无涂层硬质合金刀具车削钛合金Ti-6Al-4V实验研究

钛合金是航空航天工业中应用广泛的一种难加工材料。本文研究了无涂层硬质合金刀具干切削钛合金Ti-6Al-4V时切削力、表面粗糙度的变化规律，得到了切削深度、进给量、切削速度对切削力和表面粗糙度的影响规律。对切削力实验结果进行了回归分析得到了切削力的指数公式，并运用校正R^2拟合判定系数、累积概率图和残差图对回归模型进行了检验，检验结果表明：切削力的3个回归方程较好的拟合了实验所测的数据，钛合金切削过程中切削力近似满足指数关系。     

Ti-6Al-4V真空钎焊研究

针对目前用于Ti合金钎焊的Ti基钎料熔点偏高的现状，设计了Ti-Zr-Cu-Ni钎料，结果 表明，接头强度较高，因钎焊温度较低母材基本上保留了原始组织。同时还证明Ti-Zr-Cu钎料大幅度增加Cu的质量分数易造成钎缝中心区域生成连续分布的Ti2Cu+TiCu，严重影响接头强度。     

砂带磨削钛合金

钛合金由于具有比重小、温度高、耐腐蚀性好、在500℃以下具有良好的热稳定性等特点,加之我国的钛资源十分丰富,故钛合金被广泛地应用于飞机、火箭、人造卫星、坦克、潜艇和精密仪器上。但是,由于钛合金某些特殊的物理、机械性能、致使钛合金很难进行磨削加工。钛合金的熔点高达1725℃,其导热系数仅为铝的1/4、钢的1/5,而钛合金的摩擦系数却很高,这样,在磨削过程中将产生大量磨削热,由于磨削热不能迅速传出磨削区,则必将引起磨削区温度过高,而使工件产生磨     

马氏体组织Ti-6Al-4V钛合金多向等温锻造组织演变及力学性能强化研究

将铸态Ti-6Al-4V钛合金经过β相区热处理水淬之后获得马氏体组织,经过两步多向等温锻造之后获得了平均晶粒尺寸为1.5 μm的均匀等轴细晶组织,其室温拉伸屈服强度为906 MPa,抗拉强度为954 MPa,伸长率为16.7%,相比铸态Ti-6Al-4V钛合金,其室温力学性能得到了极大提升。研究表明,获得马氏体组织对钛合金晶粒细化有着巨大促进作用。第一步等温锻造之后的钛合金坯料组织并不均匀,存在变形区和“变形死区”,在变形区域内,心部位置应变量最大,组织细化最为明显,从心部到两端应变量逐渐减小,片层组织变形量相应减小;经过90°换向后的第二步等温锻造之后,钛合金坯料组织内的片层组织基本全部细化,形成了均匀的等轴晶组织,从心部到两端,随着应变量的减小,晶粒取向变化相应减小。     

Ti-6Al-4V钛合金板与304L不锈钢网的扩散焊

分别在800℃、825℃、850℃焊接温度、30 m in保温时间,3 MPa焊接压力下,进行Ti-6A l-4V钛合金板与304L不锈钢网的真空扩散焊接。对接头组织结构与化学元素扩散进行了扫描电镜与能谱分析,并测试了接头的剪切强度。结果表明:不添加中间过渡层金属,可以成功地实现钛合金板与不锈钢网的扩散焊接,并使接头的剪切强度达到90 MPa以上。不锈钢网中的Fe、N、iCr扩散并固溶到钛合金中,稳定了β相,使钛合金在一定深度上,其组织由原来的α+β双相结构转变为单相的β相。不锈钢中的Cr,由于钛合金中Ti的扩散进入,而在界面发生了上坡扩散现象。这种Cr在不锈钢一定深度内的富集,形成窄长的富Cr区域,冷却后转变为硬脆的σ相。但在焊接接头中没有发现明显其它的金属间化合物或氧化物相的生成,使得接头的机械性能得到了很好的保证。     

固态渗碳化硼对Ti-6Al-4V显微组织和性能的影响

研究了Ti-6Al-4V在800℃和1000C下固态渗碳化硼20h后的渗层显微组织以及对硬度等的影响。结果表明：渗层在表面为致密分布的化合物层,其成分主要为TiC、TiB以及TiB2等硬质相,而在基体内部则形成沿晶界分布的板条状或等轴状的颗粒扩散层;表面碳化硼处理可以显著提高Ti-6Al-4V的表面硬度,由359HV提高到了664HV,并且可以得到良好的表面硬、芯部软的硬度梯度;断口形貌分析发现材料由韧性断裂转变成脆性断裂。     

高速铣削钛合金Ti-6Al-4V切屑形态试验研究

对高速铣削的切屑进行了微观组织研究,建立了切削要素、切屑形态、切削力、表面粗糙度等因素之间的关系。研究发现,切削速度越高,热量向外扩散的时间越少,聚集在剪切带内的热量越多,剪切带内发生动态再结晶的可能性也就越高,大量的热量促进了剪切带内的热塑性失稳,进而使绝热剪切带产生的频率大幅度提高,切屑的锯齿化程度也就随之加大;计算了不同切削条件下绝热剪切带中心的温度、热量扩散速度等,发现热量扩散速度远低于其变形速度,进而证明了高速切削钛合金Ti-6Al-4V时,绝热剪切带内发生了动态再结晶现象。考虑到再结晶软化效应对材料本构的影响情况,建立了改进J-C本构模型,该模型用两个表达式表述不同临界应变值区间范围的材料本构特征,理论计算证明了改进J-C本构比J-C本构更准确。     

Ti-6Al-4V燕尾榫结构微动疲劳裂纹萌生及扩展行为研究

针对Ti-6Al-4V钛合金燕尾榫连接结构在不同载荷下的微动疲劳现象,采用榫形微动疲劳试验进行研究,并对裂纹萌生扩展、微动磨损及断口进行分析。结果表明,微动疲劳使构件疲劳寿命显著降低约70%;疲劳载荷对微动裂纹扩展的影响比对裂纹萌生的影响更大;微动疲劳裂纹起始于接触面边缘,与接触表面约成45°角,裂纹扩展到60~150μm后转向与接触表面垂直;微动疲劳断口形貌表面在微动磨损区具有多个裂纹源点,但只有一个主裂纹形成。     

置氢对Ti-6Al-4V合金组织和性能的影响

为掌握置氢改善钛合金切削性能的机理,利用光学显微镜与X射线衍射仪分析了置氢Ti-6Al-4V合金的显微组织,采用热膨胀仪与热常数测试仪测定了该合金的热膨胀系数和导热系数,通过高温拉伸试验研究了该合金的力学性能。结果表明:置氢后,随着氢含量的增加,合金中的β相比例提高,并且生成了δ氢化物;与未置氢钛合金相比,在900℃时的热膨胀系数最大降幅为6%,而导热系数在500℃时的增幅最大,为40%;置氮后的钛合金,在800℃时抗拉强度与伸长率的降幅分别为19%和74%。     

钛合金TC4的钻削力试验研究

钛合金TCA属于较难加工材料,其小孔钻削尤为困难。为得到钻头直径、钻削参数（进给量、切削速度）和刀具材料对钻削力的影响规律,采用标准高速钢钻头对TCA与45钢进行了钻削对比试验,并用多元线性回归分析模型分别建立了扭矩和轴向力的经验公式。结果表明,TC4的钻削力比45钢大,钻削参数对钻削力的影响规律与45钢基本相同,即钻头直径对扭矩和轴向力影响最大,进给量次之,切削速度的影响最小。     

Experimental Study on Cutting Forces and Surface Integrity in High-Speed Side Milling of Ti-6Al-4V Titanium Alloy

This article is concerned with the cutting forces and surface integrity in high-speed side milling of Ti-6Al-4V titanium alloy. The experiments were conducted with coated carbide cutting tools under dry cutting conditions. The effects of cutting parameters on the cutting forces, tool wear and surface integrity (including surface roughness, microhardness and microstructure beneath the machined surface) were investigated. The velocity effects are focused on in the present study. The experimental results show that the cutting forces in three directions increase with cutting speed, feed per tooth and depth of cut (DoC). The widths of flank wear VB increases rapidly with the increasing cutting speed. The surface roughness initially decreases and presents a minimum value at the cutting speed 200 m/min, and then increases with the cutting speed. The microstructure beneath the machined surfaces had minimal or no obvious plastic deformation under the present milling conditions. Work hardening leads to an increment in micro-hardness on the top surface. Furthermore, the hardness of machined surface decreases with the increase of cutting speed and feed per tooth due to thermal softening effects. The results indicated that the cutting speed 200 m/min could be considered as a critical value at which both relatively low cutting forces and improved surface quality can be obtained.     

Adhesion Wear on Tool Rake and Flank Faces in Dry Cutting of Ti-6Al-4V

Titanium alloys are very chemically reactive and,therefore,have a tendency to weld to the cutting tool during machining.The deterioration in the tool life caused by adhesion is a serious problem when titanium alloys are cut using carbide tools.The chemical reactivity of titanium alloys with carbide tool materials and their consequent welding by adhesion onto the cutting tool during dry cutting leads to excessive chipping,premature tool failure,and poor surface finish.In the present study,dry turning and milling tests were carried out on Ti-6Al-4V alloys with WC?Co carbide tools.The adhesion on the tool rake and flank face was explored,the adhesive joint interface between the workpiece materials and tools were observed.SEM observation showed that adhesion can be observed both on the rake and the flank face,and was more pronounced in rake face than in flank face.There was evidence of element diffusion from the tool rake face to the adhering layer(vice versa) through the adhesive joint interface,which leads to the tool element loss and microstructure change.While the adhering materials at the flank face can be easily separated from the joint interface owing to the lower temperature and less pressure at the flank face,the adhesive wear attack results in an abrasive wear in the flank face.Moreover,adhesion is more notable in turning than in milling.The proposed research provides references for studying the adhesion between the workpiece materials and the tools,the adhesion mechanisms and their effect on the tool wear.     

Fretting fatigue of laser shock peened Ti-6Al-4V

The objective of this paper is to examine fretting fatigue of laser shock peened (LSP) titanium to quantify the influence of LSP on fretting fatigue life. Contact conditions such as loads and pad geometry are chosen to generate fretting fatigue stresses similar to those occurring in blade/disk contacts in gas turbine engines. LSP treated specimens attained 5-, 10- and 25-fold increase in lives compared to untreated specimens. Metallography of the contact area and fractographic analysis of worn pads detail the fretting behavior of LSP treated specimens.     

Fretting behavior of shot peened Ti-6Al-4V under slip controlled mode

Fretting tests of shot peened Ti-6Al-4V were conducted under slip controlled mode using a dual actuator test setup which could apply an independent pad displacement at a given applied bulk stress. Fretting regime was identified based on the hysteresis loop of tangential force versus relative slip range and the evolution of tangential force. Fretting regime changed from partial slip to mixed slip and then to gross slip with increasing relative slip range, and the transition from mixed to gross slip occurred at a relative slip range of ∼50 μm regardless of the applied bulk stress magnitude for both shot peened and unpeened specimens. Fretting fatigue life initially decreased as the relative slip range increased and reached to a minimum value, and then increased with an increase of the relative slip range due to the transition in fretting regime from mixed slip to gross slip. Shot peened specimens had longer fatigue life than unpeened specimens at a given relative slip range, but the minimum fatigue life was at the same value of the relative slip range for both shot peened and unpeened specimens. The relationship between relative slip and fatigue life was also found to be independent of the applied bulk stress level. Further, tangential force was directly related to relative slip and this relationship was independent of other fretting variables.