A method for the at least partially automated diagnosis of aircraft gas turbine engines includes the steps of: 1) detecting actual parameter values of an aircraft gas turbine engine for several operational segments 2) determining deviations, of these actual parameter values from theoretical parameter values; and 3) determining damage pattern probabilities based on a similarity of at least one determined deviation, particularly based on a change between determined deviations, to deviation patterns of different known damage patterns.
Diagnosis of aircraft gas turbine engines
03.07.2018
Patent
Elektronische Ressource
Englisch
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