Patent ID: 8666632

Claim:
A fuel system for a gas turbine engine having an electronic engine control, the fuel system comprising: a plurality of fuel injectors grouped by stages in a multistage combustor; a first fuel flow metering module on a first conduit for controlling a first fuel output to a first plurality of fuel injectors in a first portion of a first stage of the multistage combustor; a second fuel flow metering module on a second conduit for controlling a second fuel output to a second plurality of fuel injectors in a second portion of the first stage of the multistage combustor, wherein operation of the first fuel flow metering module is independent of operation of the second fuel flow metering module; each fuel flow metering module including: a positive displacement pump for pumping fuel; a flow meter for measuring fuel flow; a first pressure sensor for sensing fuel pressure; a controller for receiving and analyzing information regarding fuel flow from the flow meter, fuel pressure from the first pressure sensor, and fuel demand from the electronic engine control; and an electric motor for driving the positive displacement pump in accordance with a signal received from the controller to modulate fuel output for the fuel flow metering module.