应力场强法中场径参数的研究

针对应力场强法中场径计算方法存在争议且不易求取的问题,基于应力场强法假设,研究了场径参数计算方法的理论依据;在考虑场径求取可行性的基础上,提出一种在任意载荷条件下确定试件场径的方法.给出了场径的求取步骤,选取6块不同应力集中系数的缺口试件在4种应力比下,按照步骤求取场径.对场径计算结果拟合并作图,由图所示分析影响场径大小的因素.得出结论:在相同应力比下,场径与应力集中系数呈很强的线性关系;在相同应力集中系数下,场径与应力比呈很强的二次曲线关系.通过实例对所提出的方法进行了验证,结果表明:由提出方法确定的场径计算得出的疲劳寿命更贴近于试验寿命,在保证安全的基础上提高了疲劳寿命预测的准确性.     

镍基单晶合金中温疲劳性能应力集中敏感性

疲劳是涡轮叶片的一种主要失效模式.本文开展了DD11单晶合金在650℃中温条件下2种应力集中系数(K_t=1(光滑状态)、K_t=3(缺口状态))的旋转弯曲疲劳性能研究,对比了2种应力集中系数下的疲劳强度,并开展了相关断口分析.结果表明:应力集中系数由K_t=1增大到K_t=3时,疲劳极限由446 MPa降低为311 MPa,说明DD11单晶合金疲劳性能存在应力集中敏感性;疲劳寿命由10~5提高到10~7时,光滑状态由600 MPa降低为420 MPa,疲劳强度降低幅度为180 MPa,而缺口状态由370 MPa降低为290 MPa,降低幅度为80 MPa,说明应力集中条件下DD11单晶合金的疲劳寿命对于外载变化较敏感.断口分析表明,光滑试样断口(应力500 MPa/疲劳寿命9.7×10~5)由几个相交的光滑晶体学平面组成,疲劳源萌生在距表面100μm左右的铸造孔洞;缺口试样断口(应力340 MPa/疲劳寿命8.1×10~5试样)呈平面状,与应力轴垂直,为多源疲劳模式,疲劳源观察到小刻面,在加工刀痕不连续位置萌生.     

轴向荷载作用下K型管节点应力集中系数研究

热点应力法是目前国内外学者研究焊接管节点疲劳寿命的主要方法,而应力集中系数是计算热点应力的主要参数。该文提出了焊缝模拟方法,建立了空心K节点及主管填充混凝土K节点的数值模型,研究了轴向平衡荷载作用下空心及填心K型管节点应力集中系数分布的规律,并与试验结果进行了比较,证明该文提出的数值模拟方法简单可靠,精确性好,可为管节点有限元分析提供借鉴;主管填充混凝土管节点的应力集中系数最大值减小为空心管节点的1/3,说明管内填充混凝土能有效提高管节点的疲劳寿命。     

螺栓杆应力集中系数的研究

螺栓球节点栓杆上的应力集中是导致栓杆发生疲劳破坏的主要原因。该文通过理论推导及数值分析的方法研究了螺栓杆的应力集中系数。在忽略螺纹升角的情况下,根据变形协调条件研究了螺栓杆的轴力梯度变化,采用数值计算确定常用螺栓球的螺纹位移系数及螺纹力计算公式。采用局部建模,通过迭代计算的方法确定螺栓杆应力集中系数。与完整模型的计算结果比较表明该方法的计算结果具有较高的精度,且计算效率高。     

喷丸对TB6钛合金疲劳应力集中敏感性的影响

针对航空用TB6高强钛合金,本工作研究了应力集中条件下喷丸对其疲劳性能的影响规律.采用旋转弯曲疲劳试验机分别测试了两种应力集中系数的试棒的疲劳寿命及极限,采用扫描电镜分析了疲劳断口,采用MTS试验机测试了试棒的拉伸性能,并采用白光干涉仪测试了试样的表面形貌.结果表明:当应力集中系数由Kt=1提高至Kt=2时,TB6钛合金试棒的疲劳极限从537.5 MPa下降至335.5 MPa,表现出明显的应力集中敏感性.而经过喷丸后,Kt=1和Kt=2的试棒的疲劳极限分别提高了33.5％和22.2％,缺口敏感性下降了48％.喷丸有利于降低TB6钛合金的疲劳应力集中敏感性.     

对库仑土压力理论计算误差的探讨

本文分析了库伦土压力理论在其计算回填土墙的土体侧压力的计算值与实际值之间产生误差的原因,根据实际测试结果提出了修正系数,使得计算结果与实际结果相一致。     

一种新的铝合金应变疲劳计算方法

提出了一种在铝合金构件应变疲劳分析中,计算局部应力和应变变程的新方法。这种方法称作应力功恒等法。采用这种新方法,计算了2024-T42铝合金试件在恒幅循环载荷作用下的疲劳寿命,并将疲劳寿命计算结果与试验结果进行了对比分析。对比分析结果表明,采用这种新方法计算构件应力集中处的局部应力和应变变程,具有较高的计算精度。     

一个新的接触疲劳寿命预测模型的研究

本文给出了一个新的针对应力控制接触疲劳问题的寿命预测模型。在该模型中，选用Ｍｉｓｅｓ等效应力作为接触疲劳应力控制参量；引进了非零的接触疲劳应力强度值，根据损伤力学理论，分析了接触疲劳应力强度值与基体材料性质，第二相夹杂之间的关系，同时考虑了表面起裂和亚表面起裂两种失效形式，并将对这两种失效形式的寿命预测统一到一个公式中，引进一个与油膜系数Λ有关的系数ｆ（Λ），来表征润滑程度对接触疲劳寿命的影响。应用该模型来预测一些实验的接触疲劳寿命，计算值与实测值吻合很好。     

单轴拉伸状态下V型切口的应力集中系数

为统一单轴拉伸状态下相同应力集中系数的V型切口形状尺寸设计,以提高缺口试样试验结果的可比性。比较分析目前拉伸试验、疲劳试验和持久试验等标准方法规定使用的试验切口形状尺寸以及计算公式。通过疲劳试验数据结果,依据缺口疲劳系数值和应力集中系数的拟合关系,验证最新修订版的ISO 204标准与DIN 743-2——2000标准给定的公式更适合V型切口形状试样的应力集中系数值计算。并提出以统一的计算公式和切口形状尺寸比例作为设计遵循的准则,提高单轴拉伸状态下缺口试样测试材料缺口敏感性结果的可比性。     

轴向载荷下X型管节点应力集中系数研究

用有限元方法分析了X管节点承受轴向拉力作用时沿焊缝应力集中系数的分布,发现X型管节点最大应力集中系数出现在鞍点处。同时探讨了X节点几何参数对应力集中系数的影响,提出了用于计算X节点最大应力集中系数的参数公式,通过与国际疲劳指导委员会(Fatigue Guidance Review Panel)提出的评价标准比较,证明了所提公式的正确性。     

超声载荷下TC4钛合金的疲劳寿命分析

通过计算裂纹尖端应力强度因子及疲劳裂纹扩展速率da/d N,由C.Paris模型推导出安全寿命Nf,由Bathias公式计算"哑铃"状钛合金试样的裂纹扩展寿命。通过理论计算和有限元分析超声疲劳"哑铃"状试样,得出应力最大位置。利用有限元仿真和实验数据分析TC4钛合金疲劳寿命。在20 k Hz的超声疲劳试验中,试样的断口位置表明:TC4钛合金材料内部缺陷是试样萌生裂纹使断裂位置偏离最大应力处的主要原因。并得出疲劳裂纹萌生阶段寿命决定"哑铃"状试样的疲劳寿命。     

A shear stress-based parameter for fretting fatigue crack initiation

The purpose of this study was to investigate the fretting fatigue crack initiation behaviour of titanium alloy, Ti–6Al–4V. Fretting contact conditions were varied by using different geometries of the fretting pad. Applied forces were also varied to obtain fretting fatigue crack initiation lives in both the low- and high-cycle fatigue regimes. Fretting fatigue specimens were examined to determine the crack location and the crack angle orientation along the contact surface. Salient features of fretting fatigue experiments were modelled and analysed with finite element analysis. Computed results of the finite element analyses were used to formulate a shear stress-based parameter to predict the fretting fatigue crack initiation life, location and orientation. Comparison of the analytical and experimental results showed that fretting fatigue crack initiation was governed by the maximum shear stress, and therefore a parameter involving the maximum shear stress range on the critical plane with the correction factor for the local mean stress or stress ratio effect was found to be effective in characterizing the fretting fatigue crack initiation behaviour in titanium alloy, Ti–6Al–4V.     

Fatigue life prediction of a rubber mount based on test of material properties and finite element analysis

Failure analysis and fatigue life prediction are very important in the design procedure to assure the safety and reliability of rubber components. The fatigue life of a rubber mount was predicted by combining test of material properties and finite element analysis (FEA). The natural rubber material material’s fatigue life equation was acquired based on uniaxial tensile test and fatigue life tests of the natural rubber. The strain distribution contours and the maximum total principal strains of the rubber mount at different loads in the x and y directions were obtained using finite element analysis method. The critical region cracks prone to arise were obtained and analyzed. Then the maximum total principal strain was used as the fatigue parameter, which was substituted into the natural rubber’s fatigue life equation, to predict the fatigue life of the rubber mount. Finally, fatigue lives of the rubber mount at different loads were measured on a fatigue test rig to validate the accuracy of the fatigue life prediction method. The test results imply that the fatigue lives predicted agree well with the test results.     

A method for modelling of fatigue life for rubbers and rubber isolators

A method for modelling fatigue life of rubbers and rubber isolators is presented in this paper. Firstly, a fatigue experiment is carried out for a rubber dumbbell cylindrical specimen and a rubber isolator. Based on the finite element analysis, the damage parameters including the strain energy density, the maximum principal Green–Lagrange strain and the effective stress are calculated and discussed. Secondly, three fatigue life prediction models are established by using the three damage parameters and using the relation between the measured fatigue life of a dumbbell cylindrical specimen and the computed value of the damage parameters. Thirdly, three proposed prediction models are used to investigate which one can be best used to predicting fatigue life of rubber isolators, taking a typical powertrain rubber isolator as studying example. The fatigue lives of the rubber isolator predicted by the three models are compared with the experimental life. The results demonstrate that the predicted fatigue lives of the rubber isolator using the three fatigue models agree well with the experimental fatigue life within a factor of four, and the model using the effective stress as the damage parameter can predict the fatigue life within a factor of two, which has the best accuracy among the three models.     

Analysis of the crack growth propagation process under mixed-mode loading

In the present paper, a computational model for crack growth analysis under Mode I/II conditions is formulated. The focus is on two issues – crack path simulation and fatigue life estimation. The finite element method is used together with the maximum principal stress criterion and the crack growth rate equation based on the equivalent stress intensity factor. To determine the mixed-mode stress intensity factors, quarter-point (Q-P) singular finite elements are employed. For verification purposes, a plate with crack emanating from the edge of a hole is examined. The crack path of the plate made of 2024 T3 Al Alloy is investigated experimentally and simulated by using the finite element method with the maximum tangential stress criterion. Then, the validation of the procedure is illustrated by applying the numerical evaluation of the curvilinear crack propagation in the polymethyl methacrylate (PMMA) beam and the Arcan specimen made of Al Alloy for which experimental results are available in the literature. In order to estimate fatigue life up to failure of the plate with crack emanating from the edge of a hole, the polynomial expression is evaluated for the equivalent stress intensity factor using values of stress intensity factors obtained from the finite element analysis. Additionally, the fatigue life up to failure of the Arcan specimen is analyzed for different loading angles and compared with experimental data. Excellent correlations between the computed and experimental results are obtained.     

Multiaxial creep–fatigue life prediction for cruciform specimen

This paper describes the high temperature multiaxial creep–fatigue life prediction for type 304 stainless steel. Finite element analyses were performed for determining the stress–strain state in the gage part of a cruciform specimen subjected to creep–fatigue loading under four strain waves at three principal strain ratios. Creep–fatigue lives of cruciform specimens were discussed in relation to the principal stress amplitude calculated by finite element analysis. Creep–fatigue damage was evaluated by linear damage rule and the suitability of three low cycle fatigue and three creep damage parameters was discussed.     

Effects of mean stress and stress concentration on fatigue behavior of short fiber reinforced polymer composites

An experimental study was conducted to evaluate the effect of mean stress on fatigue behavior of two short glass fiber reinforced thermoplastic composites and the effect of stress concentration on fatigue behavior of an unreinforced and a short glass fiber reinforced thermoplastic. Load‐controlled fatigue tests were conducted on unnotched (smooth) specimens at R ratios of ?1, 0.1, and 0.3 in different mold flow directions or fiber orientations and at a range of temperatures between ?40 and 125 °C. Effect of mean stress on fatigue life was found to be significant at all temperatures. Several mean stress parameters including modified Goodman, Walker, and Smith–Watson–Topper were evaluated for their ability to correlate mean stress data. A general fatigue life prediction model was also used to account for the effect of mean stress, temperature, and fiber orientation. Notched fatigue tests of an unreinforced polymer and a short glass fiber thermoplastic composite were also conducted using plate type specimens with a central circular hole and with or without the presence of mean stress. Effect of stress concentration was found to be considerable, with or without mean stress and in both the longitudinal and transverse directions. The commonly used Neuber's rule for metallic materials, nonlinear finite element analysis, as well as critical distance approaches were utilized for notch deformation and fatigue life analyses.     

CORROSION FATIGUE FRACTURE BEHAVIOUR OF A SiC WHISKERALUMINIUM MATRIX COMPOSITE UNDER COMBINED TENSIONTORSION LOADING

We describe an investigation into the fatigue fracture behaviour under combined tension–torsion loading of a SiC whisker-reinforced A6061 aluminium alloy fabricated by a squeeze casting process. Special attention was paid to the environmental effects on fatigue fracture behaviour. Tests were conducted on both the composite and its unreinforced matrix material, A6061-T6, under load-controlled conditions with a constant value of the combined stress ratio, α = τ_max /σ_max in laboratory air or in a 3.5% NaCl solution at the free corrosion potential. The corrosion fatigue strength of both the matrix and composite was less in the solution than in air. The dominating mechanical factor that determined the fatigue strength in air was either the maximum principal stress or the von Mises-type equivalent stress, depending on the combined stress ratio. However, in the 3.5% NaCl solution, the corrosion fatigue strength of both materials was determined by the maximum principal stress, irrespective of the combined stress ratio. In the case of the matrix material, crack initiation occurred by a brittle facet normal to the principal stress due to hydrogen embrittlement. However, in the composite material, the crack was initiated not at the brittle facet, but at a corrosion pit formed on the specimen surface. At the bottom of the pit, a crack normal to the principal stress was nucleated and propagated, resulting in final failure. Pitting corrosion was nucleated at an early stage of fatigue life, i.e. about 1% of total fatigue life. However, crack initiation at the bottom of a pit was close to the terminal stage, i.e. about 70% or more of total fatigue life. The dominating factor which determined crack initiation at a pit was the Mode I stress intensity factor obtained by assuming the pit to be a sharp crack. Initiation and propagation due to pitting corrosion and crack growth were closely examined, and the fatigue fracture mechanisms and influence of the 3.5% NaCl solution on fatigue strength of the composite and matrix under combined tension–torsion loading were examined in detail.     

基于应力强度因子评估WCP形状对WCP/Fe复合材料热疲劳裂纹扩展行为的影响

应力强度因子在断裂力学中广泛应用于预测由远程载荷或残余应力引起的裂缝尖端附近应力状态。本文基于平面应力条件下应力强度因子建立WC_P形状与其尖端应力之间的规律,利用有限元分析软件对含不同形状WC_P的WC_P/Fe复合材料的热应力进行模拟仿真,研究WC_P形状对WC_P/Fe复合材料热疲劳裂纹扩展行为的影响。研究结果表明,WC_P的形状显著影响应力强度因子,进一步影响WC_P/Fe复合材料的热疲劳裂纹扩展行为。含球状和不规则状WC_P的WC_P/Fe复合材料的极限抗压强度分别约为460 MPa和370 MPa。含不规则状WC_P的WC_P/Fe复合材料因应力集中而容易产生脆性开裂现象。通过热震实验进行验证,发现实验结果与模拟仿真结果相近,说明有限元法的准确性,同时为WC_P/Fe复合材料的热疲劳裂纹扩展行为研究提供科学依据和理论基础。      

Finite element analysis of defence hole systems for the reduction of stress concentration in a uniaxially-loaded plate with two coaxial holes

A comprehensive plane stress finite element study is made of the effect of three different types of defence hole systems (A, B and C) upon the stress concentration in a uniaxially-loaded plate with two coaxial holes. Throughout this project, the geometry definition, model creation aspects for meshing the plate and generating elements and nodes, model preparation for applying the appropriate loads and restraints, model checking for coincidence nodes and element distortion, and output display of the many cases investigated were all carried out interactively using SDRC (SUPERTAB-IDEAS) pre- and post-processors. The finite element analysis was carried out in the analysis section of the package, known as SUPERB. The study reveals that the introduction of defence holes on either side of the main holes helps to smooth the flow of the tensile principal stress trajectories past the original holes, and thus effect a reduction in stress concentration factor (SCF), an improvement in component strength and a reduction in its weight. Reductions in maximum SCF ranging from 7.5% to 11% have been achieved by the present technique. With such reductions in maximum stress levels, the improvement in fatigue life of a component can be significant.