Ti-47Al-2Cr-2Nb-0.2W-0.15B合金板材的制备及其拉伸性能

采用感应熔炼气体雾化法制备Ti-47Al-2Cr-2Nb-0.2W-0.15B预合金粉末,对预合金粉末进行表征,通过热等静压工艺制备TiAl基合金坯料.应用包套叠轧的方法轧制出TiAl基合金板材,对轧制的TiAl基合金板材进行不同相区的热处理,分别得到双态组织和全片层组织,对热处理后的TiAl基合金进行拉伸性能测试.结果表明:TiAl基合金的预合金粉末主要由α2相和少量γ相组成,热等静压致密化处理后的板坯组织细小均匀.拉伸实验表明,双态和全片层组织的TiAl基合金板材在高于700 ℃时,其塑性大幅提高;双态组织TiAl基合金板材的断裂形式主要以韧性断裂为主,而全片层TiAl基合金板材的断裂形式仍为脆性断裂.     

Ti-46Al-2Cr-4Nb-Y合金的高温变形及加工图

采用Gleeble-1500 热压缩模拟试验机进行压缩实验,在变形温度为1 100～1 250 ℃、应变速率为10-2～ 1 s-1的范围内,研究Ti-46Al-2Cr-4Nb-Y合金的高温变形行为,并基于动态材料模型,建立Ti-46Al-2Cr-4Nb-Y合金的加工图.结果表明:Ti-46Al-2Cr-4Nb-Y合金的高温变形流变应力对温度及应变速率敏感;流变应力随应变速率的增大而增大,随温度的升高而减小;动态再结晶是导致流变软化及稳态流变的主要原因;Ti-46Al-2Cr-4Nb-Y合金的安全热加工区域为温度1 200～1 230 ℃,应变速率10-2～10-1 s-1.     

High temperature deformation behaviors of Ti-45Al-2Nb-1.5V-1Mo-Y alloy

The high temperature deformation behaviors of Ti-45Al-2Nb-1.5V-1Mo-Y alloy were investigated in the temperature range 1100–1250 °C and the strain rate range 0.001–1.0 s^?1. The true stress-strain curves exhibit typical work hardening and flow softening features; The peak stress of current alloy decreases with increasing temperature and decreasing strain rate, which can be represented by a hyperbolic sine equation using the Zener-Hollomon parameter. Thanks to the additions of element Mo and V, and the resulting B2 phase, this alloy possesses a low activation energy value of 370 kJ/mol, as well as a wide processing window of temperature above 1150 °C and strain rate under 0.1 s^?1. The deformed microstructure consists of dominated DRX areas plus several remnant lamellar colonies; the inhomogeneous deformation microstructure is ascribed to the anisotropic plastic flow of lamellar colonies. By TEM observation and EBSD analysis further, the deformation mechanism of current alloy is concluded as dislocation slip and mechanical twins.     

Effect of growth rate on characteristic lengths of microstructure in directionally solidified Ti-46Al-2Cr-2Nb-0.2B alloy

The microstructure of TiAI based alloys is sensitive to growth rates. In this paper, Bridgman directional solidification of Ti-46Al-2Cr-2Nb-0.2B （at.%） alloy was carried out at a constant temperature gradient （G） to investigate the effects of various growth rates （v） on characteristic lengths （primary dendritic arm spacing, secondary dendritic arm spacing and lamellar spacing） of the microstructure. Results show that under the experimental conditions of G = 18 K-mm-1 and v = 15 IJm.s-1 to 70 iJm.s-1, the primary phase of directionally solidified Ti-46AI-2Cr-2Nb-0.2B alloy is a phase, the values of primary dendritic arm spacing （2,）, secondary dendritic arm spacing （λ2） and lamellar spacing （λta） decrease with the increase in growth rate. The results were compared with theoretical models and similar experimental results of TiAI based alloys. The Bouchard-Kirkaldy model agrees well with the relationship between primary dendritic arm spacing and growth rate obtained in the experiment; the relationship between them can be expressed by ,; = 758.6v-039. The relationship between the secondary dendritic arm spacing and the growth rate can be expressed by 2 = 113.9v-045, while the relationship between the lamellar spacing and growth rate can be expressed by ,; = 22.88v-v94.     

Ti–4.5Al–6.5Mo–2Cr–2.6Nb-2Zr-1Sn钛合金的高温变形行为

超高强韧钛合金是制造超规格航空结构件的骨干材料。通过热模拟压缩实验研究了Ti-4.5Al-6.5Mo-2Cr-2.6Nb-2Zr-1Sn钛合金高温变形行为,采用临界条件动力学模型建立高温下动态再结晶体积分数预测模型。本研究取得的阶段性成果将为超大尺寸、复杂形状的关键结构件的集成制造提供理论支撑。     

用循环热处理细化Ti-46Al-2Nb-2Cr合金的显微组织

采用磁悬浮感应熔炼铸造方法制备了Ti-46Al-2Nb-2Cr(at%)合金,通过显微组织观察,研究了近空冷及循环热处理条件下,粗晶铸造Ti-Al合金的显微组织细化.结果表明,通过近空冷方式可获得平均晶粒度为500 μm的全层状组织片,然后通过在α+β双相区的循环热处理可以将粗大的层片状组织细化成平均晶粒度为30 μm的全层状组织.     

Effects of Thermal Exposure on the Tensile and Fatigue Properties of Cast Ti—47Al—2Cr—2Nb--0.15B Alloy

测量了铸造Ti—47Al—2Cr—2Nb-0．15B(原子分数，％)合金的高温疲劳强度以及650℃／100h和800℃／100h热暴露后的拉伸性能和疲劳强度，采用X射线衍射和扫描电镜等方法分析了经热暴露后合金基体组织的变化和表面层的结构．随暴露温度的提高，合金的室温塑性和疲劳强度降低，650℃附近有一转折点，大于650℃时上述性能加速下降；合金高温疲劳性能具有相似的变化规律．显微分析表明，在热暴露或高温疲劳实验时，表面形成的脆性层是导致合金性能降低的直接原因；而随温度的提高，表面层由渗氧层转变为氧化层是导致合金性能随温度变化出现转折的原因．     

The microstructure evolution of directionally solidified Nb-22Ti-14Si-4Cr-2Al-2Hf alloy during heat treatment

To obtain a homogenous and optimizing microstructure, non-equilibrium directionally solidified (DS) samples at high withdrawal rate were heat treated (HT). The heat treatments were carried out at 1500 °C for 3–100 h. The DS and HT samples consisted of Nb_SS, α-Nb₅Si₃ and γ-Nb₅Si₃, and the DS morphology altered significantly after heat treatment. The well developed Nb_SS dendrites were compromised and the size decreased from more than 100 μm to less than 60 μm when the heat treated time was 6 h. On the other hand, the Nb_SS in eutectic interconnected and meanwhile connected with the dendrites, and the frequency of small size got lower with the heat treated time increasing. When heat treated for 100 h, the size of Nb_SS was comparatively uniform and concentrate in the region of 5–20 μm with a value of 63% for Ostwald ripening. The dendric and eutectic morphologies exited in the DS sample disappeared, turning into a net-work structure. The components of primary Nbss dendrites and Nbss in the intercellular regions were homogenized after heat treated for 3 h. However the enrichment of Ti, Cr and Hf in γ-Nb₅Si₃ compared to α-Nb₅Si₃ could not be eliminated by homogenizing treatment even for 100 h.     

High-temperature deformation behavior of a beta Ti-3.0Al-3.5Cr-2.0Fe-0.1B alloy

The high-temperature deformation behavior of a beta Ti-3.0 Al-3.5 Cr-2.0 Fe-0.1 B alloy was investigated by a Gleeble-1500 D thermal simulator. The height reduction was 50%, corresponding to a true strain of 0.693. The strain rate ranging from 0.01 to 10.00 s^-1 and the deformation temperature ranging from 800 to 950 ℃ were considered.The flow stress and the apparent activation energy for deformation, along with the constitutive equation, were used to analyze the behavior of the Ti-3.0 Al-3.5 Cr-2.0 Fe-0.1 B alloy. The processing map was established. The effect of strain rate on the microstructure at 850 ℃ was evaluated.The flow stress-strain curves indicated that the peak flow stresses increased along with an increase in the strain rate and decreased as the deformation temperature increased.Based on the true stress-true strain curves, the constitutive equation was established and followed as the ε= 6.58×10¹⁰[sinh(0.0113σ)]^3.44exp(-245481.3/RT). The processing map exhibited the "unsafe" region at the strain rate of10 s^-1 and the temperature of 850 ℃,and the rest region was "safe". The deformation microstructure demonstrated that both dynamic recovery(DRV) and dynamic recrystallization(DRX) existed during deformation. At the lower strain rate of 0.01 s^-1, the main deformation mechanism was the DRV, and the DRX was the dominant deformation mechanism at the higher strain rate of 1.00 s^-1.     

Local deformation and processing maps of Ti-24Al-17Nb-0.5Mo alloy

The processing maps were used to identify the optimal forging parameters of Ti-24Al-17Nb-0.5Mo alloy by evaluating the flow data according to the DMM model. The actual local strain rate and strain distribution in the samples were obtained by finite element calculations. The local microstructures of the deformed samples were related to the local deformation parameters and correlated with the processing maps at 0.3, 0.4, 0.5 and 0.6 of logarithmic strain. Flow regimes predicted by DMM analysis were then correlated with the local microstructural observations. Five domains of efficient coefficient could be distinguished. Unstable regions were microstructurally related to shear band formation within the α2 +B2 phase deformation field, and to flow localization at grain boundaries of B2 phase in the near B2 phase deformation field. Stable flow regimes were shown to be associated with dynamic globularization of the platelike α2 in the α2 +B2 phase deformation zone, and with dynamic recrystallization of B2 in the near B2 phase deformation zone.     

热机械处理对Ti-45Al-5Nb-0.3Y合金的显微组织与力学性能的影响

包套锻造Ti-45Al-5Nb-0.3Y合金由大量细小的动态再结晶等轴γ晶粒(晶粒尺寸可达1-2 μm),弯曲或破碎的层片和少量的残余平直层片组成,变形组织含有人量位错及少量变形孪晶.锻态试样抗拉强度(σb),延伸率(δ)分别达到708.1 MPa和0.95%.再通过不同的热处理分别得到晶粒细小的双态组织、近层片组织和全层片组织.经1320 ℃/30 min炉冷后得到双态组织,层片晶粒尺寸(d1)约为20 μm,层片体积分数(ψ1)约为60%,具有最高的δ,约为1-9%,σb约为658.9 MPa,为穿晶和沿晶混合断裂;经1340℃/30 min炉冷后得到近层片组织,dI约为60 gm,ψ1约为95%,O'b约为690.2 MPa,δ约为1.75%,上要为穿晶(层片)断裂;经1370℃/15 min炉冷后得到细小全层片组织(d1约为40 μm),具有最高的σb,约为715.1 MPa,5约为1.51%,为穿晶断裂.     

热处理工艺对 Ti-45Al-7Nb-0.15B-0.7W合金微观组织的影响

用电子探针对Ti-45Al-7Nb-0．15B-0．7W的铸态和经过热处理之后的微观组织进行了观察,研究热处理工艺对该合金微观组织的影响。结果表明：该合金的铸态组织经过热等静压和均匀化处理后,其晶团尺寸减小,片层组织更为完整;Ti-45Al-7Nb-0．15B-0．7W合金的α相转变温度在1280—1295℃之间。该合金在超过1295℃的温度进行热处理时,其微观组织由近片层组织转变为全片层组织。     

Ti-48Al-2Cr-2Nb-( TiB2, Ni)合金凝固组织演变规律及力学性能研究

TiAl合金已成为航空航天工程升级换代的关键材料,然而其铸态晶粒尺寸粗大,室温塑性和强度低,限制其进一步工程应用。本文采用真空感应凝壳熔炼工艺系制备铸锭,系统研究TiB2和Ni元素共同添加对Ti-48Al-2Cr-2Nb合金凝固组织和力学性能的影响。结果表明,TiB2及Ni合金化后,合金的凝固路径和初生相并未改变,晶粒尺寸从700μm细化至100μm,生成片状TiB2和富镍τ3相。T4822-( Ni, TiB2)合金的室温拉伸强度与基体合金相近,断裂伸长率提高30%。700-900℃时,T4822-(Ni, TiB2)合金的抗拉强度始终高于基体合金,在900℃时抗拉强度达到365MPa,较基体合金提高9%。800℃和900℃时T4822-(Ni, TiB2)合金的断裂伸长率分别达到25.3%和36.1%,远高于基体合金。晶粒尺寸的细化和晶界处的块状γ相是T4822-(Ni, TiB2)合金塑性提升的主要原因,其良好的高温强度则可以归因于片层团内部和界面处的硬质硼化物和富镍τ3相。     

Ti-6Al-3Nb-2Zr-1Mo钛合金热变形行为及加工图

利用Gleeble-3800热模拟试验机,在变形温度为820-1060℃及应变速率为0.001-1s_-1参数范围内对Ti-6Al-3Nb-2Zr-1Mo钛合金进行等温恒应变速率压缩试验。建立了该合金的高温变形本构方程,得到两相区和单相区的表面激活能分别为764.714 和126.936 kJ/mol。基于DMM和Prasad失稳准则建立了应变为0.4和0.7时的热加工图。分析加工图发现: Ti-6Al-3Nb-2Zr-1Mo钛合金在840–1060 ℃,应变速率为0.001–0.1 s_-1,之间主要发生DRV/DRX,此区间变形时耗散率峰值51%分别出现在940℃/0.001s_-1和880℃/1s_-1,其变形后微观组织演变机制与热加工图匹配较好,当变形发生在820℃,较高应变速率(≥1s_-1)下该合金加工时易发生流变失稳现象。     

Ti-47Al—6Nb-2Cr合金的制备与表征

采用非自耗电弧熔炼铸造方法,制备了Ti-47Al-6Nb-2Cr合金。采用金相观察、扫描电镜及透射电镜对其显微组织进行表征。结果表明,Ti-47Al-6Nb-2Cr合金在双相区近γ处理加循环快速热处理,可有效地将粗大的柱状组织细化成50μm~100μm的层状组织,这一细化过程主要是利用了块型转变的逆反应γ→α转变。     

Ti-25Al-14Nb-2Mo-1Fe合金的热变形行为及本构方程的建立

通过热模拟压缩试验研究了Ti-25Al-14Nb-2Mo-1Fe合金在变形温度950~1100 ℃,变形速率0.001~1 s^-1,最大变形程度50%条件下的热变形行为。结果表明：Ti-25Al-14Nb-2Mo-1Fe合金的流变应力对热变形工艺参数（变形温度和变形速率）的敏感性较高,其真应力-真应变曲线具有峰值应力、应变软化和稳态流动特征。采用Arrhenius双曲正弦函数和多元回归处理法确定了合金在试验条件下的应力指数n、变形激活能Q等材料参数,建立了Ti-25Al-14Nb-2Mo-1Fe合金高温变形本构关系模型。     

Ti-25V-15Cr-2Al-0.2C合金的组织、性能及其变形机制

对Ti-25V-15Cr-2Al-0．2C阻燃β钛合金的微观组织、拉伸性能和变形机制进行了研究。结果表明：(Ti，V)C和α相是β基体上的2种主要析出相；高温长期热暴露(540℃，100h)后的合金晶界上形成连续的α膜，其塑性因此急剧下降；β基体在热暴露过程中发生微弱的短程有序化(SRO)转变，这在一定程度上破坏了合金的热稳定塑性；该合金室温变形以普通位错滑移为主要形变机制，热暴露后的变形结构中出现少量平面滑移带，位错的交滑移和攀移是合金540℃高温变形的重要形变机制。     

Electron Beam Melting of Ti-48Al-2Nb-0.7Cr-0.3Si: Feasibility investigation

In this work, carried out within the European project TIALCHARGER, TiAl-based powders of Ti-48Al-2Nb-0.7Cr-0.3Si, were used to fabricate specimens and prototypes of hollow turbocharger turbines by Electron Beam Melting (EBM). This additive manufacturing technology uses an electron beam to generate parts by selectively melting the powders layer by layer according to CAD data. Components produced with these powders were characterized in terms of residual defects and resulted appropriate both in terms of overall residual porosity and maximum defect size. Furthermore the microstructure of the as produced material was investigated and heat treatments were set up in order to obtain the desired microstructure. This is an essential point for these materials because their mechanical properties are extremely sensitive to microstructure. Chemical composition of powders and massive materials were analysed. Loss of Al was observed, while the levels of impurities were very low and similar for both the powder and the part. Mechanical tests were performed on the heat treated samples and the results are in well agreement with literature data for this TiAl alloy for the desired automotive application.