Simplified fuel system for jet engines

摘要

A fuel system for delivering fuel from a fuel source to combustor in a gas turbine engine has a pump receiving fuel flow from the fuel source and producing a pressurized fuel flow that flows to a flow meter that measures the fuel flow and generates a signal thereof. A bypass valve bypasses, to the input side of the pump, a portion of the pressurized fuel flow before it reaches the flow meter. An electronic control unit is included that receives the signal and in response thereto adjusts the bypass valve until the measured fuel flow equals a predetermined desired fuel flow stored in the electronic control unit. The fuel system is also self-calibrating.