An aircraft engine diagnostic system includes at least one sensor and a diagnostic controller. The at least one sensor measures a parameter of a gas turbine engine. The diagnostic controller is in signal communication with the at least one sensor. The diagnostic controller determines an actual thrust output of the gas turbine engine and an execution of at least one control system limiter configured to limit control of the gas turbine engine based on the measured parameter. The diagnostic controller further determines an existence of an engine fault based on the actual thrust output of the gas turbine engine and an execution of the at least one control system limiter.


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    Title :

    DETECTING GAS OR FUEL LEAKS IN A GAS TURBINE ENGINE


    Contributors:
    NIZAMI SAFI (author) / ROACH ANDREW (author)

    Publication date :

    2025-03-27


    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 / G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen



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