690合金的Pb致应力腐蚀行为

采用反U型试样,对690合金样品在高压釜内进行了4400 h的应力腐蚀实验,以研究其在含Pb溶液中的应力腐蚀规律.利用扫描电镜和能谱仪等分析了690合金在含Pb高温高压水环境中的应力腐蚀行为.扫描电镜结果表明,690合金在测试溶液中发生穿晶型应力腐蚀开裂,裂纹内部堆积着腐蚀产物,并且Pb掺杂在其中.裂纹区域的元素面扫描表明,690合金表面生成的腐蚀产物膜内层富Cr、外层富Ni,腐蚀产物与基体膨胀系数的差异导致裂纹快速扩展.试样内外表面的腐蚀形貌差异明显,内壁呈晶格网状,外壁呈一定方向性腐蚀沟堑,主要是由于内外表面状态不同造成的.      

高速列车支撑槽用6005A-T6铝合金腐蚀疲劳裂纹扩展行为研究

通过微观组织分析、裂纹扩展路径及断口表面形貌分析,研究了高速列车支撑槽用6005A-T6铝合金在3.5%NaCl溶液中的腐蚀疲劳裂纹扩展行为。结果表明:6005A-T6铝合金在3.5%NaCl溶液中的疲劳裂纹扩展速率较空气环境中快3倍左右;腐蚀环境中疲劳裂纹呈沿晶扩展,扩展过程中出现较多的沿晶二次裂纹。6005A-T6铝合金中较高腐蚀电位的第二相促进周围α-Al基体在3.5%NaCl溶液中的腐蚀,并在腐蚀过程中同时释放H2,氢和腐蚀环境的联合作用促进了6005A-T6铝合金在3.5%NaCl溶液中的疲劳裂纹扩展。     

两种超高强度合金的应力腐蚀开裂行为研究

超高强合金因其优越的力学性能广泛应用于承力构件如起落架等,40CrNi2Si2MoVA超高强度合金是继30CrMnSiNi2A之后研究出的新超高强度合金,其强度高于30CrMnSiNi2A,但是其在实际服役环境中的服役性能特别是应力腐蚀性能是否优于30CrMnSiNi2A,是决定其成功取代30CrMnSiNi2A应用的关键。采用双悬臂应力腐蚀实验研究了30CrMnSiNi2A及40CrNi2Si2MoVA两种超高强度合金在质量分数为3.5%的NaCl溶液中的应力腐蚀开裂行为(SCC)。通过光学显微镜和扫描电镜(SEM)对两种超高强度合金的形貌以及断口显微组织进行了分析。实验结果表明,30CrMnSiNi2A比40CrNi2Si2MoVA更早失效,其耐应力腐蚀性能较差。两种材料在NaCl溶液中容易出现裂纹并迅速扩展,裂纹横向扩展,并出现明显的分叉行为,不同取向试样对材料应力腐蚀开裂行为的影响较小。断口分析结果表明两种超高强度合金在应力和腐蚀介质的共同作用下发生失效,裂纹扩展前期主要为解理穿晶断口,裂纹扩展中后期为沿晶形貌。     

温度对Z3CN20-09M不锈钢在含氯高温水中应力腐蚀行为的影响

研究了温度对核电用Z3CN20-09M不锈钢在含Cl的高温高压水中的应力腐蚀开裂行为的影响.材料的应力腐蚀开裂敏感性变化趋势与试验温度变化趋势并不一致.320℃时材料的应力腐蚀开裂敏感性最高,290℃时为最低,250℃时开裂敏感性介于两者之间.250℃和320℃条件下腐蚀后试样表面形成了内部致密、外部疏松的双层氧化膜,而在290℃条件下腐蚀后试样形成的是致密的单层氧化膜.大多数点蚀坑产生于铁素体相.应力腐蚀裂纹优先在点蚀坑底部或相界面形核,并倾向于沿相界面或向铁素体内部扩展.铁素体/奥氏体界面对应力腐蚀裂纹的作用取决于裂纹面与相界面的取向关系.当裂纹扩展方向平行于相界面时,裂纹易沿着相界扩展;当裂纹扩展方向垂直于相界面时,相界面对裂纹扩展起阻碍作用.      

低铬抗硫套管的H_2S/CO_2腐蚀行为研究

通过高温高压及H2S应力腐蚀开裂(SSC)实验,采用SEM、EDS、XRD和TEM技术,研究3Cr110S在模拟环境中的H2S/CO2腐蚀行为。结果表明:在模拟H2S/CO2高温高压腐蚀环境中,H2S腐蚀占主导作用,3Cr110S的均匀腐蚀速率为0.1272 mm/a,局部腐蚀轻微,试样表面腐蚀产物为FeS;在施加应力为72%、80%的最低屈服强度时,3Cr110S试样均未发生应力腐蚀开裂,具有良好的抗SSC性能;3Cr110S回火索氏体组织的条束之间位相差大,铬元素在晶界及晶内以粒状碳化物析出、位错纠结、弥散分布碳化物的位错定扎对SSC裂纹扩展起着良好的阻碍作用。     

室温下18-8不锈钢在H_2SO_4-NaCl介质中的应力腐蚀

通过恒变形和恒负荷试验,研究了18-8不锈钢在5NH_2SO_4 (0～1.O)NNaCl介质中的应力腐蚀特征,发现5NH_2SO_4 O.5NNaCl溶液是应力腐蚀破裂的最敏感介质。溶液中NaCl浓度≤O.1N,产生不均匀的腐蚀,但不产生应力腐蚀裂纹。在(O.1～1.O)NNaCl范围内产生穿晶和晶间混合型的应力腐蚀破裂。NaCl浓度高时(>0.1N)对均匀腐蚀起缓蚀作用。应力腐蚀破裂发生在极化曲线的活化区。断口扫描观察表明,试样破断是由于腐蚀隧洞沿滑移面生长并受到拉伸撕裂所致。采用透射电子显微镜观察薄片拉伸试样的裂纹扩展行为和裂纹周围显微结构证明,18-8不锈钢在H_2SO_4-NaCl介质中的裂纹扩展是以滑移和沿滑移面金属的选择性溶解的方式进行,也即穿晶应力腐蚀裂纹沿{111}滑移面扩展。在5NH_2SO_4 O.5NNaCl介质中,18-8钢裂纹扩展的表观活化能为37.5kJ/mol,表明沿滑移面的隧洞溶解不是速度控制步骤。     

不同厚度铝合金试样的应力腐蚀开裂特性研究

鉴于试样厚度对2024-T351铝合金材料的应力腐蚀开裂门槛值KISCC的影响及实际工程应用中厚壁构件的应力腐蚀敏感性评价等问题,选取能够代表实际工程应用中构件壁厚的40 mm厚双悬臂梁(DCB)试样和标准(GB 15970.6-2007)中规定的26 mm厚DCB试样,进行了应力腐蚀断裂特性研究。结果表明,40 mm厚试样得到的材料的应力腐蚀开裂门槛值KISCC值大于26 mm厚试样得到的KISCC。对S-L取向试样,40 mm厚和26 mm厚试样的应力腐蚀开裂门槛值KISCC差别不大,差异在4%左右;对S-T取向试样,40 mm厚和26 mm厚试样的KISCC值差别明显,差异在24%左右。在DCB试样应力腐蚀断口表面发现有纤维状的腐蚀产物生成,经过能谱仪(EDS)及X射线衍射(XRD)分析,纤维状的腐蚀产物是氢氧化铝。纤维状腐蚀产物的生成降低了DCB试样裂纹尖端腐蚀产物的积累,从而减轻了腐蚀产物楔形作用对应力腐蚀开裂门槛值KISCC的影响,提高了材料抗应力腐蚀的能力。并且40 mm厚DCB试样应力腐蚀断口表面的纤维状腐蚀产物明显多于26 mm DCB试样,这也是40 mm厚试样的应力腐蚀开裂门槛值大于26 mm试样的一个原因。在应力腐蚀开裂过程中,由于DCB试样裂纹尖端发生阳极反应,与主体溶液形成小阳极大阴极体系,使试样裂纹尖端呈酸性,而主体溶液呈碱性。40 mm厚试样的裂纹尖端pH约3.0,26 mm厚试样的裂纹尖端pH约3.6,厚板试样裂纹尖端处溶液酸化更严重。     

GH4169合金高温疲劳裂纹扩展的微观损伤机制

空气环境对高温合金在高温下的损伤行为有显著影响.为了研究标准热处理态GH4169合金在高温疲劳裂纹扩展过程中的微观损伤机制,在空气环境中进行650℃、初始应力强度因子幅ΔK=30 MPa·m1/2和应力比R=0.05的低周疲劳裂纹扩展试验.使用扫描电镜(SEM)及能谱(EDS)对试样的断口、外表面和剖面进行观察和分析.实验结果表明:疲劳主裂纹以沿晶方式萌生并扩展,随后沿晶二次裂纹出现,并且其数量和长度沿主裂纹方向逐渐增加,进入快速扩展阶段后,断口呈现韧窝组织形貌;在裂纹扩展过程中,δ相与基体的界面发生氧化,使得沿晶二次裂纹沿界面扩展并产生偏折,从而起到阻碍二次裂纹扩展的作用;试样外表面的主裂纹周围出现晶界氧化损伤区,其尺寸和晶界开裂程度沿主裂纹扩展方向逐渐增大.      

工模具钢中疲劳裂纹扩展特征与机制

在测定W-Mo高速钢和含Nb基体钢的疲劳裂纹扩展速率da/dN及门坎值△K_th的基础上,对裂纹扩展途径和断口形貌进行了SEM观察与分析。试验结果表明,在双对数坐标上,工模钢的da/dN-△K关系曲线明显分为三段,并各自遵循不同的扩展机制;低速区以沿晶开裂和不连续解理为主;中速区则遵循穿晶的“准解理+流变带开裂”机制;而高速区裂纹则以主裂纹前方的裂纹再生核方式向前延伸。da/dN-△K曲线的转折是相邻区域不同裂纹扩展机制相互竞争与转化的结果。     

温度,介质浓度和电位对碳钢在硝酸盐中应力腐蚀的影响

用慢应变速率法测量最大裂纹深度、平均裂纹扩展率、断面收缩率与拉伸率等,研究了碳钢在不同温度、不同介质浓度和不同电位下的非经典应力腐蚀行为。结果表明,最大裂纹深度和平均裂纹扩展速率是较好的评价应力腐蚀的参数。金相显微镜和扫描电镜观察结果表明,应力腐蚀裂纹起始于材料晶界,为沿晶阳极溶解机理。在较高温度和腐蚀电位下,材料仍处于饨化状态,在硝盐介质中,在应变条件下,材料仍遭受应力腐蚀。随介质温度和(或)硝盐浓度的降低,材料的腐蚀形态发生变化,即由应力腐蚀变为一般腐蚀。     

Stress corrosion cracking of aluminum alloys

Stress corrosion cracking of aluminum alloys is reviewed. An extensive failure analysis shows how many service failures occurred in the aerospace industry over a ten year period and what kind of alloys and stresses led to initiation and propagation of stress corrosion cracks which caused these service failures. The paper contains most of the results of stress corrosion tests with aluminum alloys that have been obtained to date with fracture mechanics techniques. Stress corrosion crack growth rate measurements are compared with the results from smooth specimen testing and it is shown that the correlation between the different test results is very satisfactory. The present and limited status of theoretical understanding of stress corrosion cracking is outlined. A major part of the paper is devoted to the results of the latest alloy development. High strength aluminum alloys of dramatically increased stress corrosion resistance are available now. In the near future, stress corrosion resistant alloys of even higher strength might become available. What is still lacking is a detailed understanding of the mechanisms by which stress corrosion cracks initiate and propagate.     

Use of neutron and synchrotron X-ray diffraction for evaluation of residual stresses in a 2024-T351 aluminum alloy variable-polarity plasma-arc weld

The residual stress fields associated with variable-polarity plasma-arc (VPPA) welds in 2024-T351 aluminum alloy plates have been measured nondestructively using neutron and synchrotron X-ray diffraction. Neutron diffraction allows in-depth measurements of the full strain tensor to be made in thick components; synchrotron X-rays allow for rapid measurements of strains inside components, although their penetration is less than that of the neutrons and constraints arising from the diffraction geometry generally lead to only two strain components being easily measurable. Hence, a combination of the two techniques, applied as described herein, is ideal for a detailed nondestructive evaluation of residual stresses in plates. The residual stresses in a 12-mm-thick VPPA-welded aluminum 2024-T351 alloy plate have been measured using neutron diffraction. The stresses were then remeasured by a combination of neutron and synchrotron X-ray diffraction after the plate had been reduced in thickness (or, skimmed) to 7 mm by machining both sides of the weld, mimicking the likely manufacturing operation, should such welds be used in aerospace structures. A strong tensile residual stress field was measured in the longitudinal direction, parallel to the weld, in both the as-welded and skimmed specimens. There was only a slight modification of the residual stress state on skimming.     

Microstructural Evolution During Friction Surfacing of Dissimilar Aluminum Alloys

The microstructural evolution during friction surfacing of an aluminum alloy 6082-T6 rod on an aluminum alloy 2024-T351 substrate was characterized using the electron backscatter diffraction technique. Crystallographic data were obtained from several regions in the consumable material and in the deposited material. From the results, it can be deduced that the grain structure formation was a complex process governed by the geometrical effect of strain and the superposition of continuous and discontinuous dynamic recrystallizations.     

含锶钪2099型铝锂合金的晶间腐蚀和剥落腐蚀性能

采用维氏硬度计(HV)、金相显微镜(OM)和扫描电镜(SEM)显微分析技术,研究了一种锶钪复合微合金化2099型铝锂合金(其化学成分为:Al-2.57Cu-1.86Li-1.31Zn-0.420Mg-0.321Mn-0.0735Zr-0.0943Sr-0.0433Sc)的晶间腐蚀性能和剥落腐蚀性能。结果表明,该合金经均匀化退火处理(475℃×24 h)、热锻压变形加工处理(三次变形量均约为100%)、固溶处理(540℃×2 h)、冷水淬火(水温大约5℃)、T8时效处理(121℃×14 h+151℃×48 h)后,合金显微硬度值达到174.6 HV,比2024-T6合金(固溶处理500℃×2 h+时效处理191℃×12 h)高23.1%。合金具有良好的抗晶间腐蚀性能和抗剥落腐蚀性能,其抗腐蚀性能明显优于2024-T6合金。该合金Sr,Zr,Sc的复合微合金化作用(细化粗大第二相、抑制再结晶和晶粒长大),第二相分散、分布不连续,以及Zn的含量高,是合金抗腐蚀性能高的主要原因。研究结果还说明了微量复合添加对铝锂合金具有奇效微合金化作用的过渡族金属元素Sr,Sc,是得到抗腐蚀性能良好的铝锂合金的一种有效途径。     

Stress corrosion cracking of aluminum alloys

Stress corrosion cracking of aluminum alloys is reviewed. An extensive failure analysis shows how many service failures occurred in the aerospace industry over a ten year period and what kind of alloys and stresses led to initiation and propagation of stress corrosion cracks which caused these service failures. The paper contains most of the results of stress corrosion tests with aluminum alloys that have been obtained to date with fracture mechanics techniques. Stress corrosion crack growth rate measurements are compared with the results from smooth specimen testing and it is shown that the correlation between the different test results is very satisfactory. The present and limited status of theoretical understanding of stress corrosion cracking is outlined. A major part of the paper is devoted to the results of the latest alloy development. High strength aluminum alloys of dramatically increased stress corrosion resistance are available now. In the near future, stress corrosion resistant alloys of even higher strength might become available. What is still lacking is a detailed understanding of the mechanisms by which stress corrosion cracks initiate and propagate. Brown Boveri Research Center, Baden, Switzerland This paper is based on an invited presentation made at a symposium on “Advances in the Physical Metallurgy of Aluminum Alloys” held at the Spring Meeting of TMS-IMD in Philadelphia, Pennsylvania, on May 29 to June 1, 1973. The symposium was co-sponsored by the Physical Metallurgy Committee and the Non-Ferrous Metals Committee of TMS-IMD.     

加载方向对Al—Zn—Mg合金型材应力腐蚀开裂行为的影响

采用恒载荷拉伸应力腐蚀试验和电化学试验研究取向对Al-Zn-Mg合金型材的应力腐蚀(SCC) 开裂的影响, 腐蚀介质采用质量分数3. 5%的Na Cl溶液, 容器温度维持在50±2℃, 并通过光学金相显微镜(OM)、扫描电子显微镜(SEM)、电子背散射衍射(EBSD) 等研究不同取向试样应力腐蚀前、后的微观形貌.结果表明横向试样在315 h时断裂, 而纵向试样在整个加载过程中未发生断裂, 纵向试样有更好的抗应力腐蚀开裂性能; 纵截面(L-S面) 的腐蚀电流密度为0. 980 m A·cm-2, 约为横截面(T-S面) 的5倍, 腐蚀倾向于沿挤压方向发展; 相比T-S面, L-S面晶粒间取向差较大, 大角度晶界多, 容易被腐蚀产生裂纹; 在应力腐蚀加载过程中, 试样先发生阳极溶解, 形成腐蚀坑, 聚集的腐蚀产物所产生的楔入力和恒定载荷的共同作用促使裂纹在腐蚀介质中加速扩展, 两种取向试样均发生了明显的晶间腐蚀, 存在应力腐蚀开裂的倾向.      

Effect of Loading History on Stress Corrosion Cracking of 7075-T651 Aluminum Alloy in Saline Aqueous Environment

An experimental study of stress corrosion cracking (SCC) was conducted on 7075-T651 aluminum alloy in a chromate-inhibited, acidic 3.5 pct sodium chloride aqueous solution using compact tension specimens with a thickness of 3.8 mm under permanent immersion conditions. The effects of loading magnitude, overload, underload, and two-step high-low sequence loading on incubation time and crack growth behavior were investigated. The results show that the SCC process consists of three stages: incubation, transient crack growth, and stable crack growth. The incubation time is highly dependent on the load level. Tensile overload or compressive underload applied prior to SCC significantly altered the initiation time of corrosion cracking. Transition from a high to a low loading magnitude resulted in a second incubation but much shorter or disappearing transient stage. The stable crack growth rate is independent of stress intensity factor in the range of 10 to 22 MPa ?{\textm} . \sqrt {\text{m}} .     

Stress corrosion cracking behavior of friction-stir-welded Al 6061-T651

In the present study, the stress corrosion cracking (SCC) behavior of friction-stir-welded AI 6061-T651 alloy was examined of −650 mV vs Ag/AgCl using a slow strain rate testing technique. The resistance to SCC was correlated to the percent change in tensile elongation with exposure to 3.5 pct NaCl aqueous solution with respect to the reference environment. It was demonstrated the the SCC resistance of friction-stir-welded Al 6061-T651 was considerably higher than that of parent material at an anodically applied potential. In friction-stir-welded Al 6061-T651 alloy, the stress corrosion cracks occur only locally in the boundary region between the dynamically recrystallized zone (DXZ) and the heat affected zone (HAZ) regions. However, the HAZ has much lower strength properties compared with the rest of the material, and thus, fracture occurs there despite the increase in stress intensity due to corrosion at the DXZ and HAZ boundary. Eventually, the tensile fracture in friction-stir-welded A1 6061-T651 was relatively unaffected by the SCCs formed in 3.5 pct NaCl aqueous solution.     

搅拌摩擦修复6061-T4铝合金裂纹的 组织和性能

采用搅拌摩擦方法对预制裂纹的6061-T4铝合金板进行修复，研究了表面裂纹和贯穿裂纹2种类型试样修复区的微观金相组织和抗拉性能及硬度分布.结果表明: 2种预制裂纹试样在合适的焊接工艺参数下，经搅拌摩擦修复后裂纹都能愈合.修复区晶粒由于动态再结晶，晶粒细化形成细小的等轴晶粒，裂纹修复后的试样抗拉强度能达到母材强度的78 %，表面裂纹试样的伸长率达到16.1 %、贯穿裂纹试样伸长率达到14.2 %，为韧性断裂；裂纹修复区的显微硬度的分布曲线基本呈现“W”形.      

Finite element prediction of high cycle fatigue life of aluminum alloys

A new method is described for calculating the long fatigue life (>10⁵ cycles) portion of the stress-life (S-N) fatigue curve for precipitation-hardened aluminum alloys. It is based upon a finite element model of the deformation of a persistent slipband (PSB), and the only material parameter required is the ultimate tensile strength (UTS) of the alloy. The stress dependence of the plastic strain at the tip of a PSB is shown to be very pronounced and to closely match that of anS-N fatigue curve. Very good agreement is obtained for 6061-T6, 2014-T6, 2024-T4, and 7075-T6 aluminum, and the fatigue strength (at 10⁸ cycles) is calculated to be 26 pct of the tensile strength of each alloy, in agreement with experimental data. By contrast, the plastic strain at a crack tip has a much weaker stress dependence. Thus, these calculations also confirm that the elongation of a PSB, and not crack growth, is the rate-controlling process in high cycle fatigue.