Structure and mechanical properties of alloys Ti-2.2% Al-2.2% V-2.2% Mo-2.5% Fe and Ti-2.2% Al-5% Fe equivalent to alloy VT16

Comparative studies of the structure and properties of alloys Ti-2.2% Al-5% Fe and Ti-2.2% Al-2.2% V-2.2% Mo-2.5% Fe in annealed, quenched, and aged conditions are performed. The strength level of the alloys corresponds to that of VT16. The possibility of replacing alloy VT16 by alloy Ti-2.2% Al-2.2% V-2.2% Mo-2.5% Fe is estimated. __________ Translated from Metallovedenie i Termicheskaya Obrabotka Metallov, No. 6, pp. 10–13, June, 2006.     

Ti-4.5Al-5Mo-1.5Cr合金增韧的价电子理论研究

利用余氏固体与分子经验电子理论和程氏改进的TFD理论计算了Ti-4.5Al-5Mo-1.5Cr与Ti-6Al-4V两种合金的相空间及其异相界面价电子结构。利用价电子结构参数－相结构因子和界面结合因子，分析讨论了合金元素Mo,Cr和V对Ti-4.5Al-5Mo-1.5Cr与Ti-6Al-4V钛合金相空间及其异相界面价电子结构的影响，进而在电子结构层次上揭示了Ti-4.5Al-5Mo-1.5Cr合金增韧的微观本质原因。     

置氢Ti-6Al-4V钛合金的热压缩变形行为研究

通过热模拟压缩实验,研究了氢对Ti-6Al-4V钛合金热变形行为的影响。结果表明,置氢可以显著降低Ti-6Al-4V钛合金高温压缩时的流动应力,提高Ti-6Al-4V钛合金的热加工变形速率一个数量级以上,并且明显降低了Ti-6Al-4V钛合金的变形温度。在变形温度760℃~800℃范围内,置氢量为0.4wt%的Ti-6Al-4V钛合金的流动应力最小;在变形温度840℃~920℃范围内,置氢量0.2wt%的Ti-6Al-4V钛合金的流动应力最小。同时,置氢前后Ti-6Al-4V钛合金的变形激活能计算结果表明,置氢量为0.4wt%的Ti-6Al-4V钛合金在α+β两相区的变形激活能为208.3kJ/mol,与未置氢Ti-6Al-4V钛合金相比降低了316kJ/mol。     

Hot deformation behaviors of Fe-microalloyed Ti-6Al-4V based on experiments and calculations

Our previous results have shown that comprehensive mechanical properties of titanium alloys can be effectively improved by addition of Fe[1]. We systematically investigate hot deformation behaviors of Ti-6Al-4V-0.35Fe in this study, which is significant to improve plastic deformation ability of titanium alloys. In experiment, we use a Gleeble 3800 thermo-mechanical simulator to obtain the relationship between thermomechanical parameters and flow stress in a range of temperatures (800-950 °C) and strain rates (0.001-10 s-1). The single-peak profiles of the flow curves indicate that dynamic recrystallization (DRX) mechanism dominates the deformation. TEM analysis indicate that the grain size in DRX changes under different deformation temperatures, and finer grains are formed at relatively lower temperature due to the dynamic globularization. The dislocation walls are formed in subgrain boundaries due to dislocation slipping-climbing. The Avrami-type DRX model and the strain compensated multivariable regression model have been applied to fit the experimental stress-strain data during hot deformation. A comparative study between these two types of constitutive models is conducted to represent the flow behavior. It is found that both models have good accuracy in predicting the flow stress of Ti-6Al-4V-0.35Fe alloy. A processing map based on dynamic material model (DMM) at the strain of 0.8 (steady-state flow stage) has been established to identify the flow instability regions and stability regions. The strain rate range of stability region is 0.001-0.6s-1 which has been expanded compared to the range of 0.0003-0.1s-1 of Ti-6Al-4V. Optimal hot working parameters are confirmed to be 920-950 °C and 0.001-0.005 s-1, and nearly complete DRX has taken place. Our results indicate that hot working property of Fe-microalloyed Ti-6Al-4V is better than that of Ti-6Al-4V alloy in 800-950 °C temperature scale, and processing cost has been decreased.     

Investigation of fatigue crack initiation in Ti-6Al-4V during tensile-tensile fatigue

Fatigue crack initiation in Ti-6Al-4V has been investigated in high cycle fatigue (HCF) and low cycle fatigue (LCF) regimes at stress ratio R=0.1 using the replication technique. In all four tested α/β microstructures, the crack was initiated by fracture of equiaxed alpha grain. Fractured alpha grains are seen on the fracture surface as flat facets with features characteristics of cleavage fracture. In the regime of low stress amplitudes and in the absence of reverse loading, cleavage fracture contributes to crack initiation and early stages of crack growth in Ti-6Al-4V. This mechanism is discussed in relation to the anomalous mean stress fatigue behavior exhibited by this alloy.     

Fatigue crack growth and fracture behavior of as-cast Ti-43.5Al-4Nb-1Mo-0.1B (TNM) compared to Ti-48Al-2Nb-2Cr (4822)

The effects of sample orientation and load ratio on the room-temperature fatigue crack growth and fracture behavior of a third-generation gamma titanium aluminide Ti-43.5Al-4Nb-1Mo-0.1B (TNM) were determined and compared with that of a second-generation alloy Ti-48Al-2Nb-2Cr (4822). Both materials are currently used as low pressure turbine blades in fuel-efficient gas turbine engines. Bend bar specimens, excised from the as-cast articles in the longitudinal and transverse directions to the casting direction, were tested at room temperature in lab air. Load ratios in the range 0.1–0.9 were used in fatigue testing to determine their effects on the fatigue threshold, Paris law slope, and stress intensity at overload in fatigue. Microscopy and fractography were used to document the effects of sample orientation on the fatigue crack path and morphology. Significant effects of changes in load ratio were observed on the fatigue threshold and Paris law slope, while effects of sample orientation were minimal for both alloys. The effects of microstructure length scale and differences in micro-constituents are discussed in relation to the properties measured.     

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。     

应用智能方法建立Ti-6Al-2Zr-1Mo-1V合金的本构关系(英文)

利用Thermecmastor-Z热模拟机进行Ti-6Al-2Zr-1Mo-1V钛合金在不同工艺参数(变形温度800,850,900,1000,1050°C,应变速率0.01,0.1,1,10s-1)条件下的热模拟压缩试验,研究变形温度和应变速率对Ti-6Al-2Zr-1Mo-1V钛合金流变应力的影响。以试验数据为基础,应用BP神经网络算法原理,建立该合金的高温流动应力与变形温度、应变和应变速率对应关系的高温本构关系预测模型。结果表明,运用神经网络方法建立的Ti-6Al-2Zr-1Mo-1V钛合金本构关系模型具有较高的预测精度,与试验结果吻合良好。此外,运用Visual Basic可视化编程语言设计并开发了具有神经网络功能的用户界面。     

氢对Ti-6Al-4V合金微观组织的影响

采用累计流量法对供应态Ti-6Al-4V合金进行了固态置氢,运用OM、XRD、TEM分析等方法研究了Ti-6Al-4V合金固态置氢后的微观组织状态及演变过程。结果表明:供应态Ti-6Al-4V合金的置氢量低于0.30%(质量分数,下同)时,置氢使得Ti-6Al-4V合金中的α相减少、β相增加;置氢量达到0.30%时,置氢Ti-6Al-4V合金中有δ氢化物(TiH2相)形成;β-Ti(H)共析转变生成α-Ti和δ氢化物时主要以切变方式进行;置氢Ti-6Al-4V合金的相变温度最多下降了180°C,与Ti-6Al-4V合金在置氢过程中的相体积比变化和共析转变有密切关系。     

Sintering properties of Ti-6Al-4V-xMo powder prepared by addition of Mo to Ti-6Al-4V scraps and subsequent pulverization

In this study, the sintering properties of Ti-6Al-4V-xMo powder prepared by an addition of Mo to Ti-6Al-4V scraps and subsequent pulverization were investigated. As the content of Mo added to Ti-6Al-4V scraps as a β stabilizer increased, the weight ratio of the α and β stabilizers in the Ti-6Al-4V-xMo changed and the original weight ratio of 6:4 varied to 5.71:8.57 when 5 wt% xMo was added. In order to compare the difference in properties of Ti-6Al-4V-xMo ingots with sintered bodies of the Ti-6Al-4V-xMo powder, we prepared sintered bodies from Ti-6Al-4V-xMo powder with an O content of about 5000 ppm and 325 mesh size. As a result, it was found that the sintered bodies of Ti-6Al-4V-xMo powder showed different properties of density and micro hardness compared to the Ti-6Al-4V-xMo ingots. These differences can be explained by the larger specific surface area of the sintered bodies, which formed a porous oxide layer on the surface due to the increase of Mo in the β zone of the Ti-6Al-4V alloys.     

油气开采用钛合金石油管材料耐腐蚀性能研究

选取5种油气开发常用钛合金材料(Ti-6Al-4V、Ti-6Al-4V-0.1Ru、Ti-6Al-2Sn-4Zr-6Mo、Ti-3Al-8V-6Cr-4Zr-4Mo和Ti-5.5Al-4.5V-2Zr-1Mo)为研究对象,使用高温高压釜模拟国内典型严酷服役工况环境,研究了不同钛合金材料耐均匀腐蚀、局部腐蚀、点蚀、应力腐蚀开裂(SCC)及缝隙腐蚀的性能,通过使用扫描电镜和能谱分析等手段对腐蚀形貌和腐蚀产物进行了分析,并使用电化学方法对不同合金的耐腐蚀机理进行了研究。结果显示,在所测试工况条件下,所有钛合金材料腐蚀反应均为阳极控制过程,均匀腐蚀速率均低于0.001mm/a,并且对应力腐蚀开裂均有良好的抗力。Ti-6Al-4V和Ti-5.5Al-4.5V-2Zr-1Mo合金出现明显的点蚀和缝隙腐蚀问题。对腐蚀机理研究表明,在工况条件温度下,随着pH值的降低,所有钛合金均发生自腐蚀电位降低,极化电阻减小,腐蚀电流增大,耐腐蚀性能下降,其中Ti-6Al-4V耐腐蚀性能下降的最为明显,研究结果为油气开发工况下钛合金石油管的选材和缝隙腐蚀问题防治提供理论基础。     

Rolling of Plates and Sheets from As-Cast Ti-6Al-4V-0.1B

Trace boron addition (~0.1 wt.%) to conventional titanium alloys reduces the as-cast prior-beta grain size by an order of magnitude to about 200 μm, a grain size typically observed after ingot breakdown. In this study, the feasibility of producing plate and sheet by hot rolling of as-cast Ti-6Al-4V-0.1B (wt.%) was evaluated. Starting from an initial thickness of 25 mm, as-cast Ti-6Al-4V-0.1B was successfully rolled to 2 mm sheet in a multistep rolling process. As-cast Ti-6Al-4V (without boron addition) rolled under similar conditions exhibited severe cracking. Tensile properties of the sheets and plates made from the boron-containing alloy met or exceeded AMS 4911 specifications for Ti-6Al-4V plates and sheets produced by conventional processing route. The process of making plate and sheet stock from cast titanium alloy ingots, without recourse to expensive ingot breakdown, can significantly reduce the number of expensive and time-consuming processing steps for making titanium alloy components, thereby enhancing the affordability and expanding the range of titanium applications.     

添加晶粒细化剂硅对Ti-6Al-4V合金组织和性能的影响(英文)

采用真空感应凝壳熔炼工艺在石墨模中制备Ti-6Al-4V和Ti6Al4V0.5Si两种钛合金。将硅作为一种晶粒细化剂加入到Ti-6Al-4V合金中,考察添加硅对铸态和模锻态Ti-6Al-4V合金组织和性能的影响。铸态合金先在900°C下进行热模锻处理,然后分别进行两种不同的热处理。一种是将模锻样品在1050°C下保温30min,然后水淬以获得细小的层片状组织;另一种是将模锻件在1050°C下保温30min,然后再在800°C下保温30min,以获得粗大的层片状组织。Ti6-Al-4V合金中添加0.5%Si后,铸态合金的晶粒尺寸从627μm减小到337μm,其极限抗拉强度增加约25MPa。具有细小、层片状组织的Ti-6Al-4V0.5Si合金的最大极限抗拉强度为1380MPa,在Hank溶液和NaCl溶液中的腐蚀速度分别为1.35×106和5.78×104mm/a。Ti-6Al-4V合金中添加0.5%Si后,在低滑动速度下的磨损率降低50%,在高滑动速度下的磨损率降低约73%。     

选区激光熔化制备Ti-6Al-4V合金的热处理工艺及力学性能

采用选区激光熔化技术(SLM)制备Ti-6Al-4V合金圆棒试样,通过不同的热处理工艺改善材料的拉伸性能,并对SLM制备的Ti-6Al-4V合金试样开展了高周疲劳性能测试。通过微观组织和疲劳试样断口分析,揭示了显微组织结构与拉伸性能的关系,以及Ti-6Al-4V合金的疲劳裂纹起始源和裂纹扩展机理。结果表明,热处理工艺对SLM成型Ti-6Al-4V合金的力学性能有显著的影响,920 ℃×1 h水冷,随后800 ℃×2 h炉冷的固溶时效热处理制度可以获得较好的综合室温拉伸性能。其室温组织为晶界上分布的α相和晶粒内部片层状分布的α+β相。SLM成型Ti-6Al-4V合金显微组织中的晶界形成与扫描路径相关,热处理过程中α相会优先在扫描分区搭接处析出。与手册锻件的疲劳寿命曲线比较,在同样的最大应力水平下,增材试样的疲劳寿命比锻件的疲劳寿命低,这种降低的趋势随着应力水平的降低而逐步增大。在400 MPa的应力水平下(R=-1),锻件的疲劳寿命已经在2×10⁷水平,增材试样的疲劳寿命依然较低,约为锻件的1%。SLM成型Ti-6Al-4V合金的应力疲劳寿命偏低,是由于试样中存在未熔合缺陷造成。扫描分区搭接处易产生未熔合缺陷,而疲劳裂纹也会沿着这些缺陷扩展。     

Effect of carbon on microstructures of Ti-45Al-3Fe-2Mo-xC alloy

The effect of carbon addition on the microstructures of TiAl-based alloy (Ti-45Al-3Fe-2Mo) was studied. The proportion of β/B2 phase reduces with the content of carbon increasing, while the colony size increases. With increasing the carbon content, the lamellar spacing first decreases from 267 nm (Ti-45Al-3Fe-2Mo) to 237 nm (Ti-45Al-3Fe-2Mo-0.3C) and 155 nm (Ti-45Al-3Fe-2Mo-0.5C), but then increases to 230 nm (Ti-45Al-3Fe-2Mo-1.0C) with further increase in C level, which is affected by the inhibition of carbon atom and precipitation of carbides at the lamellar interface. Precipitation of carbides shows a response to aging time at 800 °C. P-type carbides grow up at the boundaries and near the dislocation areas with the prolonging of aging time. And these carbides are projected different morphology in different beam directions (BD). The effects of these microstructural modifications were examined and the observations were discussed.     

Diffusion bonding/superplastic forming of Ti-6Al-6V-2Sn/SUS 304 stainless steel/Ti-6Al-6V-2Sn

The superplasticity of the Ti- 6Al- 6V- 2Sn alloy for different temperatures was evaluated by single-sheet free blowing. The optimal superplastic temperature for the Ti- 6Al- 6V- 2Sn alloy was found to be 850 °C. Diffusion bonding of Ti- 6Al- 6V- 2Sn and 304 stainless steel was carried out in a vacuum. The interface of both bonded alloys was examined by EPMA. The concentration profile of Ni exhibited a peak at the interlayer and a valley adjacent it, whereas that of Cr exhibited a peak where Ni showed the valley. X- ray diffraction (XRD) analyses showed that the Fe ₂ Ti, NiTi, and CrMn Intermetallic compounds and the Cr element formed at the interface. The thickness profiles of the blown specimens were measured and compared with theoretical calculations.     

The use of β titanium alloys in the aerospace industry

Beta titanium alloys have been available since the 1950s (Ti-13V-11Cr-3Mo or B120VCA), but significant applications of these alloys, beyond the SR-71 Blackbird, have been slow in coming. The next significant usage of a β alloy did not occur until the mid-1980s on the B-1B bomber. This aircraft used Ti-15V-3Cr-3Al-3Sn sheet due to its capability for strip rolling, improved formability, and higher strength than Ti-6Al-4V. The next major usage was on a commercial aircraft, the Boeing 777, which made extensive use of Ti-10V-2Fe-3Al high-strength forgings. Ti-15V-3Cr-3Al-3Sn environmental control system ducting, castings, and springs were also used, along with Ti-3Al-8V-6Cr-4Mo-4Zr (β-C) springs. Beta-21S was also introduced for high-temperature usage. More recent work at Boeing has focused on the development of Ti-5Al-5Mo-5V-3Cr, a high-strength alloy that can be used at higher strength than Ti-10V-2Fe-3Al and is much more robust; it has a much wider, or friendlier, processing window. This, along with additional studies at Boeing, and from within the aerospace industry in general will be discussed in detail, summarizing applications and the rationale for the selection of this alloy system for aerospace applications. This paper was presented at the Beta Titanium Alloys of the 00’s Symposium sponsored by the Titanium Committee of TMS, held during the 2005 TMS Annual Meeting & Exhibition, February 13–16, 2005 in San Francisco, CA.     

Isothermal compression behavior and constitutive modeling of Ti-5Al-5Mo-5V-1Cr-1Fe alloy

Hot compression behavior of Ti-5Al-5Mo-5V-1Cr-1Fe alloy with an equiaxed (α+β) starting microstructure was investigated by isothermal compression test and optical microscopy. Based on the true strain–stress data with temperature correction, constitutive models with a high accuracy were developed and processing maps were established. Strain inhomogeneity at different locations in the compressed sample is reduced by raising temperature, leading to a uniform distribution of α phases. For the temperature range of 800–840 °C with a strain rate of 10 s^?1, the transformed volume fraction of α phase increases and the average grain size of α phase decreases slightly with increasing the temperature, indicating co-existence of dynamic recovery and dynamic recrystallization. Flow localization and faint β grain boundaries are observed at the strain rate of 10 s^?1 in the temperature range of 860–900 °C. The processing map analysis shows that hot working of Ti-5Al-5Mo-5V-1Cr-1Fe alloy should be conducted with the strain rate lower than 0.01 s^?1 to extend its workability.     

氢含量对Ti-6Al-4V合金室温高速压缩性能的影响(英文)

利用电磁成形实验研究氢含量对Ti-6Al-4V合金室温高速压缩性能的影响,通过微观组织观察揭示氢致压缩性能机理。结果表明,氢对Ti6Al4V合金的高速压缩性能存在有益的影响。在电磁成形实验放电能量相同的条件下,Ti-6Al-4V合金的变形率随氢含量的增加呈先增加后降低的趋势。当Ti-6Al-4V合金置氢0.2%(质量分数)时,合金的变形率增加了47.0%。确定了有利于Ti6Al4V合金室温电磁成形时的最佳氢含量。分析了氢致压缩性能的机理。     

Design for Ti-Al-V-Mo-Nb alloys for laser additive manufacturing based on a cluster model and on their microstructure and properties

In this study, α+β Ti-Al-V-Mo-Nb alloys with the addition of multiple elements that are suitable for laser additive manufacturing (LAM) were designed according to a Ti-6Al-4V cluster formula. This formula can be expressed as 12[Al-Ti₁₂](AlTi₂)+5[Al-Ti₁₄]((Mo, V, Nb)₂Ti), in which Mo and Nb were added into the alloys partially instead of V to give alloys with nominal compositions of Ti-6.01Al-3.13V-1.43Nb, Ti-5.97Al-2.33V-2.93Mo, and Ti-5.97Al-2.33V-2.20Mo-0.71Nb (wt.%). The microstructures and mechanical properties of the as-deposited and heat-treated samples prepared via LAM were examined. The sizes of the β columnar grains and α laths in the Nb-containing samples are found to be larger than those of the Ti-6Al-4V alloy, whereas Mo- or Mo/Nb-added alloys contain finer grains. It indicates that Nb gives rise to coarsened β columnar grains and α laths, while Mo significantly refines them. Furthermore, the single addition of Nb improves the elongation, whereas the single addition of Mo enhances the strength of the alloys. The simultaneous addition of Mo/Nb significantly improves the comprehensive mechanical properties of the alloys, leading to the best properties with an ultimate tensile strength of 1,070 MPa, a yield strength of 1,004 MPa, an elongation of 9%, and micro-hardness of 355 HV. The fracture modes of all the alloys are ductile-brittle mixed fracture.