Method for monitoring elements in a turbine engine combustion chamber

Method for monitoring an ignition system of an aircraft turbine engine, the ignition system including a combustion chamber fitted with a spark plug and an ignition casing, the turbine engine including an accelerometer and an acoustic sensor. The method includes steps of: acquiring accelerometric and...

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Bibliographische Detailangaben
Hauptverfasser:	Coupard, Josselin Xavier, Demaison, François Maurice Marcel, Jedruszek, Marion Marguerite, Facquet, Valentin Francis Joël
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MEASURING MECHANICAL ENGINEERING PHYSICS TESTING TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR WEAPONS
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Beschreibung
Zusammenfassung:	Method for monitoring an ignition system of an aircraft turbine engine, the ignition system including a combustion chamber fitted with a spark plug and an ignition casing, the turbine engine including an accelerometer and an acoustic sensor. The method includes steps of: acquiring accelerometric and acoustic data representative of spark plug breakdown noises from signals generated by the accelerometer and the acoustic sensor, detecting breakdown peak times from the accelerometric data and the acoustic data, correlating the breakdown peak times detected from the accelerometric data and the breakdown peak times detected from the acoustic data, and establishing a diagnosis of the health of the ignition casing and a diagnosis for the spark plug on the basis of the correlation results.