CPC G01M 15/14 (2013.01) [F02C 7/266 (2013.01); F05D 2220/323 (2013.01); F05D 2260/80 (2013.01)] | 10 Claims |
1. A method for monitoring an ignition system of an aircraft turbine engine, the ignition system including at least one combustion chamber, at least one spark plug in the at least one combustion chamber, an ignition exciter box to excite the at least one spark plug, the turbine engine including at least one accelerometer and at least one acoustic sensor, the method comprising:
acquiring accelerometric and acoustic data representative of breakdown noises of the at least one spark plug, on the basis of signals produced by the at least one accelerometer and the at least one acoustic sensor,
detecting times of breakdown peaks of the at least one spark plug on the basis of the accelerometric data and times of breakdown peaks of the at least one spark plug on the basis of the acoustic data representative of breakdown noises of the at least one spark plug,
correlating the times of the breakdown peaks of the at least one spark plug detected on the basis of the accelerometric data and the times of the breakdown peaks of the at least one spark plug detected on the basis of the acoustic data representative of breakdown noises of the at least one spark plug, and
establishing a diagnosis of health of the ignition exciter box and a diagnosis of the at least one spark plug, according to the results of the correlating.
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