| Citation: | RAO Yunsong, WANG Xuemin, LI Fangjuan, et al. Improved fatigue design method and experimental verification of low-pressure turbine shaft[J]. Journal of Aerospace Power, 2025, 40（2）：20230124 doi: 10.13224/j.cnki.jasp.20230124
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Two traditional methods of nominal stress method for shaft high-low cycle combined fatigue design were summarized: large torque equivalent steady-state shear stress method and multi-axis equivalent stress method. These two traditional methods have the following limitations: the large torque equivalent steady-state shear stress method is only suitable for shaft parts with negligible bending moment load; and the multi-axis equivalent stress method is only suitable for fatigue reserve evaluation of parts with negligible stress concentration coefficient, but not for fatigue life and cumulative damage evaluation. Referring to the fatigue design methods in many related books, the advantages were refined while avoiding the disadvantages, an improved fatigue design method of shaft with wider application scope and more reasonable theoretical principle was put forward, which was then applied to the high-low cycle combined fatigue design of a low-pressure turbine shaft, and also the experimental verification. The results showed that the calculation results of this improved method coincided with the phenomena of the two-stage test, and the fatigue damage deviation was 12.6%, which was significantly better than that of the traditional method (84.7%), and met the engineering needs of the life analysis results within 2 times the scattering error control (i.e., error range: −50%—100%) of the usual requirements.
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