A method and control system for an aircraft engine comprising a gas turbine driving a fan propeller with a mechanical gear-train and a dedicated pitch change mechanism for the fan propeller includes a fuel flow signal input; a pitch change mechanism signal input; a controlled plant for relating a pitch change mechanism pitch angle (BetaP) and a fuel flow (Wf) to at least two controlled outputs and a set of constraints. A decoupling control decoupling the controlled plant and/or the constraints into two separate single-input single-output (SISO) control loops for the first and second controlled outputs and a decoupling control decoupling the constraints from the decoupled controlled outputs and the constraints from one another provide gas turbine and fan propeller coordinate control while coordinately controlling constraints and outputs. A feedforward control can compensate the load change effect on engine speed and fan propeller rotor speed control.


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    Titel :

    METHOD AND SYSTEM FOR MODEL BASED CONTROL FOR VARIABLE PITCH FAN ENGINES AND TURBO-SHAFT, TURBO-PROPELLER ENGINES


    Weitere Titelangaben:

    METHODE ET SYSTEME DE COMMANDE FONDEE SUR UN MODELE POUR REACTEURS A DOUBLE FLUX A PAS VARIABLE ET TURBOMOTEURS TURBOPROPULSEURS


    Beteiligte:
    LU MANXUE (Autor:in) / CARPENTER R SHELDON (Autor:in)

    Erscheinungsdatum :

    2016-03-30


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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