Al_2O_3–SiC复相陶瓷的摩擦磨损特性

用真空热压工艺制备了Al2O3-SiC复相陶瓷.对热压烧结的纯Al2O3以及Al2O3-SiC复相陶瓷进行了摩擦磨损实验,研究了SiC添加量对复 相陶瓷摩擦磨损性能的影响.结果表明:在压力为25 MPa,1635℃热压烧结1h,当SiC的质量含量为5%时,Al2O3-SiC复相陶瓷的耐磨性最佳,虽摩擦系数最大(0.61,Al2O3则为0.46),但磨损率(WR)仪为5×10-4mm3/(N·m).Al2O3-SiC复合材料的磨损机理为脆性断裂引起的磨粒磨损,材料的 WR与断裂韧性(KIc)和Vickers硬度(Hv)的乘积(KIc1/2HV5/8)成反比.     

ZrB2对Al2O3-ZrB2-SiC复相陶瓷室温力学性能影响

Al2O3陶瓷具有优异的室温和高温性能,但其脆性大,断裂韧性较低,限制了其应用.采用热压烧结工艺制备了应用于不同环境的Al2O3-ZrB2-SiC复相陶瓷(简称AZS),主要研究不同含量的ZrB2对Al2O3-SiC基陶瓷性能的影响.力学性能研究发现,当Al2O3陶瓷中ZrB2和SiC的体积百分比分别为20％和5％时,AZS3陶瓷具有最高的强度和韧性,分别为508.5MPa和6.65MPa· m1/2,相比纯氧化铝陶瓷的468.6MPa和5.56 MPa· m1/22提高了8.5％和19.6％.     

太阳能热发电用氧化铝基复相陶瓷抗热震性及EPMA分析

为了提高Al2O3陶瓷的抗热震性及强度,在Al2O3基陶瓷中添加SiC、nano-ZrO2+SiC,利用无压烧结工艺,制备了用于太阳能热发电的Al2O3-SiC及Al2O3-ZrO2(3Y)-SiC复相陶瓷。材料的EPMA分析结果表明:样品中ZrO2颗粒在室温下为以亚稳四方相存在,在裂纹尖端应力场的作用下,ZrO2粒子发生四方相→单斜相的相变吸收能量,从而提高了材料强度及断裂韧性;原料中的部分SiC颗粒发生氧化反应,反应生成莫来石,针棒状莫来石形成桥连结构,阻止热震情况下产生的微裂纹发展成危险裂纹,从而提高材料抗热震性。SEM研究显示,SiC晶粒在外力作用下发生穿晶断裂、被拔出及桥结作用。     

氧化铝基纳米复合陶瓷显微结构的研究

考察了Al2O3-SiC和Al2O3-ZrO2(3Y)-SiC纳米复合陶瓷的断裂方式。由于SiC的加入,材料以穿晶断裂为主。通过透射电镜观察,研究了纳米复合陶瓷中材料SiC颗粒的分布,证明所制备的材料为晶内型纳米复合陶瓷。在Al2O3-ZrO3(3Y)-SiC纳米复合陶瓷中,小的ZrO2颗粒分布于Al2O3晶粒内,大的ZrO2晶粒位于Al2O3晶粒间,ZrO2的分布影响Al2O3晶粒的形状。通过高分辨透射电镜,观察了Al2O3-SiC和Al2O3-ZrO2(3Y)-SiC纳米复合陶瓷中Al2O3/Al2O3,Al2O3/SiC,Al2O3/ZrO2的界面。在两颗晶粒间的晶界几乎没有玻璃相的存在,证明纳米复合材料中晶界得到了加强,有利于力学性能的提高。     

多孔碳化硅陶瓷的原位氧化反应制备及其性能

以SiC为陶瓷骨料,Al2O3作为添加剂,通过原位氧化反应制备了Sic多孔陶瓷,并对其氧化反应特性及性能进行了研究.结果表明:在1 300～1 500℃,随烧结温度的升高,SiC的氧化程度增加,SiC多孔陶瓷的强度逐渐增加,但开口孔隙率有所降低.莫来石相在1 500℃开始生成·当烧结温度升高到1 550℃时,莫来石大量生成,得到了孔结构相互贯通且颈部发育良好的莫来石结合SiC多孔陶瓷;由于在SiC颗粒表面上覆盖了致密的莫来石层,SiC的氧化受到抑制,开口孔隙率因而升高,SiC多孔陶瓷的强度因莫来石的大量生成而增加.由平均粒径为5.0um的SiC,并添加20%(质量分数)Al2O3,经1 550℃烧结2h制备的SiC多孔陶瓷具有良好的性能,其抗弯强度为158.7MPa、开口孔隙率为27.7%.     

CaCO_3掺杂下原位反应制备SiC/莫来石复相多孔陶瓷的性能研究

以Al2O3粉末、SiC粉末为主要原料通过原位反应烧结技术,添加CaCO3为烧结助剂制备了SiC/莫来石复相多孔陶瓷,研究了不同CaCO3添加量对于SiC/莫来石复相多孔陶瓷的相组成、显微结构、抗弯强度、气孔率的影响,结果表明:通过添加CaCO3这一碱土金属化合物,不仅能够增强SiC颗粒间的颈部连接,同时研究表明当CaCO3含量为4%时,在1400℃下保温3h制备的样品综合性能最佳,其孔隙率为35.3%,抗弯强度达到51.9MPa。     

SiC/莫来石复相多孔陶瓷气孔率和强度的影响因素

以煅烧高岭土、Al(OH)3粉末、SiC粉末为主要原料,以石墨为造孔剂制备了SiC/莫来石复相多孔陶瓷,研究了造孔剂含量、碳化硅颗粒粒径以及烧结温度对SiC/莫来石复相多孔陶瓷抗弯强度和气孔率的影响,并分别用XRD和SEM分析晶相组成和断面显微结构.结果表明:当SiC粒径为60 μm,造孔剂含量为15％时,在1400℃下保温3h制备的样品综合性能最佳,其孔隙率为30.3％,抗折强度达到58.0 MPa.     

硅锭线切割回收料制备SiC多孔陶瓷的研究

以硅锭线切割回收料为主要原料、Al2O3为烧结助剂、石墨粉为造孔剂.用普通烧结工艺制备了SiC多孔陶瓷.着重研究了Al2O3添加量对SiC多孔陶瓷的形貌、热膨胀系数、气孔率以及力学性能的影响.结果表明:当Al2O3和石墨添加量分别为30wt%和10wt%,在1450℃温度下烧成的多孔陶瓷的气孔率高达42.21%、弯强度达到30.5Mpa、热膨胀系数为6.64×10-6K-1,可以满足在熔融金属过滤等方面的应用.     

SiC/Al2O3/MVQ导热复合材料的制备与性能研究

分别使用碳化硅(SiC)、氧化铝(Al2O3)和SiC/Al2O3复配物制备了导热甲基乙烯基硅橡胶材料(MVQ),研究了SiC,Al2O3和SiC/Al2O3用量及表面改性对MVQ导热系数和力学性能的影响,结果表明,随导热填料用量的增大,MVQ导热系数增大;同等用量下,SiC/Al2O3/MVQ复合材料的导热性能均优于SiC/MVQ和Al2O3/MVQ;当SiC/Al2O3总用量为50份且SiC/Al2O3质量比为3/1时,复合材料导热系数为0.76 W/mK;随SC/Al2O3用量的增加,拉伸强度与拉断伸长率均降低,邵尔A硬度增大.表面处理后,复合材料导热性能得到进一步改善.     

热压烧结Al2O3-ZrB2-SiC复相陶瓷的高温力学性能研究

为提高Al2O3陶瓷的高温力学性能,采用热压烧结工艺(烧结温度1 800℃,烧结压力20 MPa,保温1 h)制备了Al2O3-ZrB2-SiC复相陶瓷(简称AZS),并研究了ZrB2含量对Al2O3基陶瓷高温抗折强度和抗热震性的影响。结果表明:1)在Al2O3基陶瓷中加入第二相ZrB2能有效改善材料的高温抗折强度和高温强度保持率,在1 000和1 200℃时,加入20%体积分数ZrB2的AZS陶瓷试样具有最高的高温抗折强度,而加入24%体积分数ZrB2的AZS陶瓷试样具有最高的高温强度保持率。2)AZS陶瓷的抗热震性能优于纯Al2O3陶瓷。经100℃温差急冷后,加入20%体积分数ZrB2的AZS陶瓷具有最高的残余强度,比纯Al2O3陶瓷提高了17.2%;经300和500℃温差急冷后,加入24%体积分数ZrB2的AZS陶瓷都具有最高的残余强度,比Al2O3陶瓷分别提高了35.3%和20.9%。     

低压化学气相渗透法制备2.5维SiCf/SiC复合材料

采用低压化学气相渗透法制备了具有和不具有热解炭界面层的2.5维连续SiC纤维增强的SiC复合材料(SiCf/SiC).SiC纤维的体积分数为30%和41%.所制备复合材料的气孔率为20%左右.当纤维为30%时,沉积有0.1 μm热解炭界面层的复合材料的弯曲强度由未加热解炭界面层的232MPa增加到328MPa,而且材料由灾难性断裂转变为非灾难性断裂.在同一制备条件下,纤维体积分数为41%的SiCf/SiC比30%的SiCf/SiC具有更高的气孔率.纤维为41%时,热解炭界面层厚度为0.1 μm的SiCf/SiC的弯曲强度只有244MPa,但是它具有更高的韧性和更长的纤维拔出长度.     

三维针刺C/SiC复合材料的结构特征和力学性能

采用化学气相渗透法制备了在厚度方向上具有纤维增强的三维针刺碳纤维增强碳化硅(C/SiC)陶瓷基复合材料,复合材料的密度和气孔率分别为2.15 h/cm3和16%.三维针刺C/SiC复合材料中的针刺纤维将各层紧密结合在一起,其层间抗剪切强度显著提高,为95MPa,比二维碳布叠层C/SiC复合材料的剪切强度(35MPa)高171.4%.三维针刺C/SiC复合材料的拉伸强度和弯曲强度分别为159MPa和350MPa,断裂模式为非脆性断裂,包括:裂纹扩展、偏转,碳纤维的拉伸断裂和逐步拔出.     

Synthesis of monolithic SiC aerogels with high mechanical strength and low thermal conductivity

The monolithic silicon carbide (SiC) aerogels were converted from catechol-formaldehyde/silicon composite (CF/SiO₂) aerogels through carbothermal reduction and calcination. In the process of preparing the CF/SiO₂ aerogel, a new method was proposed to produce more silicon carbide and enhanced the mechanical properties of the SiC aerogel. This method was realized by adding an alkaline silica sol as supplemental silicon source. The principle process of CF/SiO₂ aerogels converting to SiC aerogels was discussed based on experiment and results analysis, while the microstructure, mechanical properties, and thermal properties of the prepared SiC aerogels were investigated. The results show that the as-synthesized SiC aerogels consist of β-SiC and a small amount of α-SiC nanocrystalline. It possessed a mesoporous structure and a low thermal conductivity 0.049 W/(m∙K), a relatively high compressive strength 1.32 MPa, and a relatively high specific surface area 162 m²/g. Due to their outstanding thermal and mechanical properties, the prepared SiC aerogels present potential applications in thermal insulation field, such as space shuttles and aerospace carrier thermal protection materials.     

The fabrication and mechanical properties of SiC/SiC composites prepared by SLS combined with PIP

Traditionally, SiC components with complex shapes are very difficult or even impossible to fabricate. This paper aims to develop a new manufacturing process, combining selective laser sintering (SLS), cold isostatic pressing (CIP) and polymer infiltration pyrolysis (PIP), to manufacture complex silicon carbide parts and improve the mechanical properties of silicon carbide ceramic parts. The density and porosity of SiC/SiC composites were measured. Furthermore, the mechanical properties of the specimens with cold isostatic pressing and the specimens without cold isostatic pressing were compared. The bending strength of the specimens with cold isostatic pressing was 201?MPa, and the elastic modulus was 1.27?GPa. And, the bending strength of the specimens without cold isostatic pressing was 142?MPa, and the elastic modulus was 0.88?GPa. Increasing the density of SiC/SiC can enhance the mechanical properties of SiC/SiC composites.     

Fabrication of Cf/SiC Composites by Vapor Silicon Infiltration

Carbon fiber reinforced silicon carbide matrix composites were fabricated by the vapor silicon infiltration process. The density and the open porosity of the composite infiltrated at 1973 K were 2.25 g/cm³ and ∼6%, respectively. The flexural strength of the composite at ambient conditions was 300 MPa. When the infiltration temperature decreased, the density and flexural strength of the composite also decreased. However, the resulting composite materials exhibited non-brittle fracture behavior.     

Effect of Reinforcement of a Silicon Nitride Matrix by Silicon Carbide Whiskers

A fine-grain high-density tough matrix is a general prerequisite for synthesis of high-strength and crack-resistant composite materials, as well as its self-reinforcement with extended grains of β-Si₃N₄ and reinforcement with β-SiC crystals. Both approaches are used simultaneously in the present work. It is shown that the reinforcement of a silicon nitride matrix based on ultradisperse powder compositions by SiC whiskers of grade TWS provides hot-pressed ceramics with a high ultimate bending strength (950 MPa) and crack resistance (10 MPa · m^1/2). Reinforcement by fine or coarse whiskers increases the crack resistance by 30% with respect to monolithic Si₃N₄. Composites reinforced by TWS silicon carbide whiskers preserve their high strength up to 1500°C.     

C/C–SiC composites derived from single-source poly(silylene–acetylene) precursors

Carbon-fiber-reinforced carbon–silicon carbide (C/C–SiC) composites were prepared by impregnating carbon fibers with ethynylphenyl-terminated poly(silylene–acetylene) (EPTSA) as a single-source precursor with subsequent hot pressing and pyrolysis. The structural evolution, crystallization behavior, and graphitization of bulk C–SiC ceramics, as well as their mechanical properties and ablation behavior, were investigated. The EPTSA precursor starts to transform into inorganic SiC ceramic materials at 800°C, which is characterized by an amorphous structure with weight loss, shrinkage, and densification between 800 and 1000°C. The formation of SiC crystals inhibited the growth of the graphitic structure between 1000 and 1200°C. As the temperature was raised, both graphite and SiC crystals continued to grow, and the crystalline forms became more complete. The carbon-fiber cloth (T300CF)-reinforced C–SiC composite (T300CF/C–SiC) prepared using polymer infiltration and pyrolysis (PIP) exhibited excellent mechanical properties. After five PIP cycles, the flexural strength, flexural modulus, and interlaminar shear strength of the T300CF/C–SiC composite reached 169 MPa, 32.5 GPa, and 9.38 MPa, respectively. In addition, the chopped-carbon-fiber-reinforced C–SiC composite fabricated using the PIP process demonstrated good oxyacetylene-torch ablation properties.     

MCMB–SiC composites; new class high-temperature structural materials for aerospace applications

Graphite–silicon carbide (G–SiC), carbon/carbon–silicon carbide (C/C–SiC) and mesocarbon microbeads–silicon carbide (MCMB–SiC) composites were produced using liquid silicon infiltration (LSI) method and their physical and mechanical properties, including density, porosity, flexural strength and ablation resistance were investigated. In comparison with G–SiC and C/C–SiC composites, MCMB–SiC composites have the highest bending strength (210 MPa) and ablation resistance (9.1%). Moreover, scanning electron microscopy (SEM) and optical microscopy (OM) are used to analyze the reacted microstructure, pore morphology and pore distribution of carbon-based matrices. As a result, SiC network reinforcement was formed in situ via a reaction between liquid silicon and carbon. The unreacted carbon and solidified silicon are two phases present in the final microstructure and are characterized by X-ray diffraction (XRD). Based on the results obtained and the low-cost processing of pitch-based materials, the MCMB–SiC composite is a promising candidate for aerospace applications.     

New porous silicon carbide composite reinforced by intact high-strength carbon fibres

A novel processing method to produce a carbon-fibre-reinforced silicon carbide (C/SiC) is presented and the mechanical properties are evaluated. The low-cost process yields a reaction bonded silicon carbide matrix but avoids efficiently reactive damage of the carbon fibres. Thus, the C/SiC-material shows a fibre-dominated behaviour due to high fibre strength and matrix porosity. The characteristics and mechanical properties of this C/SiC are highlighted. The discussion deals with the particular mechanical characteristics of porous-matrix materials relating to similar materials investigated hitherto.