This invention concerns an aircraft 10 propulsion system in which an engine 16 has an engine core comprising a compressor (106, figure 3), a combustor (108) and a turbine (109) driven by a flow of combustion products of the combustor. A propulsive fan 12 generates a mass flow of air to propel the aircraft. An electrical energy store 30 is provided on board the aircraft. An electric motor 113 is arranged to drive the propulsive fan and the engine core compressor. A controller controls the electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The electric motor is controlled to selectively drive both the propulsive fan and engine core compressor. The electric motor may selectively assist the engine core compressor by supplementing the torque applied from the turbine. A data carrier is additionally disclosed, the carrier comprising instructions for operation of an aircraft propulsion system wherein the system is configured to output instructions to selectively assist rotation of an engine core compressor by an electrical energy store.


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    Titel :

    Aircraft electrically-assisted propulsion control system


    Beteiligte:
    PETER SWANN (Autor:in) / PAUL FLETCHER (Autor:in) / ALVISE PELLEGRINI (Autor:in) / ASHOG KULATHASAN (Autor:in)

    Erscheinungsdatum :

    2020-08-05


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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