Fuel distribution within a gas turbine engine combustor

A fuel system for a gas turbine engine comprising:

• a plurality of duplex nozzles arranged on each side of top dead center;
• a plurality of simplex nozzles;
• a primary manifold operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles;
• a secondary manifold operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles;
• and
• an equalizer valve in communication with the primary manifold and the secondary manifold, the equalizer valve movable between an open position and a closed position, the closed position is operable to permit a supply of fuel pressure to the primary manifold that is greater than fuel pressure to the secondary manifold, and the open position is operable to permit supply of fuel pressure to the primary manifold with essentially an equal fuel pressure as the secondary manifold.