A combustion system of a gas turbine engine comprising: a combustor liner defining a combustion chamber that extends between an upstream end and an exit end ; a fuel circuit including a plurality of fuel injector modules , each fuel injector module including a fuel nozzle set and extending into the combustion chamber , the fuel circuit configured to supply a fuel flow to the combustion chamber ; a pilot fuel nozzle in each fuel nozzle set of each fuel injector module , wherein each pilot fuel nozzle is configured to inject a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber ; and a main fuel nozzle in each fuel nozzle set of each fuel injector module , wherein each main fuel nozzle is configured to inject a second fuel spray toward the exit end of the combustion chamber ; wherein, the fuel circuit is configured with a first supply line coupled with the pilot fuel nozzles and a second supply line coupled with the main fuel nozzles and at ignition conditions of the gas turbine engine more than fifty percent of the fuel flow is injected through the first supply line and the pilot fuel nozzles , and at high power conditions of the gas turbine engine more than fifty percent of the fuel flow is injected through the second supply line and the main fuel nozzles ; wherein the fuel circuit is configured so that the main fuel nozzles supply a fuel rich mixture from the second supply line to the combustion chamber , and a row of quench jets are configured to supply air to the combustion chamber , providing rich-quench-lean combustion in the combustion chamber . a combustor liner defining a combustion chamber that extends between an upstream end and an exit end ; a fuel circuit including a plurality of fuel injector modules , each fuel injector module including a fuel nozzle set and extending into the combustion chamber , the fuel circuit configured to supply a fuel flow to the combustion chamber ; a pilot fuel nozzle in each fuel nozzle set of each fuel injector module , wherein each pilot fuel nozzle is configured to inject a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber ; and a main fuel nozzle in each fuel nozzle set of each fuel injector module , wherein each main fuel nozzle is configured to inject a second fuel spray toward the exit end of the combustion chamber ; wherein, the fuel circuit is configured with a first supply line coupled with the pilot fuel nozzles and a second supply line coupled with the main fuel nozzles and at ignition conditions of the gas turbine engine more than fifty percent of the fuel flow is injected through the first supply line and the pilot fuel nozzles , and at high power conditions of the gas turbine engine more than fifty percent of the fuel flow is injected through the second supply line and the main fuel nozzles ; wherein the fuel circuit is configured so that the main fuel nozzles supply a fuel rich mixture from the second supply line to the combustion chamber , and a row of quench jets are configured to supply air to the combustion chamber , providing rich-quench-lean combustion in the combustion chamber . <EOS>