Liquid-hydrogen fuel system for an aircraft

A tank pressurization system for a fuel system comprising:

• a first heat exchanger configured to add pressure to a gas region of a hydrogen fuel tank;
• a second heat exchanger immersed within liquid fuel in the hydrogen fuel tank;
• an actuator valve receiving fuel from a fuel feed system, the actuator valve configured to control fuel received from a first fuel recirculation path to the first and second heat exchangers;
• the fuel feed system comprising:
• a jet pump within the hydrogen fuel tank;
• at least one primary pump receiving fuel from the jet pump and pressurizing the fuel to an outlet path;
• the first fuel recirculation path fluidly connected from the outlet path to an inlet of the jet pump, the first fuel recirculation path passes through the hydrogen fuel tank and the second heat exchanger to a first inlet of the jet pump;
• and
• wherein the second heat exchanger immersed in the liquid fuel is configured to transfer heat from the fuel of the first fuel recirculation path to the hydrogen fuel tank and the first fuel recirculation path directly supplies the cooled fuel to the first inlet of the jet pump.