Fatigue cycle test apparatus for compressor blade of aeroengine

The utility model relates to a fatigue cycle test apparatus for a compressor blade of an aeroengine. The fatigue cycle test apparatus comprises a centrifugal force loading assembly and a high-frequency vibration loading assembly. The centrifugal force loading assembly is used for simulating centrifugal force cycle load born by the compressor blade of the aeroengine when the compressor blade is working, and the high-frequency vibration loading assembly is used for simulating high-frequency load born by the compressor blade of the aeroengine when the compressor blade is working. The high-frequency vibration loading assembly comprises a vibration stand, a support A used for fixing a compressor blade testpiece, and a support B used for fixing the centrifugal force loading assembly, wherein the vibration stand is used for applying high-frequency vibration to the compressor blade testpiece. The fatigue cycle test apparatus has a simple structure, is convenient to operate, and can simulate the centrifugal force low cycle load and the high-frequency load born by the compressor blade when the compressor blade is working to enable a test state to be fully consistent with an actual working state. Therefore, a centrifugal force load test and a high-frequency load test for the compressor blade can be achieved, the safe and believable cycle service life can be provided, and usage safety hidden troubles are avoided.