PULSE WIDTH MODULATION DRIVE FOR STAGED FUEL MANIFOLDS

A fuel system (200) for a gas turbine engine (100) of an aircraft, including a main inlet feed conduit (122) fluidly connected to a primary manifold feed conduit (110a) and a secondary manifold feed conduit (110a, 110b). A primary manifold (110) fluidly connects the primary manifold feed conduit (110a) to a plurality of primary fuel injectors (120a), and a secondary manifold (111) fluidly connects the secondary manifold feed conduit (110b) to a plurality of secondary fuel injectors (120b).