Disclosed is an aircraft system for handling cryogenic liquid. The aircraft system comprises a vessel 100 configured to store cryogenic liquid 102, and a vacuum ejector (110, Figure 2) operable to cause a portion of the cryogenic liquid to move from the vessel. The vacuum ejector may be fluidically connected to a downstream centrifugal pump (120). The ejector may receive cryogenic liquid from the vessel through an entrained fluid inlet 111, and cryogenic liquid from the pump through a motive fluid inlet 112. The vessel may be hermetically sealed and thermally insulated. The cryogenic liquid may be liquid hydrogen. The ejector may move liquid through a conduit (122) for supplying fuel to an engine 11. Also disclosed is a method of handling saturated cryogenic liquid, comprising the steps of: conveying a portion of the liquid from a vessel, and locally cooling the liquid that is moved to provide cryogenic liquid, such that saturated cryogenic liquid is locally vaporised, and heat from remaining saturated cryogenic liquid is absorbed by the vaporised cryogenic liquid, locally cooling the remaining cryogenic liquid.


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    Titel :

    Aircraft system, aircraft fuel system and method


    Beteiligte:
    CALLUM THORNER (Autor:in) / DYLAN JAMES (Autor:in) / DAVID SAVIN (Autor:in)

    Erscheinungsdatum :

    20.12.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F04F PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED , Pumpen von Arbeitsfluiden durch unmittelbare Berührung mit einem anderen Arbeitsfluid oder durch Ausnutzung der Trägheit des zu pumpenden Arbeitsfluids



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