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.


    Access

    Download


    Export, share and cite



    Title :

    COOLING ARCHITECTURE FOR LIQUID HYDROGEN SUPERCONDUCTING SYSTEM


    Contributors:

    Publication date :

    2024-12-05


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F17C Behälter zum Aufnehmen oder Speichern verdichteter, verflüssigter oder verfestigter Gase , VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES






    Liquid hydrogen high-temperature superconducting motor full-electric propulsion system

    LI BIN / ZHANG ZHE / MIN JIE et al. | European Patent Office | 2021

    Free access

    COOLING ARCHITECTURE FOR HYDROGEN FUEL CELL-POWERED AIRCRAFT

    TEJPAL RITISH | European Patent Office | 2024

    Free access