激光沉积修复TA15合金的组织和力学性能

采用激光沉积修复方法对TA15槽损伤试样进行了修复试验,考察了修复试样的组织和力学特点,发现激光修复试样组织是由基材的双态组织经由热影响区过渡到修复区的网篮组织。修复区组织为粗大的原始柱状β晶,晶粒内为α/β网篮组织,晶内α片层取向随机,宽0.4～0.5μm。分析了修复区和坡面存在熔合不良缺陷的原因,并给出了纠正措施。修复试样的室温静拉伸结果表明,试样的抗拉强度接近工业锻件水平,表明修复区与基材之间形成了致密冶金结合,但由于修复区粗大柱状晶组织,试样的冲击韧性比基材稍差。     

激光冲击对E690高强钢激光熔覆修复微观组织的影响

为研究激光冲击对E690高强钢激光熔覆修复层微观组织的影响,选用专用金属粉末对E690高强钢试样预制凹坑进行激光熔覆修复,并使用脉冲激光对激光熔覆层进行冲击强化处理,同时采用扫描电镜、透射电镜和X射线应力分析仪分别对激光冲击前后激光熔覆层的微观组织和表面残余应力进行检测。结果表明:激光熔覆修复后,激光熔覆层组织为等轴晶,熔覆层与E690高强钢基体之间冶金结合良好,其表面残余应力为均匀分布的压应力。经激光冲击后,激光熔覆层截面晶粒得到细化,并观察到大量的形变孪晶,互相平行的孪晶界分割熔覆层粗大晶粒,在激光熔覆层的晶粒细化过程中发挥着重要作用;试样表层位错在{110}滑移面上发生交滑移,在晶界周围形成了位错缠结。经激光冲击后,激光熔覆层冲击区域表面残余压应力数值相较于冲击前提升了1.1倍。     

增材/等材复合制备Sc/Zr改性Al-Mg合金工艺研究

为了实现高性能、低孔隙率Al-Mg-Sc-Zr合金在航空航天主承力结构领域的广泛应用，采用激光熔化沉积-热轧复合工艺制备了Al-Mg-Sc-Zr合金试样。基于金相显微镜、扫描电子显微镜、显微硬度和室温拉伸实验等检测方法，探究了复合工艺与微观组织和力学性能之间的关系，确定了最优工艺参数；研究了热轧压下量对沉积态试样微观组织演变、微孔缺陷闭合行为及力学性能的影响规律。结果表明：微孔缺陷随压下量的增加而逐渐减少，当压下量达到50%时，微孔缺陷完全闭合，试样的强度和硬度显著提高，熔合线区域合金元素的分布变得均匀。在优化的工艺参数条件下，复合工艺制备试样的抗拉强度、屈服强度、延伸率和硬度分别为412 MPa、243 MPa、22.8%和118.76 HV，较未轧制试样分别提高了22.6%、12.5%、54.1%和15.3%。     

激光立体成形中熔池凝固微观组织的元胞自动机模拟

本文通过采用自适应网格技术, 将激光立体成形的宏观温度场模型和凝固微观组织的低网格各向异性元胞自动机模型(cellular automaton, CA)结合, 建立了适用于激光立体成形的集成数值模型. 模型包括基材的温度场分布, 熔池形貌和熔凝过程的凝固微观组织. 模拟了激光扫描速度为15 mm/s时, 激光作用在Fe-C单晶基材上形成熔池的形状以及熔池内凝固微观组织. 计算结果揭示了熔池内固液界面从平界面失稳到胞\枝晶的非稳态凝固过程, 并得到了平界面组织形成的白亮带. 白亮带上方形成了外延生长的枝晶列.     

激光工艺参数对钛合金表面NiCrBSi合金熔覆层组织及硬度的影响

在TC4合金表面进行了激光熔覆NiCrBSi合金涂层的试验 ,利用SEM和XRD等对熔覆层的微观组织进行了分析 ,测试了熔覆层的显微硬度。结果表明 ,激光工艺参数对熔覆层的组织和硬度有极大的影响 ,随稀释率的增加 ,激光熔覆层中形成了TiB2 和TiC等颗粒增强相 ,熔覆层的硬度明显提高。     

Ti6Al4V合金表面激光沉积复合涂层的组织和性能

为了增强Ti6Al4V钛合金的耐磨性,采用激光沉积制造方法在其表面上制备了以原位生成的TiC颗粒和直接添加的WC颗粒为增强相的耐磨涂层,观察了各涂层的微观组织,并测量了涂层的显微硬度和涂层在室温大气条件下的摩擦磨损性能。结果表明各涂层和基体呈现冶金结合,原位自生的TiC和部分熔化的WC颗粒均能够均匀弥散分布于基体上,由于增强相颗粒的弥散强化及激光沉积组织的细晶强化作用,基材的硬度和耐磨性均得到了提高。原位自生的TiC涂层比WC涂层硬度梯度分布平缓,但耐磨性稍差。     

316L不锈钢粉末光纤激光选区熔化特性

采用自行研制的光纤激光选区熔化快速成型设备,研究了选区激光熔化316L不锈钢粉末工艺参数、能量输入与样件致密度、表面形貌之间的关系以及微观组织特征。结果表明:扫描速度对成型效果影响最为显著;样件致密度随着激光能量密度提高有逐渐增大的趋势;能量密度作为选区激光熔化工艺的技术指标具有可操作性;表面形貌由激光功率与扫描速度比值所决定。深入探讨了能量输入、熔化凝固行为、激光功率与扫描速度比值与样件致密度、表面形貌的关系。结果表明:选区激光熔化凝固组织层内、层间熔合处为弧形,且为冶金结合,金相组织主要由柱状晶与等轴晶组成,层内靠近熔合线周围是柱状晶,而层间靠近熔合线附近主要是细小等轴晶,晶粒直径为1μm左右。     

激光熔覆NiCrBSi涂层组织及摩擦磨损性能

采用激光熔覆技术在H13钢表面制备了NiCrBSi合金涂层,利用OM,SEM,EDX和XRD等对熔覆层的微观组织进行了分析,测试了熔覆层的显微硬度和摩擦磨损性能。结果表明,激光熔覆层与基体形成了良好的冶金结合,熔覆层的组织主要由γ-Ni,Cr7C3和CrB等相组成。熔覆层显微硬度在650~850HV之间,明显高于H13钢基体的硬度。摩擦磨损实验表明,在相同的条件下,熔覆层的耐磨性比基体有了明显的提高,磨损体积减少了92.4%。通过对磨损后的试样进行粗糙度测试后表明,涂层具有更平滑的表面。     

直升机发动机涡轮导向器激光修复组织性能研究

研究了直升机涡轮导向器叶片的激光修复技术。以直升机四级涡轮导向器分解叶片为基材,以镍基合金为熔覆材料,在激光功率为1～2kW,扫描速度为2～15mm/s,光斑直径为1～3mm,层厚为0.2～0.6mm的工艺参数条件下,研究熔覆层的表面成形、显微硬度以及微观组织形貌。结果表明,综合叶片宏观形态、硬度分析与扫描电镜分析结果,可以得到组织细密、与基体呈良好冶金结合且无明显微观裂纹的熔覆层。因此,采用激光修复技术对受损涡轮导向器叶片进行修复的方案是可行的。     

激光熔覆TiC陶瓷涂层的组织和摩擦磨损性能研究

采用激光熔覆技术在TC4合金表面上制备了TiC陶瓷涂层,分析了熔覆层的微观组织,测试了熔覆层的硬度和摩擦磨损性能。结果表明:TiC激光熔覆层分为熔覆区和稀释区两个区域,熔覆区未受到基底的稀释,由TiC颗粒和TiC树枝晶组成;稀释区受到了基底的稀释,由TiC树枝晶和钛合金组成;TiC激光熔覆层的显微硬度在HV700~1500之间,明显地改善了TC4合金表面的摩擦和磨损性能。     

TA15钛合金激光沉积温度场数值模拟与检测

在综合考虑热源模型、对流辐射换热、相变潜热、材料非线性因素对激光沉积修复温度场影响前提下,建立了激光沉积修复的数学模型,采用有限元参数化设计语言(APDL)对多道多层激光沉积修复温度场进行了数值模拟。研究了激光沉积修复瞬时温度场及其中心高度上节点温度随时间变化情况,分析了修复件中心高度上温度梯度分布情况。搭建了激光沉积修复温度测量系统,对修复时表面温度进行了测量,并与模拟温度进行了比较,两者吻合较好。为控制激光沉积修复组织、提高修复质量提供有效手段。     

X-ray diffraction study of effect of deposition conditions on α--β phase transition and stress evolution in sputter-deposited W coatings

Pure W and W-Cu-W trilayer coatings were deposited on an Fe substrate by d.c. magnetron sputtering. The α-β phase evolution, intragranular stress evolution in sputter-deposited W layer were investigated by x-ray diffraction. They are directly related to the film microstructure, density and adhesion. Therefore, control of the film stress and phase component transition is essential for its applications. The phase component transition from β-W to α-W and intragranular stress evolution from tensile to compressive strongly depend on the deposition parameters and can be induced by lowering Ar pressure and rising target power. The compressively stressed films with α-W phase have a dense microstructure and high adhesion to Fe substrate.     

Impact of localized surface preheating on the microstructure and crack formation in laser direct deposition of Stellite 1 on AISI 4340 steel

Crack formation in laser cladding of the hardfacing alloy Stellite 1 on AISI-SAE 4340 steel was prevented through locally preheating the substrate prior to the deposition process. Numerical analysis showed that the preheating process helps developing a relatively steadier melt temperature as well as decreasing the cooling rates and consequently the thermal stresses during the subsequent deposition process. Microstructural analysis revealed a thicker cross-section with smoother surface profile, more uniform surface hardness and even distribution of a dendritic morphology in the preheated sample. This confirmed the presence of a well-developed melt pool with a homogeneous composition at solidification. The microstructure of non-preheated sample was, however, considerably non-uniform consisting of macro-scale colonies of dendritic and lamellar (eutectic) structures. The experimental observations, as implied through the numerical results, showed that the preheated sample, in general, reveals more uniform structure and properties making it less prone to cracking during the deposition process.     

Resonant elastic X-ray scattering: Where from? where to?

A series of quasi-static and dynamic tensile tests at varying temperatures were carried out to determine the mechanical behaviour of Ti-45Al-2Nb-2Mn+0.8vol.% TiB₂ XD as-HIPed alloy. The temperature for the tests ranged from room temperature to 850  ∘C. The effect of the temperature on the ultimate tensile strength, as expected, was almost negligible within the selected temperature range. Nevertheless, the plastic flow suffered some softening because of the temperature. This alloy presents a relatively low ductility; thus, a low tensile strain to failure. The dynamic tests were performed in a Split Hopkinson Tension Bar, showing an increase of the ultimate tensile strength due to the strain rate hardening effect. Johnson-Cook constitutive relation was used to model the plastic flow. A post-testing microstructural of the specimens revealed an inhomogeneous structure, consisting of lamellar α₂ + γ structure and γ phase equiaxed grains in the centre, and a fully lamellar structure on the rest. The assessment of the duplex-fully lamellar area ratio showed a clear relationship between the microstructure and the fracture behaviour.     

Effect of welding speed on butt joint quality of Ti–6Al–4V alloy welded using a high-power Nd:YAG laser

Annealed Ti–6Al–4V alloy sheets with 1 and 2 mm thickness are welded using a 4 kW Nd:YAG laser system. The effects of welding speed on surface morphology and shape, welding defects, microstructure, hardness and tensile properties are investigated. Weld joints without or with minor cracks, porosity and shape defects were obtained indicating that high-power Nd:YAG laser welding is a suitable method for Ti–6Al–4V alloy. The fusion zone consists mainly of acicular α′ martensite leading to an increase of approximately 20% in hardness compared with that in the base metal. The heat-affected zone consists of a mixture of α′ martensite and primary α phases. Significant gradients of microstructures and hardness are obtained over the narrow heat-affected zone. The laser welded joints have similar or slightly higher joint strength but there is a significant decrease in ductility. The loss of ductility is related to the presence of micropores and aluminum oxide inclusions.     

Microstructure characteristics of laser forming repaired Ti60 alloy

The microstructure characteristics of laser forming repaired (LFR) Ti60 (Ti-5.6Al-4.8Sn-2Zr-1Mo-0.35Si-0.3Nb) as-deposited and annealed samples are analyzed. The microstructure of as-deposited repaired zone (RZ) consists of epitaxial columnar prior β grains, in which fine woven α laths and β-phase between α laths exist. The heat-affected zone (HAZ) experiences a continuous microstructural transition from duplex microstructure of the base metal zone (BMZ) to the microstructure of RZ. The presence of silicide precipitates is observed in both RZ and BMZ in an annealed sample by transmission electron microscopy. They are identified as (Ti, Zr) 6 Si 3 distributed mainly at the α/β interface with the size of 100 300 nm. The fine αprecipitates are detected in BMZ by electron diffraction; there was no α detected in RZ.     

液氮冷却条件下激光快速熔凝Ni-28 wt%Sn合金组织演变

研究了在液氮冷却条件下激光快速熔凝Ni-28 wt%Sn亚共晶合金的组织演化过程. 结果显示, 熔池从上至下可以分为三个区域: 表层为平行激光扫描方向的α-Ni转向枝晶区; 中部为近乎垂直于熔池底部外延生长的α-Ni柱状晶区; 底部为少量的残留α-Ni初生相和大量的枝晶间(α-Ni+Ni₃Sn) 共晶组织. 激光熔凝区组织受原始基材组织的影响很大, 熔池中的α-Ni枝晶生长方向受到了热流方向和枝晶择优取向的双重影响. 与基材中存在的层片状、棒状和少量离异(α-Ni+Ni₃Sn)共晶的混合组织相比, 熔池内的共晶组织皆为细小的规则(α-Ni+Ni₃Sn)层片状共晶, 皆垂直于熔池底部外延生长, 并且从熔池顶部至底部, 共晶层片间距逐渐增大. 分别应用描述快速枝晶生长的Kurz-Giovanola-Trivedi 模型和描述快速共晶生长的Trivedi-Magnin-Kurz模型对熔池表层凝固界面前沿的过冷度进行估算, 发现熔池表层α-Ni 枝晶和(α-Ni+Ni₃Sn)层片共晶的生长过冷度在50.4-112.5 K 之间, 远大于相应深过冷凝固(α-Ni+Ni₃Sn) 反常共晶生长的临界过冷度20 K, 这说明文献报道的临界过冷度并不是反常共晶出现的充分条件.     

Analysis of the interface between a pulsed laser deposited calcium phosphate coating and a titanium alloy substrate

Calcium phosphate coatings deposited on titanium alloy are intended to add a bioactive surface to medical implants. This work presents the characterisation of the interface between Ti-6Al-4V and a crystalline calcium phosphate coating obtained by pulsed laser deposition, with a KrF excimer laser, at 575 °C and under a 45 Pa water-vapour atmosphere. The coating–substrate system was studied by secondary-ion mass spectrometry, scanning electron microscopy, X-ray diffractometry, Raman spectroscopy and X-ray photoelectron spectroscopy. The results show that the deposition process promotes the interdiffusion of substrate elements into the coating and coating elements into the substrate oxide layer. Thus, a graded layer of mixed calcium phosphate and amorphous titanium oxide is formed. For the substrate, a hydroxyapatite coating acts more as a barrier for oxygen incoming from a gas than as an oxygen source during deposition. Moreover, oxygen diffusion into the substrate occurs. Thus, the content of oxygen of this oxide layer diminishes with depth. When the oxygen concentration is low enough it is incorporated in solid solution in the titanium alloy . PACS 81.15.Fg; 68.55.-a; 87.68.+z