Study of fatigue crack growth rate for austenitic Fe-Al-Mn alloys

A study was made of the crack growth rate (da/dN) versus stress-intensity variation ΔK behavior of Fe-Al-Mn alloys with different percentages of carbon, aluminum, and manganese at ambient temperature. The experimental results are described with respect to a Paris equation,da/dN = C(†K)ⁿ, where the exponent n, index for crack growth resistance of materials, was strongly influenced by alloy composition. It was found that higher manganese content provided better crack growth resistance, and that carbon and aluminum had an opposite effect. Scanning electron microscopy, x-ray diffraction, and mechanical properties evaluation were performed and correlated to the change of n values.     

Corrosion-fatigue crack growth in titanium alloys

Fatigue crack growth data in the form of a da/dN-ΔK-curve can be used for component design and for prediction of residual lifetime. High-strength titanium alloys have proven themselves in aerospace applications and are being seriously considered for use in automotive technology. Depending on the type of alloy (α, (α +β)- or metastable β-), microstructure and/or texture development reacts differently to thermomechanical processing, which is reflected in the mechanical properties. Fatigue crack growth in titanium can be more strongly affected by changes in microstructure than in steels or aluminum alloys. This depends in part on the anisotropic nature of the hexagonal α-phase and in part on the extreme variation in microstructural morphologies (lamellar or equiaxed) which can be present in certain high-strength titanium alloys. Such effects can be exacerbated under the influence of a corrosive environment. The influence of loading frequency must be taken into account when corrosion-fatigue crack growth is considered. While high-strength (α + β)-alloys react sensitively to the effect of loading frequency, α- and metastable β-alloys tend to be insensitive. This behavior can be explained with the differing consequences of an increased level of hydrogen ahead of a crack tip.     

Superior fatigue crack growth resistance, irreversibility, and fatigue crack growth–microstructure relationship of nanocrystalline alloys

While previous studies have reported that nanocrystalline materials exhibit poor resistance to fatigue crack growth (FCG), the electro-deposited nanocrystalline Ni–Co alloys tested in this paper show superior resistance to FCG. The high damage tolerance of our alloy is attributed to the following: alloying with Co, low internal stresses resulting in stability of the microstructure, and a combination of high strength and ductility. The high density of grain boundaries interact with the dislocations emitted from the crack tip, which impedes FCG, as predicted by the present model and measured experimentally by digital image correlation. Further, the addition of Co increases the strength of the material by refining the grain size, reducing the fraction of low angle grain boundaries, and reducing the stacking fault energy of the material, thereby increasing the prevalence of twinning. The microstructure is stabilized by minimizing the internal stress during a stress relief heat treatment following the electro-deposition process. As a result grain growth does not occur during deformation, leaving dislocation-mediated plasticity as the primary deformation mechanism. The low internal stresses and nanoscale twins preserve the ductility of the material, thereby reaching a balance between strength and ductility, which results in a superior resistance to FCG.     

The turning point in Paris region of fatigue crack growth in titanium alloy

通过对比钛合金不同显微组织下疲劳裂纹扩展速率Paris区转折点的位 置, 发现原始β晶粒尺寸是影响Paris区转折点位置的主要因素, 晶 团尺寸以及片层厚度对转折点位置没有影响. 并且通过分析转折点前、后 疲劳裂纹扩展微观阶段的转变及断裂方式变化, 得出转折点的出现是 疲劳裂纹尖端塑性区尺寸超过晶粒尺寸所致. 具有β晶粒的马氏体组 织疲劳裂纹扩展速率Paris区并不存在转折点, 说明转折点的出现不仅仅是 由于原始β晶粒的存在, 还和显微组织类型有关. 通过分析还发现, 钛合金片层组织中裂纹尖端塑性区实际尺寸大于计算得到的单向塑性 区尺寸以及循环塑性区尺寸.     

Interface effects on crack deflection and bridging during fatigue crack growth of titanium matrix composites

The effect of the interface on the crack deflection and crack bridging behavior of continuous fiber-reinforced titanium matrix composites has been investigated using three interfaces with significantly different mechanical characteristics. Each of these composites exhibited stress ranges in which fiber bridging was present and stress ranges in which stable fiber bridging was not present. The fatigue crack growth rate for all composites, even for the ones that did not exhibit fiber bridging was significantly below that of the matrix. This phenomenon, believed to be an effect of elastic crack shielding, was most significant for composites with the strongest interfacial bond. Interface failure ahead of the crack tip and its influence on the local stress intensity factor is believed to be responsible for the decrease in the shielding effect of low strength interfaces. Interface debonding was observed in all three composites, and damage to the interface ahead of the crack tip was seen in two of the three composites. A stress-based criterion for predicting debonding appeared to effectively explain the crack deflection behavior for the three composites. Evidence of crack deflection even for the strongest interface suggests that there is scope to increase the interface bond strength in SiC/Ti-alloy system for improved transverse properties without compromising the fatigue life.     

Fretting fatigue studies of titanium nitride-coated biomedical titanium alloys

Fretting fatigue is an adhesive wear mechanism caused by repetitive tangential micro-oscillation between two contacting materials pressed together under cyclic load. Bioimplants, such as hip joints and bone plates, are prone to undergo fretting fatigue failures during their service within the body. This article presents the fretting fatigue damage characterization of physical vapor deposition (PVD) TiN-coated biomedical titanium alloys (Ti-6Al-4V and Ti-6Al-7Nb) subjected to cyclic loads. The PVD TiN layer delayed the damage because of superior tribological properties compared with uncoated alloys. Delamination and abrasive wear damage of TiN at contact caused failure of the alloy. Friction coefficient curves of the PVD TiN-coated pair showed an irregular pattern caused by the influence of wear particulates and Ringer fluid at the contact.     

Derivation of closure-free crack growth rate under biaxial fatigue loading conditions

The present paper develops a new methodology to derive the closure-free (effective) crack growth rate, da/dN, from fatigue life data under biaxial loading conditions using the fracture mechanics approach. The derived da/dN curve showed a good agreement with the measured crack growth rate data for 1045 steel. The method lowers largely the cost and time required to perform the conventional closure-free crack growth tests.     

TC4-DT钛合金片层组织疲劳裂纹扩展速率研究

主要讨论了TC4-DT钛合金不同片层结构的疲劳裂纹扩展速率,试验通过几种不同的热处理工艺获得不同的片层组织结构参数,深入研究了片层组织结构参数对疲劳裂纹扩展速率的影响规律,并对裂纹扩展断口进行了分析。结果表明：双重处理空冷条件获得细片层组织较炉冷条件获得粗片层组织具有较高的疲劳裂纹扩展阻力;多重热处理由于获得的次生α片层,导致不同阶段裂纹扩展机理与双重处理的不同。在相同的第一重处理条件下,多重处理在中速扩展区的裂纹扩展速率较双重刚处理的高。由于次生α片层组织协调性好会加快裂纹的扩展,具有较双重空冷处理较高的裂纹扩展速率。     

航空铝合金搅拌摩擦焊疲劳裂纹扩展速率试验研究

通过高频疲劳实验,对航空铝合金LC4CS和7075-T6搅拌摩擦焊预制裂纹穿焊缝中心、预制裂纹穿焊缝前进边、预制裂纹穿焊缝后退边、预制裂纹垂直于焊缝四种形式的焊接接头疲劳性能进行了研究,LC4CS铝合金FSW接头抗疲劳裂纹扩展能力不如7075-T6铝合金搅拌摩擦焊接接头,但是相差不大.IIW疲劳试验设计标准对于FSW接头是比较保守的.该实验为建立合理的搅拌摩擦焊接接头的疲劳评定规范提供重要依据,从而推动了搅拌摩擦焊接技术在航天领域的广泛应用.     

Effects of dislocation dynamics and microstructure on crack growth mechanisms in two-phase titanium aluminide alloys

The fracture behaviour of two-phase titanium aluminide alloys was characterized by fracture toughness tests performed in a wide temperature range on chevronnotched three point bending bars. Temperature and rate dependent deformation processes were characterized by temperature and strain rate cycling tests. The alloy investigated had compositions and microstructures which are currently being considered for engineering applications. The paper considers the effects of microstructure and crack tip plasticity on the crack growth resistance. The temperature dependence of the fracture toughness was rationalized in terms of micro-processes which determine the glide resistance of the dislocations in the plastic zone of crack tips. The implications of such observations for the engineering application of the materials are addressed briefly.     

时效时间对7075铝合金疲劳裂纹扩展速率的影响

采用透射电镜、显微硬度仪、拉伸试验和疲劳试验等研究了 7075铝合金在欠时效(120℃×8 h)、峰时效(120℃×24 h)与过时效(120℃×48 h)状态下的微观组织、硬度、拉伸性能方面与疲劳裂纹扩展速率方面的差异.结果表明:3种时效状态的合金在高低应力强度因子范围时,疲劳裂纹扩展速率呈现不同的规律.在低应力强度...     

Effects of precipitates on fatigue crack growth rate of AA 7055 aluminum alloy

The effects of precipitates on the fatigue crack growth rate of AA 7055 Al alloy subjected to different ageing treatments were investigated using transmission electron microscope and fatigue crack growth testing.The results show that the T77 treated samples exhibit the lowest crack growth rate,while the crack growth rate of over-aged samples is the highest.In terms of the model based on the reversibility of dislocation motion within the plastic zone close to the crack tip,the improved crack growth resistance is attributed to many precipitates that are coherent with Al matrix in the under-aged and T77 treated samples.When the precipitate is coherent with the Al matrix,the larger the precipitate is,the slower the fatigue crack grows.The effects of grain boundary precipitates and precipitate free zone on the fatigue crack growth resistance are less significant than those of precipitates within grains of the alloy.     

The effects of gas nitriding on fatigue behavior in titanium and titanium alloys

Fatigue behavior has been studied on gas-nitrided smooth specimens of commercial pure titanium, an alpha/beta Ti-6Al-4V alloy, and a beta Ti-15Mo-5Zr-3Al alloy under rotating bending, and the obtained results were compared with the fatigue behavior of annealed or untreated specimens. It was found that the role of the nitrided layer on fatigue behavior depended on the strength of the materials. Fatigue strength was increased by nitriding in pure titanium, while it was decreased in the Ti-6Al-4V and Ti-15Mo-5Zr-3Al alloys. Based on detailed observations of fatigue crack initiation, growth, and fracture surfaces, the improvement and the reduction in fatigue strength by nitriding in pure titanium and both alloys were primarily attributed to enhanced crack initiation resistance and to premature crack initiation of the nitrided layer, respectively.