Ti-6Al-4V线性摩擦焊实验研究

线性摩擦焊接作为一种先进的固态连接技术,凭借其高效、优质的特点正逐渐引起人们的重视。尤其是在高推重比飞机发动机整体叶盘制造与维修领域,它已经成为最经济、实用的加工技术之一。以航空工业中广泛应用的Ti-6Al-4V合金为实验材料,进行了线性摩擦焊的实验。描述了线性摩擦焊接工件飞边的宏观形态,得出了金属挤出物的规律。初步分析了典型工件焊缝区和热影响区的显微组织。结果表明,焊缝区为高度弥散的网状组织,热影响区为拉长的α相晶粒夹杂着破损的β相晶粒。     

The Effect of Friction Stir Welding on Corrosion Behavior of Ti-6Al-4V

Fusion welding can deteriorate corrosion behavior of Ti-6Al-4V alloy. However, the use of friction stir welding leads to a more appropriate corrosion resistance. In this study, the corrosion resistance of welded zones of Ti-6Al-4V alloy using friction stir welding technique is evaluated. For these purposes, the study of structural characteristics using SEM and FESEM equipped with EDS micro-analyses was conducted. Micro-hardness test was also employed to estimate the hardness of welded zones. Corrosion behavior was investigated by a potentiostat instrument. SEM micrographs, EDS and XRD analyses confirmed non-uniformity of chemical composition within the welded zones. The results reveal that the stir zone contains typical alpha and prior beta phases. Nevertheless, thermomechanical zone included equiaxed and bimodal lamellae structure. Furthermore, the presence of different types of phases and microstructure in the thermomechanical zone led to reduced corrosion resistance. The corresponding values of corrosion current density in the stir zone, thermomechanical zone and base metal were 0.048, 0.55 and 0.032 µA, respectively. Corresponding corrosion potential for these zones was estimated as ?207, ?110 and ?157 mV. Evidently, the results show that corrosion resistance of thermomechanical zone is less than that of the stir zone and both zones have lower value than the base metal.     

Ti-6Al-4V钛合金板材焊接工艺优化

采用电子自动化激光焊接的方法,研究了不同焊接功率和焊接速度对Ti-6Al-4V钛合金板材的焊接成形性、显微组织和力学性能的影响。结果表明,当激光功率或焊接速度相同时,焊缝熔宽、焊缝背面宽度及焊缝横截面积都会随着激光功率与焊接速度的增大而增大;焊接接头抗拉强度受焊缝成形的影响大于焊缝显微组织的影响,接头的抗拉强度与咬边锐度呈反比。     

Process modeling for electron beam welding of Ti-6Al-4V

Using ANSYS software, a finite element model for electron beam welding of 14.5 mm thick Ti-6Al-4V alloy plate is developed by a sequentially coupled thermal-mechanical analysis method. For the purpose of model validation, welding trial is carried out. Meanwhile, fusion zone dimensions and residual stresses are measured. The fusion-boundary profile is reproduced accurately by using a conical volume heat source model. The predicted residual stresses are in reasonable agreement with the results determined by the hole-drilling method. Through the analysis of predicted residual stresses, it is found that the normal residual stress in the interior of plate can not be negligible and the maximum value of three dimensional residual tensile stresses arises at 10.15 mm depth in the weld zone.     

Radial Distribution Characteristics of Microstructure and Mechanical Properties of Ti–6Al–4V Butt Joint by Rotary Friction Welding

Ti–6Al–4V rods were butt-welded by rotary friction welding in this study. Additionally, the radial differences in microstructure and mechanical property of joints were investigated by hierarchy slicing method. The results displayed that the width of weld zone and heat-affected zone of joints became wider along radial direction. Meanwhile, the tensile strength of joints decreased gradually along the radial direction. According to the theoretical analysis, the temperature gradient and inhomogeneous forging pressure leaded to the radial differences. Through K-type thermocouples, the actual temperatures at different locations were measured, and the results were consistent with the theoretical analysis. Theoretically, the radial differences of rotary friction welding joint are an inherent phenomenon; thus, the size of weldment should be limited strictly below the corresponding critical size. In order to prevent radial differences from enlarging, the welding surface profile of weldment can be processed into oval shape, and a larger forging pressure can be used within the scope of the joint deformation allowed according to causes for radial differences.     

Ti-6Al-4V高能束焊对接板超塑性研究

通过单向热拉伸试验和超塑自由胀形试验研究了0．8mm厚Ti-6Al-4V激光焊接、真空电子束焊接和等离子弧焊接对接板在925℃的超塑性能。结果表明，激光焊和真空电子束焊对接板均具有良好的超塑性能，且前者略优于后者；等离子弧焊对接板单向拉伸不具有超塑性能，但可以进行超塑胀形。这和它们的输入能量密度有关，能量密度愈高，焊缝的冷却速率愈快，焊缝组织愈细，超塑性能也愈好。最后根据试验结果，采用有限元方法估算了这三种高能束焊接钛合金对接板的应变速率敏感性指数m值。     

A Preliminary Study of Deformation Behavior of Friction Stir Welded Ti-6Al-4V

A preliminary study of deformation behavior of friction stir welded (FSW) Ti-6Al-4V was performed using two different tools with cylindrical and stepped spiral pin design for the welding process. The nugget regions experienced temperature above β transus and the matrix transformed to fine acicular α during cooling of the nugget. By using stepped spiral pin design, a local region with much refined grain structure and significant tool debris particles were observed. Room temperature tensile test showed increased strength and decreased ductility in the material from this region. Fractographic analysis revealed that tool debris particles served as void nucleation sites. Tensile tests of FSW material were carried out at 625 °C in the strain rates of 3 × 10^?4 and 1 × 10^?3 s^?1. The strength was higher as compared to the as-received material. Microstructural evolution during tensile test was also investigated. Results showed that dynamic globularization occurred during the high temperature tensile test.     

Research on Laser Direct Deposition Process of Ti-6Al-4V Alloy

Laser direct deposition （LDD） of metallic components is an advanced technology of combining CAD/CAM （computer aided design/computer aided manufacturing）, high power laser, and rapid prototyping. This technology uses laser beam to melt the powders fed coaxiaUy into the molten pool by the laser beam to fabricate fuUy dense metallic components. The present article mainly studies the LDD of Ti-6Al-4V alloy, which can be used to fabricate aircraft components. The mechanical properties of the Ti-6Al-4V alloy, fabricated by LDD, are obtained using the tension test, and the oxygen content of used powders and deposited specimens are measured. In the present article, it can be seen that the mechanical properties obtained using this method are higher than the ones obtained by casting, and equal to those got by wrought anneal. One aircraft part has been made using the LDD process. Because of this aircraft part, with sophisticated shape, the effect of the laser scanning track on the internal soundness of the deposited part was discussed.     

Dehydrogenation of Hydrogenated Ti-6Al-4V Alloy

对未置氢及置氢Ti-6Al-4V合金进行了TG/DSC试验,研究了置氢钛合金的除氢行为。结果表明,当温度超过600℃时,置氢钛合金的失重规律与未置氢钛合金具有较大的差别。当加热温度在600~900℃之间时,置氢钛合金的失重随着氢含量的增加而增加。这是由于置氢合金中的亚稳相发生了分解。不考虑合金氧化的影响,置氢钛合金的最大失重与合金中的氢含量一致。置氢钛合金的最佳除氢温度为750℃。对于不同氢含量的置氢钛合金,其除氢工艺是相同的。     

Ti-6Al-4V合金的动态控制等离子焊接(英文)

介绍了一种新的动态控制等离子焊接工艺。该工艺能够在保持完全焊透的情况下减少对被焊材料的热输入。利用该工艺对Ti-6Al-4V合金实施平板对焊。利用光学显微镜、扫描电镜(SEM)和显微硬度计对焊接接头的显微组织、断口形貌和显微硬度进行表征。与钨极电弧焊接和常规的等离子焊接相比较,使用本工艺提高了焊接质量,其原因在于:1)由于热输入的减少,焊缝中先析出的β相晶粒大幅度减少,从而使马氏体的形成得到抑制;2)焊接接头具有更好的韧性和更高的硬度。     

Warm Spray Forming of Ti-6Al-4V

Warm spray (WS) is a modification of high-velocity oxy-fuel spraying, in which the temperature of the supersonic gas flow generated by the combustion of kerosene and oxygen is controlled by diluting the combustion flame with an inert gas such as nitrogen. The inert gas is injected into the mixing chamber placed between the combustion chamber and the powder feed ports, thus the temperature of the propellant gas can be controlled from ~700 to 2,000 K. Since WS allows for higher particle temperatures in comparison to cold spray, warm sprayed particles are more softened upon impact, thus resulting in greater deformation facilitating the formation of shear instability for bonding. Recently, the combustion pressure of WS has been increased from 1 (low-pressure warm spray) to 4 MPa (high-pressure warm spray) in order to increase the velocity of sprayed particles. Effects of spray parameters on microstructure, mechanical properties, and splats formation of Ti-6Al-4V were systematically studied. Obtained coatings were examined by analyzing the coating cross-section images, microhardness as well as oxygen content. In addition, flattening ratio of splats was calculated as a function of nitrogen flow rate. It was found that the increased particle velocity caused by the increased combustion pressure had significant beneficial effects in terms of improving density and controlling the oxygen level in the sprayed Ti-6Al-4V coatings.     

一种高强度Ti-6Al-4V钛合金丝材制备工艺的研究

对不同氧含量的Ti-6Al-4V钛合金采用控温热拉拔试验,制得φ1.0mm、φ2.0mm、φ2.5mm三种不同规格的丝材,研究Ti-6Al-4V钛合金中氧含量及控温热拉拔制备方法对材料组织和力学性能的影响.分析结果表明:氧含量对Ti-6Al-4V钛合金轧制坯料金相有明显的影响,氧含量越高,α相的相对含量越多,φ8.0mm轧制坯料等轴α相的尺寸为2～5μm,拉拔成φ2.0mm后获得约0.5μm的超细晶粒;随着合金中氧含量的增加、拉拔规格的细化,丝材的力学性能提高,塑性下降;含氧0.14wt%的Ti-6Al-4V φ2.0 mm丝材抗拉强度和塑性分别达到1270 MPa和12%,综合力学性能优良:进一步分析发现,Ti-6Al-4V丝材室温拉伸时发生沿等轴α相晶界的韧性断裂,超细晶粒及高密度位错是材料获得高强度的根本所在.     

Ti-6Al-4V合金的疲劳性能

简要综述了Ti-6Al-4V合金的显微组织和织构对其疲劳性能的影响及其机理.     

Surface Strengthening of Ti-6Al-4V Alloy by Glow Plasma Carbonization Process

利用辉光等离子渗碳技术对Ti-6Al-4V进行了表面强化处理。等离子气体为氩气,渗碳温度和时间分别为950 ℃和3 h,工作压力为30~35 Pa。为了避免传统气体渗碳过程中易于产生氢脆的现象,用固体石墨棒作为碳源。渗碳结束后,分别利用OM、FESEM和XRD对渗碳层做分析,并在坏-块摩擦磨损试验机上对处理和未处理样品进行摩擦磨损对比实验。结果发现,渗碳层深度约为416 μm,其表面碳化物(TiC和V8C7)提高了合金表面的硬度和耐磨性能。     

The laser additive manufacture of Ti-6Al-4V

Laser additive manufacturing (LAM) is a manufacturing technique with cost-reduction potential for titanium aerospace components. The mechanical properties of LAM Ti-6Al-4V have been investigated extensively, but little work on microstructure evolution has been performed to date. The results presented here provide a first look at the relationships between LAM processing parameters and microstructure in as-deposited Ti-6Al-4V. For more information, contact P.A. Kobryn, U.S. Air Force Research Laboratory, Materials and Manufacturing Directorate, AFRL/MLLMP, Wright-Patterson AFB, OH 45433 USA; (937) 255-1313; fax (937) 255-3007; e-mail Pamela.Kobryn@afrl.af.mil.     

Ti及Ti-6Al-4V的水基凝胶注模成形研究

将凝胶注模工艺应用于金属Ti及Ti-6Al-4v合金粉末的坯体成形，研究了高固相含量的Ti粉和Ti-6Al-4V合金粉末的料浆的制备。结果表明，用凝胶注模工艺制备出了固相含量为54φ%的钛合金粉末料浆和形状复杂的坯体；粉末的颗粒形状是影响料浆固相含量的重要因素，球形粉末配制成的浆料固相含量最高，近球形次之，片状最低；分散剂柠檬酸铵也可以显著提高浆料的固相含量。     

Ti-6Al-4V钛合金的等离子W-Mo共渗

采用双层辉光等离子表面合金化技术对Ti-6Al-4V钛合金进行W-Mo共渗,研究了880～1000 ℃ W-Mo共渗时基体温度对渗层厚度的影响,采用SEM和XRD观察、检测渗层组织结构和相组成.结果显示,Ti-6Al-4V合金的W-Mo渗层组织良好.纳米压痕试验结果表明,合金渗层硬度高于基体.     

Stress relaxation behavior of Ti-6Al-4V alloy

1　INTRODUCTIONTi 6Al 4VisoneofthemostimportantTial loys[1,2 ] .Butthisalloyhasbadformabilityforitshighelasticresilience .Therefore ,hotsizingisimpor tant[36 ] .Asthebaseofhotsizing ,thestudyofstressrelaxationhasimportanttheoreticalvalueandpracticalsignificance .Ontheotherhand ,Ti 6Al 4Visusedasfastenermaterialssometimes .Whenthefastenersworkatthetemperaturehigherthanroomtemperature ,stressrelaxationmayresultsinacci dents .Sohowtopreventthestressrelaxationisveryimportant[7] .Uptonow ,…     

Ti-6Al-4V合金中的绝热剪切断裂

利用分离式霍普金森压杆（SHPB）装置在3900s-1应变率条件下对Ti-6Al-4V合金进行动态加载,获得完全分离的断裂试样。使用扫描电子显微镜对试样的断裂特征进行观察。结果表明：试样中出现绝热剪切断裂,试样断口上交替分布着两个不同特征的典型区域（韧窝区及平滑区）。其中,韧窝区由微孔洞形核、长大并最终连接形成,表现出韧性断裂特征。在平滑区观察到超细晶粒（UFGs）,且晶粒间可观察到微裂纹,说明平滑区由微裂纹沿晶界扩展形成,表现出脆性断裂特征。由此可知,Ti-6Al-4V合金在动态加载过程中沿绝热剪切带发生的断裂失效过程不均匀,韧性及脆性两种断裂模式的共同作用导致该合金样品的最终断裂。     

ZTC4(Ti-6Al-4V)铸造钛合金的退火热处理工艺

介绍了航空航天等工业中大量应用的ZTC4(Ti-6Al-4V)铸造钛合金的退火热处理工艺,包括消除应力退火,普通退火,真空或保护性气氛退火以及真空双重退火.