残余应力集中及其对疲劳极限和短裂纹扩展的影响

缺口根部的残余应力存在应力集中效应,应力集中值不仅取决于缺口几何形状而且和材料的屈服强度有关。残余应力集中系数是一个分布值,其数值甚至可超过理论应力集中系数。软试样喷丸后缺口处的残余应力易于松弛及喷丸时的表面损伤使其对疲劳极限的贡献小。残余压应力使缺口处裂纹闭合力增大甚至可出现非扩展裂纹。     

基于计算机有限元分析的激光冲击强化钛合金疲劳性能研究

基于限元分析软件ABAQUS和MSC.Fatigue,建立了激光冲击TC17钛合金标准紧凑拉伸试样及其疲劳裂纹扩展的有限元分析模型。对不同区域下激光冲击强化TC17钛合金后的残余应力分布及疲劳裂纹扩展性能进行分析,进而探讨了残余应力场对疲劳裂纹扩展的影响。结果表明,激光冲击TC17钛合金经后,试样上下表面处理区域均呈现压应力分布,最大残余压应力达-473 MPa,残余压应力层深度达0.76 mm,同时,表面残余压应力随激光功率密度和冲击区域的增大,逐渐增大并达到饱和。相对于未冲击件,激光冲击使TC17试样疲劳寿命大幅延长,疲劳裂纹扩展速率显著降低;且随冲击区域的增大,疲劳寿命不断延长,表明激光冲击诱导的残余应力场对TC17钛合金疲劳裂纹扩展具有较好的抑制作用。     

7A09超高强铝合金表面强化实验研究

利用气动式喷丸机对7A09超高强铝合金试样进行喷丸强化,对喷丸强化前后试样小孔两侧残余应力分布进行测试,探讨了喷丸时间对7A09铝合金疲劳寿命的影响,分析机械喷丸强化前后铝合金试样疲劳断口。结果表明,机械喷丸强化后,7A09超高强铝合金表层分布高幅值残余压应力,表层残余压应力分布显著地降低了疲劳裂纹扩展速率,疲劳寿命明显提高;通过扫描疲劳断口,发现未处理试样的疲劳裂纹源位于孔壁上表面的尖角处,而机械喷丸强化试样的裂纹源逐渐转移到强化层以内,在最终断裂区内分布大量韧窝,且韧窝形态随喷丸时间的延长而增大,并且韧窝尺寸更深,说明机械喷丸改善了最终断裂区的塑性。     

淬火残余应力对铝合金厚板裂纹应力强度因子及扩展趋势的影响

为探究淬火残余应力对铝合金厚板疲劳裂纹扩展的影响规律,建立7075铝合金厚板表面三维裂纹数值仿真模型。采用顺序热力耦合法求解淬火残余应力场,将残余应力场作为初始载荷条件求解裂纹应力强度因子,并与无残余应力场的应力强度因子值进行对比,研究两种条件下应力强度因子的分布规律和两者之间的异同;通过分析在初始淬火残余应力条件下不同半径裂纹受不同均匀拉应力荷载作用时的裂纹应力强度因子随裂纹位置角的演变曲线,探究淬火残余应力对裂纹扩展趋势的影响规律。结果表明,淬火残余应力的存在改变了铝合金厚板应力强度因子的分布规律和裂纹的扩展趋势,淬火残余应力使表层附近的裂纹扩展受到遏止,裂纹易于在厚度方向优先扩展。     

残余压应力对缺口疲劳性能的影响

本文研究了喷丸和滚压后缺口报部的残余压应力分布及其对疲劳极限和裂纹扩展速率的影响。残余应力在缺口部位有应力集中效应，其数值不仅取决于缺口的几何形状还和材料强度有关。表面形变后高强度材料的残余应力集中系数大又不易在交变载荷下松弛，因此提高缺口疲劳极限比光滑件更显著，在预测疲劳裂纹扩展时可将残余压应力作为附加闭合力迭加在裂纹自身的闭合力上用这种方法计算得的裂纹扩展速率和实验值很接近。     

A356铸造铝合金的疲劳裂纹萌生及短裂纹扩展研究

研究了A356-T6铸造铝合金的缺口疲劳裂纹萌生与早期扩展行为及机制.结果表明,热等静压试样的疲劳抗力优于非热等静压试样.对于钝缺口试样,疲劳裂纹萌生于缺口根部附近的多个平面,最终哪个裂纹源扩展成主裂纹取决于局部微观组织.对于缺口几何形状不同的热等静压和非热等静压疲劳试样,在疲劳过程中,不管是在高应力状态下,还是在低应力状态下,都出现了铝基体的循环塑性变形和共晶硅粒子断裂导致疲劳裂纹萌生.对于非热等静压试样,铸造缩孔在构件的疲劳过程中起着重要作用,但即使缺口根部存在较大尺度的铸造缩孔,导致了疲劳裂纹萌生,但也同时观察到疲劳裂纹从共晶硅粒子、金属间化合物、铝基体的滑移带和铁基金属间化合物等处萌生.对于脆性的A356铸造铝合金可采用修正的断裂力学参量ΔKn、局部应力范围Δσ或局部应变幅Δε/2作为控制参量来表征疲劳裂纹萌生行为,而缺口有效应力强度因子范围ΔKneff和ΔJs参量可用来表征缺口场中短裂纹扩展行为.     

焊接残余应力对7N01铝合金疲劳裂纹扩展影响

焊接残余应力作为平均应力影响裂纹扩展. 将残余应力与外载平均应力分离,通过构建典型焊接残余应力场,借助扩展有限元计算焊接残余应力场的应力强度因子. 开展了紧凑拉伸（CT）试样的疲劳扩展试验,基于Walker公式将裂纹尖端平均应力强度因子K_m（静态量）和应力强度因子幅值ΔK（动态量）分离,获得疲劳裂纹扩展速率da/dN与K_m及ΔK的非线性关系. 结果表明,不同外载荷下,应力比与裂纹长度为非线性关系;残余应力对裂纹扩展存在尺度效应:CT试样裂纹长度小于2 mm时,残余应力场明显影响疲劳裂纹扩展速率;当裂纹长度大于2 mm,外载荷为主导因素.     

残余应力对U75V重轨钢疲劳裂纹扩展速率的影响

通过残余应力测试仪Stress3000测试了不同工艺处理U75V重轨钢表面残余应力,利用Sinco Tec疲劳试验机研究了残余应力对疲劳裂纹扩展速率的影响,并对疲劳断口形貌进行了观察。结果表明:不同工艺处理U75V重轨钢表面残余应力均为压应力,淬火态试样表面平均残余应力大于轧态试样;随退火温度升高和退火时间延长,试样表面残余应力下降明显。随表面残余压应力的增大,疲劳裂纹常数m值逐渐减小,即裂纹扩展速率随着表面残余压应力的增加而减小。断口形貌观察发现表面残余压应力较大时,断口疲劳辉纹更为细小,有利于降低表面疲劳裂纹扩展速率。     

残余应力与外加载荷共同作用对裂尖前端应力场的影响

用机械预压缩法在裂纹前端引入残余应力,模拟了残余应力与外加载荷共同作用下CT试样裂尖前端的应力场,对比分析了外加载荷、刚体压缩位置和缺口半径对裂尖前端残余应力重新分布的影响。结果表明,随着外加载荷的增大,残余应力拉压应力峰值均有远离缺口前端的趋势,外加载荷和刚体压缩位置的改变对裂纹尖端周向张开应力几乎没有影响。小的缺口半径会产生更大的张开应力,更容易导致裂纹的起裂和扩展。     

考虑淬火残余应力铝合金厚板中椭圆裂纹Ⅰ型强度因子计算

基于实验及Shiratori的有限元数据,拟合出铝合金板淬火残余应力的分布函数,用Shen-Glinka法确定椭圆裂纹的Ⅰ型应力强度因子的权函数,推导出权函数系数的表达式。在此基础上分析几种裂纹表面经典应力分布时的Ⅰ型应力强度因子,与Shiratori的有限元结果吻合良好,验证所建立的权函数具有较高的精度。结合淬火残余应力分布函数,推导出椭圆裂纹在淬火残余应力场中的Ⅰ型应力强度因子,得出不同点残余应力强度因子随裂纹扩展的变化趋势不同。     

RESIDUAL STRESS CONCENTRATION AND ITS EFFECTS ON FATIGUE LIMIT AND SHORT CRACK GROWTH

Residual stress concentration at a notch depends on both notch geometry and yield strength ofthe material.It varies through the depth,and its magnitude may be higher than the theoreticalone.Compressive residual.stress concentration at the notch of shot-peened specimen of softmaterial is easily to he relaxed,with the surface damage during shot-peening results in a mi-nor contribution to the fatigue limit.Compressive residual stress increases the crack closureeffect at the notch and may lead to a non-propagating crack.     

In situ observation on fatigue crack growth in SCS-6/Ti-15-3 composite at elevated temperatures

Direct observation on fatigue crack growth behavior in SiC (SCS-6) fiber-reinforced Ti-15-3 alloy matrix composite subjected to a constant tension–tension loading mode was performed by scanning electron microscope using a single edge-notched specimen in vacuum at room temperature and 550 °C. The fatigue crack growth rate at 550 °C was lower than that at room temperature, and the difference between the fatigue crack growth rates at room temperature and 550 °C increased with increasing fatigue cycles. The crack opening displacement at 550 °C was smaller than that at room temperature when the crack length exceeded a definite value, though the interface friction stress between the fiber and matrix at elevated temperature was much smaller than that at room temperature. The above results were explained qualitatively by a residual stress mechanism at the crack front and the crack closure behavior at crack wake, which could be produced by matrix creep asymmetry in tension and compression at elevated temperature during each fatigue cycle.     

激光冲击强化对TC4 钛合金缺口叶片疲劳强度的影响

目的 提高航空发动机叶片抗外物损伤的性能。方法 采用薄壁件激光冲击强化工艺,对某型发动机TC4钛合金叶片包含一阶弯曲振动节线区域的表面进行处理,随后在叶片前缘一阶弯曲振动节线位置设计不同应力集中系数的缺口。参考有限元仿真软件分析结果和相关标准要求,预制应力集中系数Kt为3.2的缺口。通过力值校核和有限元仿真之间的多次迭代,明确应力测试位置与缺口危险点应力之间的关系。通过振动疲劳试验对激光冲击强化效果进行评价。通过扫描电子显微镜观察疲劳断口的形貌,采用残余应力仪对梯度残余应力进行测试,并提取相应位置的半峰全宽值,对激光冲击强化提升缺口叶片疲劳强度的原因进行分析。结果 经激光冲击强化处理后的钛合金缺口叶片在107次循环下的疲劳强度提升了63.2%;残余压应力层深度可达1.5 mm,且表层位错密度提升了67.5%;经激光冲击强化处理后钛合金缺口叶片裂纹萌生于近表面。结论 激光冲击强化引入的表层梯度残余压应力和位错增殖是缺口叶片疲劳强度提升的主要原因。     

Fatigue crack/residual stress field interactions and their implications for damage-tolerant design

Residual stress fields are now widely accepted to have significant influence on fatigue crack growth. Tensile stresses have detrimental effects on fatigue lives, whereas compressive residual stresses can be beneficial. Control of fatigue lives via residual stress is now established in many industrial applications, using techniques such as shot peening or cold expansion. However, knowledge of the processes that occur when a fatigue crack grows through a pre-existing stress field is far from complete. Although the residual stress field will clearly have an effect on crack growth, the crack will equally have an effect on the residual stress field. The determination of this effect is not trivial, and direct measurement may be the designer’s best safeguard. This article outlines the complementary effects that a growing fatigue crack and a residual stress field have on each other. Two types of residual stress field are considered: mechanically induced and thermally induced. The results are discussed in terms of the implications that residual stress interactions have for damage-tolerant-based design.     

激光冲击强化对2524铝合金疲劳寿命的影响

目的探索激光冲击工艺参数对2524铝合金疲劳寿命的影响。方法开展不同激光能量、不同冲击次数下的激光冲击强化实验,测试其残余应力和表面硬度,并进行裂纹扩展实验和显微组织观察。结果激光冲击强化能显著提高材料的表面硬度,且材料的硬度值随着冲击能量和冲击次数的增加而递增,但硬度增长率随冲击次数增多而降低。激光冲击强化在试样表层形成较大的残余压应力,使用6.25 J的激光能量冲击1次,最大残余压应力可达-222MPa,并且残余压应力随着激光能量和冲击次数增加而增加,但冲击强化次数存在阈值。相较于未冲击试样,激光冲击1次的试样的疲劳寿命提升32%,冲击2次的疲劳寿命提升41%。对试样断口进行微观形貌观察,在裂纹长度为28 mm处,未冲击试样、激光冲击1次和冲击2次试样的疲劳条带间距分别为1.06、0.628、0.488μm,裂纹扩展速率分别为1.06×10^-3、6.28×10^-4、4.88×10^-4 mm/N。结论激光冲击强化能显著提高2524铝合金的表面硬度,并在表面产生较大的残余压应力。激光冲击强化能够有效迟滞2524-T3铝合金的疲劳裂纹扩展速率,进而有效延长疲劳寿命。     

Specific Features of the Nucleation and Growth of Fatigue Cracks in Steel under Cyclic Dynamic Compression

The processes of the fracture of 40Kh and U8 steels under cyclic dynamic compression are studied. It has been found that the main cause for the fracture of the cyclically compressed specimens is the propagation of cracks due to the effect of residual tensile stresses, which arise near the tips of the cracks at the stage of the unloading of the specimens. The growth rate of a crack has the maximum value at the initial stage of its propagation in the vicinity of the stress concentrator. As the crack propagates deep into the specimen, its growth rate decreases and depends only slightly on the real cross section of the specimen. The model of the process of the fatigue fracture of the steels under dynamic loading by a cyclically varied compressive force is proposed. It has been found that the high fatigue endurance is provided by tempering at 200°C for the 40Kh steel and at 300°C for the U8 steel.     

Effect of laser shock processing on residual stress and fatigue behavior of 6061-T651 aluminum alloy

Laser shock processing is a very new technique and an emerging modem process that generates compressive stresses much deeper into the surfaces of metals or alloys. A brief parametric study of the effect of laser parameters on fatigue behavior and residual stress state generated in 6061-T651 alloy specimens was summarized. Residual stress of 6061-T651 alloy was analyzed both before and after laser processing with multishocks. The material remains in compressive residual stress of approximate 1 mm in depth which is approximately 10 times deeper than that can be achieved with the conventional technique, and the maximal compressive residual stress at the surface of the sample is about -350MPa. Near the surface, yield strength and hardness are found to be increased by the laser shock. The ratio of fatigue crack initiation life for the laser-shocked to unshocked specimens is found to be 4.9 for specimens. The results clearly show that LSP is an effective surface treatment technique for improving the fatigue performance of aluminum alloys.     

芯棒直接孔挤压强化7050铝合金疲劳性能研究

为了探究实心芯棒、开缝芯棒两种芯棒直接孔挤压强化方法对7050铝合金疲劳性能的影响,建立了芯棒直接孔挤压强化7050铝合金三维有限元仿真模型,开展了芯棒直接孔挤压强化试验,对比分析了未挤压强化、芯棒直接孔挤压强化试样的孔壁应力、疲劳性能。研究结果表明：芯棒直接孔挤压强化试样铰削加工前后,孔壁最大残余压应力差值小于20 MPa；芯棒直接孔挤压强化后试样孔壁形成的残余压应力能够抵消部分受载过程中产生的拉应力；实心芯棒孔挤压强化试样的中值疲劳寿命是未挤压强化试样的1.46倍,开缝芯棒孔挤压强化试样的中值疲劳寿命是未挤压强化试样的1.52倍；芯棒直接孔挤压强化减小了疲劳源数量,缩小了疲劳裂纹扩展区的疲劳辉纹间距,提高了试样的疲劳寿命。