The present invention relates to a method for the at least partially automated diagnosis of aircraft gas turbine engines having the steps of: 1) detecting (S10) actual parameter values (NH, EGT) of an aircraft gas turbine engine for several operational segments (z1, z2, . . . ); 2) determining (S20) deviations (ΔNH, ΔEGT), of these actual parameter values from theoretical parameter values; and 3) determining (S40) damage pattern probabilities (P(HPC), P(LPC)) based on a similarity of at least one determined deviation, particularly based on a change (δ) between determined deviations (Δ), to deviation patterns (δNH, δEGT) of different known damage patterns.
DIAGNOSIS OF AIRCRAFT GAS TURBINE ENGINES
2016-09-08
Patent
Electronic Resource
English
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