Ti60钛合金中富钕稀土相颗粒对叶片室温振动疲劳性能的影响

采用振动疲劳实验及SEM断口分析等方法,研究了含稀土元素Nd的Ti60高温钛合金稀土相颗粒对叶片振动疲劳裂纹萌生的影响.结果表明:叶片振动疲劳寿命与稀土相颗粒的尺寸和分布位置具有密切关系.稀土相颗粒尺寸越大,对叶片振动疲劳裂纹的萌生作用也越大,疲劳寿命降低;外露于或镶嵌于叶片表面的稀土相颗粒明显促进了叶片振动疲劳裂纹的萌生.     

Ti—15—3钛合金的疲劳断裂行为研究

研究了Ｔｉ－１５－３合金板材光滑和缺口疲劳及疲劳裂纹萌和方式，发现光滑疲劳试样裂纹多起源于板材原始表面，形成面源；面具有中心孔和边缺口试样的疲劳裂纹多起源于缺口处的机加工端面，形成角源的线源。而且５２０℃时效后所获得的板材的拉伸强度是比５４０℃时效的高７３ＭＰａ，但疲劳极限差别不大。     

TA15钛合金的高周疲劳性能和断裂特征

研究了双态组织的TA15钛合金的高周疲劳性能和疲劳断裂特征,结果表明,β转变组织中次生α相的数量和形态对疲劳性能有显著影响,次生相α相的球化显著降低了合金抗裂纹扩展的能力,而大量的片状次生α相则通过造成疲劳裂纹的分枝有效地降低了疲劳裂纹的扩展速度,提高了疲劳极限.     

ZTC4（Ti-6Al-4V）铸造钛合金的室温低周疲劳行为

研究了ZTC4钛合金应变控制的室温低周疲劳行为,对循环应力-应变和应变疲劳寿命数据进行了分析,通过双对数线性回归处理,得出了Manson-Coffin处理模型的疲劳参数。结果表明：ZTC4钛合金总应变幅在0.6%～0.8%时,材料存在轻度循环软化的现象;总应变幅为0.4%～0.5%时,循环初期表现出循环硬化的现象,而后循环软化。合金的疲劳裂纹萌生于试样表面,裂纹扩展区存在明显的疲劳条带,合金疲劳断口呈现韧性断裂特征。     

Ti—25Al—10Nb—3V—1Mo合金的高周疲劳性能及断裂特征

实验测定了Ｔｉ－２５Ａｌ－１０Ｎｂ－３Ｖ－１Ｍｏ合金６５０℃下高周疲劳Ｓ－Ｎ曲线及热暴露后合金的疲劳性能。结果表明，Ｔｉ－２５Ａｌ－１０Ｎｂ－３Ｖ－１Ｍｏ合金具有较高的疲劳强度，可以满足转子零件的要求。对比光滑和缺口试样的高周疲劳性能，可以看出该合金缺口敏感程度高，且随着应力水平的增加而增大。     

热处理对Ti6242S钛合金组织性能及探伤的影响

采用固溶时效及退火两种工艺对Ti6242S钛合金大棒材进行热处理,研究了不同热处理坯料尺寸对显微组织、力学性能以及探伤杂波水平的影响。结果表明:固溶时效态Ti6242S钛合金大棒材越靠近心部初生α含量越高,而退火态显微组织中等轴初生α相含量较固溶时效态更高;普通退火处理后蠕变性能较差,固溶时效态综合性能最好;固溶时效处理后大棒材水浸探伤底波的均匀性略有提高,而普通退火无此效果。     

Ti/TiN/Zr/ZrN多层膜对钛合金疲劳性能的影响

采用真空阴极电弧沉积技术在TC11钛合金基体上沉积约10μm厚的Ti/Ti N/Zr/Zr N多层膜,通过对比镀膜前后试样的屈服强度、抗拉强度、疲劳强度、疲劳寿命,以及断口形貌,研究沉积Ti/Ti N/Zr/Zr N多层膜对基体疲劳性能的影响,探讨疲劳断裂机理。结果表明:多层膜对TC11钛合金基体材料的屈服强度和抗拉强度影响不大,但由于膜层硬而脆而降低了基体材料的收缩率和延伸率;多层膜提高基体材料的疲劳极限;低应力下,裂纹源在多层膜表面萌生,并向内部扩展,在多层结构的膜层界面处受到阻碍,发生偏转,从而提高基体疲劳寿命;高应力下,膜层容易破裂,裂纹源增多,降低基体疲劳寿命;应力水平在520 MPa到650 MPa范围内,疲劳寿命增量从+40.82%降到-36.88%。     

Ti60合金热变形行为与应变补偿型本构模型

目的 确定Ti60合金在高温下的应变行为,促进材料性能的优化和工程应用的发展。方法 在变形温度为900、950、990、1 020、1 050℃,应变速率为0.001、0.01、0.1、1、5 s^-1,最大变形量为60%条件下,利用Gleeble-3800热模拟实验机对Ti60试样进行不同应变速率的热压缩实验。结果 Ti60合金的高温流变应力-应变规律如下：当温度一定时,随着应变速率的升高,峰值应力上升,当温度和应变速率一定时,随着应变的升高,应力表现为先上升后下降的趋势,而在1 020℃、0.01s^-1条件下,表现反常,这可能与第二相的动态析出有关。不同真应变下的变形激活能Q=838.996 201 9 kJ/mol,相应的本构方程相关系数n=2.889 582,α=0.013 182 009,A=1.335 7×10³³,建立了Ti60合金热变形Arrhenius本构关系模型■,用于预测和优化Ti60合金在高温条件下的峰值应力。采用应变补偿方法计算了五次多项式的各个系数和其他应变对应的应力。通过比较由模型计算得到的流...     

铸态Ti40阻燃钛合金高温拉伸力学性能及断裂行为研究

研究了不同试验温度下铸态Ti40合金的高温拉伸力学性能变化规律,并采用光学显微镜和扫描电子显微镜对拉伸样断口形貌进行观测,确定其断裂机制。结果表明:合金的抗拉强度随着试验温度的升高而显著下降,而塑性则分别表现出两个塑性较优区和脆性区,即400℃以下低温和900~1000℃高温的较好塑性区以及500~800℃的热脆区和1000℃以上的高温脆性区。脆性区试样断口形貌均呈现为沿晶脆性断裂,这一断裂机制与合金粗大晶粒以及严重的氧化相关。高温塑性区断口形貌为穿晶韧性断裂,则合金具有较高的塑性和较低的变形抗力,可作为较好的热加工温度区间。     

Ti－15－3钛合金的成分控制及性能研究

研究了铝和氧对Ｔｉ－１５－３钛合金的力学性能和冷成形性能的影响，提出了该合金的成分控制范围，为该合金的工业化稳定生产提供了依据。针对我国的国情，提出了与３０ＣｒＭｎＳｉＡ结构钢等强度的时效制度，并研究了相应的力学性能。     

Dwell and Normal Cyclic Fatigue Behaviours of Ti60 Alloy

An experimental study of dwell and normal cyclic fatigue behaviours was carried out using specimens from a Ti60 forging with a bimodal microstructure.Apparent decrease in the fatigue life was found under dwell fatigue condition as compared to that under normal cyclic condition.Strain produced in each cycle in dwell fatigued specimens was observed larger than that in its normal cyclic-fatigued counterparts.Interior crack initiation was found in most dwell fatigued specimens as compared to the subsurface crack initiation under normal cyclic fatigue condition.Flat and bright facets were found at crack initiation sites in both cases.The facet density is higher in dwell condition,which is consistent with the crystal orientation and Schmid factors analysis of a grains around secondary cracks using electron back-scattered diffraction(EBSD) methods.Dwell loading favours cleavage in a grains with their basal plane normals aligned no more than 15° to the loading axis,which may account for its lower fatigue life according to the present study.     

Static and fatigue characterization of the Ti5553 titanium alloy

This paper presents and discusses static (elastoviscoplastic and damage) and high‐cycle fatigue characterization of two microstructures of the Ti5553 alloy. The difference between these two microstructures is related to their heat treatment and precisely to the temperature of the final aging. For each microstructure, several tests were carried out to identify their static and fatigue properties and the test results were correlated to the microstructure. A fractographic analysis of the rupture sections was performed in order to investigate the fracture mechanisms of the two microstructures. Finally, the fatigue properties of the two microstructures were compared with those found in results reported in the literature for two other classical titanium alloys used for aeronautical applications.     

Ti2AlNb合金与钛基复合材料的低温固相扩散连接机理

Ti2AlNb合金和Ti基复合材料可以使用直接固相扩散的方法进行连接,但较高的扩散温度使得母材发生相变,其接头性能也因此变差。采用Ti箔中间层的方法优化Ti2AlNb合金和Ti基复合材料的固相扩散连接接头性能。结果表明:加入30μm的Ti箔中间层后,扩散连接温度由950℃降低至850℃,变形率由5%降低至1.7%,扩散连接温度的降低有效地改变了接头界面的组织,典型界面组织为Ti2AlNb/富B2相/α+β双相组织/Ti基复合材料,其中接头界面处α+β双相组织的形成提高了接头的强度。最佳扩散连接工艺参数为850℃/60min/5 MPa时,剪切强度达到最大值399MPa,实现了Ti2AlNb和Ti基复合材料在低温下的扩散连接。     

析出相对Ti60钛合金蠕变和持久性能的影响

研究了固溶态的Si、硅化物以及α2相对Ti60高温钛合金蠕变和持久性能的影响.结果表明,α片层之间析出的硅化物能提高Ti60钛合金的600℃蠕变抗力,且当α片层内部有α2相析出时蠕变抗力提高更明显,但是硅化物的大量析出和大颗粒硅化物的存在却降低了Ti60钛合金的600℃持久性能;α2相的析出同时提高材料的蠕变抗力和持久性能;减少硅化物的析出以提高固溶态的Si对低应力下蠕变抗力的作用不显著,但是能改善高应力下的持久性能.在蠕变和持久实验条件下固溶态的硅和硅化物的不同作用,可通过不同外加应力水平下材料变形机制的差异加以解释.     

Ti60合金在650～750℃高温下的氧化行为

研究了Ti60合金(Ti-5．6A1-4．8Sn-2．0Zr-1．0Mo-0．85Nd-0．34Si)在650～750℃下的高温氧化行为；采用恒温或循环氧化增重方法、氧化速度常数、活度等理论计算研究了合金氧化的热力学和动力学规律；用X射线衍射(XRD)、扫描电子显微镜(SEM)等方法，研究氧化膜的表面形貌和结构；采用俄歇电子能谱(AES)分析元素沿深度方向的分布，研究元素在氧化过程中的扩散行为。研究结果表明：Ti60合金在650℃和700℃有较好的抗氧化性能，其循环氧化动力学曲线基本上符合抛物线规律；在750℃，氧化严重，其循环氧化动力学曲线近似符合抛物线一直线规律。氧化层由金红石结构的TiO2氧化物和少量的Al2O3组成。氧化表面形貌为网篮状组织，这是由于α相和β相的成分和结构不同，界面扩散和体扩散差异导致的氧化程度不同所造成的。稀土第二相处氧化严重，表面裂纹大多产生于稀土第二相颗粒。     

Simulated flight fatigue of an alpha/beta titanium alloy

Simulated flight (FALSTAFF) fatigue tests have been carried out on precracked single edgenotch test-pieces of (Ti4Al4Mo2Sn0.5Si) IMI 550 titanium alloy. Predictions of simulated flight fatigue behaviour have been made from constant amplitude fatigue data, using a damage accumulation approach, with no allowance for load history. The predicted lives were conservative compared with the measured lives, and accurate within a factor of approximately two. Retardation of fatigue crack growth increased with increasing load amplitude. The microstructure produced by β-solution heat treatment at 1010°C, followed by ageing, was found to improve simulated flight fatigue lives by up to approximately 100% compared with standard solution treatment at 900°C, followed by ageing.     

Effects of thermal exposure on cyclic deformation and fracture behavior of Ti600 titanium alloy

Effects of thermal exposure on cyclic deformation and fracture behavior of Ti600 alloy were investigated by laser scanning confocal microscope (LSCM), scanning electron microscope (SEM) and transmission electron microscope (TEM). The results demonstrated that both the nonthermal exposure (NTE) specimens and the thermal exposure (TE) specimens showed the cyclic softening, within a total strain amplitude range from ±0.45% to ±1.00%. During thermal exposure, since the harder α₂ (Ti₃Al) phase precipitated in the α_p (primary α) phase, the resistance of crack propagation of α_p phase could be increased by the precipitation of α₂ phase. Therefore, the fracture behavior of TE specimens is different with that of NTE specimens. For the NTE and TE specimens, the crack mainly passes through the α_p phase with “cutting” and “bypass”, respectively.     

Low cycle fatigue of a titanium 829 alloy

The fatigue behaviour of titanium 829 in its oil quenched (‘basketweave’) and air cooled (‘aligned’) microstructural forms has been examined at 600°C and room temperature under fully reversed, total strain controlled conditions. Identical endurances are observed for each microstructure together with a low transition life. Similarly, almost perfect cyclic stability is exhibited irrespective of microstructure, temperature, strain range and rate. This is tentatively attributed to the ability of the aligned colonies present in both microstructures to accomodate plasticity. It is argued that a reduction in strain rate shortens life due to environmental effects. Multiple crack initiation is generally associated with facet-like features, with later growth surfaces bearing striations only after fatigue at 600°C.     

Ti60合金高温连续氧化行为研究

研究了Ti60合金（Ti-5.6Al-4.8Sn-2.0Zr-1.0Mo-0.85Nd-0.34Si)在620℃，720℃和800℃时的连续氧化行为，用扫描电子显微镜和X射线衍射仪和X射线能谱仪研究分析了Ti60钛合金氧化层形貌，微观结构和成分分布，以研究Ti60合金在不同温度下的氧化机理，结果表明：Ti60和在620℃有较好的抗氧化性能，其连续氧化动力学符合抛物线规律。在720℃和800℃，氧化严重，其连续氧化曲线近似直线规律。