Fatigue behavior of SiC reinforced Ti(6AI-4V) at 650 °C

Axial, low cycle fatigue properties of 25 and 44 fiber vol pct SiC/Ti(6Al-4V) composites, measured at 650 °C, were compared with the fatigue properties of unreinforced Ti(6Al-4V) at the same temperature. A prior study of the fatigue behavior of this composite system at room temperature indicated that the SiC fiber reinforcement did not provide the anticipated improvement of fatigue resistance of this alloy. At 650 °C, the composite fatigue properties degraded somewhat from those at room temperature. However, these properties degraded more for the unreinforced matrix at 650 °C with the result that the composite fatigue strength was two to three times the fatigue strength of the matrix alloy. The reasons for this reversal are discussed in terms of crack initiation at broken fibers and residual matrix stresses.     

Effect of environment on the thermal fatigue response of an SCS-6/Ti-24Al-11Nb composite

A study has been conducted examining the thermal fatigue characteristics of an α₂/SiC composite; in particular, SCS-6 reinforced Ti-24Al-11Nb (at. pct). The effort included the investigation of the effect of the environment by cycling coated and uncoated specimens in air and in an inert environment. Damage assessment was determined by postcycling room-temperature tension testing as well as by microstructural examination, including both optical microscopy and scanning electron microscopy (SEM). Significant reductions in postcycling tensile strength were observed for coated and uncoated specimens thermally cycled in air from 150 °C to 815 °C for 500 cycles, while no measurable loss of strength was found for specimens cycled in a low-pressure inert environment under otherwise identical conditions. The synergistic effect of residual stresses due to a coefficient of thermal expansion (CTE) mismatch and environment on the degradation of tensile properties of the thermally cycled composite is found to be the critical damage evolution mechanism for both coated and uncoated composites cycled in air. Residual stresses alone were found not to be critical in creating damage that could be tracked by a loss in residual strength.     

Microstructure and properties of spray-deposited 2014+15 vol pct SiC particulate-reinforced metal matrix composite

A metal matrix composite (MMC) of 2014 aluminum alloy reinforced with 15 vol pct SiC particulate was produced by the spray-forming-deposition process. The as-deposited preform revealed a high density and a homogeneous reinforcement distribution. Reactive products were not found on interfaces between the reinforcement and the matrix. Compared to the control alloy, the composite showed accelerated aging after solutionizing at 502 °C, while aging was retarded after solutionizing at 475 °C. Analysis indicated that the activation energy was almost the same for the aging process after different solutionizing treatments. This suggested that while the thermal barrier for the aging process was the same, other factors affecting the aging process should be considered. For example, the effective concentration of the precipitate forming elements possibly decreased after incompletely solutionizing at 475 °C. After heat treatment, the composite showed a tensile strength similar to the control alloy. The wear resistance of the composite improved considerably. The aging behavior of the composite was also studied using the nanoindentation technique. Steep gradient distribution of elastic modulus and hardness around the reinforcement SiC particulate was observed. Theoretical analysis showed that this could be attributed to the gradient distribution of precipitates, resulting from a gradient distribution of dislocation density around the SiC particulates caused by residual thermal misfit stresses.     

纳米SiC增强纯Al基复合材料的微观组织和力学性能

与采用微米尺度SiC颗粒为增强相制备的Al基复合材料相比,以纳米SiC颗粒为增强相制备的Al基复合材料具有更加优异的力学性能,可极大提高SiC增强Al基复合材料的服役可靠性及应用范围。采用传统粉末冶金方法制备纳米SiC颗粒增强纯Al基复合材料,研究烧结温度和增强相体积分数对复合材料微观结构和力学性能的影响。研究表明,烧结温度和增强相体积分数均对复合材料的微观结构和力学性能有重要影响。随烧结温度升高,复合材料中的残留微孔减少,密度和强度均得到显著提高。含体积分数为3%纳米SiC颗粒的复合材料在610℃具有最高的强度,进一步提高纳米SiC颗粒的含量并不能提高材料的力学性能,这主要是由于当纳米SiC颗粒的体积分数超过3%时将出现明显的团聚,从而降低强化效应。     

C/C复合材料SiC涂层裂纹形貌及分布的研究

由于涂层与C/C复合材料之间热膨胀系数不匹配,当冷却至室温时在高温下制备的抗氧化涂层会产生裂纹,为分析涂层裂纹的组态,通过在碳毡和真空穿刺两种C/C复合材料基体上制备单层、双层SiC涂层来研究涂层裂纹的形貌及分布.利用金相显微镜和扫描电镜观察两种涂层裂纹的形貌和分布,解释了裂纹与涂层所受热应力及基体原有缺陷的关系,利用XRD分析了单层和双层涂层的成分,说明了不同类型SiC结构与涂层裂纹之间的联系.结果表明涂层裂纹分布及裂纹宽度与基体纤维方向有关;随着涂层厚度增大,微裂纹数量减少;基体原有缺陷会导致涂层产生穿透性裂纹.     

Failure of SiC particulate-reinforced metal matrix composites induced by laser thermal shock

Thermal failure of SiC particulate-reinforced 6061 aluminum alloy composites induced by both laser thermal shock and mechanical load has been investigated. The specimens with a single-edge notch were mechanically polished to 0.25 mm in thickness. The notched-tip region of the specimen is subjected to laser beam rapid heating. In the test, a pulsed Nd:glass laser beam is used with duration 1.0 ms or 250 μs, intensity 15 or 70 kW/cm², and spot size 5.0 mm in diameter. Threshold intensity was tested and fracture behavior was studied. The crack-tip process zone development and the microcrack formation were macroscopically and microscopically observed. It was found that in these materials, the initial crack occurred in the notched-tip region, wherein the initial crack was induced by either void nucleation, growth, and subsequent coalescence of the matrix materials or separation of the SiC particulate-matrix interface. It was further found that the process of the crack propagation occurred by the fracture of the SiC particulates.     

Three-dimensional modelling of thermal residual stresses and mechanical behavior of cast SiC/A1 particulate composites

Thermal residual stresses developed during casting of SiC/aluminum particulate-reinforced composites were investigated as a function of cooling rate and volume fraction of particles using thermo-elastoplastic finite element analysis. The phase change of the matrix during solidification and the temperature-dependent material properties as the composite is cooled from the liquidus temperature to room temperature were taken into account in the model. Further, the effect of thermal residual stresses on the mechanical behavior of the composites was also studied. Based on the study, it was found that the matrix undergoes significant plastic deformation during cool down and has higher residual stress distribution as the cooling rate increases. The model which does not include the solidification of the matrix tends to overestimate the residual stresses in the matrix and underestimate the tensile modulus of elasticity of the composites. In addition, the presence of thermally induced residual stresses tends to decrease the apparent modulus of elasticity and increase the yield strength of the composites compared to those without residual stresses.     

SiC纳米及晶须增强Si_3N_4基复相陶瓷断裂行为的研究

用扫描电镜、透射电镜及努氏压痕法研究了添加SiC晶须、纳米颗粒及晶须和纳米颗粒的三种Si3N4基复相陶瓷在外力作用下的断裂行为。这三种材料断裂的主要方式是沿晶断裂 ,偶尔可见穿晶断裂。在裂纹发展的路径上当裂纹尖端遇到了晶须、集聚的纳米颗粒及类晶须时 ,会产生扭转、偏转、断裂、拔出和终止 ,从而使裂纹能量消耗 ,抑制和阻碍了裂纹的扩展和传播 ,起到了增韧补强的作用。     

莫来石/SiC复相材料的烧结工艺和成分优化

利用工业氧化铝和超细氧化硅合成莫来石，并结合SiC制备出了莫莱石／SiC复相材料。研究了烧结工艺及氧化铝和氧化硅的摩尔比对复相材料密度和强度的影响，并以材料的热震残余强度为指标、利用正交设计法研究了微量添加剂的影响效果。结果表明，复相材料的体积密度随烧结温度的升高和烧结时间的延均出现先升高后降低的规律，而开口气孔率的变化规律则相反；随结合相中Al2O3与SiO2的摩尔比的提高，复相材料的密度增加、气孔密度降低，而强度则先增后减，通过烧结工艺与结合相和添加剂成分的优化，材料密度最高可达2．5g/cm^2，抗折强度达34．5MPa，耐压强度可达90MPa，热震后的残余强度率为67．2％。     

高温热震对具有SiC涂层的C/C复合材料压缩性能的影响

采用化学气相反应法在C/C复合材料表面制备SiC涂层,对SiC涂层C/C复合材料试样进行热震实验。利用X射线衍射仪(XRD)、扫描电镜(SEM)及能谱分析等研究涂层的形貌和结构,采用压缩性能试验研究热震次数及热震温度对SiC涂层C/C复合材料试样压缩性能的影响。结果表明:试样的抗压强度在197.9~237.0 MPa之间,平均抗压强度为210.4 MPa。在1 100℃下进行热震实验,抗压强度随热震次数增加呈近似线性降低趋势;当热震次数一定时(15次循环热震),在900~1 500℃温度范围内,抗压强度随热震温度升高逐渐降低。热震温度为1 500℃时,热震后试样的抗压强度略有升高,主要与热震过程中氧化形成的SiO2玻璃的高温自愈合作用有关。     

The anisotropic mechanical properties of a Ti matrix composite reinforced with SiC fibers

The anisotropic mechanical properties of a Ti alloy composite reinforced with SiC fibers have been investigated and rationalized using analytical models. The appropriate material model for this composite involves the following features: an interface that debonds and slides, a flaw insensitive ductile matrix, and high-strength elastic fibers subject to residual compressive stress caused by thermal expansion mismatch. This, model is broadly consistent with the longitudinal, transverse, and shear properties of the composite.     

Cracking mechanisms in thermally cycled Ti-6AI-4V reinforced with SiC fibers

A titanium alloy (Ti-6A1-4V) reinforced with continuous SiC fibers (SCS-6) was thermally cycled between 200 ‡C and 700 ‡C in air and argon. The composite mechanical properties deteriorate with an increasing number of cycles in air because of matrix cracks emanating from the specimen surface. These cracks also give oxygen access to fibers, further resulting in fiber degradation. The following matrix cracking mechanisms are examined: (1) thermal fatigue by internal stresses resulting from the mismatch of thermal expansion between fibers and matrix, (2) matrix oxygen embrittlement, and (3) ratcheting from oxide accumulating within cracks. Matrix stresses are determined using an analytical model, considering stress relaxation by matrix creep and the temperature dependence of materials properties. Matrix fatigue from these cycli-cally varying stresses (mechanism (1)) cannot solely account for the observed crack depth; oxygen embrittlement of the crack tip (mechanism (2)) is concluded to be another necessary damage mechanism. Furthermore, an approximate solution for the stress intensity resulting from crack wedging by oxide formation (mechanism (3)) is given, which may be an operating mech-anism as well for long cracks. S.H. THOMIN, formerly Graduate Student, Department of Materials Science and Engineering, Massachusetts Institute of Technology, Cambridge, MA     

Diffusion bonding reactions between a SiC/SiC composite and two superalloys during joining by hot isostatic pressing

Diffusion reactions during solid state joining of a ceramic SiC/SiC composite to two superalloys, Hastelloy X and Incology 909, by hot isostatic pressing (HIP) have been investigated. The HIP pressure was 200 MPa in all joining cycles, and the temperature/dwell time were either 800°C/15 min, 900°C/1 h or 1000°C/ 1 h. The reaction zones formed consisted of a thin layer of carbides surrounded by several layers containing silicides and free carbon. The thickness of the reaction layers increased with increasing temperature, but were more affected by the composition of the alloy. With more carbide formers in the alloy, the thickness of the reaction layer decreased. The SiC composite was found to be considerably more prone to reactions with these superallys during HIP as compared to Si₃N₄ under similar conditions.     

Mechanical interrogation of interfaces in monofilament model composites of continuous SiC fiber-aluminum matrix

The interfacial region between continuous SiC fiber and aluminum alloy matrix, in monofilament metal matrix composites (MMC), has been characterized. The study utilized two SiC fibers, produced by Textron (SCS-2) and Sigma (Σ) and two aluminum alloys: A11100 and A16061. Characterization methods employed included: optical and electron microscopy (i.e. SEM and EPMA), mechanical testing of as-received and heat treated single fiber samples and monitoring of acoustic emission (AE) during tensile tests. In addition, interfacial shear strength (ISS) was experimentally determined by t wo different techniques, indentation and fragmentation. Indentation tests were carried out in the temperature range of 0–320°C. Results indicate that load is transferred from the matrix to the fiber, primarily by frictional stresses. The friction between fiber and matrix during loading of composite stems residual compressive thermal stresses, which result from the temperature differential between consolidation and testing temperatures, and the difference between the thermal expansion coefficients of the fiber and matrix. Consolidation had no effect on fiber strength and no reaction zones formed. Exposure for 7000 h at 6000δC had no significant effect on ISS. Fiber fractures were accompanied by intense AE. The breaks produced a small piece between adjacent larger fragments, and gave rise to characteristic AE with distinct waveforms for the two different fibers (Σ and SCS-2).     

镁碳质塞棒棒头抗热震性优化及工业应用

浇铸钙处理钢时,铝碳质或尖晶石-碳质塞棒棒头容易被钢水中的游离[Ca]侵蚀,而使用镁碳质材料能降低[Ca]的侵蚀作用,进而提高棒头的使用寿命。研究了SiC细粉添加量对镁碳质棒头材料性能的影响,设计了镁碳质棒头复合结构并测试了产品的抗热震性,同时对比了镁碳质棒头与尖晶石-碳质棒头材料的常规性能和钢厂测试结果。研究结果表明,随着SiC细粉添加量的增多,材料常温强度和高温强度增大,而线膨胀系数下降。复合结构改善了棒头与棒身材料之间的物理匹配,提高了棒头稳定性,具体表现为镁碳质棒头试验样品经1 100℃热震循环3次后表面及内部均无裂纹。镁碳质棒头材料的力学强度虽稍弱于尖晶石-碳质棒头材料,但浇铸钙处理钢的表现更好。分析发现,导致尖晶石-碳质棒头材料损毁的直接原因是游离[Ca]的侵蚀。     

Time-dependent deformation in an enhanced SiC/SiC composite

Time-dependent deformation in an enhanced SiC/SiC composite has been studied under constant load at high temperatures of 1200 °C, 1300 °C, and 1400 °C. Creep damage evolution was evaluated by a Young’s-modulus change of partial unloading and microscopic observation. The addition of the glassy phase in the matrix is very effective for protecting the composite from oxidation. The transient creep is dominant in creep life at all the temperatures. An empirical equation is proposed to describe creep behavior of the composite. It is found that creep activation energy increases with creep time at stresses lower than matrix cracking stress, but the activation energy remains constant at stresses higher than the matrix cracking stress. The creep strain rate of the composite is considered to be controlled by creep of fibers based on examining the time, strain, stress, and temperature dependencies of creep strain rates.     

颗粒尺寸对真空浸渗SiC/Al复合材料性能的影响

采用无压浸渗法制备了SiC/Al复合材料,考察了复合材料中SiC颗粒尺寸对复合材料的组织结构、抗弯强度、摩擦磨损性能的影响.结果表明:随着SiC颗粒尺寸的减小,SiC/Al复合材料的残余气孔率逐渐减小,密度和抗弯强度逐渐增加;粒度配比有利于提高复合材料的抗弯强度.与灰铸铁配副时,材料的摩擦系数与磨损率明显依赖于碳化硅颗粒尺寸,二者均随颗粒尺寸的增大而先降低后增大.粒度配比能明显改善复合材料的干摩擦磨损性能.粗细颗粒的粒度配比具有相互强化的作用,有利于降低摩擦系数和磨损率,并使其趋于稳定.     

Observation of fatigue damage process in SiC fiber-reinforced Ti-15-3 composite at high temperature

Unnotched SiC (SCS-6) fiber-reinforced Ti-15-3 alloy composite is subjected to a tension-tension fatigue test in a vacuum of 2×10⁻³ Pa at 293 and 823 K with a frequency of 2 Hz and R=0.1. Direct observation of the damage evolution process during the test is carried out by scanning electron microscopy (SEM). Test temperature dependent and independent fatigue damage behaviors are observed. The early stage fiber fractures observed at the polished surface are not influenced by the test temperature; however, matrix crack initiation and propagation behaviors differ greatly with temperature. The evolution of interface wear damage also differs with temperature, becoming more severe at 823 K, and the interface wear damage zone increases with the increase of the number of fatigue cycles. The macroscopic fatigue damage appears as a modulus reduction associated with interface sliding, matrix crack propagation, and plastic deformation of the matrix. The deformation zone of the composite tested at 823 K spreads more than that at 293 K. The fatigue life of the composite tested at 823 K is longer than that at 293 K. This behavior is related to the difference in spread of the damage zone in the matrix.     

An analysis of thermal residual stresses in Ti-6-4 alloy reinforced with SiC and Al2O3 fibres

Thermal residual stresses in Ti6Al4V alloy reinforced with silicon carbide (SiC) and sapphire alumina (Al₂O₃) fibres are estimated based on an elastic-viscoplastic micromechanics analysis. Effects of fibre volume fraction and different manufacturing procedures are considered and comparisons made with published experimental results for the SiC fibre composite. Stress components in the Ti-6-4/Al₂O₃ are generally less than half the corresponding values in the Ti-6-4/SiC composite.     

Strength of Al-Zn-Mg-Cu matrix composite reinforced with SiC particles

The AA7075 alloys reinforced with SiC and without SiC particles were fabricated by a pressureless infiltration method, and then, their tensile properties and microstructures were analyzed. The spontaneous infiltration of molten metal at 800 °C for 1 hour under a nitrogen atmosphere made it possible to fabricate 7075 Al matrix composite reinforced with SiC, as well as a control 7075 Al without SiC. A significant strengthening even in the control alloy occurred due to the formation of in-situ AlN particle even without an addition of SiC particles. Composite reinforced with SiC particles exhibited higher strength values than the control alloy in all aging conditions (underaged (UA), peak-aged (PA), and overaged (OA)), as well as a solution treated condition. Spontaneous infiltration was further prompted owing to the combined effect of both Mg and Zn. This may lead to an enhancement of wetting between the molten alloy and the reinforcement. Consequently, strength improvement in a composite may be attributed to good bond strength via enhancement of wetting. The grain size of the control alloy is greatly decreased to about 2.5 μm compared to 10 μm for the commercial alloy. In addition, the grain size in the composite is further decreased to about 2 μm. These grain refinements contributed to strengthening of the control alloy and the composite.