| 摘要 |
In a control system for a gas turbine aeroengine having a control unit made up of an electronic control unit (ECU) which calculates a fuel flow rate comman d value based at least on the detected rotational speed of the turbine and the desired power output and a fuel control unit (FCU) including at least a fuel metering valve which meters fue l to be supplied to the engine based on the calculated fuel flow rate command value, the ECU is integrally connected to the FCU, thereby reducing the size and weight of the control units and hence, reducing the occurrence of resonance which would otherwise be likely to occu r. In the system, an alternator is integrally connected to the FCU and the rotational speed of the turbine is detected based on the wave form generated by the alternator. Moreover, the ECU calculates the fuel flow rate command value such that the fuel flow rate to be supplied to the engine is brought to a prescribed value. This makes it unnecessary to provid e the overspeed protector. |
