Gas turbine engine with an operating-fuel cooled generator

Claim 1

A gas turbine engine for aircraft, comprising: a compressor; a rotor shaft; at least one turbine; a generator which can be cooled by turbine fuel and is disposed between said compressor and said turbine, said generator being driven by said rotor shaft and serving to supply energy to auxiliary devices of said aircraft, said generator including a generator housing, a stator, and a rotor; a heat exchanger which co-axially surrounds said generator housing, said heat exchanger including a partition which extends essentially coaxial to said rotor shaft and divides said heat exchanger into two chambers through which cooling medium flows; said two radially sequentially located and axially continuous flow chambers including a radially inner primary chamber through which turbine fuel flows, and a radially outer secondary chamber through which compressor air flows to be cooled by said turbine fuel flowing through the radially inner primary chamber whereby the generator stator is also cooled by said turbine fuel flowing through the radially inner primary chamber; and direction-changing means associated with said generator housing and said heat exchanger for furthermore supplying turbine-fuel cooled compressor air to said rotor which is cooled thereby.