A fuel system (200) for a hydrogen fuelled aircraft propulsion system (103) comprises a tank (104) configured to store hydrogen, a first inductor (436a-c) provided within the tank (104) and configured to heat hydrogen fuel within the tank (104), and a second inductor (432a-c) provided externally to the tank (104), and configured to induce a current in the first inductor (436a-c).
GAS TURBINE ENGINE
GASTURBINENTRIEBWERK
MOTEUR À TURBINE À GAZ
07.05.2025
Patent
Elektronische Ressource
Englisch