Method for monitoring a control device of a fuel metering valve of a turbojet engine
View Patent ↗A method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine, the control device supplying a control current to a servo valve in order to modify the position of the fuel metering valve. The method includes determining the position of the fuel metering valve during a flight of the aircraft, determining the travelling speed of the fuel metering valve, and determining the control current when the travelling speed of the fuel metering valve is zero. A mean control current is calculated when the travelling speed of the fuel metering valve is zero, the mean control current forming an indicator of deterioration of the control device. The deterioration indicator is compared with a reference base of indicators with deterioration so as to infer the type of deterioration from it, and an abnormality score is calculated for the deterioration indicator. The abnormality score is compared with a decision threshold of abnormality characteristic of the type of deterioration, and an alarm is released in case of violation of the decision threshold of abnormality.
1. Method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine, the control device supplying a control current to a servo valve in order to modify a position of the fuel metering valve, the method comprising:
determining the position of the fuel metering valve during a flight of the aircraft;
determining the travelling speed of the fuel metering valve based on said position of the fuel metering valve;
determining the control current when the travelling speed of the fuel metering valve is zero due to an absence in variation of said position of the fuel metering value;
calculating a mean control current when the travelling speed of the fuel metering valve is zero, the mean control current forming an indicator of deterioration in function of the control device;
comparing the deterioration indicator with a reference base of indicators of deterioration so as to infer a type of deterioration in function of the control device;
calculating an abnormality score for the deterioration indicator;
comparing the abnormality score with a decision threshold of abnormality that is characteristic of the type of deterioration; and
releasing an alarm in case of violation of the decision threshold of abnormality.
2. Method according to claim 1 , in which the reference base of indicators of deterioration comprises an indicator of deterioration of a positive drift, and an indicator of deterioration of a negative drift.
3. Method according to claim 1 , wherein the deterioration indicator is normalized according to standard deviation and average value of the deterioration indicator obtained over a plurality of flights during a learning phase.
4. Method according to claim 3 , in which the abnormality score of the deterioration indicator is a function of the absolute value of said normalized deterioration indicator.
5. Method according to claim 1 , further comprising comparing the evolution of the slope of the abnormality score with a threshold of maximal abnormality before failure.
6. Method according to claim 5 , wherein the value of the threshold of maximal abnormality before failure is defined by learning during several no-deterioration flight cycles of an aircraft.