ZL111材料疲劳裂纹扩展速率试验

应用Instron1341电液伺服试验机进行了ZL111材料的裂纹扩展速率试验,利用Paris公式分析了该材料的裂纹扩展试验数据,结果表明:可以利用Paris公式获得的疲劳裂纹扩展速率公式计算指定应力强度因子幅下裂纹扩展速率.     

GDL-1型高强韧贝氏体钢的疲劳裂纹扩展特性的研究

通过疲劳裂纹扩展试验,研究了不同热处理状态下GDL-1型高强韧贝氏体钢的疲劳裂纹扩展速率和疲劳裂纹扩展门槛值,得出了有价值有意义的结论.     

温度与应力比对6061铝合金疲劳裂纹扩展行为的影响

为了研究温度与应力比对航空铝合金疲劳裂纹扩展行为的影响,利用电液伺服疲劳试验机对6061铝合金材料开展了不同温度(室温、-70、150 ℃)、应力比(0.1、0.5)条件下的疲劳裂纹扩展速率试验,获得不同条件下的疲劳裂纹扩展速率曲线,揭示温度与应力比对疲劳裂纹扩展的影响规律。结果表明,在相同应力比下,室温与高温150 ℃下的疲劳裂纹扩展速率曲线(da/dN-ΔK)基本一致,低温-70 ℃下的疲劳门槛值与疲劳裂纹扩展速率明显提高,这表明低温环境下6061铝合金材料具有较高的抗疲劳裂纹扩展性能;在相同温度下,随着应力比的增大,疲劳门槛值降低,疲劳裂纹扩展速率升高。讨论了温度与应力比对疲劳裂纹扩展行为影响的可能原因。     

基于有限元方法的疲劳裂纹闭合行为

裂纹闭合行为将很大程度改变疲劳裂纹扩展行为。针对316L不锈钢,结合常幅加载和单个拉伸过载试验和动态数值模拟方法,对疲劳裂纹扩展行为中的裂纹闭合现象开展了一系列研究工作。详细对比了不同扩展阶段的裂纹闭合行为随裂纹长度、应力比和过载影响因素的变化,以及对裂纹扩展速率的影响。同时,研究了单个拉伸过载和裂纹闭合行为之间的内在联系和机理。结合裂纹闭合理论和有限元计算结果,等效应力强度因子被用来描述316L不锈钢的裂纹扩展过程,并提出316L不锈钢的裂纹扩展速率的预测模型。     

一种新型的低周疲劳裂纹扩展速率模型

基于低周疲劳裂纹扩展机制,假设裂纹尖端循环塑性区内应变分布服从HRR理论解,利用裂纹尖端锐化、钝化启裂低周疲劳裂纹扩展机制,结合Ramberg-Osgood循环应力应变曲线和Manson-Coffin疲劳寿命曲线等断裂力学理论,推导出一种新的低周疲劳裂纹扩展速率数学模型.与30Cr1Mo1V和St-4340的低周疲劳裂纹扩展速率试验数据进行对比,结果表明该低周疲劳裂纹扩展速率模型能够较好地预测材料的低周疲劳裂纹扩展速率.     

基于直流电压降法的传热管疲劳裂纹扩展速率测量

介绍了基于直流电压降法测量蒸汽发生器传热管690合金轴向疲劳裂纹扩展速率的销加载拉伸方法.该方法与其他方法相比较,可以直接采用原始管状材料,在线连续测量管状试样在不同应力强度因子下的疲劳裂纹扩展.通过对标准紧凑拉伸试样的类比分析,建立传热管试样的销加载拉伸模型,并对该模型进行电学和力学有限元模拟分析,确定直流电压降数据采集方法.验证试验采用核电蒸汽发生器用690合金传热管,分别研究了室温和高温325℃空气中载荷和温度对材料疲劳裂纹扩展速率的影响,试验结果采用Paris-Erdogan公式进行拟合,吻合度较好.扫描电镜下观察端口形貌,疲劳裂纹的扩展为穿晶形式,在穿晶断口上观察到明显的疲劳辉纹和微塑性区.     

车轮钢程序谱载疲劳裂纹扩展性能研究

借助MTS TESTSTAR材料试验机的TESTWARE应用软件，建立了程序谱疲劳裂纹扩展试验程序。用该方法测试了HDSA车轮过载疲劳和程序谱疲劳裂纹扩展速率。试验结果表明，过载使裂纹扩展停滞，递增、递减程序谱疲劳裂纹扩展速率明显加快，列车运行中连续急刹车方式对车轮使用寿命不利。     

航空用超高强度钢中夹杂物导致疲劳裂纹萌生与扩展的微观行为

采用扫描电镜原位观测的方法,跟踪观察了低周疲劳载荷下航空用超高强度钢MA250中夹杂物导致裂纹萌生与扩展的微观行为,得到了MA250钢低周疲劳裂纹萌生与扩展的基本特性,讨论了精确测定MA250钢疲劳裂纹扩展速率的方法.     

316L不锈钢的疲劳裂纹扩展行为试验

 工程构件普遍承受疲劳载荷,从而导致疲劳失效。针对由316L不锈钢制成的标准紧凑拉伸试样,开展了一系列疲劳裂纹扩展试验。试验内容包括不同应力比下的常幅加载和在常幅加载过程中引入单个拉伸过载峰。试验结果表明：316L不锈钢具有很强的应力比效应,裂纹扩展速率随应力比的增大而增大。在引入单个拉伸过载峰后,观察到出现迟滞效应前发生了短暂的加速扩展现象。通过一种新的双参数模型来描述材料的应力比效应,并使用改进的Wheeler模型对过载后的裂纹扩展行为进行预测。预测结果表明：该方法能够更好地描述不同工况下316L不锈钢的疲劳裂纹扩展行为。     

热处理钢轨残余应力对疲劳裂纹扩展速率的影响

钢轨残余应力对其疲劳性能影响较大,文章采用回火试验和金相分析方法,研究了不同残余应力值对U75V热处理钢轨疲劳裂纹扩展速率的影响。通过回火试验,分析不同回火时长对钢轨残余应力的影响,得出随着回火时间的增加残余应力逐渐减小;通过对回火工艺处理后的钢轨进行金相组织检测,观察不同回火时长的钢轨金相组织,分析疲劳裂纹尖端处裂纹扩展路径,根据裂纹扩展的方式与长度来分析不同回火时长对疲劳裂纹扩展速率的影响;通过回火工艺控制,可有效降低钢轨残余应力,进而有效地降低钢轨裂纹扩展速率,提高钢轨抗疲劳性能。     

Frequency and wave-form effects on the fatigue crack growth behavior of alloy 718 at 298 K and 823 K

The fatigue crack growth rate (FCGR) of Alloy 718 was measured on CT type specimens at 298 and 823 K. At 823 K, the influence of frequency was studied in the range between 5 – 10^-3 Hz and 20 Hz, using a sinusoidal wave form signal. A substantial increase in FCGR occurred, particularly at low stress intensity levels, as the temperature was increased from 298 to 823 K and as the frequency was decreased at 823 K. At elevated temperature, the effect of cyclic stress wave form was equally investigated, using triangular and square wave form signals producing the same frequency of 5.10^-2 Hz. The triangular load led to higher FCGR than the square wave form. In addition the hold time of 10 s both at the maximum and the minimum load associated with the square load had no significant effect on the FCGR. Electron microscopy was used to observe the substructures that developed ahead of fatigue cracks. These observations showed that in certain circumstances plastic deformation proceeded by the propagation of planar bands which were identified as twins. At room temperature, twinning was found to be abundant only in the threshold regime. At 823 K, twinning was observed in the domain of higher FCGR, particularly at low frequencies. Fractography was carried out to study the micromechanisms of crack propagation. At 823 K. intergranular cracking occurred as the frequency was decreased. The comparison between the substructures formed in low cycle fatigue and those associated with the plastic zones of propagating cracks is made. The importance of planar deformation and twinning on intergranular cracking and on the acceleration of FCGR when the loading rate is decreased at 823 K, is discussed.     

Fatigue of annealed and cold worked stable and unstable stainless steels

Fatigue crack growth rates (FCGR) in AISI 301 and 302 austenitic stainless steel alloys have been measured in controlled load cycles withR = 0.05. Both annealed and cold rolled conditions were examined. The austenite phase of the AISI 301 alloy was unstable under stress and transformed martensitically to α′ to a much greater extent than the AISI 302 alloy. At low values of mean stress the unstable alloy had a lower FCGR than the more stable 302 alloy. The FCGR increased with mean stress until values of mean stress ⪞70 MPa, where the FCGR was independent of mean stress and was the same for both alloys. Various metallographic and macroscopic measurements were made to try to understand this behavior. It was concluded that residual compressive stress due to transformation at the crack tip was responsible for the lower crack growth rates of the unstable 301 alloy. Cold worked specimens had significantly lower crack growth rates than the annealed specimens, and both alloys behaved identically. Formerly with the Department of Metallurgy, University of Illinois at Urbana-Champaign     

Influence of strain-induced martensitic transformations on fatigue crack growth rates in stainless steels

The fatigue crack growth rates (FCGR) of two unstable austenitic stainless steels (Fe-16 Cr-13Ni) and (Fe-18Cr-6.5Ni-0.19C) were determined in theM_s-M_d temperature range where a strain induced μ → α′ martensitic transformation occurs near the crack tip. These FCGR were compared to the rates measured in the stable austenitic phase of a Fe-31.5Ni and a Fe-34 Ni alloy and in the martensitic phase obtained by quenching the Fe-31.5 Ni alloy below M_s. In the Fe-31.5 Ni, the FCGR are an order of magnitude higher in the martensitic than in the austenitic structures for ΔK ≤ 40 ksi in. The FCGR of the stainless steels decrease markedly when the test temperature approachesM _s in theM _s - M_d range. The FCGR for the alloy Fe-18Cr-6.5 Ni-0.19 C in a warm-worked condition are consistently higher than for the same alloy in the annealed condition for ΔK ≤ 40 ksi √in.. The results are discussed in terms of the influence of phase structures, stacking fault energy and work hardening exponent on the FCGR.     

Fatigue crack growth behavior in inconel 706 at 297 K and 4.2 K

The near-threshold fatigue crack growth rate (FCGR) behavior of Inconel 706 was investigated at ambient (297K) and liquid helium (4.2 K) temperatures, respectively. Specimen orientation did not affect the FCGR properties of Inconel 706. At 297 K, a significant influence of R-ratio on the rates of crack propagation was observed while at 4.2 K, the R -ratio effect was minimal. The extent of oxide-induced crack closure was shown to be insignificant in influencing near-threshold crack growth kinetics of Inconel 706 at both temperatures of 297 and 4.2 K. Roughness-induced crack closure was believed to be the dominant mechanism responsible for the influence of R -ratio on the FCGR properties of Inconel 706; this was proved quantitatively by direct crack closure measurements conducted at 297 and 4.2 K. A greater degree of roughness-induced crack closure was observed at 297 K than at 4.2 K; this correlated with the more pronounced R-ratio effect at 297 K. Decreasing the temperature from 297 to 4.2 K decreased the growth rates of fatigue cracks in Inconel 706. The effect of temperature on crack propagation behavior increased with increasing R-ratio. Crack closure could not rationalize this temperature effect. Moreover, the increase in material strength or Young's modulus on cooling from 297 to 4.2 K could not totally account for the influence of temperature on the near-threshold FCGR properties. Dislocation dynamics appears to offer a qualitative explanation for this temperature effect.     

Effect of Environment on Fatigue and Creep Crack Growth in Inconel X-750 at Elevated Temperature

The fatigue crack growth rates (FCGR) of Inconel X-750 were measured in air and in vacuum at 25 °C and 650 °C as a function of test frequency. The wave shape was triangular and the frequency varied from 10 Hz to 0.01 Hz. The creep crack growth rates (CCGR) were also measured on single edge notch specimens at 650 °C in air and in purified argon. For a givenAK, the FCGR increases when temperature increases and frequency decreases. At low frequency the FCGR approach the creep crack growth rates. The mode of fracture changes from transgranular at 10 Hz to intergranular at 0.01 Hz. The effect of air environment is to accelerate the transition from transgranular to intergranular fracture modes with decreasing frequency. The role of oxidation in accelerating crack growth rate in fatigue and in creep is discussed in detail. F. GABRIELLI, was formerly a visiting scientist at Massachusetts Institute of Technology.     

Interactions between mechanical and environmental variables for short fatigue cracks in a 2024-T3 aluminum alloy in 0.5M NaCl solutions

An investigation of the interactions between mechanical and environmental variables on the shortfatigue-crack growth rate (FCGR) for a 2024-T3 aluminum alloy in 0.5M NaCl solution was carried out. Fatigue-crack growth tests were performed under a constant stress-intensity-factor range (‡K) control using single-edge-cracked tension specimens. The relationship between FCGR and crack length (0.5 to 15 mm) was determined at a cyclic frequency of 10 Hz over six ΔK levels (4,5,6,7, 8, and 10 ), two load ratios (R) (0.1 and 0.5), and three dissolved oxygen concentrations (0, 7, and 30 ppm). Tests in gaseous environments (namely, high-purity oxygen) were also conducted for comparison. Short-crack effects were observed, with the FCGR in the short-crack regime accelerated by as much as a factor of 2. The observed crack-size effects tend to appear only at the lower loading levels (ΔK<10 and R=0.1) and are more pronounced at higher oxygen levels. Fractographic examinations suggested that hydrogen embrittlements is responsible for the environmental enhancement of the FCGR for both short and long cracks in this material/environment system. A transport model was developed to estimate the crack-tip oxygen concentration and to examine its correlation to changes in the FCGR with crack length. The model correctly accounted for the decrease in short-crack effect on the FCGR with crack length under a given mechanical condition at each oxygen level, but did not explain the disappearance of short-crack effects at ΔK≥10 .     

Interactions between mechanical and environmental variables for short fatigue cracks in a 2024-T3 aluminum alloy in 0.5M NaCl solutions

An investigation of the interactions between mechanical and environmental variables on the short-fatigue-crack growth rate (FCGR) for a 2024-T3 aluminum alloy in 0.5M NaCl solution was carried out. Fatigue-crack growth tests were performed under a constant stress-intensity-factor range (ΔK) control using single-edge-cracked tension specimens. The relationship between FCGR and crack length (0.5 to 15 mm) was determined at a cyclic frequency of 10 Hz over six ΔK levels (4, 5, 6, 7, 8, and 10 MPa ), two load ratios (R) (0.1 and 0.5), and three dissolved oxygen concentrations (0, 7, and 30 ppm). Tests in gaseous environments (namely, high-purity oxygen) were also conducted for comparison. Short-crack effects were observed, with the FCGR in the short-crack regime accelerated by as much as a factor of 2. The observed crack-size effects tend to appear only at the lower loading levels (ΔK<10 MPa and R=0.1) and are more pronounced at higher oxygen levels. Fractographic examinations suggested that hydrogen embrittlement is responsible for the environmental enhancement of the FCGR for both short and long cracks in this material/environment system. A transport model was developed to estimate the crack-tip oxygen concentration and to examine its correlation to changes in the FCGR with crack length. The model correctly accounted for the decrease in short-crack effect on the FCGR with crack length under a given mechanical condition at each oxygen level, but did not explain the disappearance of short-crack effects at ΔK≥10 MPa .     

Fatigue crack growth mechanisms in Ti6242 lamellar microstructures: Influence of loading frequency and temperature

Fatigue crack growth experiments were carried out on Ti6242 alloy with large colony size. The alloy was heat treated to provide three different lamella size; fine, coarse, and extra coarse. Tests were conducted at two temperatures, 520 °C and 595 °C, using two loading frequencies, 10 and 0.05 Hz. The latter frequency was examined with and without a 300-second hold time. All tests were performed in air environment and at a stress ratio of 0.1. This study shows that at 520 °C, the Fatigue crack growth rate (FCGR) is not significantly influenced by changes in the microstructure. For 0.05 Hz/low ΔK, however, the FCGR is higher in the fine lamellar microstructure and is accompanied by- the appearance of a plateau, which disappears in the extra large lamella microstructure. Furthermore, the addition of a 300-second hold time does not alter the crack growth rate. At 595 °C, while the general level of the FCGR is higher than that at 520 °C, the effects of loading frequency and hold time remain similar to those reported at the lower temperature. Unlike the results at 520 °C, however, the FCGR at low δK is not influenced by variations in lamellar microstructure. Under all test conditions, the fatigue process is predominantly controlled by one single mechanism associated with transcolony fracture and formation of quasi-cleavage facets. The fatigue crack growth results and the associated fracture behavior as obtained in this study are correlated to the crack-tip shear activity and transmission at the α/β interfaces. A general hypothesis accounting for the role of loading frequency, temperature, and microstructure on the observed cracking mechanisms is presented.     

Effect of Hf and Zr Contents on Stress-rupture and Fatigue Crack Growth Rate Performances in FGH96PM Superalloy

Four experimental FGH96alloys with various contents of Hf and Zr(0and 0.04%,0.3% and 0.04%,0.6% and 0.04%,0.3%and 0.06%,respectively)were produced using PREP(plasma rotating electrode process)+HIP(hot isostatic pressing)route.The unnotched and notched stress-rupture properties and fatigue crack growth rate(FCGR)of all the experimental alloys were investigated to study the effect of Hf and Zr.Relevant fracture morphology and microstructure were observed by scanning electron microscopy and transmission electron microscopy.The results revealed that appropriate content of Hf could lengthen stress-rupture life,eliminate notch sensitivity and slower FCGR.Microstructure analysis showed that the amount ofγ′phase should be increased or decreased by adjusting Hf and Zr contents,and MC carbide and oxide coupled growth should be increased by adding Hf content,which caused oxycarbide to precipitate along grain boundary and strengthen the alloy.It was found that excessive Zr in Hfcontaining FGH96alloy had certain deleterious effects on stress-rupture property because there was strong Zr segregation at prior particle boundary,leaving a long chain of large-size oxides along the boundary.The optimal content of Hf and Zr in FGH96alloy was 0.6%and 0.04%,respectively.     

The orientation dependence of fatigue-crack growth in 8090 Al-Li plate

A series of fatigue-crack growth rate (FCGR) tests was carried out on 8090 Al-Li plate to examine the effects of specimen orientation on fatigue-crack growth. The directionality of fatigue fracture behavior is found to be related to the strong {110}〈112〉 texture in this alloy. Based on a previously developed transgranular FCGR model using restricted slip reversibility (RSR) concepts, [1] a mechanistic model is developed for transgranular fatigue-crack growth in highly textured materials. The model takes the form of the Paris relationship with a power law exponent of 3, and the material texture is shown to strongly influence the proportional factor. The effect of texture on FCGR is related through a geometric factor cos² ϕ, where ϕ defines the angle between the load axis and the normal of the favorable slip plane. The effect of specimen orientation on FCGR in 8090 Al-Li alloy is shown to be related to a combination of its anisotropic mechanical properties and the variation of angleϕ with specimen orientation. The model further predicts that fatigue-crack growth rates will be slower in many textured materials than texturefree materials becauseϕ > 0 and cos₂ ϕ < 1.