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
08.09.2016
Patent
Elektronische Ressource
Englisch
Advanced Lubricants for Aircraft Turbine Engines
SAE Technical Papers | 1985
|Aircraft Turbine Engines - Design and Operation
NTIS | 1969
|Aerothermodynamics of Aircraft Gas Turbine Engines
NTIS | 1978
|Aircraft propulsion and gas turbine engines
TIBKAT | 2008
|