结构类似的炭材料和C/C复合材料的滑动摩擦磨损行为

制备粗糙层热解炭(RL)和光滑层热解炭(SL)基体的C/C复合材料,测试该C/C复合材料与40Cr钢配副时的摩擦磨损行为,并对磨损表面进行SEM观察.对比研究高强石墨和光滑层结构的块状热解炭在相同条件下的滑动摩擦磨损行为.结果表明:PAN炭纤维改善C/C复合材料的摩擦磨损行为;在实验载荷范围内,与高强度石墨材料相比,含RL炭C/C复合材料的摩擦因数降低0.08～0.12;体积磨损量增幅降低;与热解炭试样相比,具有SL炭C/C复合材料的摩擦因数降低0.02～0.05,体积磨损量低0.2 mm~3左右;随着时间的延长,大部分C/C复合材料的摩擦因数基本相对稳定或呈小幅下降,而石墨、热解炭块的摩擦因数均呈不同幅度的上升;具有RL炭的C/C复合材料摩擦表面膜厚度随载荷增加而降低,具有SL炭的C/C复合材料摩擦表面较粗糙;高强石墨能形成较完整致密的摩擦膜,但磨粒磨损严重,磨屑易在摩擦膜边缘形成层状堆积;热解炭块摩擦表面磨屑堆积松散,有较多的孔洞以及热解炭层整体剥落的形貌.     

载气对CVI C/C材料密度和热解炭结构分布的影响

采用定向流动热梯度CVI工艺,以丙烯作炭源气,以针刺炭纤维整体毡作预制体分别研究了加氢气和氮气作载气对C/C复合材料密度和热解炭结构分布的影响。结果表明,载气对热梯度CVI C/C材料密度和热解炭结构沿径向分布的均匀性有重要影响。当其它工艺条件相同时,经过400 h的沉积,采用N2作载气时所得炭盘的平均体密度为1.54 g/cm3,炭盘密度沿径向分布的偏差Δρ为0.24 g/cm3,在炭盘的外侧易形成SL结构热解炭;而采用H2作载气时,可以得到平均体密度为1.67 g/cm3、热解炭结构分布高度均匀的全RL结构PyC基C/C复合材料,且炭盘密度沿径向分布的偏差Δρ仅为0.11 g/cm3,密度分布均匀性提高一倍以上。不管是采用N2还是H2作载气,炭盘的密度沿周向分布都十分均匀(Δρ≤0.02 g/cm3),且炭盘的较低密度部位均位于中间偏内侧。     

不同基体炭结构的C/C复合材料摩擦表面特性和摩擦磨损机理

与表面镀Cr的40Cr钢配副进行滑动摩擦实验后,在JSM 6360LV扫描电镜上观察6种具有不同基体炭结构的C/C复合材料的磨损表面形貌。结果表明:完全光滑层(SL)炭结构的C/C复合材料摩擦表面在任何载荷下均难以形成完整的磨屑膜;完全粗糙层(RL)炭结构、粗糙层/树脂炭(RL/RC)的材料摩擦表面在低载荷时能形成较厚的磨屑膜,在高载荷时表面摩擦膜均很薄;完全RC结构试样摩擦表面在低载荷时完整、致密,在高载荷时有显著的磨屑膜剥落;RL/SL/RC、SL/RC结构试样在低载荷时的表面摩擦膜薄,而高载荷时,RL/SL/RC材料的基体炭磨损比SL/RC的严重;RL/SL或SL炭在摩擦中的损伤呈现阶梯状磨损形貌,RL炭在摩擦后难以分辨出原始形貌,RC炭在部分摩擦表面则为条纹状磨损形貌;RL/SL/RC、SL/RC结构的C/C复合材料摩擦形貌的稳定性高,材料耐磨性好,在一定载荷范围内有利于降低材料的摩擦因数和体积磨损。     

炭／炭复合材料导热系数影响因素的研究

研究了影响炭／炭复合材料导热系数的主要因素：炭纤维取向，热处理温度和CVD热解炭的结构，结果表明，在炭／炭复合材料中，影响炭／炭复合材料导热系数的主要因素是CVD热解炭结构；以RL结构为主的CVD热解炭，导热系数高，热处理温度对材料导热系数的影响不及CVD热解炭的微观结构对其的影响。     

不同基体炭C/C复合材料的摩擦磨损性能

以炭纤维针刺毡为预制体,采用化学气相沉积法(CVI)和结合液相浸渍树脂或沥青法制备了热解炭为粗糙层与光滑层结构的准三维C/C复合材料,并研究了这些材料在0.6 MPa的模拟刹车压力下的摩擦磨损性能与磨损机理.研究表明:基体炭为粗糙层热解炭与树脂炭的C/C复合材料摩擦表面能形成较厚且连续的自润滑摩擦膜,摩擦稳定性最好,摩擦因数适中,氧化磨损小,磨损机理主要为膜的部分脱落、氧化磨损与相对较小的磨粒磨损;基体炭为光滑层热解炭与树脂炭或沥青炭的C/C复合材料摩擦表面形成的摩擦膜较薄且不连续,摩擦稳定性差,摩擦磨损较大,磨损机制主要为膜的部分脱落、磨粒磨损与更严重的氧化磨损;随着密度的升高,C/C复合材料摩擦稳定性增加,摩擦因数增加,磨损降低;基体炭为单一沥青炭的C/C复合材料,由于没有热解炭对纤维的保护,纤维断裂多,线性磨损尤其大,磨损机理主要为大量的磨粒磨损与氧化磨损.     

碳纤维表面生长纳米碳管及其增强的炭/炭复合材料

采用化学气相沉积工艺在碳纤维表面生长了纳米碳管,将此种碳纤维作为增强材料,以中间相沥青为基体炭前驱体采用浸渍炭化工艺制备了炭/炭复合材料.观察了所得复合材料断口的微观形貌,测试了抗弯强度及热物理性能.结果表明,碳纤维表面的纳米碳管可以有效地提高纤维与基体的粘结力,复合材料的抗弯性能提高了50%,而对复合材料的导热性能影响较小.     

熔渗法制备C/C-Cu复合材料的力学性能

以炭纤维(Cf)针刺整体毡为预制体,分别采用化学气相渗透(Chemical vapor deposition,CVI)和浸渍炭化(Impregnation and carbonization,I/C)制备不同密度和基体炭的C/C坯体;通过添加Ti元素改善熔融Cu与C/C坯体的润湿性.采用真空熔渗法制备C/C-Cu复合材料.对复合材料的力学性能及其与坯体之间的关系进行研究,并与常用滑板材料的力学性能进行比较.结果表明:随着坯体密度的增加,复合材料的抗弯强度下降,而坯体密度为1.4 g/cm3的复合材料的冲击韧性达到最大值.与用I/C坯体制备的复合材料相比,用CVI坯体制备的复合材料具有更高的强度和韧性,其弯曲曲线呈“假塑性”断裂特征,断裂时纤维从热解炭层或熔渗金属相中拔出,熔渗金属相呈“韧窝状”的塑性断裂形貌.冲击断裂时,复合材料倾向于沿TiC/熔渗金属界面断裂.C/C-Cu复合材料的抗弯强度为180～300 MPa、冲击韧性高于3.5 J/cm2,优于常用滑动电接触材料的性能,是一种极具潜力的新型滑动电接触材料.     

不同预制体炭/炭复合材料在髋关节模拟试验机中的磨损颗粒表征(英文)

采用髋关节模拟试验机检测穿刺碳布预制体和碳毡预制体炭/炭复合材料的磨损行为。分离提取产生的磨损颗粒,检测颗粒形貌和尺寸分布并提出颗粒的演化过程。结果表明:炭/炭复合材料磨损颗粒的尺寸分布在亚微米至数十微米之间,颗粒形貌呈现破损纤维状、纤维碎片状、片状和球状。穿刺碳布预制体炭/炭复合材料比碳毡预制体炭/炭复合材料的磨损颗粒尺寸分布范围更广泛,磨损颗粒中的破损碳纤维状和片状形貌较多。热解碳颗粒的演变主要是其表面的规则化过程,而碳纤维颗粒的演变主要与髋关节模拟试验机提供的应力方向有关。     

添加BN对光滑层热解炭结构的C/C复合材料摩擦性能的影响

通过粉末层铺法向全网胎炭纤维预制体中添加六方氮化硼粉末和化学气相沉积热解炭增密制备C/C-BN复合材料。在MM 1000摩擦试验机上对其摩擦磨损性能进行测试,并对摩擦表面进行光学形貌观察以及对材料的组织结构和磨屑进行SEM形貌观察。结果表明:与C/C复合材料相比,C/C-BN复合材料的线性磨损率降低了40%,质量磨损率降低了70%;摩擦表面中的六方BN在摩擦过程中始终保持稳定,BN的存在使光滑层热解炭结构的C/C复合材料的摩擦因数曲线变得平稳、波动小并且对刹车压力响应迅速,摩擦表面上形成了一层薄的摩擦膜。     

原位生长碳纳米管对炭/炭复合材料导热性能的影响

以炭纤维表面原位生长有碳纳米管(Carbon nanotubes,CNTs)的针刺毡体作为前驱体制备出生长有CNTs的炭/炭复合材料,并与在同样工艺条件下通过致密化最终热处理得到的纯炭/炭复合材料进行对比.结果表明,在密度几乎相同的情况下,生长有CNTs的炭/炭复合材料的室温Z轴热导率约为11.10 W/(m·K),几乎为纯炭/炭复合材料的室温Z轴热导率(6.28 W/(m·K))的2倍,其原因可能在于CNTs可以有效改善炭纤维和热解炭之间的界面特性,明显减少炭/炭复合材料中纤维和热解炭界面处周裂纹的出现,还可以诱导热解炭形成一种拥有更高导热率更易石墨化的粗糙结构.     

炭/炭复合材料航空刹车副的湿态摩擦性能

对两种不同的炭/炭复合材料湿态下的摩擦磨损性能进行对比分析。结果表明:具有粗糙层热解炭的炭/炭刹车副由于其晶格结构较为完善,生长组织择优取向度和各向异性度均高于含有光滑层结构热解炭的炭/炭刹车副。前者的石墨化度及可石墨化能力均大于后者,由于前者的表面缺陷较少,所吸附的水分子较少,因而在湿态下刹车时,其刹车力矩将很快恢复到正常干态刹车时的力矩水平,对环境的适应能力大于光滑层结构的炭/炭刹车副。     

Preparation and mechanical properties of carbon/carbon composites with high textured pyrolytic carbon matrix

Short carbon fiber felts with an initial porosity of 89.5% were deposited by isobaric, isothermal chemical vapor infiltration using natural gas as carbon source. The bulk density of the deposited carbon/carbon (C/C) composites was 1.89 g/cm³ after depositing for 150 h. The microstructure and mechanical properties of the C/C composites were studied by polarized light microscopy, X-ray diffraction, scanning electron microscopy and three-point bending test. The results reveal that high textured pyrolytic carbon is deposited as the matrix of the composites, whose crystalline thickness and graphitization degree highly increase after heat treatment. A distinct decrease of the flexural strength and modulus accompanied by the increase of the toughness of the C/C composites is found to be correlated with the structural changes in the composites during the heat treatment process.     

碳界面层制备工艺对SiC_f/SiC材料力学性能的影响

用低压化学气相沉积(LPCVD)法,以丙烯(C_3H_6)为碳源,氮气(N_2)为稀释气制备了2.5维连续碳化硅纤维增韧碳化硅(SiC_f/SiC)复合材料的碳界面层,其厚度为～0.1 mm.研究了不同丙烯含量(体积分数,下同)(60%,50%,45%)对碳层形貌、微观结构及SiC_f/SiC力学性能的影响.结果表明:当C_3H_6含量为60%时,热解碳层表面光滑,石磨化度高;当C_3H_6为50%和45%时,碳层粗糙,有很多较大颗粒存在,石磨化度低.3种复合材料的弯曲强度差别不大,分别为303,311和320 MPa.然而,当C_3H_6含量为60%时,材料韧性断裂,断裂功高;为50%和45%时,材料脆性断裂,断裂功低.不同的纤维拔出滑移阻力是SiC_f/SiC断裂行为不同的原因.     

Oxidation behavior of C/C composites with the fibre/matrix interface modified by carbon nanotubes grown in situ at low temperature

Carbon nanotubes (CNTs) were grown in situ on the fibre surface of unidirectional carbon fibre preform. The carbon fibre preform with nanotube modified fibres was then densified by chemical vapor infiltration to obtain CNT-reinforced C/C (CNT-C/C) composite. The effects of CNTs on the oxidation kinetics and mechanism of C/C composites were investigated. The results show that due to the growth of CNTs, a more perfect structure of pyrolytic carbon (PyC) and better fibre/PyC interface had been obtained, which in turn result in slower mass loss. Furthermore, higher graphitization degree leads to larger activation energy of CNT-C/C composite, compared with C/C composite.     

准三维C/C复合材料的层间剪切性能及其断裂机理

以炭纤维针刺毡为预制体, 采用化学气相浸渗(CVI)法或结合液相法制备了热解炭、树脂炭和沥青炭基质的准三维C/C复合材料, 研究了这些材料的层间剪切性能及其断裂机理. 结果表明: CVI基质炭比沥青基质炭更有利于C/C复合材料的层间剪切性能的提高; 剪切强度随密度增高而增大, 致密度越高, 基体支撑越强, 同时微裂纹和孔隙度就越低, 断裂裂纹不易形成或扩展, 强度性能就越好; 纯沥青基质炭试样为"突发"的脆性断裂方式, 其他基质炭试样表现为韧性断裂方式.     

Influence of load on sliding tribology of C/C composite with 40Cr steel couple coated by Cr

With the 40Cr steel couple coated by Cr, the sliding tribology behavior of two kinds of C/C composites with different matrix was tested using a M2000 wear tester. The results show that with the increasing of load, the friction coefficients of the composite with resin carbon matrix（RC） decrease quickly from 0.156 under 60 N to 0.123 under 150 N, while those of the composite with rough lamination/smooth lamination/resin carbon （RL/SL/RC） change only between 0.122 and 0.101. The wear volume loss of the two composites increases except for under 100 N. The SEM morphology shows that with the increasing of load, the worn surface of the composite with RC becomes more and more integrated while the size of the debris becomes less and less. The Raman spectrum shows that the graphitization on the worn surface of the fibers draws down after 100 N, the graphitization of the boundary between the fiber and the matrix carbon rises up to 150 N, but the graphitization of the matrix carbon draws down all the while. With the increasing of load, the graphitization on the worn surface of all the worn areas becomes closer and closer, which indicates the worn surface of the different component has the similar friction ability. The composites with RL/SL/RC have better tribological characteristic than the composite with RC.     

热梯度CVI C/C材料的结构与性能

以炭纤维整体毡为预制体，采用热梯度CVI工艺制备了两种不同结构基体炭的C／C材料，即RL结构和SL结构材料。采用光学金相仪，X射线衍射仪，硬度计，激光导热仪等设备研究了沉积态和热处理态C／C材料的显微结构及热物理性能。对比研究了两种结构材料的力学性能及摩擦摩损性能。结果表明：当密度超过一定值后，密度对C／C材料的力学性能和摩擦性能的影响远不如CVD炭结构的影响大；不管是沉积态还是热处理态，RL结构材料的刹车性能曲线明显优于SL结构材料的刹车性能曲线，这意味着CVD炭的微观结构不同是造成C／C材料摩擦性能差异的根本原因。     

C／C复合材料的导热系数

用热物性综合测试仪测定了不同热处理温度下Ｃ／Ｃ复合材料的导热系数，通过Ｘ射线衍射石墨化度的测定及晶粒尺寸计算，分析了材料的材质。进一步讨论了热处理温度、石墨化度与导热系数之间的关系。表明试样中存在性质不同的３个组元，随热处理温度的升高，平行于碳纤维长向的导热系数值从２２００℃的１４７Ｗ／ｍ·Ｋ升高到２８００℃的１８０Ｗ／ｍ·Ｋ左右，而垂直方向从相应的４９Ｗ／ｍ·Ｋ升高到７０Ｗ／ｍ·Ｋ。     

Fracture mechanism of 2D-C/C composites with pure smooth laminar pyrocarbon matrix under flexural loading

Using natural gas as carbon source, 2D needle felt as preform, 2D-C/C composites were prepared by thermal gradient chemical vapor infiltration. Their microstructures were observed under polarized light microscope (PLM) and scanning electron microscope (SEM), and the flexural behaviors before and after heat-treatment were studied with a universal mechanical testing machine. The fracture mechanism of the composites was discussed in detail. The results show that, carbon matrix exhibits pure smooth laminar (SL) characteristic including numerous wrinkled layered structures and some inter-laminar micro-cracks. With the decreasing density, the strength of the composites decreases and the toughness increases slightly; after 2500 °C heat-treatment, the inter-laminar micro-cracks in matrix increase, the strength decreases, and the toughness obviously increases. The fracture mode of the composites changes from brittle to pseudo-plastic characteristic due to more crack deflections in SL matrix.