Influence of high-speed milling parameter on 3D surface topography and fatigue behavior of TB6 titanium alloy

High-speed milling of titanium alloys is widely used in aviation and aerospace industries for its high efficiency and good quality.In order to optimize the machining parameters in high-speed milling TB6 titanium alloy,experiments of high-speed milling and fatigue were conducted to investigate the effect of parameters on 3D surface topography and fatigue life.Based on the fatigue fracture,the effect mechanism of surface topography on the fatigue crack initiation was proposed.The experiment results show that when the milling speed ranged from 100 m/min to 140 m/min,and the feed per tooth ranged from 0.02 mm/z to 0.06 mm/z,the obtained surface roughness were within the limit（0.8 μm）.Fatigue life decreased sharply with the increase of surface equivalent stress concentration factor.The average error of fatigue life between the established model and the experimental results was 6.25%.The fatigue cracks nucleated at the intersection edge of machined surface.

High cycle fatigue behavior of the second generation single crystal superalloy DD6

The second generation single crystal superalloy DD6 with 0.10%Hf and 0.34%Hf （in mass fraction） was subjected to high-cycle fatigue （HCF） loading at temperatures of 700 ℃ in ambient atmosphere. SEM was used to determine the initiation site and the failure mechanism. Evolution of the microstructure was investigated by TEM observation. The results show that fatigue limit of DD6 alloy with 0.34%Hf is a little smaller than that of the alloy with 0.10%Hf. The fatigue cracks initiated on the surface or near the surface of the specimens. The crack would propagate along { 111 } octahedral slip planes, rather than perpendicular to the loading axis of specimen. Typical fatigue striation formed in steady propagation of fatigue crack. The fracture mechanisms of the high cycle fatigue of DD6 alloys with 0.10%Hf and 0.34%Hf are quasi-cleavage fracture. Different types of dislocation structures were developed during high cycle fatigue deformation.

Fatigue Crack Growth Rate of Ti-6Al-4V Considering the Effects of Fracture Toughness and Crack Closure

Fatigue fracture is one of the main failure modes of Ti-6A1-4V alloy,fracture toughness and crack closure have strong effects on the fatigue crack growth（FCG）rate of Ti-6A1-4V alloy.The FCG rate of Ti-6A1-4V is investigated by using experimental and analytical methods.The effects of stress ratio,crack closure and fracture toughness on the FCG rate are studied and discussed.A modified prediction model of the FCG rate is proposed,and the relationship between the fracture toughness and the stress intensity factor（SIF）range is redefined by introducing a correcting coefficient.Notched plate fatigue tests（including the fracture toughness test and the FCG rate test）are conducted to investigate the influence of affecting factors on the FCG rate.Comparisons between the predicted results of the proposed model,the Paris model,the Walker model,the Sadananda model,and the experimental data show that the proposed model gives the best agreement with the test data particularly in the near-threshold region and the Paris region,and the corresponding calculated fatigue life is also accurate in the same regions.By considering the effects of fracture toughness and crack closure,the novel FCG rate prediction model not only improves the estimating accuracy,but also extends the adaptability of the FCG rate prediction model in engineering.

Influence of Ultrasonic Surface Rolling Process and Shot Peening on Fretting Fatigue Performance of Ti-6Al-4V

At present,there are many studies on the residual stress field and plastic strain field introduced by surface strengthening,which can well hinder the initiation of early fatigue cracks and delay the propagation of fatigue cracks.However,there are few studies on the effects of these key factors on fretting wear.In the paper,shot-peening(SP)and ultrasonic surface rolling process(USRP)were performed on Ti-6Al-4V plate specimens.The surface hardness and residual stresses of the material were tested by vickers indenter and X-ray diffraction residual stress analyzer.Microhardness were measured by HXD-1000MC/CD micro Vickers hardness tester.The effects of different surface strengthening on its fretting fatigue properties were verified by fretting fatigue experiments.The fretting fatigue fracture surface and wear morphology of the specimens were studied and analyzed by means of microscopic observation,and the mechanism of improving fretting fatigue life by surface strengthening process was further explained.After USRP treatment,the surface roughness of Ti-6Al-4V is significantly improved.In addition,the microhardness of the specimen after SP reaches the maximum at 80μm from the surface,which is about 123%higher than that of the AsR specimen.After USRP,it reaches the maximum at 150μm from the surface,which is about 128%higher than that of AsR specimen.It is also found that the residual compressive stress of the specimens treated by USRP and SP increases first and then decreases with the depth direction,and the residual stress reaches the maximum on the sub surface.The USRP specimen reaches the maximum value at 0.18 mm,about−550 MPa,while the SP specimen reaches the maximum value at 0.1 mm,about−380 MPa.The fretting fatigue life of Ti-6Al-4V effectively improved after USRP and SP.The surface integrity of specimens after USRP is the best,which has deeper residual compressive stress layer and more refined grain.In this paper,a fretting wear device is designed to carry out fretting fatigue experiments on specimens with different surface strengthening.

Influence of laser peening on microstructure and fatigue lives of Ti-6Al-4V

The influence of low energy laser peening on fatigue lives of Ti-6Al-4V was investigated. Laser peening was carried out on Ti-6Al-4V samples. Laser peened samples were characterized by residual stress analysis, surface roughness measurements, X-ray diffraction, optical microscopy, nanoindentation hardness tests, scanning and transmission electron microscopy and fatigue testing. Laser peening resulted in the formation of nanocrystallites on the surface and near surface regions with associated increase in hardness and introduction of compressive residual stress. Owing to positive influence of nanostructured surface and compressive residual stress, fatigue lives of the laser peened samples were significantly increased compared to the unpeened samples.

Fatigue Property of Additively Manufactured Ti-6Al-4V under Nonproportional Multiaxial Loading

The low cycle fatigue strength properties of the additively manufactured Ti-6Al-4V alloy are experimentally investi-gated under proportional and nonproportional multiaxial loading.The fatigue tests were conducted using hollow cylinder specimens with and without heat treatments,at room temperature in air.Two fatigue tests were conducted:one for proportional loading and one for nonproportional loading.The proportional loading was represented by a push-pull strain path(PP)and the nonproportional loading by a circle strain path(Cl).The failure lives of the additively manufactured specimens were clearly reduced drastically by internal voids and defects.However,the sizes of the defects were measured,and the defects were found not to cause a reduction in fatigue strength above a critical size.The fracture surface was observed using scanning electron microscopy to investigate the fracture mechanisms of the additively manufactured specimens under the two types of strain paths.Different fracture patterns were recognized for each strain paths;however,both showed retention of the crack propagation,despite the presence of numerous defects,probably because of the interaction of the defects.The crack propagation properties of the materials with numerous defects under nonproportional multiaxial loading were clarified to increase the reliability of the additively manufactured components.

Coordinately Improving the Wear and Fatigue Properties of Ti6Al4V Alloy by Designed CrZr-alloyed Layer

A CrZr-alloyed layer was prepared through a pre-zirconizing and subsequent chromizing treatment on a Ti6Al4V substrate.After the removal of the top Cr deposit and Ti4Cr layers,a（Cr,Zr）-Ti solidsolution layer was obtained.The microstructure,composition,microhardness and toughness of the（Cr,Zr）-Ti solid-solution layer were evaluated.The results showed that the pre-addition of Zr played an important role in inhibiting the precipitation of the soft Ti4Cr phase,which in turn allowed us to obtain a material characterized by a remarkable hardness.Wear and fatigue tests showed that the（Cr,Zr）-Ti solid-solution layer could coordinately improve the properties of the Ti6Al4V alloy.This was mainly due to the good match of hardness and toughness of the（Cr,Zr）-Ti solid-solution layer.In addition,the gradual change in composition and mechanical properties was conducive to the coordinated deformation between the（Cr,Zr）-Ti solid-solution layer and the Ti6Al4V substrate during fatigue tests.This reduced the stress concentration in correspondence of the interface between the two materials.

Using Cavitation Peening to Improve the Fatigue Life of Titanium Alloy Ti-6Al-4V Manufactured by Electron Beam Melting

Although Electron Beam Melting (EBM) is an innovative technology, the fatigue properties of materials manufactured by EBM may be lower than those of casted and wrought materials due to defects and surface roughness. In order to enhance the fatigue life of components or structures manufactured by EBM, a mechanical surface treatment technology, e.g., peening, would be effective because peening introduces high compressive residual stress at the surface which can extend the fatigue life considerably. In the present study, specimens were manufactured by EBM using titanium alloy Ti-6Al-4V powder. Two types of specimens were prepared: as-built and as-machined specimens. Specimens of each type were treated by cavitation peening or shot peening. The fatigue lives of the specimens were evaluated by a plate bending fatigue tester. The residual stress and surface roughness were also evaluated. The results obtained showed that the fatigue strength of as-built specimens can be improved by 21% by cavitation peening or shot peening, and the fatigue life under particular applied stresses can also be extended by 178% by cavitation peening.

Study on the Overload and Dwell-Fatigue Property of Titanium Alloy in Manned Deep Submersible

With the rapid development of ocean technology, the deep-sea manned submersible is regarded as a high-tech equipment for the exploration and exploitation of ocean resources. The safety of manned cabin has a decisive effect on the whole system. Ti-6 Al-4 V with the superior strength-to-weight ratio and corrosion resistance has been used for the manned cabin. The manned cabin experiences loading spectrum with different maximum stresses and different dwell time during their service life. The load sequence effects on dwell fatigue crack growth behavior of Ti-6 Al-4 V under different dwell time are investigated experimentally in this paper. The experimental results show that the crack tip plastic zone is enlarged by the dwell time and the overload retardation zone increases with dwell time under the same overload rate. A dwell fatigue crack growth model is proposed by modifying the crack tip plastic zone under the loading history with combinations of the single overload and dwell time factors are included in the modified model. Based on the experimental data, the overload retardation zone and the crack growth rates of Ti-6 Al-4 V are predicted by the modified model. A reasonable model for the load sequence effect on the dwell fatigue crack growth rates of Ti-6 Al-4 V is verified.

渗碳工艺对18CrNiMo7-6合金钢缺口件疲劳性能的影响

为分析渗碳工艺对18CrNiMo7-6缺口构件疲劳性能的影响,对应力集中系数Kt=1.86的缺口试样进行渗碳热处理并测定其旋转弯曲疲劳性能,同时对试样表层组织、硬度以及应力场进行了表征。结果表明,渗碳热处理可以明显提升试样表面硬度并引入残余压应力,并且可以显著提升缺口试样的疲劳性能,相较于未渗碳试样疲劳极限提升超过100%;随着有效硬化层深度的增加,缺口试样的疲劳极限均呈现先增后减的趋势。未渗碳试样和渗碳试样的疲劳源均在缺口根部表面处,且均为多源断裂。疲劳过程中渗碳试样表面残余奥氏体在循环应力作用下诱导马氏体相变,其转变量存在一个临界值。

Effects of laser shock processing,solid solution and aging,and cryogenic treatments on microstructure and thermal fatigue performance of ZCuAl_(10)Fe_(3)Mn_(2)alloy

The materials used in variable temperature conditions are required to have excellent thermal fatigue performance.The effects of laser shock processing(LSP),solid solution and aging treatment(T6),and cryogenic treatment(CT)on both microstructure and thermal fatigue performance of ZCuAl_(10)Fe_(3)Mn_(2) alloys were studied.Microstructure and crack morphology were then examined by scanning electron microscopy(SEM)and energy-dispersive X-ray spectroscopy(EDS).The result showed that,after being subjected to the combination treatment of T6+CT+LSP,the optimal mechanical properties and thermal fatigue performance were obtained for the ZCuAl_(10)Fe_(3)Mn_(2) alloy with the tensile strength,hardness,and elongation of 720 MPa,300.16 HB,and 16%,respectively,and the thermal fatigue life could reach 7,100 cycles when the crack length was 0.1 mm.Moreover,the ZCuAl_(10)Fe_(3)Mn_(2) after combination treatment shows high resistance to oxidation,good adhesion between the matrix and grain boundaries,and dramatically reduced growth rate of crack.During thermal fatigue testing,under the combined action of thermal and alternating stresses,the microstructure around the sample notch oxidized and became loose and porous,which then converted to micro-cracks.Fatigue crack expanded along the grain boundary in the early stage.In the later stage,under the cyclic stress accumulation,the oxidized microstructure separated from the matrix,and the fatigue crack expanded in both intergranular and transgranular ways.The main crack was thick,and the path was meandering.

S含量对18CrNiMo7-6齿轮钢中夹杂物和疲劳性能的影响

以w[S]为0.002%(低S含量)和0.022%(高S含量)的两种18CrNiMo7-6齿轮钢为研究对象,参照齿轮热处理工艺获得伪渗碳试样,并对其力学性能、显微组织、疲劳性能和夹杂物分布进行了分析表征。结果表明,两种齿轮钢的强度基本相当,而高S含量试验钢具有更好的塑性和低温冲击韧性,并且其疲劳极限、疲劳寿命均优于低S含量试验钢,疲强比由0.445提高到0.479。S含量显著影响钢中的夹杂物分布情况:低S含量试验钢中夹杂物以MnS-Oxide为主,数量较少,同时尺寸更大;而高S含量试验钢夹杂物以CaS-MnS-Oxide复合型夹杂物为主,数量提高1倍以上,但尺寸更为细小。高S含量试验钢采用Ca处理工艺对夹杂物进行改性,夹杂物尺寸明显细化,有利于钢的塑韧性提升,并改善疲劳性能。

Early Crack Propagation Behavior of Laser Metal Deposited Ti-6Al-4V Alloy Under High Cycles Fatigue Loading

The crack initiation and early propagation are of great significance to the overall fatigue life of material.In order to investigate the anisotropic fracture behavior of laser metal deposited Ti-6Al-4V alloy(LMD Ti64)during the early stage,the fourpoint bending fatigue test was carried out on specimens of three different directions,as well as the forged specimens.The results indicate the anisotropic crack initiation and early propagation of LMD Ti64.The direction perpendicular to the deposition direction exhibits a better fatigue resistance than the other two.The crack initiation position and propagation path are dominated by the microstructure in the vicinity of U-notch.LMD Ti64 has a typical small crack effect,and the early crack propagation velocities in three directions are similar.Affected by the slip system of LMD Ti64,secondary cracks frequently occur,which are often found to have an angle of 60°to the main crack.The electron backscatter diffraction analysis indicates that LMD Ti64 has preferred orientations,i.e.,strong 0001//Z texture and 001//Z texture.Their crystallographic orientation will change as the direction of columnarβgrains turns over,resulting in the fatigue anisotropy of LMD Ti64 in crack initiation and early crack propagation process.

Effect of wet shot peening on Ti-6Al-4V alloy treated by ceramic beads

Ti-6Al-4V alloy was processed by wet shot peening with ceramic beads. The effects of the shot peened intensity on the microstructure, surface morphology, and residual stress were investigated. A tensile-tensile fatigue test was performed and the fracture mechanism was proposed. The results demonstrate that the surface roughness after wet shot peening is obviously lower than that after dry shot peening. With the increase of the shot peened intensity, the depth of the residual stress layer increases to 250 ktrn, and the maximum stress in this layer increases to -895 MPa. The fatigue strength also increases by 12.4% because of the wet shot peening treatment. The dislocation density of the surface layer is significantly enhanced after the wet shot peening with ceramic beads. The microstructure of the surface layer is obviously refined into ultra-fine grains.

枸杞多糖和1,6-二磷酸果糖协同抗运动疲劳作用及其机制

目的:研究枸杞多糖与1,6-二磷酸果糖的协同抗疲劳作用,为改善和促进运动员体力恢复、提高训练和比赛成绩提供科学依据。方法:将140只小鼠随机分为空白对照组(生理盐水)、枸杞多糖组(20mg.kg-1)及1,6-二磷酸果糖组(300mg.kg-1),并将两者按2×2表分组,以负重游泳小鼠作为研究抗运动疲劳实验的小鼠模型。检测各组小鼠力竭游泳时间、肝糖原、肌糖原、乳酸脱氢酶(LDH)、超氧化物歧化酶(SOD)、血乳酸(LAC)和血尿素氮(BUN),分析两者协同抗疲劳的效果和机制。结果:与空白对照组比较,枸杞多糖和1,6-二磷酸果糖组小鼠负重游泳时间延长,两者剂量分别为20mg.kg-1和300mg.kg-1时最佳(P<0.01),两者之间存在交互作用。与空白对照组比较,枸杞多糖组小鼠LDH、SOD活力提高(P<0.01),LAC和血BUN水平降低,1,6-二磷酸果糖使小鼠肝糖原和肌糖原的储备量显著提高(P<0.01)。结论:枸杞多糖与1,6-二磷酸果糖配伍能起到协同抗疲劳作用,其原因可能是1,6-二磷酸果糖增加了小鼠的肝糖原和肌糖原的贮备,能够提供更多能量;枸杞多糖提高LDH、SOD活力,加快代谢产物的分解,使小鼠在耐力运动中坚持时间更长。

三维表面粗糙度对18CrNiMo7-6钢旋转弯曲疲劳寿命的影响

目的探究固定载荷下三维表面粗糙度Sa对18CrNiMo7-6钢旋转弯曲疲劳寿命的影响。方法通过砂纸研磨制备不同表面粗糙度及纹理方向的18CrNiMo7-6钢旋转弯曲疲劳试样,测量所有试样的表面粗糙度参数Sa及三维表面形貌参数Sq、Sz、Ssk、Sku。对试样进行旋转弯曲疲劳试验,分析疲劳寿命。结果在相同或相近粗糙度的情况下,轴向纹理疲劳试样疲劳寿命大于周向纹理疲劳试样疲劳寿命。相同纹理方向的情况下,表面三维粗糙度Sa越低,试样疲劳寿命越高。试样疲劳寿命次数与表面粗糙度参数Sa及三维表面形貌参数Sq、Sz、Ssk、Sku均有明显的相关性。结论对于18CrNiMo7-6钢旋转弯曲疲劳试样,拥有平行于疲劳应力的机械加工纹理比垂直于疲劳应力的机械加工纹理具有更小的危害性。降低18CrNiMo7-6试样表面粗糙度,能够有效提高试样旋转弯曲疲劳寿命。纹理方向平行于疲劳应力方向的试样,表面偏斜度Ssk对零件疲劳寿命影响不明显。

腹腔镜胆囊切除术对老年胆囊结石患者术后IL-6、C反应蛋白及疲劳综合征的影响

目的研究腹腔镜胆囊切除术对老年胆囊结石患者术后Il-6、C反应蛋白及疲劳综合征的影响。方法将54例老年胆囊结石患者采用单双号法分为对照组和观察组各27例,其中对照组行开腹胆囊切除术,观察组行腹腔镜胆囊切除术,观察两组患者手术前后Il-6、C反应蛋白水平,并记录疲劳指数变化情况。结果两组患者术前第1天IL-6、C反应蛋白值比较,差异无统计学意义(P>0.05),术后第2天观察组患者的IL-6、C反应蛋白分别为(34.51±5.29)ρ/ng·L-1、(12.67±2.55)ρ/ng·L-1,均较对照组低,差异有统计学意义(P<0.05)。两组患者术后疲劳综合指数均呈明显下降趋势,观察组下降幅度较对照组明显,差异具有统计学意义(P<0.05)。结论采用腹腔镜胆囊切除术治疗老年胆囊结石,能够降低机体应激反应,提高手术治疗质量,值得推广应用。

人参皂甙Rg1与1,6-二磷酸果糖配伍抗疲劳作用的研究

观察人参皂甙Rg1与1,6-二磷酸果糖配伍的抗疲劳效果,寻找最佳配伍剂量。根据雄性清洁级昆明种小鼠按体重随机分为安静对照组、运动对照组、人参皂甙Rg1对照组及4个配伍组。通过析因实验设计分析人参皂甙Rg1与1,6-二磷酸果糖提高运动耐力的效果及两者的交互作用。结果不同剂量人参皂甙Rg1对小鼠力竭游泳时间影响有显著差异(P<0.05)。各配伍组力竭游泳时间均有显著延长,C组延长最显著;与人参皂甙Rg1对照组相比,各配伍组力竭游泳时间均显著降低(P<0.01)。MDA含量A组显著低于运动对照组和D组,与安静对照组相比,各组均升高。SOD/MDA比值A、C组显著高于运动对照组,C组显著高于人参皂甙Rg1对照组,与安静对照组相比,各组均有下降趋势,D组下降最显著(P<0.01)。乳酸脱氢酶C、D组显著低于运动对照组和人参皂甙Rg1对照组(P<0.05)。与运动对照组及人参皂甙Rg1对照组相比,配伍在一定程度上减少心肌、骨骼肌细胞线粒体和其他细胞超微结构损伤。结论:与FDP配伍未能延长小鼠力竭游泳时间,配伍可减轻耐力运动对小鼠心肌和骨骼肌的细胞损害,一定程度上保护线粒体的呼吸功能,缓解细胞缺氧损伤。

频率及应力比对18CrNiMo7-6合金钢疲劳性能的影响

通过旋转弯曲疲劳试验和轴向疲劳试验方法得到了不同试验条件下的S-N曲线,研究了不加载频率及应力比对18CrNiMo7-6合金钢疲劳性能的影响。使用扫描电镜观察了试样的断裂表面。结果表明:常规加载频率下存在频率效应,并且随加载频率的增加,材料的疲劳强度呈增加趋势,并且屈服强度随应变速率的增大逐渐增大,发现不同加载频率下的断裂机理并无明显差别。在最大应力相同时,随应力比的增大,18CrNiMo7-6合金钢疲劳寿命逐渐增大。利用有限元方法使用BrownMiller模型计算了不同应力比条件下18CrNiMo7-6合金钢的疲劳寿命,计算结果与试验结果匹配较好。

Gradient nanostructure,enhanced surface integrity and fatigue resistance of Ti-6Al-7Nb alloy processed by surface mechanical attrition treatment

Current Ti-based orthopedic implants often suffer from fatigue damage,therefore shortening their service lifespan.To solve this issue,in this study,mechanically polished Ti-6Al-7Nb(P-Ti6Al7Nb)was subjected to surface mechanical attrition treatment(SMAT).Effects of various SMAT process parameters,including ball diameter and treatment duration,on the surface integrity of P-Ti6Al7Nb were investigated,specifically in terms of surface quality,surface nanocrystalline layer,and residual stress.Subsequently,the microstructure,in-depth residual stress and microhardness distributions,surface roughness,and fatigue behavior in simulated body fluids of optimally SMATed Ti-6Al-7Nb(S-Ti6Al7Nb)were examined and compared to those of P-Ti6Al7Nb.Results showed that based on the experimental conditions established in the present research,the optimal parameters were determined to be a 3 mm ball diameter and a 15 min treatment duration,which resulted in excellent surface integrity;S-Ti6Al7Nb showed a 300μm-thick gradient nanostructured layer comprising the thickest nanocrystalline layer of about 20μm,a 1000μm-deep residual compressive stress field with the maximum surface residual compressive stress,and a microconcave topography but free of any defects or cracks.The microstructural evolution mechanism was also elucidated,revealing that the combination of multidirectional primary and secondary twins’intersections and twin-dislocation interactions contributed to grain refinement.Compared to P-Ti6Al7Nb,S-Ti6Al7Nb exhibited a 40%improvement in fatigue strength,owing to synergistic effects of the gradient nanostructured layer,surface work hardening,high amplitude of residual compressive stress,and improved surface integrity.These factors effectively prevented the initiation of fatigue crack at the surface and shifted it to the sublayer,and inhibited the subsequent crack propagation.