| Citation: | WEI Dasheng, FENG Junqi, MA Mengdi, et al. Design method and test verification of simulated specimen of aeroengine disc center hole[J]. Journal of Aerospace Power, 2022, 37（10）：2157-2166 doi: 10.13224/j.cnki.jasp.20220205
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According to the finite element simulation results of the turbine disc, the stress state at the inspection position of the disk center was determined, and the ratio of the circumferential stress and axial stress and the radial stress gradient of the circumferential stress at the disc center hole were taken as the design indexes to ensure the consistency of stress state of the simulated specimen with the actual disc. Two kinds of simulators, namely, the multi axial simulators reflecting the biaxial stress state, and the plate notch simulators reflecting the stress gradient, were designed for the inspection position of the center hole of the wheel disc. Low cycle fatigue tests were carried out by using these two kinds of specimens under actual load conditions of the disc, and the test results were statistically analyzed. Furthermore, the multi-axial fatigue life prediction model and the life model considering the influence of stress gradient were used to evaluate the fatigue life of these two simulated specimens. The scatter bands of the prediction results of biaxial simulated specimen were within 2 and those of the flat notch simulated specimen were within 3. The results could provide engineering reference for the life evaluation of aeroengine structures.
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