TURBINE ENGINE ASSEMBLY AND DUAL FUEL AIRCRAFT SYSTEM

摘要

A turbine engine assembly (101) and dual fuel aircraft system having a cryogenic fuel system (500), having a cryogenic fuel reservoir (502), a vaporizer heat exchanger (504), a liquid supply line (506) operably coupling the fuel reservoir to an input of the vaporizer heat exchanger, a gas supply line (508) operably coupling an output of the vaporizer heat exchanger to the combustion section, and a second heat exchanger (510) thermally connecting the liquid supply line and the gas supply line to transfer heat from the gas supply line to the liquid supply line.