脆性温度点时效对22Cr双相不锈钢冲击性能的影响

为了解脆性转变点时效时间对22Cr双相不锈钢冲击性能的影响,研究了经不同热处理(固溶处理、固溶 脆性点时效处理)后材料的冲击性能。结果表明:原始板材、1 050℃固溶处理的试样具有良好的冲击韧度,冲击功均在280 J以上,微观断口为韧窝;850℃时效处理显著降低试样的冲击韧度,随着时效时间的延长,室温冲击功由时效0.5 h的60 J下降到2 h的5 J,微观断口为解理;475℃时效处理也降低试样的冲击韧度,随着时效时间的延长,冲击功略有降低,微观断口为韧窝 解理。     

COD与J积分的尺寸效应及其一致性

本文对马氏体时效不锈钢不同尺寸的三点弯曲试样用阻力曲线方法进行了COD和J积分的测试,研究了它们的尺寸效应。在本实验范围内得出了同一材料不同尺寸的试样采用阻力曲线方法外推而得的启裂COD(δ_i)和J积分(J_i)值基本相同的结论。同时本实验的结果从尺寸效应和阻力特性的角度证实了COD和J积分两判据的一致性。图2,表4,参考文献10。     

三点弯曲试样测试J积分值试验研究

采用两个不同钢种的三点弯曲试样,以载荷-缺口张开位移曲线下的塑性面积为基础计算J积分值,依据GB/T 21143-2014和GB/T 21143-2007、GB/T 2358-1994附录D两个标准相结合,用这两种不同的方法计算J积分值。结果表明:相对于不同的裂纹扩展量Δa,J积分值从低值到高值,两种方法计算J积分值的平均相对偏差<2.0%,结果一致,说明用GB/T 21143-2007、GB/T 2358-1994附录D两个标准相结合也可以准确计算J积分值,提供了一种用三点弯曲试样测试J积分值的计算方法。     

基于SENT试样获取材料断裂韧度的载荷分离法研究

单边裂纹拉伸(Single edged notched tension,SENT)试样因其低约束特性逐渐被用于管道材料的断裂韧度评定。根据有限元法,提出SENT试样的应力强度因子表达式,J积分计算中的增量塑性功算式以及塑性因子算式,并与文献中公式进行对比证实公式的精确性和有效性。依据ASTM用于CT试样获取断裂韧度载荷分离理论规则化方法提出适用于SENT试样的量纲一载荷分离法,并通过有限元计算证实SENT试样载荷分离的成立性。由量纲一载荷分离理论中的规则化方法完成了汽轮机低压转子材料30Cr2Ni4MoV、电站用P92管道钢以及5083-H112铝合金SENT试样断裂韧度值以及J阻力曲线测定,获得了各材料合理的J阻力曲线及条件断裂韧度JQ值。     

反应堆压力容器模拟钢等温热时效的硬度研究

研究反应堆压力容器模拟钢（Cu含量大于0.25%wt）的等温热时效强化行为。模拟钢900℃固溶处理后水淬保留的过饱和Cu原子在时效过程中析出长大,使得材料出现强化。试验选取3个平行试样用30 kg载荷进行维氏硬度测量,每个样品测量五次,取平均值作为测量结果。结果表明,试样硬度随时效时间增加发生变化。在此基础上分析了时效强化曲线并得到了合金元素Ni对时效硬化峰时间及峰形的影响。     

考虑裂尖约束效应的小尺寸CIET试样延性断裂行为

应用单试样规则化法完成了压力容器用钢SA-508紧凑拉伸(Compact tension,CT)、三点弯曲(Single edge-notched bending,SEB)和小尺寸含内侧边裂纹C形拉伸(C-shaped inside edge-notched tension,CIET)三类试样的延性裂纹扩展行为试验,获得了J-Δa阻力曲线。结果表明,SA-508钢的J-Δa阻力曲线受试样构形和裂纹尺寸的影响较大,其根本原因在于试样裂纹尖端约束不同而引起延性断裂行为差异。引入J-Q-M三参数约束理论考察断裂试样的裂尖约束效应,采用权重平均法求解与距离无关的约束参数Q。弹塑性有限元分析结果表明,平面应变条件下的Q参数与载荷水平无关,但三维条件下的Q参数却仍受载荷水平的影响。基于J-Q-M三参数约束方法,建立三类试样满足J-Q-M控制的有效尺寸条件。进一步地,结合条件启裂韧度J0.2BL、J0.5BL试验结果和J-Q-M理论,获得了基于Q参数的约束修正J-Δa阻力曲线簇,可用于任意约束试样以及实际含裂纹结构的延性断裂行为预测。     

921A钢的延性断裂韧性测试研究

以GB/T 21143的柔度法及美国标准ASTM E1820-11推荐规则化数据还原技术为基准,对921A钢试样进行预制疲劳裂纹、收集试验数据、试验数据后处理、有效性评估等几个方面的试验研究。研究结果表明:通过采用规则化数据还原技术以及柔度法对所有试样进行数据处理,两种数据处理方法得到的J—Δa曲线以及启裂韧度JQ均较为接近,且试验预测的最终裂纹长度与光学显微镜实测裂纹长度吻合。说明了采用GB/T 21143可以有效测定高强度塑性材料的延性断裂韧性。     

基于CJP模型的疲劳裂纹扩展率曲线及应用方法

利用数字图像相关技术开展工业纯钛5种不同高宽比CT试样的疲劳裂纹扩展率试验,分别采用传统应力强度因子范围ΔK和基于CJP模型理论框架的新应力强度因子范围ΔK_(CJP)对数据进行分析,得到的da/d N-ΔK和da/d N-ΔK_(CJP)曲线均有效反映了试验数据分布规律,具有良好的拟合效果。相较于传统参量ΔK,ΔK_(CJP)直接由裂尖位移场求解,无需进行修正即可用于材料疲劳裂纹扩展率描述,具有与CT试样高宽比无关的特性;作为ΔK_(CJP)的两个组成参量,ΔK_F、ΔK_R与传统ΔK数据间均呈现出某种总体变化趋势,分别可用二次多项式和线性方程表征。构造了ΔK_(CJP)与ΔK的关联函数,并由此推导出ΔK_(CJP)表达式,为da/d N-ΔK_(CJP)曲线在材料与结构的失效分析和安全评价中的应用提供了有效途径,拓宽了CJP模型的工程应用范围。     

氢对347L不锈钢堆焊层的低频疲劳特性的影响

应用弹塑性断裂力学和ΔJ参数 ,研究了原始状态与热渗氢后 3 4 7L不锈钢堆焊层短裂纹的疲劳破坏特性。并用 da/d N=C(ΔJ) n 计算了裂纹扩展速度和门槛值。结果表明 ,在氢的作用下 ,3 4 7L钢堆焊层裂纹扩展的门槛值 (ΔJth) ,从 3 55× 1 0 - 6 MN/m,下降为热渗氢后的 2 52× 1 0 - 6MN/m,da/d N～ΔJ曲线也比原始状态的向左移 ,提高了裂纹扩展速度。断口分析表明 ,氢既有在柱状晶界及滑移面上位错塞积处聚集 ,促进脆化的作用 ,同时还有与交变载荷的动态协同作用     

试样重组技术的可行性研究

从冷态夏比冲击破断试样上截取三种不同长度的插入段进行电子束焊接重组,通过对重组前后试样冲击吸收功对比以及重组后焊接接头处的显微组织观察,对试样重组技术可行性进行初步研究。结果表明,焊缝与热影响区的宽度较小,未对V型缺口附近的母材组织产生影响;重组前后试样的夏比试验数据具有较好一致性,重组试样可以再现原始试样的试验结果。     

0Cr18Ni9不锈钢的高温疲劳裂纹扩展规律

研究奥氏体不锈钢0Cr18Ni9在高温(550℃)下的疲劳裂纹扩展规律。测试采用标准CT(compact tension)试样,最大载荷范围为6.5 kN～14 kN,应力比为0.1(室温)和0.05(550℃)。裂纹扩展过程通过QUESTAR长焦距显微镜直接观测,同时采用COD(crack opening displacement)规记录加载线位移。由于在高温条件下,测试终止时试样的裂纹前缘呈明显弧形,故此给出实测表面处裂纹长度有效值的修正方法。对高温疲劳裂纹扩展问题,采用应力强度因子范围ΔK作为裂纹扩展驱动力参数,同时考虑高ΔK和低ΔK值对裂纹扩展规律的影响,得到0Cr18Ni9不锈钢在550℃下的疲劳裂纹扩展规律表征模型,给出裂纹扩展率的上限结果。     

高温时效对25Cr35Ni-Nb合金碳化物的影响

25Cr35Ni-Nb合金被广泛用作乙烯裂解炉和制氢转化炉炉管材料,服役温度高达1050℃。将25Cr35Ni-Nb合金炉管在不同温度时效100 h,通过对不同温度显微组织的观察和维氏硬度测试,研究了不同温度时效后碳化物的变化规律。研究结果表明：随着时效温度的升高,晶界碳化物宽度不断增大,由原始铸态平均宽度1.5μm,增大到1200℃时效后的5.3μm;从900℃到1100℃,奥氏体晶内碳化物平均尺寸由1μm长大至2μm,然而,随着时效温度提高至1200℃,晶内碳化物平均尺寸下降至1.7μm。当时效温度从900℃增加为1100℃时,维氏硬度从173 HV10升高为192 HV10,1200℃时,维氏硬度为193 HV10。碳化物尺寸及维氏硬度与时效温度之间定量关系对炉管服役温度范围的确定提供了参考。     

Numerical and experimental method for the prediction of the propagation life of fatigue crack on metallic materials

A prediction method for the propagation life of fatigue crack for cracked components was provided and verified in this study to predict the propagation life of fatigue cracks on components in engineering applications conveniently and directly. In the simulation aspect, a finite element (FE) model of cracked specimen was created to obtain the stress intensity factor range ΔK. The FE model was verified by comparing simulated ΔK to a formulary calculated one. The simulated ΔK could be used for studying the relationship with crack size. In the experimental aspect, the fatigue crack propagation test was conducted on three specimens. The material coefficients C and m were fitted according to Paris’ law. The load cycles with different crack depths were recorded in the testing process. The propagation life of fatigue cracks of specimen was predicted via the relationship between ΔK and crack size a according to Paris’ law. The comparison between predicted life and experimental life of specimens indicated the feasibility of the method. The proposed prediction method in this study for the propagation life of fatigue cracks can be used in engineering applications.     

Influences of post weld heat treatment on fatigue crack growth behavior of TIG welding of 6013 T4 aluminum alloy joint (Part 1. Fatigue crack growth across the weld metal)

The present study evaluates the influences of PWHT on FCG behavior and tensile properties of TIG butt welded Al 6013-T4 sheets. Crack propagation tests were carried out on compact tension (CT) specimens. The T82 heat treatment was varied in three artificial aging times (soaking) of 6, 18 and 24 hours. The results of T82 heat treatment with artificial aging variations were tested for their fatigue crack growth rates at the main metal zone, the heat-affected zone (HAZ), and the welded metal zone. It has been observed that the various agings in heat treatment T82 are sensitive to the mechanical properties (fatigue crack growth rate test, tensile test). The results show that PWHT-T82 for 18 hours aging is the highest fatigue resistance, while the aging 18 hours provided the highest tensile test result.     

The effect of rubber contact on the fretting fatigue strength of railway wheel tire

The cause of the ICE train derailment, which occurred in 1998 at Eschede, was fatigue failure originating on the inside of the wheel tire. Rubber-sprung resilient wheels were used for the trailer cars. The wheel tire is mounted on the wheel disc. Thirty-four rubber pads were arranged between the wheel disc and the wheel tire. It was postulated that fretting fatigue between the rubber block and the inner side of the tire might have an influence on the initiation of the incipient crack. In order to clarify the influence of the rubber contact on the fatigue strength of the tire, fretting fatigue experiments under rubber contact conditions were performed. During the fundamental fretting fatigue test using bridge pads and small size carbon steel specimens, no typical fretting damage such as fretting wear and minute cracks were observed due to contact of the rubber. Stress conditions of the rubber-sprung wheel under vertical and lateral wheel loads were evaluated by a three-dimensional elastic stress analysis. Since the rubber is a super-elastic material, the Mooney-Rivlin model was used in the FEM calculation. It was found that the wheel tire is subjected to a cyclic stress during one revolution of the wheel and the maximum stress occurred at the center of the inner surface of the tire where the fatigue crack initiated. Fatigue strength of the wheel tire was determined by the rotating bending fatigue testing of specimens taken from the tire. It was found that the tire with an 862 mm diameter at a wheel load of 80 kN had a safety factor more than 3.5 from a fatigue limit diagram with a failure probability of 0.01. To confirm the fretting damage under the rubber contact and the result of the fatigue strength evaluation, fatigue tests of a full size wheel were made. After 20 million cycles at the wheel load of 280 kN, which was just below the endurance limit estimated by the endurance limit diagram, no fretting damage and no fatigue cracks were observed. The wheel was, however, fractured at 1.56 million cycles under the maximum load of 308 kN, which was just above the endurance limit. The estimation of the safety factor of 3.5 estimated from the endurance diagram was confirmed by the full size fatigue testing. It was concluded that there was no effect of fretting due to the rubber contact on the fatigue strength of the rubber-sprung single-ring railway wheel.     

Correction of constraint loss in fracture toughness measurement of PCVN specimens based on fracture toughness diagram

The aim of this paper is to suggest an approach to generate master curves by using miniature specimens, especially pre-cracked Charpy V-notched (PCVN) specimen, made of SA508 carbon steel. Firstly, fracture toughness diagram is derived from comparing finite element analyses results with the fixed mesh size at crack tip between standard compact tension and PCVN specimens. To compensate the constraint effects from different geometry, further examination based on the fracture toughness diagram was performed. In this context, a scale factor to deal with specimen size effects is proposed by statistically manipulating the numerical analysis data. Finally, the proposed scale factor is applied to calculate reference temperature which affects on the master curve. We expect that the approach can be applicable to compensate the geometrical constraint effects on fracture toughness of SA508 carbon steel when the PCVN specimen is used.     

单边裂纹弯曲试样的转动修正方法研究

由SEB( single edged bending)试样变形几何关系,提出断裂韧度测试中用于SEB试样J积分塑性功计算的裂纹嘴张开位移V0与加载点在加载线位移VLL的弹塑性转换公式.对SEB试样进行弹塑性有限元分析表明:试样转动中心位置受材料本构关系的影响微小,仅与裂纹长度α与试样宽度W之比有关,进而提出SEB试样转动半径R(裂纹嘴初始位置到转动中心的距离)的表达式,并对公式的有效性进行验证;应用线弹性柔度公式预测裂纹长度,可以忽略试样转动效应的影响,而刚性转动对SEB试样的J积分计算有一定影响,需采用考虑转动效应的载荷与加载线位移关系曲线来获得真实的J-△α阻力曲线.     

钝裂纹或缺口下失效评定图的变化及修正方法研究

应用增量理论弹塑性有限元方法以及弹塑性断裂力学 Ｊ积分理论, 深入研究和全面探讨了一种用于含裂纹结构完整性评定的工程方法——失效评定图, 以及钝裂纹或缺口根部曲率半径、缺口长度、缺口端部椭圆离心率、试样形式和材料等对其的影响。提出了钝裂纹或缺口应力强度因子和极限载荷修正方法。通过这一方法建立的失效评定图可有效地消除缺口因素对失效评定图的影响, 由此, 可完全等效地将裂纹失效评定图用于含缺口结构的完整性评定。     

Heat aging effects on the material property and the fatigue life of vulcanized natural rubber, and fatigue life prediction equations

When natural rubber is used for a long period of time, it becomes aged; it usually becomes hardened and loses its damping capability. This aging process affects not only the material property but also the (fatigue) life of natural rubber. In this paper the aging effects on the material property and the fatigue life were experimentally investigated. In addition, several fatigue life prediction equations for natural rubber were proposed. In order to investigate the aging effects on the material property, the load-stretch ratio curves were plotted from the results of the tensile test, the compression test and the simple shear test for virgin and heat-aged rubber specimens. Rubber specimens were heat-aged in an oven at a temperature ranging from 50°C to 90°C for a period ranging from 2 days to 16 days. In order to investigate the aging effects on the fatigue life, fatigue tests were conducted for differently heat-aged hourglass-shaped and simple shear specimens. Moreover, finite element simulations were conducted for the specimens to calculate physical quantities occurring in the specimens such as the maximum value of the effective stress, the strain energy density, the first invariant of the Cauchy-Green deformation tensor and the maximum principal nominal strain. Then, four fatigue life prediction equations based on one of the physical quantities could be obtained by fitting the equations to the test data. Finally, the fatigue life of a rubber bush used in an automobile was predicted by using the prediction equations, and it was compared with the test data of the bush to evaluate the reliability of those equations.