Distributed aircraft engine fuel system

A gas turbine engine (10) includes a plurality of fuel injectors (24, 26; 44, 46, 48; 66, 68, 70, 72; 74, 76, 78, 80, 82, 84, 86, 88) grouped operatively by stages in a multistage combustor (12; 12'; 12"). A fuel system (30; 30'; 30") for the gas turbine engine includes at least one fuel metering module (42) per stage of the multistage combustor. Each fuel metering module includes a pump (54), a flow meter (56), a pressure sensor (58), a controller (60), and a motor (62), which work together to control fuel output.