A system for the management of thermal transfer in a gas turbine engine includes
a heat generating sub-system in operable communication with the engine, a fuel
source to supply a fuel, a fuel stabilization unit to receive the fuel from the
fuel source and to provide the fuel to the engine, and a heat exchanger in thermal
communication with the fuel to transfer heat from the heat generating sub-system
to the fuel. A method of managing thermal transfer in an aircraft includes removing
oxygen from a stream of a fuel fed to an engine used to drive the aircraft, transferring
heat from a heat generating sub-system of the aircraft to the fuel, and combusting
the fuel. A system for the thermal management of an aircraft provides for powering
the aircraft, supplying a fuel deoxygenating the fuel, and transferring heat between
a heat generating sub-system of the aircraft and the fuel.