An aircraft propulsion system a cryogenic fuel system, a superconducting electrical device that is operable at a cryogenic temperature, a cooling system where a cooling fuel flow is utilized for maintaining the superconducting electrical device at the cryogenic temperature, an ejector where the primary fuel flow from the fuel system drives the cooling fuel flow through the cooling system to form a combined fuel flow, and a separator where a first portion of the combined fuel flow from the ejector is routed to the core engine and a second portion of the combined fuel flow is routed back to the cooling system.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Cooling architecture for liquid hydrogen superconducting system


    Beteiligte:

    Erscheinungsdatum :

    17.06.2025


    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



    COOLING ARCHITECTURE FOR LIQUID HYDROGEN SUPERCONDUCTING SYSTEM

    ALAHYARI ABBAS A | Europäisches Patentamt | 2024

    Freier Zugriff

    AIRCRAFT PROPULSION SYSTEM WITH COOLING ARCHITECTURE FOR LIQUID HYDROGEN SUPERCONDUCTING SYSTEM

    ALAHYARI ABBAS A | Europäisches Patentamt | 2024

    Freier Zugriff



    Hydrogen fuel automobile liquid cooling device and hydrogen reactor circulating cooling system

    LEI BINGFEN / LI JUNZHI / QIANG XIAOWEN et al. | Europäisches Patentamt | 2025

    Freier Zugriff