An aircraft propulsion system (20; 80) a cryogenic fuel system (36), a superconducting electrical device (30; 90) that is operable at a cryogenic temperature, a cooling system (32; 82) where a cooling fuel flow (60, 62, 64, 66) is utilized for maintaining the superconducting electrical device (30; 90) at the cryogenic temperature, an ejector (46) where the primary fuel flow (54) from the fuel system (36) drives the cooling fuel flow (60, 62, 64, 66) through the cooling system (32; 82) to form a combined fuel flow (56), and a separator (48) where a first portion (58) of the combined fuel flow (56) from the ejector (46) is routed to the core engine (22) and a second portion (62) of the combined fuel flow (56) is routed back to the cooling system (32; 82).
AIRCRAFT PROPULSION SYSTEM WITH COOLING ARCHITECTURE FOR LIQUID HYDROGEN SUPERCONDUCTING SYSTEM
FLUGZEUGANTRIEBSSYSTEM MIT KÜHLARCHITEKTUR FÜR EIN SUPRALEITENDES SYSTEM MIT FLÜSSIGEM WASSERSTOFF
SYSTÈME PROPULSIF D'AÉRONEF AVEC ARCHITECTURE DE REFROIDISSEMENT POUR SYSTÈME SUPRACONDUCTEUR À HYDROGÈNE LIQUIDE
04.12.2024
Patent
Elektronische Ressource
Englisch
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