SiC晶须增强6061Al基复合材料的热机械疲劳性能 Ⅱ．疲劳寿命和损伤机制

研究了体积分数为15%和28%SiCW／6061Al基复合材料的同相和反相热机械疲劳寿命和损伤机制。结果表明在小应变范围时,同相比反相疲劳寿命长,而在大应变时,同相疲劳寿命接近（对于28%SiCW)、甚至短于（对于15%SiCW)反相热机械疲劳寿命;15%SiCW/6016Al基复合材料的反相热机械疲劳寿命高于28%SiCW/6016Al基复合材料的寿命。两种材料的同相热机械疲劳寿命曲线存在交叉点,寿命高低取决于应变水平;同相和反相热机械疲劳的损伤均为空洞在SiC晶须周围基体中形核、长大和连接。     

SiC晶须增强6061Al基复合材料的热机械疲劳性能 Ⅰ．应力应变行为

对体积分数为15%和28%的SiCW/6061Al复合材料进行了同相和反相热机械疲劳（TMF）实验,研究了疲劳过程中的应力应变行为和变形机制。结果表明,两种材料在同相和反相加载下均表现为循环软化;反相加载产生拉伸平均应力,同相加载产生压缩平均应力;在相同应变范围下,高体积分数复合材料的循环应力范围比低体积分数复合材料的应力范围大。     

SiC纤维增强Ti基复合材料疲劳研究进展

对SiC纤维增强Ti基复合材料(SiCf/Ti)疲劳损伤机制、疲劳寿命及其影响因素进行详细的回顾,并重点综述了影响SiCf/Ti寿命的主要因素,包括外在因素(控制模式、应力比、加载频率、温度和环境)和内在因素(基体合金、纤维性质、纤维体积分数、界面和纤维涂层),提出了当前研究存在的问题和今后潜在的发展方向。     

IC10合金热机械疲劳性能与寿命预测

600～1 100 ℃时对IC10合金进行同相位、反相位、135-相位和-135-相位的应变控制热机械疲劳实验.发展了一种三参数幂函数能量方法的寿命预测方法,并用于材料的热机械疲劳寿命预测.对Manson-Coffin方程、拉伸迟滞能模型(Ostergren)、基于微裂纹扩展模型的能量方法和三参数幂函数能量方法热机械疲劳寿命预测能力进行评估,结果表明:材料的热机械疲劳应力-应变滞后回线的形状与温度-机械载荷之间的相位角有关;温度-机械载荷之间的相位角对材料的热机械疲劳性能有一定的影响;三参数幂函数能量方法物理意义明确,形式简单,寿命预测结果分布在2倍的分散带内,可以用来预测IC10合金的热机械疲劳寿命.     

H13热作模具钢热-机械疲劳损伤和寿命的预测

采用MTS热-机械疲劳试验机测定了H13热作模具钢在200～600℃、机械应变为0. 7%和0. 9%的同相和反相热-机械疲劳寿命,并基于循环损伤理论采用Ostergren寿命预测模型预测了H13钢的疲劳损伤和疲劳寿命。结果表明:无论是同相还是反相热-机械疲劳,其应力-应变响应曲线均明显不对称;高温半周的应力-应变响应曲线出现明显的应力松弛,且其塑性应变高于低温半周;随着循环周次的增加,H13钢的滞回能逐渐增大,机械应变增加,损伤加剧;与反相热-机械疲劳相比,H13钢的同相热-机械疲劳寿命更高。采用Ostergren寿命预测模型获得的机械应变为0. 7%和0. 9%的H13钢同相和反相热-机械疲劳寿命分别为323和313周次及198和194周次,均与实测值较为吻合。     

基于耦合损伤的镍基单晶高温合金同相热机械疲劳寿命预测

在应力控制的同相热机械疲劳试验基础上,研究了DD6高温合金同相热机械疲劳损伤机理。基于连续介质损伤力学,建立了反映蠕变损伤和疲劳损伤耦合作用的寿命预测模型,并利用纯蠕变、疲劳的试验数据获取了模型中的损伤参数。进一步,本文开展了带保载时间的DD6高温合金同相热机械疲劳试验,试验寿命在基于耦合损伤的预测寿命的2.3倍分散带内,这表明本文发展的基于耦合损伤的寿命预测模型能够较为准确地预测DD6高温合金同相热机械疲劳寿命,可以为工程应用中DD6高温合金结构的寿命预测提供基础。     

粉末冶金法制备SiC晶须增强MB15镁基复合材料

采用粉末冶金法制备了SiC晶须增强镁基复合材料(SiCW／MB15)试样。通过检测基体显微硬度探讨了SiCW对镁合金时效规律的影响，并借助扫描电镜(SEM)、透射电镜(TEM)和拉伸试验，研究了混粉方式对复合材料室温力学性能、SiCW分布及显微结构的影响。结果表明，MB15及其复合材料的时效硬化曲线上均存在双峰现象；SiCW的加入既提高了MB5的硬度，又加快了其时效速度：混粉方式对晶须分布及SiCW／MB15复合材料的室温力学性能影响很大。     

SiCf/Ti6242复合材料热机械疲劳损伤原位研究

采用声发射技术和高分辨X射线成像技术对SiC_f/Ti6242复合材料在热机械疲劳过程中的损伤进行了原位监测。实验中采用同相位梯形波加载来模拟钛基复合材料整体叶环服役时的实际载荷工况,应力变化范围130～1300 MPa,温度变化范围100～500℃,500℃时保持最大载荷2min。结果表明,声发射信号主要出现在加载阶段和保载阶段,声发射系统检测到纤维断裂、基体裂纹信号,而在卸载阶段声发射信号非常稀少。利用高分辨X射线成像技术对声发射确认已损伤的样品进行检查,发现试样内部存在连接多个纤维的基体裂纹;在样品裂纹区域,部分断裂纤维的钨芯出现缩颈。声发射技术和高分辨X射线成像技术均表明SiC_f/Ti6242复合材料热机械疲劳损伤机制由纤维断裂和基体裂纹共同控制。     

晶须增强铝基复合材料的热压缩变形行为研究

研究了2vol%Mg2B2O5w/6061铝合金复合材料在热变形过程中,不同变形温度、应变速率下流变应力的变化,并通过计算机拟合建立了热压缩变形本构方程。结果表明,压缩变形过程中复合材料的流变应力随着变形温度的升高而降低,随着应变速率的增大而升高。当应变速率在0.01¹.00/s之间时,材料呈现出动态回复特征。复合材料在热变形过程中的应变速率和流变应力关系符合双曲正弦函数关系。     

FRACTURE BEHAVIOUR OF SiC WHISKER REINFORCED Al COMPOSITES

The dynamic tensile processes of silicon carbide whisker reinforced Al composite(SiC_w/Al)with 22% V_f have been in situ observed with a scanning electron microscope equipped with atensile stand.The results show that a number of microcracks have formed as the tensile stressincreases to 180～190 MPa.Microcracks form in most cases at the whisker ends.The frac-ture behaviour of SiC_w/Al composite observed has been explained theoretically.KEY WORDS composite,fracture,stress distribution,SiC whiskers,aluminum     

碳化硅晶须增强铝复合材料的断裂研究

在备有拉伸台的扫描电子显微镜上原位观察了V_f为22％的碳化硅晶须增强铝(SiC_W/Al)复合材料压铸态试样和T_6态试样的动态拉伸过程。结果发现外加应力达到180-190MPa时复合材料内部就已形成许多微裂纹,裂纹一般在晶须端部形成,其扩展亦有一定的规律。经过对复合材料简化模型的复变函数分析和计算,求出了晶须周围应力场,进一步通过塑性力学的分析,从理论上解释了本文所观察到的实验现象。     

硼酸铝晶须增强Al复合材料的性能及界面结构

采用挤压铸造工艺制备出复合良好的9Al_2O_3 2B_2O_3晶须增强6061Al合金及纯Al复合材料研究表明,T6处理不能提高9Al_2O_3 2B_2O_3w/6061Al复合材料的力学性能,其原因是T6处理后复合材料中的界面反应明显加重利用透射电子显微术对此复合材料界面的观察与分析认为,界面上存在着严重的化学反应,反应物为Al_2MgO_4将制造态与T6态的界面结构对比发现,正是这种界面化学反应对材料的性能产生不利影响而在9Al_2O_3 2B_2O_3w/纯Al界面上未发现任何化学反应。界面能谱EDS成分分析结果表明,上述界面化学反应是由材料制造过程中基体合金中的Mg在界面上原子偏聚造成的     

SiC晶须增强硬Al合金复合材料的界面析出及其对性能的影响

本文对粉末冶金法制备的SiC晶须增强2124Al和2024Al两种复合材料进行了拉伸试验和断口观察,TEM和HREM证实在SiC_w/2024Al界面处存在链状不连续分布的θ(Al_2Cu)沉淀相,这种沉淀相降低了复合材料的室温强化效果,并对其塑性产生不利的影响。     

CHARACTERIZATION OF THERMO-MECHANICAL FATIGUE PROPERTIES FOR PARTICULATE REINFORCED COMPOSITES

A Voronoi cell element, formulated with creep, thermal and plastic strain was applied for investigation of thermo-mechanical fatigue behavior for particulate reinforced composites. Under the in-phase fatigue loading, the maximum of tensile deformation at the maximum given loading are larger than that at the same maximum under the out-phase fatigue. The stiffness decreases nonlinearly with the increasing of the phase angle, which results in increasing of the area of fatigue loop curve and the decrease in fatigue life. The spatially centralizing of inclusions results in decreasing of the plastic strain amplitude and the area of fatigue loop curve, which will also reduce the consumption of single-circle plastic strain energy and prolong the fatigue life.     

MECHANICAL PROPERTIES AND INTERFACIAL STRUCTURES OF ALUMINIUM BORATE WHISKER REINFORCED ALUMINIUM COMPOSITES

Quality 9Al_2O_3-2B_2O_3 whisker reinforced 6061Al or Al composites have beenprepared by technique of squeeze casting.The mechanical properties of the9Al_2O_3·2B_2O_3(w)/6061Al composites could be hardly improved by T6 treatment,owingto cause the remarkable interracial reaction.An observation under high resolution trans-mission electron microscope on interfaces shows that the serious chemical reaction occursand the product is Al_2MgO_4.But no such reaction is found at the interfaces of 9Al_2O_3.2B_2O_3(w)/Al composite.EDS analysis on the interfaces shows that above mentionedinterracial reaction may be resulted from the interracial segregation of Mg atoms in6061Al matrix during sequeeze casting.     

FATIGUE BEHAVIOUR OF SiC_p/6061Al COMPOSITE

The fatigue of SiC_p/6061Al composite containing 15 v.-% SiC particles has been compared with 6061Al alloy.Dislocation structure and microprocess of fatigue crack initiation and propagation in the composite have been investigated by using SEM and TEM.The results in- dicate that the fatigue strength at 10~7 cycles of the composite is 196 MPa,i.e.about 25% higher than matrix alloy.The voids and microcracks initiated at and near the interface be- tween SiC_p and matrix,where has a higher density of dislocations,will propagate and link up to form the fatigue crack.It is an important evidence to note that the dislocation channels where screw dislocation can travel are formed near interface and corner region of SiC_o in the composite subjected to fatigue stress(σ_(max)=274 MPa N=2.4×10~5 cycles),demonstrating the relationship between fatigue crack initiation and dislocation movement in the SiC particles reinforced 6061 Al alloy composite.     

SiC_p/6061Al复合材料的疲劳行为SCIEI

本文测定了用15v.-%SiC颗粒(10和2.5μm)增强的Al基复合材料的疲劳强度,并用SEM和TEM研究了疲劳裂纹形成及扩展与位错结构的相互联系,结果表明:两种尺寸SiC颗粒的复合材料在10~7循环寿命下的疲劳强度都是196MPa,比基体合金提高了25%,低于10~7循环周次寿命时含粗颗粒复合材料疲劳性能优于含细颗粒复合材料。SEM观察到疲劳微裂纹及微孔洞通常在SiC_P与基体界面附近形成,并在疲劳过程中相互连接成疲劳裂纹;TEM观察到界面处特别是SiC_P尖角处存在高密度位错,足够的疲劳循环周次后该处出现位错通道。     

EFFECTS OF HEAT TREATMENT ON THE THERMAL EXPANSION BEHAVIOR OF SiC WHISKER REINFORCED ALUMINUM COMPOSITE

1. IntroductionHigh specific stiffness and strength, good fatigue properties and tribological propertiesmake SiC whisker reinforcement aluminum composite as attractive class of candidates formany applications such as aerospace and electronic industries[1--2]. As structural componellts with temperature variable the materials used must have good performance includingnot only high mechalilcal properties, but also lower and stable coefficients of thermal expansion. Therefore, it is very important…