The invention relates to a gas turbine engine, particularly an aircraft engine, comprising a combustion chamber and a gas turbine for generating driving power and/or thrust, a compressor that has at least two stages and encompasses a low-pressure compressor and a high-pressure compressor which can at least be indirectly driven by the gas turbine in order to compress air or a gas mixture for the combustion chamber and which are each provided with a drive shaft. The invention is characterized by the following features: - the high-pressure compressor can be driven by the low-pressure compressor by means of a torque-transmitting driving connection between the drive shaft of the low-pressure compressor and the drive shaft of the high-pressure compressor; - a controllable hydrodynamic machine is disposed within the driving connection in order to transmit the entire driving power from the drive shaft of the low-pressure compressor to the drive shaft of the high-pressure compressor or some of the driving power.
