| 摘要 |
In a control system for a gas turbine aeroengine having a control unit made up of an electronic control unit (ECU) 80 which calculates a fuel flow rate command value based at least on the detected rotational speed of the turbine and a desired power output, and a fuel control unit (FCU) 30 including at least a fuel metering valve 32 which meters fuel to be supplied to the engine based on the calculated fuel flow rate command value, the ECU 80 is integrally connected to the FCU 30, thereby reducing the size, weight and possible resonance of the control units. An alternator (PMA) 60 is integrally connected to the FCU 30 and the rotational speed of the turbine is detected based on the wave form generated by the alternator. The hardware construction is disclosed (fig 5) with the ECU integrated into one chip. The ECU is configured to have an overspeed protector function making a separate protector unnecessary. |
