A turbine engine system includes aircraft systems including at least one hydrogen fuel tank, engine systems comprising a compressor section, a combustor section having a burner, and a turbine section, and a hydrogen fuel flow supply line configured to supply hydrogen fuel from the at least one hydrogen fuel tank into the burner for combustion. The turbine engine system has a bypass ratio between 5 to 20.


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    Titel :

    HYDROGEN POWERED GEARED TURBOFAN ENGINE WITH REDUCED SIZE CORE ENGINE


    Beteiligte:
    MULDOON MARC J (Autor:in) / STAUBACH JOSEPH B (Autor:in) / LENTS CHARLES E (Autor:in)

    Erscheinungsdatum :

    12.01.2023


    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



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