In order to simulate the typical working condition of aircraft engine

the effects of the high and low cycle compound fatigue on the fatigue performance of a certain level compressor blade were researched.To achieve the purpose

a high and low cycle combined fatigue test system was designed

and the compound fatigue test

vibration test and simulation analysis were conducted. It was concluded that the first order vibration frequency of the blade of 1530Hz was confirmed

and the compound fatigue test can significantly reduce blade life to 58.6% than pure low cycle loading; through analysis of the curves of S-N and P-S-N

the degree of fitting of SN curve can reach to 099. The fracture of the blades and the macroscopic and microscopic characteristics of the fracture showed fatigue source

high cycle loading extended area

low cycle loading extended area and fracture area at the same time. The clear characteristics area of fracture under the compound fatigue effect was found. The rationality and feasibility of this test system were illustrated.