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.


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    Titel :

    Diagnosis of aircraft gas turbine engines


    Beteiligte:
    KANDO ANDRE (Autor:in) / ABDULLAHI HASSAN (Autor:in) / TSALAVOUTAS ANASTASIOS (Autor:in) / SPEER THOMAS (Autor:in)

    Erscheinungsdatum :

    03.07.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G07C TIME OR ATTENDANCE REGISTERS , Zeit- oder Anwesenheitskontrollgeräte / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / G05B Steuer- oder Regelsysteme allgemein , CONTROL OR REGULATING SYSTEMS IN GENERAL



    DIAGNOSIS OF AIRCRAFT GAS TURBINE ENGINES

    KANDO ANDRE / ABDULLAHI HASSAN / TSALAVOUTAS ANASTASIOS et al. | Europäisches Patentamt | 2016

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