基体炭种类对C/C复合材料断裂韧性的影响

以针刺网胎/无纬布为预制体,采用CVD法和液相浸渍法制备了热解炭基、树脂炭基、沥青炭基C/C复合材料,并研究了这些材料的断裂韧性及其断裂机理。研究表明:沥青炭基C/C复合材料的XY向断裂韧性明显高于热解炭基和树脂炭基,其XY向和Z向分别达到4.54MPa·m~(1/2)和3.15 MPa·m~(1/2),表现为假塑性断裂;三种基体炭C/C复合材料的XY向断裂韧性均大于Z向。     

不同炭基体对炭/炭复合材料力学性能的影响

结合化学气相沉积（CVD）和前驱体浸渍裂解工艺,分别以丙烯、糠酮树脂和煤沥青为前驱体制备了密度在1.85g/cm3以上的三维炭/炭（C/C）复合材料,对比研究了沥青炭、热解炭+沥青炭以及热解炭+树脂炭结构（分别为A、B、C组）的等三种不同炭基体C/C复合材料的增密效率与力学性能,采用排水法表征C/C复合材料的孔隙率及密度,利用扫描电镜进行炭基体的微观结构表征,采用万用电子力学试验机进行拉伸强度、压缩强度、剪切强度等力学性能表征。结果表明,在热解炭质量含量相同的前提下,树脂浸渍裂解增密速率低于沥青浸渍裂解工艺,树脂炭基体孔隙率低于沥青炭基体。不同炭基体结构的C/C复合材料力学性能次序为：热解炭+树脂炭双元炭基体最高,纯沥青炭基体次之,热解炭+沥青炭双元炭基体最低,分析原因为热解炭与树脂炭双元炭基体的界面结合强度高,而沥青炭为混乱无序碳结构,热解炭和沥青炭双元炭基体界面结合强度弱,因此力学强度最低。     

沥青炭基C/C复合材料的载流摩擦磨损性能

通过对纯沥青炭基C/C复合材料、含炭黑沥青炭基C/C复合材料和添加氯化铁的沥青炭基C/C复合材料的载流摩擦磨损实验,发现含炭黑沥青炭基C/C复合材料的摩擦系数和磨损量最大,纯沥青炭基C/C复合材料的摩擦系数和磨损量次之,添加氯化铁的沥青炭基C/C复合材料的摩擦系数和磨损量最小,并对3种沥青炭基C/C复合材料的摩擦磨损机理进行了讨论。     

炭基体结构状态对C/C复合材料抗烧蚀性能的影响

碳基体在C／C复合材料的组成中占有很大的比重，因此炭基体不同的结构状态往往对C／C复合材料的各项性能有显著的影响。本文利用不同的原料和加工工艺制备出了三种具有不同炭基体的C／C复合材料，这三种碳基体分别是热解炭，沥青炭以及解热炭－树脂炭混合炭基体。对这三种材料多项性能的测试结果表明，炭基体的结构状态如石墨化度，炭片层结构的取向度的不同对C／C复合材料的各项性能均有显著的影响；基本趋势是C／C材料的石墨化度越高，材料的导电性能，导热性能以及抗烧蚀性能越好，压缩强度越低。三种炭基体中沥青炭基体沿纤维轴向的取向度最低，其抗烧蚀性能最差。     

热解炭结构对C/C复合材料热物理性能影响

炭布叠层为预制体，采用等温CVI工艺制备出炭/炭（C/C）复合材料。通过调节丙烯与氢气的比例得到热解炭结构分别为粗糙层（RL），光滑层（SL），各向同性（ISO）的三种C/C复合材料，研究了热解炭组织结构对C/C复合材料热导率的影响，讨论了C/C复合材料的导热机理。结果表明：RL织构C/C复合材料的热导率无论是在平行方向还是在垂直方向上都明显高于SL和ISO织构C/C复合材料，在两个方向上，RL织构C/C复合材料的最大热导率比SL织构C/C复合材料分别大41.0%和31.7%，是ISO织构C/C复合材料的2倍多，且3种C/C复合材料的热导率随温度的升高呈现不同的变化趋势。     

C/C坯体对C/SiC复合材料组织结构和导热性能的影响

以无涂层、C+SiC复合涂层处理的炭布/网胎预制体,分别经过化学气相渗透、树脂浸渍/炭化制备了3种C/C坯体,熔融渗硅后获得不同的C/SiC复合材料,对其组织结构和导热性能进行了研究。结果表明:热解炭坯体的C/SiC复合材料存在集中分布的Si,混合基体炭的C/SiC中可见较多微裂纹,C+SiC涂层的材料中残留Si含量少,基体组织均匀;热解炭坯体的C/SiC复合材料热扩散率和导热系数最大;混合基体炭的坯体,纤维经过C+SiC涂层,可明显提高材料的热扩散率和导热系数,且随温度的升高,导热系数的下降速率增大。     

C/C复合材料中基体炭的微观结构表征

采用扫描电子显微镜、金相偏光显微镜对不同结构基体炭，包括热解炭、沥青炭、树脂炭进行形貌表征和分析。通过试验观察到热解炭的微观结构主要分为粗糙层结构、光滑层结构、过渡层结构和各向同性结构，热解炭表面为球冠形结构；沥青炭的主要形貌结构主要有镶嵌型结构，区域与镶嵌并存结构，区域与流线型并存结构，流线型结构；树脂碳的结构主要为表面光滑的块状结构。     

多晶硅炉热场用C/C复合材料的硅化腐蚀失效机理

以2D叠层炭布为增强体的炭/炭（C/C）复合材料作为多晶硅炉用热场盖板,对其在硅液/硅蒸汽共同作用下的硅化腐蚀失效机理进行了研究。通过多功能密度测试仪、扫描电子显微镜（SEM）和X射线衍射仪（XRD）分析了硅化作用对C/C复合材料致密度、微观结构及物相组成的影响,并对侵蚀后的C/C复合材料失效机理进行了分析。结果表明：硅化侵蚀后的C/C复合材料致密度高,存在大量的Si元素,生成了大量的β-SiC,且微观缺陷较多,层间开裂严重,呈现脆性断裂模式。理论分析发现,高温下单位摩尔质量的热解炭和单位摩尔质量的硅发生反应生成单位摩尔质量的SiC后,总体积膨胀约为单位摩尔热解炭体积的6.3倍,不同物相间的热失配导致热应力集中,引起C/C复合材料变形开裂失效,裂纹产生的扩散通道加剧了硅液/硅蒸汽对C/C复合材料的硅化侵蚀作用。     

C/C多孔体对C/C-SiC复合材料微观结构和弯曲性能的影响

以4种纤维含量相同(32%,体积分数,下同),用化学气相渗透(chemical vapor infiltration,CVI)法制备了4种密度的碳纤维增强碳(carbon fiber reinforced carbon,C/C)多孔体,基体炭含量约20%～50%.利用液相渗硅法(liquid silicon infiltration,LSI)制备了C/C-SiC复合材料,研究了C/C多孔体对所制备的C/C-SiC复合材料微观结构和弯曲性能的影响.结果表明:不同密度的C/C多孔体反应渗硅后,复合材料的物相组成均为SiC,C及单质Si;随着C/C多孔体中基体炭含量的增加,C/C-SiC复合材料中SiC含量逐渐减少而热解炭含量逐渐增加.C/C-SiC复合材料弯曲强度随着材料中残留热解炭含量增加而逐渐增加,热解炭含量为约42%的C/C多孔体所制备的C/C-SiC复合材料的弯曲强度最大,达到320 MPa.     

针刺炭纤维预制体结构单元对C/C复合材料性能的影响

采用6K炭纤维无纬布/网胎交替叠层及12K炭纤维无纬布/网胎交替叠层,在针刺工艺,致密化、热处理工艺完全相同的情况下,制备了密度为1.8g/cm3的热解炭/树脂炭双元基体的两种C/C复合材料产品,考察了针刺预制体结构单元对C/C复合材料性能的影响.结果表明,两种C/C复合材料的热学（垂直方向导热系数）、电学性能及石墨化度基本相当;而针刺6K炭纤维无纬布/网胎预制体C/C复合材料的拉伸、弯曲、压缩、层间剪切强度分别为127MPa,189MPa,263MPa,24.6MPa;其平行方向导热系数为54.6W/m＆#183;K,比常规针刺12K炭纤维无纬布/网胎预制体C/C复合材料相应提高了38％,32.2％,32.8％,38.9％,21％,彰显了细化针刺预制体结构单元对C/C复合材料力学性能的显著影响.     

Microstructure and elastic properties of individual components of C/C composites

Carbon fiber reinforced carbon matrix (C/C) composites are often used for structural and frictional applications at a wide range of temperatures due to their excellent mechanical and thermal properties. Tailoring of mechanical properties through optimization of microstructure is critical for achieving maximum composite performance. This article addresses the evolution of the fiber and matrix microstructure and related nano-mechanical properties in two different C/C composites after being subjected to heat treatment at temperatures between 1800 and 2400 °C. Microstructure and corresponding nano-mechanical properties of C/C composites were studied using Polarized Light Microscopy (PLM), High-Resolution Transmission Electron Microscopy (HRTEM) and nanoindentation techniques. Increased heat treatment temperature (HTT) led to formation of a better-organized microstructure of fiber and matrix and also to formation of thermal cracks. The elastic modulus of rough laminar CVI pyrocarbon decreased from 18 to 12 GPa with increased HTT. In contrast, the isotropic CVI pyrocarbon and charred resin matrix displayed only a slight change of elastic modulus. The elastic modulus of PAN fiber increased from 18 to 34 GPa, indicating the development of a better-organized microstructure in the fiber-axial direction.     

Pitch resin addition induced evolution of composition,microstructure and mechanical property of C/C-SiC-ZrC composites

Precursor infiltration and pyrolysis (PIP) has been widely used to fabricate C/C-SiC-ZrC composites. However, the use of organic polymeric precursor of zirconium carbide (PZC) can usually cause the degradation of their mechanical property due to the reaction of ZrO₂ intermediate with pyrocarbon (PyC) and carbon fibers (C_f) during pyrolysis. In this study, pitch resin was directly added into the mixture solution of PZC and polycarbosilane (PCS) to supply extra carbon. The composition, microstructure and mechanical property of the as-prepared composites were investigated systematically. The pure ZrC-SiC with a high ZrC content is obtained at 1500 °C when the PZC/PCS/resin mass ratio is 20:1:5. The resulting C/C-SiC-ZrC composites have the highest flexural strength of 247.4 MPa since the degradation of PyC and C_f is greatly alleviated by the addition of resin. The damage mechanism of PyC and C_f during pyrolysis was revealed under the different fabrication conditions.     

炭前驱体形态对C/C复合材料导热系数的影响

利用热塑性中间相沥青为黏结剂,短炭纤维.增强体,一步热压成型制备C/C导热复合材料.采用SEM和偏光显微镜观察等分析手段,研究了2∶1,2.5∶1和3∶1三种不同管径比对C/C复合材料的影响.结果表明:通过热压模具空腔结构的改变可以引起炭前驱体挤出形态的变化,使得轴向基体炭有序生长与短炭纤维增强体呈现有序排列,其中间相液晶分子垂直和平行于模压压力方向均排列成纤维状长程有序结构,短切纤维呈现出与压力平行方向排布.当空腔管径比为3:1,轴向导热系数由86.2 W/(m·K)增大至115.5 W/(m· K),各向异性比由1.6减小为1.2.由此所得块体C/C复合材料具有显著的二维取向结构,轴径向导热系数趋于平衡.     

Single-walled carbon nanotube buckypaper and mesophase pitch carbon/carbon composites

Carbon/carbon composites consisting of single-walled carbon nanotube (SWCNT) buckypaper (BP) and mesophase pitch resin have been produced through impregnation of BP with pitch using toluene as a solvent. Drying, stabilization and carbonization processes were performed sequentially, and repeated to increase the pitch content. Voids in the carbon/carbon composite samples decreased with increasing impregnation process cycles. Electrical conductivity and density of the composites increased with carbonization by two to three times that of pristine BP. These results indicate that discontinuity and intertube contact barriers of SWCNTs in the BP are partially overcome by the carbonization process of pitch. The temperature dependence of the Raman shift shows that mechanical strain is increased since carbonized pitch matrix surrounds the nanotubes.     

炭/炭复合材料界面微观结构的研究

炭纤维增强炭基（炭／炭）复合材料中的界面结构直接影响着炭／炭材料的力学、热物理等各种性能。采用SEM、TIM等微观观察手段,就几种炭／炭复合材料界面的微观结构进行考察。对观察到的炭纤维与基体炭间的界面、同一纤维束中两根纤维间的界面,基体与其他外加物质间的界面、不同取向炭纤维间的界面、不同基体前驱体层间的界面等界面类型的细微结构进行了图示分析与讨论。     

轴棒法C／C复合材料微观结构及性能分析

采用轴棒法4D预制体、煤沥青为前驱体,经过常压、高压相结合的液相浸渍一炭化的致密工艺,制备出高密度轴棒法C／C复合材料。研究了轴棒法C／C复合材料的微观结构及其对轴向室温、高温（2800℃）拉伸破坏形式的影响。结果表明：轴棒法C／C复合材料轴向增强体采用炭棒,出现了一个特殊的界面,即炭棒与基体的“间隙”,主要原因是炭棒内部结合较强和纤维、基体的热膨胀系数不匹配而引起的;间隙的存在,使得轴棒法C／C复合材料的轴向室温、高温拉伸破坏形式出现较大差异,室温拉伸由于界面结合强度弱而引起的炭棒完整的拔出,未起到纤维应有的增强作用;高温拉伸却由于受热膨胀,间隙愈合,界面结合变强,试样从有效部位断裂,纤维增强作用明显提高。     

Influence of adding Mesocarbon Microbeads into C/C composites on microstructure and properties during carbonization

This work tests the effect on microstructure, flexural strength, flexural moduli, plus the electrical and thermal conductivity of carbon/carbon composites with Mesocarbon Microbeads (MCMBs) content ranging 0–30% by weight during carbonization. These composites were reinforced by oxidative PAN Base fiber felts, and matrix precursor was resol‐type‐phenolic resin. MCMBs with a weight fraction of 0–30% were added to the matrix to elucidate the effect. Liquid‐phase impregnation was applied to reinforce matrix carbon. Cured composites were stabilized at 230°C, then heat‐treated at 400, 600, 800, 900 and 1000°C for carbonization. The measured flexural strength after heat‐treated at 1000°C was 51.20, 49.59, 43.55, and 38.76 MPa for MCMBs with 0, 10, 20, and 30% added to composites; mean flexural moduli were l.73, 1.24, 0.73, and 0.57 MPa, respectively. Adding MCMBs reduced both strength and modulus because of cracks and avoids caused by different shrinkage between resin and MCMBs; adding 30 wt % MCMBs raised thermal conductivity of C/C composites from 1.55 to 1.78 W/mK and reduced electric resistivity from 1.8 × 10^?2 to 5.97 × 10^?3 Ω cm. effect. © 2006 Wiley Periodicals, Inc. J Appl Polym Sci 102: 3102–3110, 2006     

Comparative study of interphase evolution in polysiloxane resin-derived matrix containing carbon micro and nanofibers during thermal treatment

The work presents the results of research on composite materials made of silicon-containing polymer-derived ceramic matrix composites (PDC-Cs) and nanocomposites (PDC-NCs). Carbon micro and nanofibers (CFs and CNFs) were used as reinforcements. The interactions between carbon micro and nanofibers and polysiloxane matrix, as well as interphase evolution mechanism in composite samples during their heating to 1000 °C were studied. CF/resin and CNF/resin composites were prepared via liquid precursor infiltration process of unidirectionally aligned fibers. After heating to 700 °C–800 °C, decomposition of the resin in the presence of CNFs led to the formation of fiber/organic-inorganic composites with pseudo-plastic properties and improved oxidation resistance compared to as-prepared fiber/resin composites. The most favourable mechanical properties and oxidation resistance were obtained for composites and nanocomposites containing the maximum amount of carbon nanoparticles precipitated in the SiOC matrix during the heat treatment at 800 °C. The precipitated carbon phase improves fiber/matrix adhesion of composites.