Flugzeugantriebssystem mit Kühlarchitektur für ein Supraleitendes System mit Flüssigem Wasserstoff

Details

Veröffentlichungs-Nr.

EP4471262

Aktenzeichen

EP24179110

Anmeldetag

30. Mai 2024

Veröffentlichung

4. Dezember 2024

Rechtsraum

EP

IPC

F02C3/22B64D37/34F02C3/32F02C7/224F02C9/40F02K5/00

Abstract

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).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete