A system for a gas turbine engine (20) includes an engine control system (22). The engine control system (22) includes a processor (62) and a non-transitory memory (64) storing instructions, which instructions when executed by the processor (62), cause the processor (62) to: obtain a current engine installation configuration for the gas turbine engine (20) and the aircraft, determine an expected normalized value of the engine parameter based on the current engine installation configuration and one or more of a normalized engine power (SHPN) of the gas turbine engine (20), an engine inlet temperature, an airspeed, or an altitude, determine a fully deteriorated engine (FDE) value of the engine parameter using the expected normalized value of the engine parameter, determine a current value of the engine parameter for the gas turbine engine (20), and determine the engine operating margin for the engine parameter based on the FDE value of the engine parameter and the current value of the engine parameter.


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    Title :

    SYSTEMS AND METHODS FOR DETERMINING GAS TURBINE ENGINE OPERATING MARGINS


    Additional title:

    SYSTEME UND VERFAHREN ZUR BESTIMMUNG VON GASTURBINENTRIEBWERKS-BETRIEBSMARGEN
    SYSTÈMES ET PROCÉDÉS DE DÉTERMINATION DE MARGES DE FONCTIONNEMENT DE MOTEUR À TURBINE À GAZ


    Contributors:

    Publication date :

    2024-02-28


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung



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