A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition.


    Access

    Download


    Export, share and cite



    Title :

    Aircraft power outtake management


    Contributors:

    Publication date :

    2019-05-07


    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 / G05B Steuer- oder Regelsysteme allgemein , CONTROL OR REGULATING SYSTEMS IN GENERAL



    AIRCRAFT POWER OUTTAKE MANAGEMENT

    CHEN BRYAN / CHMIEL DARIUSZ / BEAUCHESNE-MARTEL PHILIPPE et al. | European Patent Office | 2023

    Free access

    AIRCRAFT POWER OUTTAKE MANAGEMENT

    CHEN BRYAN / CHMIEL DARIUSZ / BEAUCHESNE-MARTEL PHILIPPE et al. | European Patent Office | 2021

    Free access

    Power management on aircraft

    Schröter, Torben | SLUB | 2013


    Power management on aircraft

    Schröter, Torben | TIBKAT | 2013


    Power management on aircraft

    Schröter, Torben | Tema Archive | 2013