The purpose of this paper is to propose electric drive specific power, electric drive efficiency, and electrical propulsion fraction as the key performance parameters for a partially turboelectric aircraft power system and to investigate their impact on the overall aircraft performance. Breguet range equations for a base conventional turbofan aircraft and a partially turboelectric aircraft are found. The benefits and costs that may result from the partially turboelectric system are enumerated. A break even analysis is conducted to find the minimum allowable electric drive specific power and efficiency, for a given electrical propulsion fraction, that can preserve the range, fuel weight, operating empty weight, and payload weight of the conventional aircraft. Current and future power system performance is compared to the required performance to determine the potential benefit.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Partially Turboelectric Aircraft Drive Key Performance Parameters


    Beteiligte:

    Kongress:

    AIAA Propulsion and Energy Forum 2017 ; 2017 ; Atlanta, GA, United States


    Erscheinungsdatum :

    2017-07-10


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Partially Turboelectric Aircraft Drive Key Performance Parameters

    Jansen, Ralph / Duffy, Kirsten P. / Brown, Gerald | AIAA | 2017


    Partially Turboelectric Aircraft Drive Key Performance Parameters (AIAA 2017-4702)

    Jansen, Ralph / Duffy, Kirsten P. / Brown, Gerald | British Library Conference Proceedings | 2017



    Partially Turboelectric and Hybrid Electric Aircraft Drive Key Performance Parameters (AIAA 2018-5023)

    Duffy, Kirsten P. / Jansen, Ralph | British Library Conference Proceedings | 2018