Patent ID: 6434473
Filing Date: 2002-08-13
Classification: F02C,F05D,Y02T,Y10T

Abstract:
A system for controlling a gas turbine aeroengine having at least a turbine which is rotated by gas produced by the engine to rotate a rotor that sucks in air, having:turbine rotational speed detecting means for detecting a rotational speed of the turbine; desired power output detecting means for detecting a desired power output of the engine specified by an operator; an electronic control unit which calculates a fuel flow rate command value based at least on the detected rotational speed of the turbine and the desired power output; a fuel control unit including at least a fuel metering valve which meters fuel to be supplied to the engine based on the calculated fuel flow rate command value; and a fuel supplying system which supplies fuel to the engine through the fuel control unit; wherein the improvement comprises; the electronic control unit and the fuel control unit being a unitary hardware structure; an alternator which supplies electric power to the electronic control unit and the fuel control unit, the alternator being integrally connected to the fuel control unit; and wherein the turbine rotational speed detecting means detects the rotational speed of the turbine based on an output of the alternator.