Device and system for testing high-pressure turbine rotor of aero-engine

The present disclosure relates to an apparatus and system for testing a high pressure turbine rotor of an aero-engine. The apparatus comprises an apparatus for providing signal transmission, comprising: a rotor member provided with one or more rotating conductive means thereon; a stator member comprising one or more conductive devices, where the one or more conductive devices on the stator member conductively contact the one or more rotating conductive devices on the rotor member; and an adapter shaft comprising a first section and a second section, where the rotor member is coupled between the second section of the adapter shaft and the stator member, and where the first section of the adapter shaft is provided with one or more holes to form a passage through the one or more holes in the first section. The equipment disclosed by the invention is connected to the rear end of the high-pressure turbine rotor, and a hole is formed in the first section of the adapter shaft, so that a high-pressure turbine rear be