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.


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    Title :

    Cooling architecture for liquid hydrogen superconducting system


    Contributors:

    Publication date :

    2025-06-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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