LIQUID HYDROGEN EVAPORATORS AND HEATERS

In accordance with at least one aspect of this disclosure, there is provided a hydrogen fuel system for aircraft. The hydrogen fuel system includes a gas turbine engine (10) and a fuel feed conduit (122). The fuel feed conduit is defined at least in part by, in fluid series, a liquid hydrogen tank (124) fluidly connected to a combustor (108) of the gas turbine engine, a liquid hydrogen pump (132) to drive fuel to the combustor of the gas turbine engine, an evaporator (134), and an electric heat source (144) in thermal communication with the evaporator to add heat into a flow of hydrogen passing through the evaporator. In embodiments, the electric energy source associated with the electric heat source to power the electric heat source.