双向载荷条件下Ⅰ型裂纹的疲劳扩展

研究了双轴向应力状态下Ⅰ型穿透裂纹的疲劳扩展规律，采用构形合理且经精确标定应力强度因子值的双向十字形试样，在电液伺服双轴向疲劳试验机上对低合金钢（１６ＭｎＲ）进行了多种载荷比的疲劳裂纹扩展速率试验，得到了双轴向应力状态下的Ｐａｒｉｓ方程，为目前按缺陷评定规范依据单轴向疲劳试验所得数据对工程构件进行疲劳评定提供参考数据，并就当前研究者们对于双向应力场中横向载荷对疲劳裂纹扩展行为的影响的不同看法进行分析探讨。     

拉弯复合应力下焊接头表面裂纹疲劳扩展规律的研究

通过对16MnR钢对焊的弓形试极疲劳裂纹扩展试验，研究了在拉弯复合应力下对焊接头表面裂纹疲劳扩展规律。采用Newman－Raju公式分析了有限宽板在拉弯复合应力下表面裂纹的应力强度因子的计算。试验研究表明在拉弯复合应力下当a／t≤0．8时表面裂纹疲劳扩展规律仍可用Paris公式来描述，并且c向和a向的Paris系数之间仍存在着C_c＝0．9~nC_a的关系。     

模拟压力容器接管的新型十字试板的角裂纹疲劳扩展性能

用新型十字试板进行了双轴载荷下的角裂纹疲劳扩展性能的研究,以模拟压力容器接管处角裂纹的疲劳扩展行为。试板角裂纹尖端的应力强度因子采用三维边界元法计算,裂纹疲劳扩展的形貌变化采用降载勾线法记录。试验结果表明,裂纹疲劳扩展规律与双向载荷比及裂纹初始形状有关,裂纹沿长度方向的扩展速率可以用 Paris 公式表示,但在深度方向则不然。     

铸钢焊接接头裂纹扩展行为研究

简要介绍了某深水气田开发项目中出现的高强度铸钢类型，针对该材料的焊接，选用气体保护药芯焊丝开发焊接工艺。测定了焊接接头区域疲劳裂纹扩展速率及疲劳裂纹扩展门槛值，结果表明：整体焊接接头疲劳裂纹扩展性能较好，耐裂纹性能按高低顺序为焊缝>热影响区>铸钢母材。     

表面裂纹疲劳扩展形貌变化规律的研究

首先进行了１６Ｍｎ板材半椭圆表面裂纹疲劳扩展试验。试验结果表明，采用Ｎｅｗｍａｎ－ｒａｊｕ应力强度因子时，表面裂纹深度方向和表面方向的扩展速率均符合Ｐａｒｉｓ公式。在此基础上，从Ｎｅｗｍａｎ－Ｒａｊｕ应力强度因子计算式和Ｐａｒｉｓ疲劳裂纹扩展速率公式出发，通过理论和数值分析，建立了３类表面裂纹在受拉伸、弯曲、和拉弯组合加载下的疲劳扩展形貌统一表达式，并通过疲劳试验结果对其进行了考核。结果表明，采用统一表达式预测裂纹形貌的各项统计指标均优于其他两种表达式     

07MnCrMoVR钢焊件疲劳裂纹扩展速率

为鉴定０７ＭｎＣｒＭｏＶＲ钢焊件的疲劳性能，通过试验得到了焊接接头以及焊接热影响区的疲劳裂纹扩展速率，同时给出了它们存活率为９７．７３％时的各自疲劳裂纹扩展速率，并对焊接接头与焊接热影响区疲劳裂纹扩展速率进行比较。最后还把结果与“在役含缺陷压力容器安全评定规程”［１］和ＢＳＩＰＤ６４９３［２］推荐结果进行了对比，认为该钢种疲劳裂纹扩展速率在其容许范围内慢于１６ＭｎＲ钢的疲劳裂纹扩展速率     

最大荷载对硬质聚氯乙烯疲劳裂纹扩展的影响

为研究相同应力比下最大疲劳荷载对硬质聚氯乙烯（UPVC）疲劳裂纹扩展的影响，开展了单边缺口三点弯曲SE(B)试件Ⅰ型疲劳裂纹扩展试验，基于Paris公式绘制了疲劳裂纹扩展速率曲线，对试件断口微观形貌进行对比分析。结果表明：在不同荷载条件下，随着最大荷载降低，UPVC疲劳寿命增加；UPVC疲劳断裂过程符合次级断裂模式，最大荷载越大，断口微孔洞、纤维拉丝越明显。     

有机玻璃YB-DM-11的疲劳裂纹扩展特性研究

研究了试样类型、应力比对有机玻璃YB-DM-11疲劳裂纹扩展速率、疲劳裂纹扩展平均寿命的影响。结果表明：试样类型对有机玻璃疲劳裂纹扩展速率影响很小,但紧凑拉伸试样的寿命大于中心裂纹拉伸试样;对于中心裂纹拉伸试样,当应力比为正时,应力比增大,疲劳裂纹扩展速率增加,疲劳裂纹扩展平均寿命减小;应力比为负时,裂纹闭合效应导致裂纹扩展加速;负应力比时的裂纹扩展速率大于正应力比,但疲劳裂纹扩展平均寿命明显小于正应力比。     

共聚聚丙烯疲劳裂纹扩展研究

参照金属材料疲劳裂纹扩展速率试验方法,采用材料疲劳试验机对无规共聚聚丙烯(PP–R)材料进行了Ⅰ型疲劳裂纹的扩展速度及裂纹扩展机理的研究,测试得到了疲劳裂纹扩展每0.5 mm长度下所对应的循环次数,进而拟合出da/d N(疲劳裂纹扩展长度与循环次数之比)与ΔK(应力强度因子)的疲劳裂纹扩展速率曲线图,发现PP–R疲劳裂纹扩展可分为裂纹扩展源阶段,裂纹扩展稳定阶段和裂纹快速扩展阶段3个阶段,其中扩展源阶段出现明显的增韧现象,稳定扩展阶段呈现出明显的线性特点;同时选取了4个典型的断面区域进行了扫描电子显微镜拍照,得到了4种差异很大的断面显微组织并进行了分析。     

电工陶瓷材料裂纹扩展规律的研究

本文应用双扭法研究了四种电瓷材料静态疲劳裂纹扩展规律。试验结果表明:在空气介质中,所有试验电瓷材料均存在明显的裂纹亚临界扩展现象,且随裂纹尖端应力强度因子(K_1)增大呈现三个阶段关系。在不同介质中,裂纹扩展的敏感性按下列顺序变小:水、空气和煤油。试验还表明电瓷材料静态疲劳裂纹扩展规律与材料的配方、环境和受力等因素有关。     

2.25Cr-1Mo复杂应力状态下低周疲劳寿命预测

通过对无预裂纹圆柱形缺口试件的常温、高温低周疲劳总寿命试验以及对带有预裂纹圆柱形缺口试件的常温、高温裂纹扩展寿命试验,并利用ＮＨＲＤＳ有限元程序进行了缺口附近轴对称问题的循环应力和应变计算,研究了非均匀分布复杂应力状态下低周疲劳寿命。结果表明,２ ．２５Ｃｒ １Ｍｏ 材料复杂应力状态下低周疲劳总寿命和裂纹扩展寿命可采用当量形式的Ｍａｎｓｏｎ Ｃｏｆｆｉｎ 公式进行表征。     

Failure behavior of adhesively bonded joints with a rubber modified epoxy adhesive under tensile-shear combined cyclic loading

Rubber-modified epoxy adhesives are used widely as structural adhesive owing to their properties of high fracture toughness. In many cases, these adhesively bonded joints are exposed to cyclic loading. Generally, the rubber modification decreases the static and fatigue strength of bulk adhesive without flaw. Hence, it is necessary to investigate the effect of rubber-modification on the fatigue strength of adhesively bonded joints, where industrial adhesively bonded joints usually have combined stress condition of normal and shear stresses in the adhesive layer. Therefore, it is necessary to investigate the effect of rubber-modification on the fatigue strength under combined cyclic stress conditions. Adhesively bonded butt and scarf joints provide considerably uniform normal and shear stresses in the adhesive layer except in the vicinity of the free end, where normal to shear stress ratio of these joints can cover the stress combination ratio in the adhesive layers of most adhesively bonded joints in industrial applications.

In this study, to investigate the effect of rubber modification on fatigue strength with various combined stress conditions in the adhesive layers, fatigue tests were conducted for adhesively bonded butt and scarf joints bonded with rubber modified and unmodified epoxy adhesives, wherein damage evolution in the adhesive layer was evaluated by monitoring strain the adhesive layer and the stress triaxiality parameter was used for evaluating combined stress conditions in the adhesive layer. The main experimental results are as follows: S–N characteristics of these joints showed that the maximum principal stress at the endurance limit indicated nearly constant values independent of combined stress conditions, furthermore the maximum principal stress at the endurance limit for the unmodified adhesive were nearly equal to that for the rubber modified adhesive. From the damage evolution behavior, it was observed that the initiation of the damage evolution shifted to early stage of the fatigue life with decreasing stress triaxiality in the adhesive layer, and the rubber modification accelerated the damage evolution under low stress triaxiality conditions in the adhesive layer.     

Fatigue Failure Criterion of Adhesively-Bonded Joints Under Combined Stress Conditions

A study was conducted to investigate fatigue failure criteria for adhesively-bonded joints under combined stress conditions. Two types of adhesively-bonded joint specimens were used: the scarf joint and the butterfly-type butt joint. Both types of joints have considerably uniform combined stress distributions in the adhesive layer. Furthermore, the stress distributions of these joints were analyzed by a finite element method. The results showed that the maximum principal, the von Mises equivalent and the maximum shear stresses in the uniform stress region of the adhesive layer at the endurance limit are correlated with the principal stress ratio.     

Mixed-Mode Fracture in Soda-Lime Glass Using Indentation Flaws

Mixed-mode failure of soda-lime glass under inert and fatigue test conditions was studied using Knoop indentation flaws. For annealed cracks (residual stress-free) crack extension (catastrophic or subcritical) is by an abrupt transition from the initial crack plane to a noncoplanar crack plane followed by a reorientation of the crack normal to the applied stress. Although fatigue strength of these inclined flaws increased linearly with respect to orientation of the flaws to the applied stress up to an angle of 60°, this increase was considerably less than what was predicted by existing theories. It is believed that subcritical crack growth causes the crack to be realigned perpendicular to the applied stress before failure for all orientations; hence, fatigue strength does not show the dramatic increase at orientation angles as predicted by theory. For as-indented cracks the contact residual stress causes the crack extension to be less inclined to the initial crack plane than for annealed cracks, but in this case also, the crack realigns itself perpendicular to the applied stress. Again, fatigue strength is relatively insensitive to the orientation angle as predicted by theory and subcritical crack growth is believed to play a primary role in determining this strength dependency.     

Improvement of impact fatigue strength of adhesive joint by CTBN modification

Impact fatigue behaviors of the steel/CTBN-modified adhesive/steel butt joint were investigated. The adhesive butt joint specimens used in the present work were bonded with epoxy–polyamide and CTBN-modified epoxy–polyamide adhesives. Fatigue tests were also conducted under nonimpact stress conditions to compare with the results from the impact fatigue test. The experiments showed that for the joint specimen from the adhesive modified with the CTBN the fatigue strength becomes higher under both of the stress conditions. In particular, the fatigue strength was improved remarkably under impact stress condition, that is, the distinct stress cycles dependence of impact strength was decreased by modifying the adhesive with CTBN. Furthermore, the effect of adhesive thickness on the fatigue strength was also discussed for the adhesive joint modified with CTBN. Under impact stress conditions, the relation between the fatigue strength and the adhesive layer thickness is different from that under the nonimpact one.     

An investigation of fatigue failure prediction of adhesively bonded metal/metal joints

A fracture mechanics-based model for fatigue failure prediction of adhesive joints has been applied in this work. The model is based on the integration of the kinetic law of evolution of defects originated at stress concentrations within the joint. Final failure can be either brittle (fracture toughness-driven) or ductile (tensile/shear strength-driven) depending on the adhesive. The model has been validated against experiments conducted on single-lap shear joints bonded with a structural adhesive. Three different kinds of adhesives, namely a modified methacrylate, a one-part epoxy and a two-part epoxy supplied by Henkel, have been considered and three different overlap lengths have been tested. Fracture toughness and fatigue crack growth properties of the adhesives have been determined with mode I tests. The number of cycles to failure has been successfully predicted in several cases. It is interesting to notice that in the case of joints loaded at the same average shear stress, the shorter the joint, the longer the duration. This fact is also captured by the model.     

Crack initiation and propagation paths for brittle failures in aligned and misaligned pipe butt fusion joints

Medium density polyethylene pipes of 63, 90, and 125mm outside diameter, together with 63mm high density polyethylene pipes, were butt fusion joined to give aligned and controlled misaligned joints. These fabricated systems were tested at elevated temperatures under constant and fluctuating internal pressure loading. For brittle failures at the butt fusion joint, a thorough examination has been made of the points of crack initiation and the crack propagation path in relation to weld microstructure, It has been observed that the butt fusion process induces the presence of a long sharp notch formed when the internal weld bead rolls towards the pipe. This notch initiates circumferential joint failures, particularly in misaligned butt joints. Points of disturbance on the inner weld bead appear capable of inducing axial cracks at the butt fusion joint but only for aligned joints. The microstructure at the butt fusion joint was seen to have little influence on the crack propagation path.     

Comparison of fracture behavior between acrylic and epoxy adhesives

An experimental study was conducted on the strength of adhesively bonded steel joints, prepared epoxy and acrylic adhesives. At first, to obtain strength characteristics of these adhesives under uniform stress distributions in the adhesive layer, tensile tests for butt, scarf and torsional test for butt joints with thin-wall tube were conducted. Based on the above strength data, the fracture envelope in the normal stress-shear stress plane for the acrylic adhesive was compared with that for the epoxy adhesive. Furthermore, for the epoxy and acrylic adhesives, the effect of stress triaxiality parameter on the failure stress was also investigated. From those comparison, it was found that the effect of stress tri-axiality in the adhesive layer on the joint strength with the epoxy adhesive differed from that with the acrylic adhesive. Fracture toughness tests were then conducted under mode l loading using double cantilever beam (DCB) specimens with the epoxy and acrylic adhesives. The results of the fracture toughness tests revealed continuous crack propagation for the acrylic adhesive, whereas stick-slip type propagation for the epoxy one. Finally, lap shear tests were conducted using lap joints bonded by the epoxy and acrylic adhesives with several lap lengths. The results of the lap shear tests indicated that the shear strength with the epoxy adhesive rapidly decreases with increasing lap length, whereas the shear strength with the acrylic adhesive decreases gently with increasing the lap length.     

Fatigue and static performances of butterfly joints under hygrothermal exposure conditions

In this study, the static and dynamic behaviors under different environmental conditions of mechanical insert butt joints with butterfly joint locks that could be used instead of adhesively bonded butt joints in composite plate joints were investigated. The experimental specimens and butterfly‐shaped joining components with the same material configuration were cut from a [(0/90)₈]_s laminated composite plate with a water jet in harmony with the geometric parameters. The fatigue experiments were carried out at a constant load ratio of 0.1 and at different maximum fatigue loads. To compare the joints with each other, the experiments were conducted under a 10‐Hz fatigue frequency and under a tension–tension load with constant amplitude of a sinus curve shape. © 2012 Wiley Periodicals, Inc. J. Appl. Polym. Sci., 2013