Finite element simulation of fretting wear-fatigue interaction in spline couplings
Finite element simulation of fretting wear-fatigue interaction in spline couplings
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DOI：
10.1179/175158308x320791
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发表时间：
2008-03
期刊：
影响因子：
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通讯作者：
J. Ding;S. Leen;E. J. Williams;P. Shipway
中科院分区：
文献类型：
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作者：
J. Ding;S. Leen;E. J. Williams;P. Shipway
本文描述了一种基于有限元的方法，用于模拟与微动磨损相关的材料去除对花键联轴器微动疲劳参数的影响。增量磨损模拟技术是通过用于对称加载的联轴器的单齿有限元模型来实现的，假设所有齿上的磨损相等，并使用相对粗糙的网格模型，以提高计算效率。采用表面插值技术将预测的磨损分布映射到非对称 360°（18 齿）模型上，并在一颗齿上进行详细细化，以预测磨损对应力、应变和疲劳参数演变以及后续寿命预测的影响。寿命预测基于临界平面多轴疲劳参数方法，以及组合载荷循环和磨损引起的疲劳参数变化的累积损伤。此外，还介绍了旋转弯矩和脉动扭矩引起的磨损对微动疲劳损伤累积的影响。低频、扭矩和轴向载荷引起的磨损会导致所有齿上出现严重滑动状况，预计会减少微动疲劳参数，从而延长使用寿命。相反，与部分滑动条件相对应的较高频率、旋转力矩和脉动扭矩引起的磨损预计会增加远离接触边缘的微动疲劳参数，从而导致远离接触边缘的微动疲劳裂纹，并且对于本文研究的情况，如实验观察到的，会导致预测寿命缩短。结果是根据已发布的按比例缩小的航空发动机花键测试数据进行解释的。
This paper describes a finite element based method for simulating the effects of material removal, associated with fretting wear, on fretting fatigue parameters in a spline coupling. An incremental wear simulation technique is implemented with a single tooth finite element model of the coupling for symmetric loading, assuming equal wear on all teeth, using a comparatively coarse mesh model, for computational efficiency. A surface interpolation technique is implemented to map the predicted distributions of wear onto a non-symmetric, 360° (18-tooth) model, with detailed refinement on one tooth, to predict the effect of wear on the evolution of stress, strain and fatigue parameters and on subsequent life prediction. The life prediction is based on a critical plane multiaxial fatigue parameter approach, along with cumulative damage for combined load cycles and for wear induced changes in the fatigue parameters. Furthermore, the effect of wear due to the rotating bending moment and fluctuating torque on fretting fatigue damage accumulation is presented. Low frequency, torque and axial loading induced wear, leading to gross slip conditions on all teeth, is predicted to reduce fretting fatigue parameters and hence increase life. In contrast, higher frequency, rotating moment and fluctuating torque induced wear, corresponding to partial slip conditions, is predicted to increase fretting fatigue parameters away from the contact edges and hence lead to fretting fatigue cracking away from the contact edges and, for the case studied here, to a reduction in predicted life, as observed experimentally. The results are interpreted vis-à-vis published test data for scaled aeroengine splines.