Tensile Mechanical Behavior and Failure Mechanism of a Plain-Woven SiCf/SiC Composites at Room and Elevated Temperatures

Ceramic matrix composites (CMCs) are the preferred materials for solving advanced aerospace high-temperature structural components;it has the comprehensive advantages of higher temperature (~1500˚C) and low density. In service environments, CMCs exhibit complex damage mechanisms and failure modes, which are affected by constituent materials, meso-architecture and inhere defects. In this paper, the in-plane tensile mechanical behavior of a plain-woven SiCf/SiC composite at room and elevated temperatures was investigated, and the factors affecting the tensile strength of the material were discussed in depth. The results show that the tensile modulus and strength of SiCf/SiC composites at high temperature are lower, but the fracture strain increases and the toughness of the composites is enhanced;the stitching holes significantly weaken the tensile strength of the material, resulting in the material is easy to break at the cross-section with stitching holes.

Ballistic Performance and Damage Characteristics of Chemical Vapor Infiltration Quasi 3D-Cf/SiC Composites

To investigate the ballistic performance and damage characteristics of quasi threedimensional（3D） needle-punched Cf/SiC composites prepared by chemical vapor infiltration（CVI）,penetration experiments were conducted by using 7.62 mm armor piercing incendiary（API）.Macro and micro fracture morphologies were then observed on recycled targets.The results show that the protection coefficient of 3D Cf/SiC composites is 2.54.High porosity and many micro thermal stress cracks may directly lead to the lower ballistic performance.Flat fracture morphology was observed on the crater surface.The low dynamic fracture strength along layer direction may be attributed to the voids and microcracks caused by residual thermal stress.The damage characteristics of Cf/Si C composites include matrix cracking,fiber bundle cracking,interfacial debonding,fiber fracture,and fiber bundle pull-out.And interfacial debonding and fiber fracture may play major roles in energy absorption.

Carbon Fiber Breakage Mechanism in Aluminum(Al)/Carbon Fibers(CFs) Composite Sheet during Accumulative Roll Bonding(ARB) Process

We put forward a method of fabricating Aluminum(Al)/carbon fibers(CFs) composite sheets by the accumulative roll bonding(ARB) method. The finished Al/CFs composite sheet has CFs and pure Al sheets as sandwich and surface layers. After cross-section observation of the Al/CFs composite sheet, we found that the CFs discretely distributed within the sandwich layer. Besides, the tensile test showed that the contribution of the sandwich CFs layer to tensile strength was less than 11% compared with annealed pure Al sheet. With ex-situ observation of the CFs breakage evolution with-16%,-32%, and-45% rolling reduction during the ARB process, the plastic instability of the Al layer was found to bring shear damages to the CFs. At last, the bridging strengthening mechanism introduced by CFs was sacrificed. We provide new insight into and instruction on Al/CFs composite sheet preparation method and processing parameters.

连续SiCf/TC17复合材料室温偏轴拉伸性能研究

采用磁控溅射法结合热等静压工艺制备SiCf/TC17复合材料,通过SEM观察试样的断口形貌,研究了复合材料在室温的偏轴拉伸性能及断裂机制。结果表明:纤维偏轴角度在0°~2°间,复合材料轴向性能变化较小,拉伸强度稳定在1960~1987 MPa;纤维偏轴角度再增大时(>2°),材料拉伸强度近似呈单调线性降低,由1870 MPa降至1797 MPa。纤维偏轴角度较小时(≤2°),平坦区基体与纤维断裂面平整,且两者的断裂面平行。纤维/基体界面没有明显的脱粘破碎迹象;纤维偏轴角度较大时(>2°),部分纤维存在“斜切断裂”,纤维拔出距离变长,且不再与基体的断裂面保持在同一平面,基体撕裂损伤严重。依据断口形貌结合局部承载模型,详细论述了SiCf/TC17复合材料两种拉伸失效的断裂过程。纤维偏轴角度较小时(≤2°),裂纹萌生于纤维间距较小的反应层,在界面处钝化或偏转进而形成不同截面的平坦区,当纤维超过承载能力极限,试样整体断裂;纤维偏轴角度较大时(>2°),“拉-剪”耦合效应导致C涂层与反应层间的界面脱粘破碎形成裂纹源,裂纹加速反应层受损或导致界面脱粘致使纤维断裂,当基体及剩余纤维超过承载能力极限,试样整体断裂。

Electromagnetic wave absorption and mechanical properties of SiC nanowire/low-melting-point glass composites sintered at 580°C in air

Si C nanowires are excellent high-temperature electromagnetic wave (EMW) absorbing materials. However, their polymer matrix composites are difficult to work at temperatures above 300℃, while their ceramic matrix composites must be prepared above 1000℃ in an inert atmosphere. Thus, for addressing the abovementioned problems, SiC/low-melting-point glass composites were well designed and prepared at 580℃ in an air atmosphere. Based on the X-ray diffraction results, SiC nanowires were not oxidized during air atmosphere sintering because of the low sintering temperature. Additionally, SiC nanowires were uniformly distributed in the glass matrix material. The composites exhibited good mechanical and EMW absorption properties. As the filling ratio of SiC nanowires increased from 5wt%to 20wt%, the Vickers hardness and flexural strength of the composite reached HV 564 and 213 MPa, which were improved by 27.7%and 72.8%, respectively, compared with the low-melting-point glass. Meanwhile, the dielectric loss and EMW absorption ability of SiC nanowires at 8.2–12.4 GHz were also gradually improved. The dielectric loss ability of low-melting-point glass was close to 0. However, when the filling ratio of SiC nanowires was 20wt%, the composite showed a minimum reflection loss (RL) of-20.2 dB and an effective absorption (RL≤-10 dB) bandwidth of2.3 GHz at an absorber layer thickness of 2.3 mm. The synergistic effect of polarization loss and conductivity loss in SiC nanowires was responsible for this improvement.

Damping performance of SiC nanoparticles reinforced magnesium matrix composites processed by cyclic extrusion and compression

This work dealt with the damping performance and its underlying mechanism in SiC nanoparticles reinforced AZ91D composite(SiC_(np)/AZ91D)processed by cyclic extrusion and compression(CEC).It was found that the CEC process significantly affects the damping performance of the composite due to alterations in the density of dislocations and grain boundaries in the matrix alloy.Although there would be dynamic precipitation of the Mg17Al12 phase during processing which increases the phase interface and limits the mobility of dislocations and grain boundaries.The results also showed that the damping capacity of 1%SiC_(np)/AZ91D composite continuously decreases with adding CEC pass number and it consistently increases with rising the applied temperature.Considering the first derivative of the tanδ-T curve,the dominant damping mechanism based on test temperature can be divided into three regions.These three regions are as follows(i)dislocation vibration of the weak pinning points(≤T_(cr)),(ii)dislocation vibration of the strong pinning points(T_(cr)∼T_(V)),and(iii)grain boundary/interface sliding(≥T_(V))

Effects of Co_(2)O_(3)Addition on Microstructure and Properties of SiC Composite Ceramics for Solar Absorber and Storage

SiC composite ceramics for solar absorber and storage integration are new concentrating solar power materials.SiC composite ceramics for solar absorber and storage integration were fabricated using SiC,black corundum and kaolin as the raw materials,Co_(2)O_(3)as the additive via pressureless graphite-buried sintering method in this study.Influences of Co_(2)O_(3)on the microstructure and properties of SiC composite ceramics for solar absorber and storage integration were studied.The results indicate that sample D2(5wt%Co_(2)O_(3))sintered at 1480℃exhibits optimal performances for 119.91 MPa bending strength,93%solar absorption,981.5 kJ/kg(25-800℃)thermal storage density.The weight gain ratio is 12.58 mg/cm2after 100 h oxidation at 1000℃.The Co_(2)O_(3)can decrease the liquid phase formation temperature and reduce the viscosity of liquid phase during sintering.The liquid with low viscosity not only promotes the elimination of pores to achieve densification,but also increases bending strength,solar absorption,thermal storage density and oxidation resistance.A dense SiO_(2) layer was formed on the surface of SiC after 100 h oxidation at 1000℃,which protects the sample from further oxidation.However,excessive Co_(2)O_(3)will make the microstructure loose,which is disadvantageous to the performances of samples.

Near-seamless joining of Cf/SiC composites using Y_(3)Si_(2)C_(2)via electric field-assisted sintering technique

A novel Y_(3)Si_(2)C_(2)material was synthesized at a relatively low temperature(900℃)using a molten salt method for the first time,and subsequently used as the joining material for carbon fiber reinforced SiC(Cf/SiC)composites.The sound near-seamless joints with no obvious remaining interlayer were obtained at 1600℃using an electric field-assisted sintering technique(FAST).During joining,a liquid phase was formed by the eutectic reaction among Y_(3)Si_(2)C_(2),γ(Y–C)phase,and SiC,followed by the precipitation of SiC particles.The presence of the liquid promoted the sintering of newly formed SiC particles,leading to their complete consolidation with the Cf/SiC matrix.On the other hand,the excess of the liquid was pushed away from the joining area under the effect of a uniaxial pressure of 30 MPa,leading to the formation of the near-seamless joints.The highest shear strength(Ä)of 17.2±2.9 MPa was obtained after being joined at 1600℃for 10 min.The failure of the joints occurred in the Cf/SiC matrix,indicating that the interface was stronger than that of the Cf/SiC matrix.The formation of a near-seamless joint minimizes the mismatch of thermal expansion coefficients and also irradiation-induced swelling,suggesting that the proposed joining strategy can be potentially applied to SiC-based ceramic matrix composites(CMCs)for extreme environmental applications.

Effect of C/Mo Duplex-coating on Thermal Residual Stresses in SiCf/Ti2AlNb Composites

Three-dimensional finite element physical models considering the layered distribution of materials at the interface were developed to study the effect of the coating system on distributions of thermal residual stresses in SiCf/Ti2AlNb composites.Two coating systems were comparatively studied,namely C coating and C/Mo duplex-coating.The thermal residual stresses after 1 080 ℃/1 h solution treatment and 800 ℃/20 h ageing treatment in the composites were also analyzed.The experimental results show that Mo coating can decrease thermal residual stress magnitude in the matrix.However,it would increase the thermal residual stresses in the interfacial reaction layer of TiC.The change of radial thermal residual stress in TiC layer is inconspicuous after solid solution and ageing treatment,but the hoop and axial thermal residual stresses increase obviously.However,the heat treatment can obviously reduce hoop and axial thermal residual stresses of the matrix,which is benefit to restrain the initiation and propagation of cracks in the matrix.

Effects of Heating Rate on Properties and Structures of 3D-Cf/SiC Composites by PIP Process

The properties and structures of 3D-Cf/ SiC composites prepared by rapid precursor infiltration pyrolysis process were studied.PCS solution was infiltrated into 3D-carbon fiber perform in vacuum,then these performs were dried at room temperature and pyrolyzed with three kinds of heating rate,3 900 min,1 500 min and 1 000 min respectively.The distinction of 3D-Cf/SiC samples fabricated at three kinds of heating rate was not obvious.Bending strength of sample at 1 000 min heating rate was 762.5 MPa,and a little better than the others.Three samples at various heating rate had similar micro-graph of fracture surface and fracture toughness.The research results show that mechanics performances of Cf/SiC composites did not decrease when heating rate was properly increased.

Joining and machining of(ZrB2-SiC)and(Cf-SiC)based composites

Filler materials of(ZrB_2-SiC-B_4C-YAG) composite were developed for gas tungsten arc welding(GTAW) of the ZrB_2-SiC and Cf-SiC based composites to themselves and to each other. Reaction with filler material,porosity and cracks were not observed at weld interfaces of all the joints. Penetration of filler material in to voids and pores existing in the Cf-SiC composites was observed. Average shear strength of 25.7 MPa was achieved for joints of Cf-SiC composites. By incorporation of Cf-SiC(CVD) ground short fibre reinforcement the(ZrB_2-SiC-B_4C-YAG) composite was machinable with tungsten carbide tool. The joint and machined composites were resistance to oxidation and thermal shock when exposed to the oxy-propane flame at 2300℃ for 300s. The combination of(ZrB_2-SiC-B_4C-YAG) and Cf-SiC based composites can be used for making parts like thermal protection system or nozzles for high temperature applications.

Cf/SiC复合材料表面抗氧化涂层研究进展

Cf/SiC复合材料因其低密度,高比强度,优异的抗热震、抗氧化和抗烧蚀性能以及高温强度保持率,被认为是高速飞行器的重要热防护材料之一。然而,由于碳纤维在500℃以上发生显著氧化导致材料逐渐失效,因此需对其进行有效的氧化防护。抗氧化涂层被认为是实现Cf/SiC复合材料长时氧化防护的有效手段。本文基于热防护系统对Cf/SiC复合材料抗氧化性能的苛刻要求,综述了现有Cf/SiC复合材料表面抗氧化涂层的研究进展,着重对抗氧化涂层制备技术及涂层体系进行了梳理。提升Cf/SiC复合材料抗氧化涂层使用温度(≥1800℃)及结合强度是当前需要重点解决的问题,制备更长服役时间、更高服役温度同时兼具抗氧化、抗水蒸气腐蚀乃至较好隔热性能的多功能涂层是未来发展的重要方向。

SiC/SiC复合材料层板低速冲击及其剩余强度试验研究

高速飞行器中的陶瓷基复合材料结构在服役过程中不可避免地会遇到低速冲击问题,低速冲击后的损伤形式以及剩余承载能力是影响飞行器结构安全的关键问题。本研究以二维编织SiC/SiC复合材料板件为研究对象,在不同能量下开展了低速冲击试验,分析了低速冲击载荷下试验件的表面损伤状态,通过计算机断层扫描技术观察了试验件内部的损伤形貌,结合冲击过程中的冲击响应曲线以及应变历史曲线,分析了SiC/SiC复合材料低速冲击过程的损伤机理。针对含勉强目视可见损伤的试验件开展了冲击后剩余强度试验,研究了勉强目视可见损伤对SiC/SiC复合材料剩余承载性能的影响。结果表明,在低速冲击载荷的作用下,试验件的表面损伤主要包括无表面损伤、勉强目视可见损伤、半穿透损伤以及穿透损伤,试验件的内部损伤主要有锥形体裂纹、纱线断裂以及分层损伤。低速冲击损伤会严重影响SiC/SiC复合材料的剩余性能,虽然试验件损伤勉强目视可见,但其剩余压缩强度为无损件81%,剩余拉伸强度仅为无损件的68%。

Processing and characterization of C_f/SiC composites

Carbon fiber-reinforced SiC composites were prepared by precursor pyrolysis-hot pressing （PP-HP） and precursor impregnation-pyrolysis （PIP）, respectively. The effect of fabrication methods on the microstructure and mechanical properties of the composites was investigated. It was found that the composite prepared by PP-HP exhibits a brittle fracture behavior, which is mainly ascribed to a strongly bonded fiber/matrix interface and the degradation of the fibers caused by a higher processing temperature. On the contrary, the composite prepared by PIP shows a tough fracture behavior, which could be rationalized on the basis of a weakly bonded fiber/matrix interface as well as a higher strength retention of the fibers. As a result, in comparison with the composite prepared by PP-HP, the composite prepared by PIP achieves better mechanical properties with a flexural strength of 573.4 MPa and a fracture toughness of 17.2 MPa.m^1/2.

Recent Progresses and Critical Issues of SiC_f/SiC Composite Under Irradiation Environments

SiC with fiber-reinforced composites, which are presently considered as the primary structural materials in some fusion reactor conceptual designs, are more attractive and competitive for structural materials in a fusion energy system because of its excellent chemical and mechanical properties such as high fracture toughness, induced-low activation, afterheat under 14MeV neutron irradiation environment at elevated temperature, and good compatibility with coolant and breeder materials. Thus it is important to investigate the research progress of advanced SiC composite, including transmuted helium gas, radiation swelling, radiation effects on mechanical properties, irradiation-enhanced creep, fatigue, physical properties associated with fusion design and their critical issues. This report summarized these results and addressed the major critical issues under irradiation conditions.

Ti预处理的SiC_(f)/SiC与镍基高温合金复合铸件的界面组织与强度

由SiC_(f)/SiC复合材料与K403镍基高温合金熔体制备的一体化铸件,冷却到室温时会出现自行断裂。通过采用Ti粉埋覆包渗工艺在1100℃下对SiC_(f)/SiC表面进行预处理,并在适当工艺下与K403镍基高温合金熔体进行陶瓷型精密铸造,成功实现SiC_(f)/SiC与K403镍基高温合金的一体化成形和界面的牢固结合。结果表明:Ti预处理层平均厚度为17μm左右,Ti向SiC_(f)/SiC渗透、扩散和反应,形成含TiC,Ti3SiC2,Ti5Si3Cx,SiC相的显微组织;经过与高温镍基金属液复合铸造后,预处理层演变成厚约120μm的界面反应层,其典型界面组织为Ni2Si+C+Al4C3+MC(M主要含Ti及少量的Cr,Mo,W)。预处理层的存在减轻Ni与SiC的有害石墨化反应,缓解高温金属液对SiC_(f)/SiC的热冲击,形成的界面反应层降低热膨胀系数失配造成的热应力,使得SiC_(f)/SiC与K403一体化铸件结合界面的室温剪切强度达到63.5 MPa。

Cf/SiC复合材料铣削加工过程仿真分析及试验研究

针对Cf/SiC复合材料铣削加工过程中刀具磨损快、加工效率低、加工工艺优化试验成本高等问题,开展Cf/SiC复合材料三维铣削仿真分析及试验研究。基于ABAQUS软件建立Cf/SiC复合材料三维铣削加工仿真有限元模型,预测加工过程中的铣削力,通过试验验证该模型的正确性。对比仿真预测的理论值和试验测得的实际值发现二者的平均误差仅为15%,所获取的一组较优的加工参数为Cf/SiC复合材料铣削加工参数优化提供了理论依据。

SiCf/TC17/GH4169复合材料界面结构和元素扩散研究

采用多组元两步构筑成型方法并结合热等静压技术制备了SiCf/TC17/GH4169复合材料,研究了复合材料界面微观结构组成和元素扩散规律。结果表明,在SiCf/TC17/GH4169复合材料中,SiC纤维保持完整、圆度均匀,纤维和TC17合金形成了连续致密的TiC反应层,TC17钛合金和GH4169发生元素扩散,形成了多个反应层。GH4169中Ni、Fe、Cr扩散进入TC17,形成了TiNi_(3)、Fe Cr、TiNi、Ti_(2)Ni等反应产物,TiNi_(3)和FeCr呈交错分布,TiNi和Ti_(2)Ni各自均呈连续条状分布。TC17和GH4169形成的多个反应层总厚度为25μm,加入TC17过渡组元后,能够改善SiC纤维和GH4169界面相容性,避免纤维被高温合金侵蚀。

Compression Creep Behavior of High Volume Fraction of SiC Particles Reinforced Al Composite Fabricated by Pressureless Infiltration

The compression creep deformation of the high volume fraction of SiC particles reinforced AI-Mg-Si composite fabricated by pressure-less infiltration was investigated. The experimental results show that the creep stress exponents are very high at temperatures of 673 K, 723 K and 773 K, and if taking the threshold stress into account, the true stress exponent of minimum creep strain rate is still approximately 5, although the volume fraction of reinforcements is very high. The creep strain rate in the high volume fraction reinforced aluminum alloy matrix composites is controlled by matrix lattice diffusion. It is found that the creep-strengthening effect of high volume fraction of silicon carbide particles is significant, although the particles do not form effective obstacles to dislocation motion.