航空发动机轮盘模拟件裂纹预制分析与试验研究

Data of aviation accidents shows that the operation reliability of aero-engine disks has been one of the determining factors for the safe flight of airplane. Therefore, it is valuable and important to diagnosis the disk structural defects in time. To provide the necessary foundation for damage identification of disks, a feasible prefabricating crack method for disk structure is proposed. Firstly, the singularity distribution characteristics in root stress of the V notch in the disk simulator are analyzed in theory sufficiently. Secondly, an equivalent load method is proposed based on the loading conditions and geometrical features. The stress condition and fatigue life are also analyzed. Finally, to verify the feasibility of the proposed method for prefabricating crack, a fatigue experiment is carried on. The experiment results show that the relative errors of stress in x direction and the number of fatigue loading cycles are 2.7% and 12.7% respectively, which demonstrate the proposed method for prefabricating crack and corresponding numerical analysis method can be used for damage identification of aero-engine turbine disks.