RADIAL EQUILIBRATED COMBUSTION NOZZLE ARRAY

A fuel injection system (100) for a gas turbine engine (102) includes a first plurality of fuel nozzles (110) arrayed in a circular pattern. Each of the nozzles in the first plurality of fuel nozzles (110) includes a first airflow area defined therethrough. A second plurality of fuel nozzles (112) radially inward from the first plurality of fuel nozzles (110). Each of the nozzles in the second plurality of fuel nozzles (112) includes a second airflow area defined therethrough. The first airflow area is larger than the second airflow area. A third plurality of fuel nozzles (114) can be radially inward from the second plurality of fuel nozzles (112). Each of the nozzles in the third plurality of fuel nozzles (114) can include a third airflow area defined therethrough. The second airflow area can be larger than the third airflow area.