CARBON PERGAMON Carbon40(2002)905-910 Thermal shock behavior of 3-dimensional C/SiC composite Xiaowei Yin,, Laifei Cheng, Litong Zhang, Yongdong Xu langhai 200031, China State Key Laboratory of solidification Processing, Northwestern Polytechnical ty. Xi an, Shaanxi 710072. China Received 15 May 2001; accepted 11 August 2001 Abstract The thermal shock behavior of a three-dimensional carbon fiber re infiltration(CVi) technique was studied using the air quenched metho technique of measuring mechanical properties using three-point fiexure displayed good resistance to thermal shock, and retained 83% of the original strength after quenching from 1300 to 300C 100 times. The critical AT of C/SiC in combustion environment was 700C. The critical number of thermal shocks for the C/SiC composite was about 50 times. When the number of thermal shocks was less than 50 times, the residual flexural strength of C/SiC composites decreased with the increase of thermal shock times. When the number of thermal shocks of C/SiC was greater than 50, the strength of C/Sic did not further decrease because the crack density was saturated. 2002 Elsevier Science Ltd. All rights reserved Keywords: A Carbon composites; B. Chemical vapor infiltration; D Mechanical properties 1. Introduction studies have been conducted on unidirectional0-90. and two-dimensional woven-fiber composites [7-ll]. These Carbon-fiber-reinforced atrIx composite studies have shown that thermal shock damage results in by the chemical vapor infiltration(CVI) proc noncatastrophic strength decreases above a critical quench (CVn) has been developed for potential use in temperature difference, ATe, in contrast to monolithic engines [1, 2]. C/SiC composite is expected to be suitable ceramics that typically exhibit a catastrophic decrease of for high-temperature use, but thermal shock and strength at AT. Furthermore, these composites retain a ycling effects are anticipated to be one factor significant portion of their prequench strength above AT performance in many instances, so that therma whereas monolithic ceramics are completely fractured or damage must be understood prior to use can only support an insignificant load Thermal shock resistance of monolithic materials has Kagawa et al. studied the thermal shock resistance of en extensively studied, and theoretical analyses have uniaxial-SiC-fiber comp with borosilicate glass and een successfully applied to explain experimental observa- lithium aluminosilicate(LAs)matrices [12]. The borosil- tions [3-6]. However, a comprehensive understanding of cate composite exhibited decreases in modulus and flexural the thermal shock behavior of carbon-fiber-reinforced strength at AT>600oC, whereas the LAs composit ceramic composites (CFCCs) has showed no degradation in mechanical properties at AT up despite recent advances in the architecture design and to 1000oC Singh et al. studied the thermal shock resistance processing of these materials. Experimental thermal shock of the two-dimensional Nicalon fiber reinforced Sic matrix ricated by chemical vapor infiltration(CVI) technique Corresponding author. Tel :+86-21-6472-2874; fax: +86- [13, 14]. The SiC/Sic composites exhibited decreases in 21-6415-0768 fexural strength at AT>700C. The thermal shock damage in all of the 0008-6223/02/S-see front matter 2002 Elsevier Science Ltd. All rights reserved PII:S0008-6223(01)00225-1
Carbon 40 (2002) 905–910 Thermal shock behavior of 3-dimensional C/SiC composite a, b b b Xiaowei Yin , Laifei Cheng , Litong Zhang , Yongdong Xu * a Crosslight, Minghua Technical Development Co. Ltd., Room 1506 Yitai Li Building, 446 Zhaojiabang Rd., Shanghai 200031, China b State Key Laboratory of Solidification Processing, Northwestern Polytechnical University, Xi’an, Shaanxi 710072, China Received 15 May 2001; accepted 11 August 2001 Abstract The thermal shock behavior of a three-dimensional carbon fiber reinforced SiC matrix fabricated by chemical vapor infiltration (CVI) technique was studied using the air quenched method. Damage to composites was assessed by a destructive technique of measuring mechanical properties using three-point flexure and SEM characterization. C/SiC composites displayed good resistance to thermal shock, and retained 83% of the original strength after quenching from 1300 to 3008C 100 times. The critical DT of C/SiC in combustion environment was 7008C. The critical number of thermal shocks for the C/SiC composite was about 50 times. When the number of thermal shocks was less than 50 times, the residual flexural strength of C/SiC composites decreased with the increase of thermal shock times. When the number of thermal shocks of C/SiC was greater than 50, the strength of C/SiC did not further decrease because the crack density was saturated. 2002 Elsevier Science Ltd. All rights reserved. Keywords: A. Carbon composites; B. Chemical vapor infiltration; D. Mechanical properties 1. Introduction studies have been conducted on unidirectional, 0–908, and two-dimensional woven-fiber composites [7–11]. These Carbon-fiber-reinforced SiC-matrix composite fabricated studies have shown that thermal shock damage results in by the chemical vapor infiltration (CVI) process (C/SiC- noncatastrophic strength decreases above a critical quench (CVI)) has been developed for potential use in gas-turbine temperature difference, DT , in contrast to monolithic c engines [1,2]. C/SiC composite is expected to be suitable ceramics that typically exhibit a catastrophic decrease of for high-temperature use, but thermal shock and thermal strength at DT . Furthermore, these composites retain a c cycling effects are anticipated to be one factor limiting significant portion of their prequench strength above DT , c performance in many instances, so that thermal shock whereas monolithic ceramics are completely fractured or damage must be understood prior to use. can only support an insignificant load. Thermal shock resistance of monolithic materials has Kagawa et al. studied the thermal shock resistance of been extensively studied, and theoretical analyses have uniaxial-SiC-fiber composites with borosilicate glass and been successfully applied to explain experimental observa- lithium aluminosilicate (LAS) matrices [12]. The borosilitions [3–6]. However, a comprehensive understanding of cate composite exhibited decreases in modulus and flexural the thermal shock behavior of carbon-fiber-reinforced strength at DT.6008C, whereas the LAS composite ceramic composites (CFCCs) has not been obtained, showed no degradation in mechanical properties at DT up despite recent advances in the architecture design and to 10008C. Singh et al. studied the thermal shock resistance processing of these materials. Experimental thermal shock of the two-dimensional Nicalon fiber reinforced SiC matrix fabricated by chemical vapor infiltration (CVI) technique *Corresponding author. Tel.: 186-21-6472-2874; fax: 186- [13,14]. The SiC/SiC composites exhibited decreases in 21-6415-0768. flexural strength at DT.7008C. The thermal shock damage E-mail address: xwyin2001@yahoo.com.cn (X. Yin). in all of these composites consisted of matrix cracks. 0008-6223/02/$ – see front matter 2002 Elsevier Science Ltd. All rights reserved. PII: S0008-6223(01)00225-1
X. Yin et al. Carbon 40(2002)905-910 Up to now, our knowledge on the behavior of carbon fiber-reinforced Sic matrix composite subjected to thermal transients is rather limited. The thermal shock behavior of C/SiC(CVI) is tested in the present study 900 00 2. Experimental procedure 2. 1. Preparation of C/SiC composite 返300 Combustion Air T-300 carbon fiber from Toray (Japan) was employed. g 0 he fiber preform was prepared using a three-dimensional 0 150 braid method, and was supplied by the Nanjing Institute of Distance(mm) Glass Fiber, People's Republic of China. The volume fraction of fibers was about 40%. LCVI was employed to Fig. 2. Relation curve between temperature difference and dis- deposit a pyrolytic carbon layer and the silicon carbide tance from flame center matrix. A thin pyrolytic carbon layer was deposited on the surface of the carbon fiber as the interfacial layer with to the length direction of the sample was from 0 to 1000oC C3 Hs at 800C. Methyltrichlorosilane (MTs, CHa SiCI as shown in Fig. 2 used for the deposition of the Sic matrix. MTS vapor was carried by bubbling hydrogen. Typical conditions for 23. Measurement of composite deposition were 1000C, a hydrogen MTS ratio of 10, and a pressure of 5 kPa. Argon was employed as the dilute ny loading rate thod Flexural strength was measured using the three-point to slow down the chemical reaction rate of deposition. T bending method. The span dimension was 20 mm, and the dimension of as-received C/SiC sample was 4 mmX6 loading rate was 0.5 mm min. The tests were conducted mmX140 mm In order to improve the thermal stability of on an Instron-1195 device at room temperature. The the mechanical properties, the as-received samples were fracture surface was observed with a scanning electron heat-treated in a vacuum at 1300C for 3 h microscope(SEM, JEOL JXA-840. The microstructure of the texture was analyzed with a transmission electro 2.2. Thermal shock tests microscope(TEM, JEOL FX-2000) Thermal shock tests were conducted in burner rigs. A schematic of the burner rig system is illustrated in Fig. 1. 3. Results and discussion The combustion temperature was measured by temperature probe along the length direction of test samples from the 3.1. Efect of aT on the mechanical properties flame center. The samples were kept in the com atmosphere for 30 s and then cooled in an air atr The assessment of thermal shock damage was done by for 60 s. The thermal shock temperature difference comparing load-displacement curves of unquenched and nozzle chamber holde (a)cooling position (b) heating position Fig. 1. Schematic of burner rig and thermal-shock device
906 X. Yin et al. / Carbon 40 (2002) 905 –910 Up to now, our knowledge on the behavior of carbon fiber-reinforced SiC matrix composite subjected to thermal transients is rather limited. The thermal shock behavior of C/SiC(CVI) is tested in the present study. 2. Experimental procedure 2.1. Preparation of C/SiC composite T-300E carbon fiber from Toray (Japan) was employed. The fiber preform was prepared using a three-dimensional braid method, and was supplied by the Nanjing Institute of Glass Fiber, People’s Republic of China. The volume fraction of fibers was about 40%. LCVI was employed to Fig. 2. Relation curve between temperature difference and disdeposit a pyrolytic carbon layer and the silicon carbide tance from flame center. matrix. A thin pyrolytic carbon layer was deposited on the surface of the carbon fiber as the interfacial layer with to the length direction of the sample was from 0 to 10008C, C H at 8008C. Methyltrichlorosilane (MTS, CH SiCl ) as shown in Fig. 2. 38 3 3 was used for the deposition of the SiC matrix. MTS vapor was carried by bubbling hydrogen. Typical conditions for 2.3. Measurement of composites deposition were 10008C, a hydrogen:MTS ratio of 10, and a pressure of 5 kPa. Argon was employed as the dilute gas Flexural strength was measured using the three-pointto slow down the chemical reaction rate of deposition. The bending method. The span dimension was 20 mm, and the 21 dimension of as-received C/SiC sample was 4 mm36 loading rate was 0.5 mm min . The tests were conducted mm3140 mm. In order to improve the thermal stability of on an Instron-1195 device at room temperature. The the mechanical properties, the as-received samples were fracture surface was observed with a scanning electron heat-treated in a vacuum at 13008C for 3 h. microscope (SEM, JEOL JXA-840). The microstructure of the texture was analyzed with a transmission electron 2.2. Thermal shock tests microscope (TEM, JEOL FX-2000). Thermal shock tests were conducted in burner rigs. A schematic of the burner rig system is illustrated in Fig. 1. 3. Results and discussion The combustion temperature was measured by temperature probe along the length direction of test samples from the 3.1. Effect of DT on the mechanical properties flame center. The samples were kept in the combustion atmosphere for 30 s and then cooled in an air atmosphere The assessment of thermal shock damage was done by for 60 s. The thermal shock temperature difference parallel comparing load-displacement curves of unquenched and Fig. 1. Schematic of burner rig and thermal-shock device
X. Yin et al. Carbon 40(2002)905-910 1200 △T=700°C 900 △T=1000 04 Fig 3. Infuence of thermal shock on load-displacement behavior of C/SiC composites Fig. 4. TEM micrography of PyC interphase between fiber and matrIx quenched composites. The influence of thermal shock on the load-displacement behavior of C/Sic composite is characteristics. As shown in Fig. 5, C/SiC shows apparent shown in Fig 3. It is apparent from these curves that the characteristics of fiber pull-out after being thermally mechanical properties of thermally shocked compos shocked 100 times at AT=700oC different from the unquenched sample. Thermally shocked As shown in Fig. 6, at AT<700oC, the flexural strength samples show changes in a number of composite charac- of C/Sic does not decrease with the increase of AT. When teristics. The elastic modulus and matrix cracking strength AT is larger than 700C, the flexural strength decrease are lower for quenched composites because of the lower with the increase of AT. As can be shown, the critical ar portion and earlier thermal shock temperature difference△T。)is700°C deviation from linearity, respectively. In addition, the According to the thermoelastic theories when a material ultimate strength, and work-of-fracture (area under the is subjected to a thermal transient of suddenly decreasing curve)are also lower for composites after thermal shock temperature(AT),e.g in a quench test, the surface of the than the as-received samples, Similar load-displacement material is placed under a tensile stress and the interior curves were obtained for Nicalon/CVI SiC and Nicalon/ under a compressive stress. When the temperature differ- olymer SiC composites [14 ence equals a critical value(ATs), the tensile thermal stres The effects of thermal shock on the maximum fiexural generated is sufficient to cause the formation of a surface rength may result from the following two causes: the crack. The tensile strength(o )can be expressed as follows oxidation of fibers, or the fracture of fibers under the [14] thermal stress. The decrease of modulus of composites may be due to matrix cracking, fiber fracture and interface When C/SiC composites were cooled from high tem- erature. the tension surface and the compressive stress in the interior created by the thermal gradient, which causes the matr cracks on the surface of composites. High strength fibers hindered the propagation of matrix cracks, and the me- chanical degradation was reduced by crack deflection and crack bridging. Therefore, the bonding between fiber and matrix should be weak enough in order to make the fiber and matrix debond and the cracks deflect around fibers Otherwise, the matrix cracks will propagate into the fibers and reduce the strength of the composites a C-interface exists between the C-fibers and sic 2KVX1,98819lD39 atrix, with a thickness of about 0.3 um(Fig 4), which ensures the weak bonding between C fibers and Sic Fig. 5. Morphology of fracture section of C/SiC after thermal- matrix. Therefore, C/SiC composites show tough fracture
X. Yin et al. / Carbon 40 (2002) 905 –910 907 Fig. 3. Influence of thermal shock on load-displacement behavior of C/SiC composites. Fig. 4. TEM micrography of PyC interphase between fiber and matrix. quenched composites. The influence of thermal shock on the load-displacement behavior of C/SiC composite is characteristics. As shown in Fig. 5, C/SiC shows apparent shown in Fig. 3. It is apparent from these curves that the characteristics of fiber pull-out after being thermally mechanical properties of thermally shocked composites are shocked 100 times at DT57008C. different from the unquenched sample. Thermally shocked As shown in Fig. 6, at DT,7008C, the flexural strength samples show changes in a number of composite charac- of C/SiC does not decrease with the increase of DT. When teristics. The elastic modulus and matrix cracking strength DT is larger than 7008C, the flexural strength decreases are lower for quenched composites because of the lower with the increase of DT. As can be shown, the critical slope of the linear portion of the curve and earlier thermal shock temperature difference (DT ) is 7008C. c deviation from linearity, respectively. In addition, the According to the thermoelastic theories, when a material ultimate strength, and work-of-fracture (area under the is subjected to a thermal transient of suddenly decreasing curve) are also lower for composites after thermal shock temperature (DT ), e.g. in a quench test, the surface of the than the as-received samples. Similar load-displacement material is placed under a tensile stress and the interior curves were obtained for Nicalon/CVI SiC and Nicalon/ under a compressive stress. When the temperature differpolymer SiC composites [14]. ence equals a critical value (DT ), the tensile thermal stress c The effects of thermal shock on the maximum flexural generated is sufficient to cause the formation of a surface strength may result from the following two causes: the crack. The tensile strength (s ) can be expressed as follows t oxidation of fibers, or the fracture of fibers under the [14]: thermal stress. The decrease of modulus of composites may be due to matrix cracking, fiber fracture and interface debonding. When C/SiC composites were cooled from high temperature to low temperature, the tension stress on the surface and the compressive stress in the interior are created by the thermal gradient, which causes the matrix cracks on the surface of composites. High strength fibers hindered the propagation of matrix cracks, and the mechanical degradation was reduced by crack deflection and crack bridging. Therefore, the bonding between fiber and matrix should be weak enough in order to make the fiber and matrix debond and the cracks deflect around fibers. Otherwise, the matrix cracks will propagate into the fibers and reduce the strength of the composites. A C-interface exists between the C-fibers and SiC matrix, with a thickness of about 0.3 mm (Fig. 4), which ensures the weak bonding between C fibers and SiC Fig. 5. Morphology of fracture section of C/SiC after thermalmatrix. Therefore, C/SiC composites show tough fracture shock (DT57008C)
X. Yin et al. Carbon 40(2002)905-910 1200 300 60 1200 Fig. 6. The effect of quench temperature difference on the flexural rength of c/Sic aE△T X200 100Nn W03 where E is the Youngs modulus, a is the coefficient of thermal expansion, and y the Poissons ratio of the material. Regarding Eq (1), we obtain an expression for △T a(1-吵) In the present paper, the tensile strength of C/Sic is about 323 MPa, the value of y is about 0. 63, e is about 50 GPa. Therefore, from Eq. (2), AT = 683C, which is consistent with the experimental result. As shown in Fig. 7a, the cracks on the surface of the matrix were formed at lower Al, which does not affect the strength. Above△T。(700°C), the propagation of cracks :2:22· inwards cause the fracture of fibers and the decrease of strength (Fig. 7b). At AT>1000.C, the interior matrix cracks that propagate through fibers cause a further de- crease of strength, as shown in Fig. 70 3. 2. Effect of quench number on the flexural strengi The driving force for crack propagation is derived from the elastic energy stored in the body caused by repeated cooling and heating. When the elastic energy is larger than the surface energy required for propagation of cracks, the cracks will propagate. During the initial stage of thermal shock, with the increase of quench number, surface cracks propagate inwards, which leads to the increase of crack density in composites. The increase of matrix crack density may result in the decrease of the mechanical properties of 11819NnWD3 At AT>ATe, the flexural strength as a function of quench cycle number is shown in Fig 8. As shown in Fig 8, with the increase of quench cycle number, the flexural Fig. 7. Morphology of microcracks after thermal shock for 100 rength of the composite decreases gradually. When the cycles.(a)△T=600°C,(b)△T=700°℃,(c)△7=1000°C
908 X. Yin et al. / Carbon 40 (2002) 905 –910 Fig. 6. The effect of quench temperature difference on the flexural strength of C/SiC. ] aEDTc s 5 ] (1) t 1 2 n where E is the Young’s modulus, a is the coefficient of thermal expansion, and n the Poisson’s ratio of the material. Regarding Eq. (1), we obtain an expression for DTc st s d 1 2 n DT 5 ]]]. (2) c aE In the present paper, the tensile strength of C/SiC is about 323 MPa, the value of n is about 0.63, E is about 50 GPa. Therefore, from Eq. (2), DT (6838C, which is c consistent with the experimental result. As shown in Fig. 7a, the cracks on the surface of the matrix were formed at lower DT, which does not affect the strength. Above DT (7008C), the propagation of cracks c inwards cause the fracture of fibers and the decrease of strength (Fig. 7b). At DT .10008C, the interior matrix cracks that propagate through fibers cause a further decrease of strength, as shown in Fig. 7c. 3.2. Effect of quench number on the flexural strength The driving force for crack propagation is derived from the elastic energy stored in the body caused by repeated cooling and heating. When the elastic energy is larger than the surface energy required for propagation of cracks, the cracks will propagate. During the initial stage of thermal shock, with the increase of quench number, surface cracks propagate inwards, which leads to the increase of crack density in composites. The increase of matrix crack density may result in the decrease of the mechanical properties of composites. At DT .DT , the flexural strength as a function of c quench cycle number is shown in Fig. 8. As shown in Fig. 8, with the increase of quench cycle number, the flexural Fig. 7. Morphology of microcracks after thermal shock for 100 strength of the composite decreases gradually. When the cycles. (a) DT56008C, (b) DT57008C, (c) DT510008C
X. Yin et al. Carbon 40(2002)905-910 000 that there exists a critical value for the quench number of C/SiC composites. When the quench number reaches the 800 critical value, the mechanical properties of composites do 三5杀 not decrease with increase of quench number. At the same time. Fig. 8 also indicates that the decrease of mechanical properties of C/Sic during thermal shock results from physical damage, not from chemical corrosion (i.e. oxida- tion). Otherwise, the strength of composites will continu- ously decrease with the increase of quench numbe In the present experiment, the critical number of quench ycles is 50 times. As shown in Fig. 9, the crack density is saturated after 50 cycles. With the increase of quench number during the initial stage of thermal shock, crack Number of quench Cycle propagate into the interior of composites, fiber and matrix Fig. 8. Effect of thermal-shock times on the flexural strength debond, and cracks bridge between fibers, which may C/SiC(△T=1000°C) cause the continuous decrease of strength. with the further increase of quench number, the fibers are damaged, which composite is thermally shocked more than 50 cycles, the leads to the observed decrease of strength. When the rength does not decrease further until the quenching quenching number is larger than the critical value, the umber is as high as 100 cycles. The above results indicate crack density is saturated, and the strength of the compos- ites does not decrease further. After the composite is quenched more than 100 times at AT=1000.C, the re- sidual flexural strength is still 83% of the original value 4. Conclusions 1. C/SiC composites have good thermal shock resistance After the composite was quenched more than 100 times the residual flexural strength was 83% of the original 2. The AT of C/SiC is 700C. Above AT the cracks on the surface of the matrix will propagate into the interior of the composites and make the fibers degrade, causing BOKU X190 100Nm WD3 a decrease of the flexural strength 3. The critical number of thermal shock cycles of c/Sic (a) composite is about 50 cycles. When the number of thermal shocks is less than 50 cycles, the residual flexural strength of C/SiC composite decreases with the increase of thermal shock cycles. When the number of thermal shock cycles of C/Sic is greater than 50, the strength of C/Sic does not further decrease because the crack density is saturated. Acknowledgements The research work has been supported by the National atural Scientific Foundation of the Peoples Republic of China and Nation Aviation Scientific Foundation 2:8yt037 References Fig. 9. Morphology of cracks in C/SiC(a)50 cycles(b) 100 [1 Lamouroux F, Bourrat X, Sevely J, Naslain R. Structure/ oxidation behavior relations in the carboneous constituents of
X. Yin et al. / Carbon 40 (2002) 905 –910 909 that there exists a critical value for the quench number of C/SiC composites. When the quench number reaches the critical value, the mechanical properties of composites do not decrease with increase of quench number. At the same time, Fig. 8 also indicates that the decrease of mechanical properties of C/SiC during thermal shock results from physical damage, not from chemical corrosion (i.e. oxidation). Otherwise, the strength of composites will continuously decrease with the increase of quench number. In the present experiment, the critical number of quench cycles is 50 times. As shown in Fig. 9, the crack density is saturated after 50 cycles. With the increase of quench number during the initial stage of thermal shock, cracks propagate into the interior of composites, fiber and matrix debond, and cracks bridge between fibers, which may Fig. 8. Effect of thermal-shock times on the flexural strength of cause the continuous decrease of strength. With the further C/SiC (DT510008C). increase of quench number, the fibers are damaged, which leads to the observed decrease of strength. When the composite is thermally shocked more than 50 cycles, the quenching number is larger than the critical value, the strength does not decrease further until the quenching crack density is saturated, and the strength of the compos- number is as high as 100 cycles. The above results indicate ites does not decrease further. After the composite is quenched more than 100 times at DT510008C, the residual flexural strength is still 83% of the original value. 4. Conclusions 1. C/SiC composites have good thermal shock resistance. After the composite was quenched more than 100 times, the residual flexural strength was 83% of the original value. 2. The DT of C/SiC is 7008C. Above DT , the cracks on c c the surface of the matrix will propagate into the interior of the composites and make the fibers degrade, causing a decrease of the flexural strength. 3. The critical number of thermal shock cycles of C/SiC composite is about 50 cycles. When the number of thermal shocks is less than 50 cycles, the residual flexural strength of C/SiC composite decreases with the increase of thermal shock cycles. When the number of thermal shock cycles of C/SiC is greater than 50, the strength of C/SiC does not further decrease because the crack density is saturated. Acknowledgements The research work has been supported by the National Natural Scientific Foundation of the People’s Republic of China and Nation Aviation Scientific Foundation. References Fig. 9. Morphology of cracks in C/SiC. (a) 50 cycles (b) 100 [1] Lamouroux F, Bourrat X, Sevely J, Naslain R. Structure/ cycles. oxidation behavior relations in the carboneous constituents of
910 X. Yin et al. Carbon 40(2002)905-910 2D-C (T300)/P C/SiC (CVI) composites. Carbon [9] Bhatt RT, Phillips RE. Thermal effect on the mechanical properties of SiC-fiber-reinforced-reaction-bonded silico [2] Cavalier JC, Lacombe A, Rouges JM. Ceramic matrix-composites. J Mater Sci 1990, 26: 3401-7 omposites, new high performance materials. In: [0 JE, Singh RN. Thermal shock damage in a two- AR, Lamicq P, Massiah A, editors, Developments ional woven fiber-reinforced-CVI SiC-matrix compo- science and technology of composite materials, London, UK m Ceram Soc1996;7911:2857-64 Elsevier, 1989, pp 99-110, in French l1 Miller ra. oxidation behavior of mullite-coated 3]Kingery WD. Factors affecting thermal shock resistance J Lee KN SiC/SiC composites under thermal cycling between ceramic materials. J Am Ceram Soc 1955: 38(1): 3-15. room temperature and 1200-1400C. J Am Ceram Soc 4 Hasselman DPH. Thermal stress resistance parameters for 1996:793)620-6 ceramIcs [12 Kagawa Y, Kurosawa N, Kishi T. Thermal shock resistance Bull1970;49(12):1033-7 of SiC-fibre-reinforced borosilicate glass and lithium [5] Hasselman DPH. Thermal stress resistance of engineering aluminosilicate matrix composites. J Mater Sci 1993: 28:735 ramics. Mater Sci Eng 1985: 71: 251-64. [6]Hasselman DPH. Strength behavior of polycry [13] Wang H, Singh RN. Thermal shock behavior of two dimen- lumina subjected to thermal shock. J Am Cerar sional woven-fiber-reinforced ceramic composites. JAm 1970;53(9):490-5 Ceram Soc1996;797:1783-92 [7 Singh RN, Wang H. Thermal shock behavior of fiber-re- [14] Singh RN, Wang H. Thermal shock behavior of fiber-re- mposites Eng inforced ceramic matrix composites. Composites Eng 1995;5(10-11):1287-97 1995:5(10-11:1287-9 8 Long MC, Moore Re, Day DE, Wesling JG, Burns R. omposite, Ceram Eng Sci Proc 1989; 10(9-10): 1231-43
910 X. Yin et al. / Carbon 40 (2002) 905 –910 2D-C (T300)/P C/SiC (CVI) composites. Carbon [9] Bhatt RT, Phillips RE. Thermal effect on the mechanical y 1993;31(8):1273–88. properties of SiC-fiber-reinforced-reaction-bonded silicon [2] Cavalier JC, Lacombe A, Rouges JM. Ceramic matrix nitride-matrix-composites. J Mater Sci 1990;26:3401–7. composites, new high performance materials. In: Bunsell [10] Webb JE, Singh RN. Thermal shock damage in a twoAR, Lamicq P, Massiah A, editors, Developments in the dimensional woven-fiber-reinforced-CVI SiC-matrix composcience and technology of composite materials, London, UK: site. J Am Ceram Soc 1996;79(11):2857–64. Elsevier, 1989, pp. 99–110, in French. [11] Lee KN, Miller RA. Oxidation behavior of mullite-coated [3] Kingery WD. Factors affecting thermal shock resistance of SiC and SiC/SiC composites under thermal cycling between ceramic materials. J Am Ceram Soc 1955;38(1):3–15. room temperature and 1200–14008C. J Am Ceram Soc [4] Hasselman DPH. Thermal stress resistance parameters for 1996;79(3):620–6. brittle refractory ceramics: a compendium. Am Ceram Soc [12] Kagawa Y, Kurosawa N, Kishi T. Thermal shock resistance Bull 1970;49(12):1033–7. of SiC-fibre-reinforced borosilicate glass and lithium [5] Hasselman DPH. Thermal stress resistance of engineering aluminosilicate matrix composites. J Mater Sci 1993;28:735– ceramics. Mater Sci Eng 1985;71:251–64. 41. [6] Hasselman DPH. Strength behavior of polycrystalline [13] Wang H, Singh RN. Thermal shock behavior of two dimenalumina subjected to thermal shock. J Am Ceram Soc sional woven-fiber-reinforced ceramic composites. J Am 1970;53(9):490–5. Ceram Soc 1996;79(7):1783–92. [7] Singh RN, Wang H. Thermal shock behavior of fiber-re- [14] Singh RN, Wang H. Thermal shock behavior of fiber-reinforced ceramic matrix composites. Composites Eng inforced ceramic matrix composites. Composites Eng 1995;5(10–11):1287–97. 1995;5(10–11):1287–97. [8] Long MC, Moore RE, Day DE, Wesling JG, Burns R. Thermal shock behavior of an SiC-fiber-reinforced-cordierite composite. Ceram Eng Sci Proc 1989;10(9–10):1231–43
