fuel manifold such that the fuel supply system provides a second supply of fuel of the overall supply of fuel to the second set of fuel nozzles through the second fuel manifold, the second fuel manifold being separate from the first fuel manifold such that the second supply of fuel is separate from the first supply of fuel,
• wherein the first fuel manifold and the second fuel manifold are aligned with the longitudinal centerline with one of the first fuel manifold or the second fuel manifold being disposed radially between the other of the first fuel manifold or the second fuel manifold and the longitudinal centerline,
• wherein the liner and the dome assembly further define a first fuel-air mixing flowpath of each fuel nozzle of the first set of fuel nozzles that is configured to provide a first flow rate of the compressed air therethrough to mix with the first supply of fuel in the combustion chamber and a second fuel-air mixing flowpath of each fuel nozzle of the second set of fuel nozzles that is configured to provide a second flow rate of the compressed air therethrough to mix with the second supply of fuel in the combustion chamber, the second flow rate being different than the first flow rate, and
• wherein the fuel supply system is configured such that, during operation of the gas turbine engine, at least 50% of the overall supply of fuel is the first supply of fuel and a remainder of the overall supply of fuel is the second supply of fuel.