航空发动机轮盘长时间在交变大载荷下工作，其盘心、螺栓孔、端齿等应力集中的特征部位容易发生低周疲劳失效。为准确评估轮盘特征部位的疲劳寿命，需设计反映应力梯度的模拟件并开展相应的疲劳试验，从而为发动机结构设计提供重要依据。现有的模拟件设计方法通常保证危险点一定范围内的应力/应变分布与真实构件的一致，但这些方法对“一定范围”的定义缺乏理论依据且未能形成统一认识。为此，提出了一种临界距离范围内SWT参量分布一致的模拟件设计方法，建立了轮盘盘心、螺栓孔、端齿等危险部位的模拟件设计方法，并开展了模拟件的低周疲劳试验。将端齿模拟件100%转速对应的平均疲劳寿命与轮盘旋转疲劳试验结果对比，相对误差为7%，且均为表面薄弱晶面起裂。最后，讨论了该模拟件设计方法的稳健性。

The discs in aero-engines are continuously subjected to large cyclic loading， of which the bores， bolt holes， curvic couplings and other feature areas are susceptible to Low Cycle Fatigue （LCF） failure. To accurately predict the fatigue life of the discs， it is necessary to design simulating specimens to reflect the stress gradient and perform fatigue experiments， which will provide an important basis for the design of the aero-engine structure. The existing simulating specimen design methods usually require that the stress and strain distribution within a certain range of the hotspot of simulating specimen should be consistent with those of the disc. However， the definition of "certain range" in these methods lacks theoretical basis and no uniform understanding has been reached. This study proposes a simulating specimen design method considering the consistency of SWT parameter distribution at the hotspots of simulating specimens and discs. The simulating specimens for the bores， bolt holes， curvic couplings of the disc are designed. A series of LCF experiments on simulating specimens are conducted. The average fatigue life of the curvic coupling simulating specimens corresponding to 100% rotational speed is compared with the results of the turbine disc rotational fatigue experiment， and the relative error is 7%， with both cracks initiating from the weak crystallographic facets on the surface. Finally， the robustness of the simulating specimen design method is discussed.