The invention provides a high-speed rotor blade flying-off test device, comprising a driving system, a vacuum anti-explosion system, a lubrication cooling system and a monitoring and control system. A driving motor is connected with a rotor test article through a transitional transmission mechanism, the vacuum anti-explosion system includes a vacuum chamber, the vacuum chamber is internally provided with a flying-loss protective cover, and a rotor rotation space and a blade flying-loss protective space are formed in the flying-loss protective cover, and are separated through a buffering separator plate. The buffering separator plate is arranged inside the flying-loss protective cover inside the vacuum chamber, after a blade on the rotor test article flies off, the blade stays in the blade flying-loss protective space, thus the blade that flies off does not collide with the rotating rotor test article, so that a test can be guaranteed to be carried out normally, at the same time, safety of test personnel and test equipment can be also effectively guaranteed, so as to ensure rotation safety of an engine rotor, and a technological means of an important empirical basis is provided for engine design finalizing.