The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.


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    Title :

    Balancing the power of two turboshaft engines of an aircraft


    Contributors:

    Publication date :

    2016-05-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F23N Regelung oder Steuerung der Verbrennung , REGULATING OR CONTROLLING COMBUSTION / 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



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