腐蚀环境对预腐蚀TC4-DT钛合金疲劳性能的影响

基于飞机结构材料TC4-DT钛合金在服役过程中因工作的特殊环境而导致腐蚀疲劳断裂的问题,研究了TC4-DT钛合金在3.5%NaCl溶液、油箱积水和试验室空气环境下的腐蚀疲劳寿命。通过扫描电镜(SEM)观察了断口形貌;探讨了腐蚀环境对疲劳裂纹萌生扩展的影响机理。结果表明:TC4-DT钛合金有一定的耐腐蚀性,其疲劳寿命受环境影响从大到小的顺序依次是:油箱积水、3.5%NaCl溶液、试验室空气。腐蚀损伤和疲劳损伤存在竞争关系,在高应力水平下,试件疲劳寿命主要受交变载荷影响;在低应力水平下,试件疲劳寿命主要受腐蚀环境影响。当Kt=1时,油箱积水对试件疲劳寿命的影响最大,其次是3.5%NaCl溶液和试验室空气环境,且应力水平降低影响增大;当Kt=3时,由于缺口效应,盐水和油箱积水环境下试样的疲劳寿命相近,均略低于试验室空气环境下的。     

环境对双相钢疲劳性能的影响

本文研究了自来水和3.5％NaCl水溶液分别在全浸和干湿交替状态下对热轧双相钢疲劳性能的影响.结果表明:与空气中的疲劳寿命相比,腐蚀环境有不同程度的降低作用,并以喷雾盐水影响最大.在相同腐蚀条件下,环境的影响随应力幅的降低而增强.马氏体抗疲劳断裂的能力高于铁素体.试样表面和断口的观察结果发现,腐蚀疲劳裂纹萌生与腐蚀坑密切相关,蚀坑以阳极溶解方式形成.     

缺口对TC21合金高周和低周疲劳的影响

研究了缺口对TC21合金在不同温度高周和低周疲劳强度的影响。疲劳试样为光滑和V型缺口（Kt=3）2种试样，疲劳载荷为应力控制，循环应力比为0．1，高周疲劳实验温度为315℃，低周疲劳实验温度为室温及400℃。结果表明，在循环应力较低，缺口根部未塑性变形时，缺口使疲劳强度明显降低。循环应力升高使缺口根部产生塑性变形时，缺口对疲劳强度影响降低，当循环应力升高使光滑试样失稳时，缺口试样的疲劳强度高于光滑试样的疲劳强度。断口的SEM分析表明，缺口试样的疲劳裂纹在缺口根部萌生，即使高周疲劳裂纹源也是多个。     

航空AZ31镁合金腐蚀疲劳性能研究

研究了AZ31镁合金在3.5 wt%Na Cl水溶液中的腐蚀疲劳寿命及腐蚀疲劳断口。结果表明:相比空气中的疲劳极限,AZ31镁合金试样在3.5 wt%Na Cl水溶液中的腐蚀疲劳极限下降了34.1%。AZ31镁合金的腐蚀疲劳裂纹萌生于多源腐蚀坑。在Paris公式的基础上,结合试验结果,提出了修正后的腐蚀疲劳模型,其适用于中高应力幅下的疲劳寿命计算。     

高速列车用Al7SiMg合金的应力腐蚀性能研究

对高速列车铸件用的Al7SiMg铝合金试样,分别在空气和NaCl水溶液环境中进行慢应变速率拉伸性能测试,比较其测试数据结果及断口形貌,研究Al7SiMg合金的应力腐蚀性能。研究结果表明:在质量分数为3.5%的NaCl水溶液环境中的拉伸性能略低于空气中的,在空气环境中测得的抗拉强度与NaCl水溶液环境中测得的抗拉强度之比值为0.96,而相应的两种环境中测得的伸长率之比例为0.85,计算得到的I_(SSRT)指数为0.049。观察试样断口形貌可以看出,Al7SiMg合金试样在质量分数为3.5%的NaCl水溶液环境中与空气中拉伸均表现出韧性断裂为主、存有少量沿晶开裂的特征,Al7SiMg合金的应力腐蚀并不敏感。     

7×××航空铝合金盐水环境疲劳性能研究

通过不同取样方向(L向与L-T向)的7×××铝合金光滑试样(Kt=1)与缺口试样(Kt=3)在盐水环境中进行疲劳试验,得到了不同取向方向及应力集中系数的中值疲劳寿命对比曲线,研究了不同取样方向及应力集中系数对7×××铝合金盐水环境疲劳性能的影响。结果表明:取样方向与应力集中系数对盐水环境下预腐蚀试样的疲劳寿命有显著影响,同取样方向时,光滑试样的疲劳性能总体强于缺口试样的,L向光滑试样比缺口试样的疲劳极限高81.9%,L-T向光滑试样比缺口试样的疲劳极限高55.8%;同应力集中系数时,L向试样疲劳性能总体强于L-T向的,L向的光滑试样比L-T向的疲劳极限高28.1%,L向的缺口试样比L-T向的疲劳极限高9.7%。     

轧制变形TC1和TC2钛合金的高周疲劳性能

通过进行应力控制的疲劳试验,研究了TC1和TC2钛合金热轧板材在不同试验温度下的高周疲劳性能,并对两类钛合金板材的疲劳性能进行了比较.结果表明,在相同的最大循环应力下,TC1和TC2钛合金板材的高周疲劳寿命均随着温度的升高而降低,且当温度相同时,TC2钛合金板材的疲劳寿命均高于相同轧制方向的TCl钛合金板材.此外,实验温度越高,TC1和TC2钛合金板材的疲劳极限越低,且在不同温度下,TC2钛合金板材的疲劳极限均明显高于相同轧制方向的TC1钛合金板材.     

几种钛合金的抗腐蚀疲劳性能

本文研究了TC4、Ti451棒坯和TA5、TC4、BT14板坯试样的腐蚀疲劳性能。在大气、自来水和3.5%NaCl盐水中,应力比R=-1、频率50Hz,于室温条件下进行了疲劳试验。分别测定了条件疲劳极限。并给出了S-N曲线。结果表明,钛合金具有良好的抗盐水腐蚀疲劳特性,这一特性与合金材质、冷却条件和交变强化有密切关系。     

表面加工方法对TC4钛合金表面完整性及高周疲劳性能的影响

研究了磨削、一次喷丸、二次喷丸3种表面加工方法对TC4钛合金表面完整性及高周疲劳性能的影响规律,采用白光干涉仪、X射线残余应力测试仪对经不同方法加工的试样的表面形貌、表面粗糙度和表面残余应力分布等表面完整性参数进行了表征。采用旋转弯曲疲劳试验机分别测试了不同方法加工的光滑试样(应力集中系数Kt=1)和缺口试样(Kt=2)的旋转弯曲疲劳S-N曲线。结果表明,相比磨削,一次喷丸和二次喷丸处理后TC4钛合金光滑试样和缺口试样的疲劳极限均显著提高,TC4钛合金的疲劳缺口敏感性下降。另外,二次喷丸的疲劳极限增益效果优于一次喷丸的,原因是二次喷丸在TC4钛合金表面形成了更优的残余压应力场分布和更低的表面粗糙度。     

STRESS CORROSION CRACKING OF AN ALUMINIUM ALLOY UNDER COMPRESSIVE STRESS

用WOL缺口压缩试样研究LC4铝合金在3.5％NaCl水溶液中的压应力腐蚀.有限元计算指出,试样加压缩位移时缺口附近有压应力集中.实验结果表明,当压缩位移大于临界值后产生压应力腐蚀裂纹. 实验测出压应力腐蚀裂纹的门槛值为K_(ISCC*)=27.6MPam~(1/2),等于拉应力腐蚀门槛值的3.5倍.在相同K_I下压应力腐蚀裂纹的孕育期比拉应力高一个数量级.压应力腐蚀时获得带有平行条纹花样的准解理断口,这和拉应力腐蚀的沿晶断口完全不同。     

Effect of corrosive environment on the fatigue crack initiation and propagation behavior of Al 5454-H32

Fatigue behavior of aluminum alloy 5454- H32 was studied under laboratory air and 3 % NaCl solution environment using smooth cylindrical and notched plate specimens. Presence of 3 % NaCl environment during fatigue loading drastically reduced alloy fatigue life. The deleterious effect was pronounced in both types of specimens in the long- life regions, where the fatigue lives were lowered by as much as a factor of 10. However, the sharply notched specimens showed only a modest reduction in fatigue life in corrosive environment. The severe influence of the corrosive environment in the long- life (low- stress) regime cannot be explained merely by the early initiation of the fatigue crack from surface pits; the environmental contribution in the early crack growth regime must also be considered an important factor. Fracture surface studies revealed extensive pitting and some secondary cracking in the crack initiation region. It was shown that lowered fatigue life in Al 5454- H32 occurs by early initiation of fatigue cracks from surface pits. In addition, a corrosion pitting and secondary cracking process may be operative in the small crack growth region. This could have enhanced the early crack growth rate and thus contributed to the lower fatigue life in the long- cycle region.     

Comparison of corrosion- fatigue properties of precorroded 6013 bare and 2024 bare aluminum alloy sheet materials

The corrosion- fatigue resistance of precorroded 6013 bare and 2024 bare aluminum alloy sheet materials was evaluated to compare the effect of corrosion on initiation and propagation of fatigue cracks. The specimens were precorroded in 3.5% NaCl water solution per ASTM G 44 for periods of 4 and 30 days, and then were subjected to cyclic testing to failure in a 3.5% NaCl corrosive environment. The notched 6013 specimens showed better corrosion- fatigue resistance for the longer exposure time only. In all other cases, the 2024 material had better resistance. Fractographic and microstructural examinations sug-gested that the lower corrosion- fatigue life of the 6013 alloy is due to intergranular corrosion. Although the surface corrosion (pitting) on the 2024 alloy appeared severe, there was little evidence of intergranu-lar corrosion in this alloy.     

Corrosion fatigue behavior of the high-strength magnesium alloy AZ 80

The fatigue performance of the high-strength magnesium alloy AZ 80 is studied in air as well as in aqueous 0.5 and 3.5% NaCl solutions. The effect of mechanical surface treatments, specifically mechanical polishing, shot peening, and roller burnishing on the S-N curves, is investigated using an electropolished surface as a reference. While mechanical polishing as well as shot peening improves fatigue performance in air, no improvement is observed in NaCl solutions. However, roller burnishing, which combines a smooth surface finish with residual compressive stresses in sufficient depths, leads to outstanding fatigue performance even in 3.5% NaCl solution.     

Effect of corrosive environment on fatigue property and crack propagation behavior of Al 2024 friction stir weld

In this investigation, 2024 aluminium alloy plates were friction stir welded, a sequence of experiments was performed including fatigue and crack propagation tests in air, under pre-corrosion and in a 3.5% NaCl solution, in combination with fractography analyses of near-threshold region, Paris region and finial fracture region with the aid of scanning electron microscopy (SEM). Results showed that the corrosive environment caused a dramatical decrease in fatigue lives of FS welds, the corrosion fatigue lives of FS welds were almost a half of those of the as-welded specimens. The crack growth rates in FS welds were higher than their counterparts in base materials, under the corrosive environment, the crack growth rate differences between base materials and FS welds become increasingly apparent with the increase of stress intensity factor range ΔK, but the pre-corrosion process had little effect on the FS welds' crack propagation behavior except for shortening the crack initiation lives greatly.     

300M钢腐蚀疲劳裂纹萌生的超载特性

本文对３００Ｍ钢在空气与３．５％ＮａＣｌ溶液中疲劳裂纹萌生的周期超载和单次超载特性进行了试验研究与理论分析。试验结果表明，３．５％ＮａＣｌ溶液中，单次超载所致腐蚀疲劳裂纹迟滞萌生的迟滞强度远小于周期超载的对应值。３．５％ＮａＣｌ溶液与空气中，超载迟滞强度均随超载比增大或等效应力幅水平的提高而增大，在腐蚀疲劳裂纹萌生寿命估算中，只考虑单次超载的迟滞规律，会得出大大保守的寿命估计，只有将单次超载和周期     

Corrosion fatigue crack growth behavior of oil-grade nickel-base alloy 718. Part 1: Effect of corrosive environment

The effect of corrosive environment on corrosion fatigue crack growth (CFCG) behavior of oil-grade nickel-base alloy 718 is studied. The results demonstrate that there is no obvious effect of 3.5 wt.% NaCl solution at RT, 50 °C and 80 °C on CGCG rates while 21 wt.% NaCl solution at 80 °C produces a deleterious effect on CFCG rates compared to the ones tested in air. Potentiodynamic polarization results show that alloy 718 exhibits passive behavior in 3.5 wt.% NaCl solution, while pitting corrosion resistance decreases with increasing solution temperature. Nevertheless, alloy 718 shows active corrosion behavior in 21 wt.% NaCl solution at 80 °C.     

TB6钛合金疲劳及裂纹扩展性能研究

本文对TB6钛合金锻件弦向和径向两种取样方向分别进行了室温和200℃下旋转弯曲高周疲劳、轴向低周疲劳和疲劳裂纹扩展性能试验研究。试验结果表明,弦向（C）和径向（R）两种取样方向对该合金锻件的旋转弯曲高周疲劳、轴向低周疲劳性能和疲劳裂纹扩展性能没有影响;温度升高可加速该合金锻件的疲劳裂纹萌生,但在裂纹扩展阶段,该合金高温下的韧性优势与屈服强度降低的劣势平衡的结果使其在室温～200℃温度范围内的疲劳性能基本不受温度的影响;在10—20mm的厚度范围内,厚度对该合金的疲劳裂纹扩展性能没有影响;在3．5％NaCl盐雾环境中。腐蚀介质对TB6钛合金的疲劳裂纹扩展速率在初始阶段有迟滞作用,但在应力强度因子范围大于14MPa m后有加速作用。     

Comparison of accelerated SCC tests performed on the aluminium alloy 2014-T651

The stress corrosion cracking (SCC) behaviour of plates of the Al-Cu-Si-Mn-Mg alloy 2014-T651 was investigated in short transverse direction performing various accelerated tests. Corrosive media used were: aqueous 3.5% NaCl solution, an aqueous solution of 2% NaCl + 0.5% Na₂CrO₄ at pH = 3 (according to LN 65666), and substitute ocean water according to ASTM D1141. C-ring and tensile specimens were loaded under constant deformation, constant load and slow strain rate conditions. Alternate immersion tests in 3.5% NaCl solution clearly indicate the low SCC resistance of the alloy 2014-T651 in short transverse direction. Under continuous immersion conditions the acidified 2% NaCl solution containing chromate is an appropriate synthetic environment, while neutral 3.5% NaCl solution does not promote severe stress corrosion cracking. The SCC susceptibility of 2014-T651 is also observed in slow strain rate tests using substitute ocean water as well as acidified 2% NaCl solution inhibited by chromate. In 3.5% NaCl solution the evaluation of slow strain rate data is complicated by pre-exposure effects.     

Corrosion fatigue behavior of epoxy-coated Mg–3Al–1Zn alloy in NaCl solution

The corrosion fatigue behavior of epoxy-coated Mg–3Al–1Zn alloy was investigated in air and 3.5 wt%NaCl solution. Epoxy coating as a new method was used to improve the corrosion fatigue property of the material.Results show that the fatigue limit(FL) of the coated specimens is higher than that of the uncoated specimens in3.5 wt% NaCl solution because of the strengthening and blocking functions of the epoxy coating. The FL of the coated specimens in 3.5 wt% NaCl solution is as high as that in air. It implies that the coated specimens are not as sensitive to the environment as the magnesium alloy. The low tensile strength and the short elongation of the pure epoxy coating lead to that the fatigue crack of the coated specimen is always initiated from the epoxy-coating film Pores and pinholes accelerate the fatigue crack initiation process. Pinholes are caused by the corrosion reactions between the epoxy coating and the NaCl solution.     

Spannungsrißkorrosionsuntersuchungen an Strangpreßbarren der Legierungen 8090-T851 und 2091-T851

On the stress corrosion cracking behaviour of flat extrusions of the alloys 8090-T851 and 2091-T851 The stress corrosion cracking (SCC) behaviour of flat extrusions of the Al-Li-Cu-Mg-Zr alloys 8090-T851 and 2091-T851 was investigated performing accelerated tests under constant deformation, constant load, and slow strain rate conditions. The used corrosive environments were an aqueous 3.5% NaCl solution and an aqueous solution of 2% NaCl + 0.5% Na₂CrO₄ at pH = 3. Round tensile specimens and tuning fork type specimens were alternately immersed in 3.5% NaCl solution according to ASTM G44 under constant deformation, whereas they were continuously immersed in the other tests. The investigated flat extrusions of the alloy 8090-T851 were stress corrosion resistant in the extrusion and the long transverse directions. With the alloy 2091-T851 failure was observed at 75% of the 0.2 proof stress which may be caused by stress corrosion cracking or stress assisted intergranular corrosion. In the short transverse direction the SCC behaviour of the extrusions of both Al-Li alloys is comparable with that of a 2024-T351 alloy plate revealing a high SCC susceptibility.