A gas turbine engine including a core air passage, a combustor, and a steam line. The combustor is located in the core air passage and combusts hydrogen fuel producing combustion gases. The steam line is fluidly coupled to the core air passage at a position downstream of the combustor to receive a portion of the combustion gases. A conduit thermally coupled to an external surface of an aircraft may be fluidly coupled to the steam line to receive the combustion gases and to heat the external surface. The gas turbine engine may also include a water vapor condenser fluidly connected to the steam line to receive the combustion gases and to condense the water vapor of the combustion gases. At least one nozzle may be fluidly coupled to the water vapor condenser to inject the condensed water into the core air passage.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    ICE PROTECTION SYSTEMS FOR AIRCRAFT FUELED BY HYDROGEN


    Beteiligte:

    Erscheinungsdatum :

    07.03.2024


    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



    Ice protection system for hydrogen-fueled aircraft

    BOUCARD VILAS / THATIPATI VISHNU VADHAN / ADHACHARI SUBRAMANI et al. | Europäisches Patentamt | 2024

    Freier Zugriff

    Hydrogen Fueled Aircraft

    Emerald Group Publishing | 1988



    Will hydrogen-fueled aircraft be safe?

    Brewer, G.D. | Tema Archiv | 1982


    Monitoring system for hydrogen-fueled aircraft

    MINAS KONSTANTINOS | Europäisches Patentamt | 2023

    Freier Zugriff