Abstract: A gas turbine engine with an electrically driven fuel pump unit wherein the rotor of the gas turbine engine operates an electric generator. The generator supplies two separate circuits. One circuit serves in the customary way to supply electricity for the flight system of an airplane or missile in which the gas turbine engine is used, while the second circuit is connected to an electrically driven fuel pump unit for the purpose of driving the latter. The circuit which is provided for the fuel pump unit can be at a higher electrical voltage than the circuit which is connected to the flight system. Mechanical gear units, which would otherwise be necessary, can be omitted; and the electrical conduit cross sections necessary for delivering energy are extremely small in cross section and of relative light weight which is advantageous in airplane and missile applications of the gas turbine engine.

Abstract: A gas turbine engine for aircraft. A generator, which undertakes to supply energy for auxiliary devices, is spaced between a compressor and a turbine. A heat exchanger which surrounds the generator housing, and through which compressor air and fuel flow, is provided for cooling the generator. The compressor air which is cooled by the fuel is supplied to the rotor of the generator, and possibly to a bearing of the rotor shaft.