WO2011118757A1 - C/cコンポジット材及びその製造方法 - Google Patents
C/cコンポジット材及びその製造方法 Download PDFInfo
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- WO2011118757A1 WO2011118757A1 PCT/JP2011/057309 JP2011057309W WO2011118757A1 WO 2011118757 A1 WO2011118757 A1 WO 2011118757A1 JP 2011057309 W JP2011057309 W JP 2011057309W WO 2011118757 A1 WO2011118757 A1 WO 2011118757A1
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- composite material
- carbon
- fibers
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- 239000002131 composite material Substances 0.000 title claims abstract description 68
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 23
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 22
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 9
- 238000000034 method Methods 0.000 title abstract description 10
- 239000000835 fiber Substances 0.000 claims abstract description 48
- 239000004744 fabric Substances 0.000 claims abstract description 32
- 239000011159 matrix material Substances 0.000 claims abstract description 22
- 238000003475 lamination Methods 0.000 claims abstract description 10
- 239000002296 pyrolytic carbon Substances 0.000 claims abstract description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 59
- 239000004917 carbon fiber Substances 0.000 claims description 59
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 39
- 239000000463 material Substances 0.000 claims description 33
- 238000005452 bending Methods 0.000 claims description 28
- 238000010030 laminating Methods 0.000 claims description 14
- 239000002994 raw material Substances 0.000 claims description 14
- 239000002759 woven fabric Substances 0.000 claims description 11
- 230000000052 comparative effect Effects 0.000 description 13
- 239000011229 interlayer Substances 0.000 description 9
- 239000010410 layer Substances 0.000 description 7
- 238000012986 modification Methods 0.000 description 5
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- 239000011295 pitch Substances 0.000 description 5
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- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 4
- 238000005087 graphitization Methods 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 4
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- 239000005011 phenolic resin Substances 0.000 description 3
- 239000012808 vapor phase Substances 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
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- 230000000149 penetrating effect Effects 0.000 description 2
- 238000013001 point bending Methods 0.000 description 2
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- 239000004065 semiconductor Substances 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
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- 150000002739 metals Chemical class 0.000 description 1
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- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
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Definitions
- the present invention relates to a C / C composite material and a method for producing the same, and in particular, a C / C composite material capable of improving the thermal conductivity in the stacking direction at room temperature without reducing bending strength or interlaminar shear strength and the same. It relates to a manufacturing method.
- ⁇ C / C composite materials have high strength and high toughness by combining with carbon fibers in addition to the corrosion resistance and heat resistance of carbon.
- the C / C composite material is also characterized by being lighter than metals because of the low specific gravity of carbon. Because of these characteristics, it has been studied for use in aerospace, semiconductor and solar cell panel manufacturing, nuclear materials, metal heat treatment jig applications, etc. In addition to the above, high thermal conductivity is required. In particular, when it is necessary to support a material having a large area, it is often necessary to improve the thermal conductivity in the stacking direction of the C / C composite material.
- Patent Document 1 In order to increase the strength and high thermal conductivity of the C / C composite material, for example, the thermal conductivity is improved by impregnating pyrolytic carbon inside the carbonaceous felt, and the bulk density is regulated. Thus, the strength is improved (see Patent Document 1 below). Although the purpose is different, in order to optimize the strength characteristics and thermal conductivity of the C / C composite material, proposals have been made to regulate the bending strength and the thermal conductivity in the stacking direction (see below). Patent Document 2).
- Patent Document 1 it is possible to improve the thermal conductivity in the direction perpendicular to the stacking direction, but it is difficult to improve the thermal conductivity in the stacking direction. Further, the strength of the C / C composite material cannot be sufficiently increased simply by regulating the bulk density. Further, the technique described in Patent Document 2 cannot improve the thermal conductivity at a low temperature (normal temperature) to a desired value.
- an object of the present invention is to provide a C / C composite material that can improve the thermal conductivity in the stacking direction at room temperature while improving the bending strength and interlaminar shear strength, and a method for producing the same.
- the present invention provides a carbon fiber selected from a raw material group consisting of a layered body using continuous fibers, a layered body using chopped fibers, a 2D woven fabric, and a layered body using felt.
- a C / C composite material having a laminate in which at least two or more raw materials are laminated, and including a matrix component inside the laminate, wherein the bending strength is 100 MPa or more at room temperature.
- the thermal conductivity in the direction is 30 W / (m ⁇ K) or more. If it is the said structure, the thermal conductivity of the lamination direction at normal temperature can be improved, aiming at the improvement of bending strength.
- the layered body using continuous fibers refers to a layered body in which, for example, integrated long carbon fibers arranged in one direction up to both ends in the plane direction are arranged in parallel, and a layered body using chopped fibers.
- a short carbon fiber is two-dimensionally randomly spread in a thin and flat surface and pressed to form a layered body.
- a 2D woven fabric is, for example, a long strip of long carbon fibers arranged in parallel.
- the tow formed in a shape is arranged vertically and horizontally, and the tows are intersected with each other to form a woven fabric, and the layered body using felt, for example, gathers short carbon fibers randomly in three dimensions, A layered body that is pressed at a certain pressure.
- the present invention is a carbon selected from a raw material group consisting of a layered body using continuous fibers, a layered body using chopped fibers, a 2D woven fabric, and a layered body using felt.
- a C / C composite material having a laminate in which at least two raw materials containing fibers are laminated, and containing a matrix component inside the laminate, and having an interlayer shear strength of 10 MPa or more and a lamination direction
- the thermal conductivity is 30 W / (m ⁇ K) or more. If it is the said structure, the thermal conductivity of the lamination direction at normal temperature can be improved, aiming at the improvement of interlayer shear strength.
- the matrix component is composed of vapor-phase pyrolytic carbon or pitch-derived carbon.
- the matrix can be easily produced, and the bending strength and interlaminar shear strength can be further improved, and the thermal conductivity in the stacking direction at room temperature can be further improved.
- carbon fibers are arranged in the stacking direction of the laminate. With such a configuration, since heat conduction is performed by the carbon fiber, the thermal conductivity in the stacking direction at room temperature can be further improved.
- the present invention has a laminate having a structure in which two or more laminar bodies containing carbon fibers having two or more cloths made of continuous fibers and felt are laminated, and the laminate.
- C / C composite material containing a matrix component inside, wherein the fibers of the cloth are extended in one direction in a plane perpendicular to the lamination direction, and at least one cloth in the layered body is other The fibers extend in a direction different from the cloth, and a part of the felt fibers penetrates the cloth in the stacking direction.
- both strengths of the C / C composite material can be further increased.
- both strengths of the C / C composite material can be increased in multiple directions instead of one direction.
- both strengths of the C / C composite material can be further increased.
- the extending direction of the fibers in the one cloth and the extending direction of the fibers in the other cloth are perpendicular to each other. As long as the extending direction of one fiber is configured to be perpendicular to the extending direction of the other fibers, both strengths of the C / C composite material can be increased in any direction.
- the matrix component is composed of vapor-phase pyrolytic carbon or pitch-derived carbon. Such a configuration is desirable for the same reason as described above.
- the present invention provides at least two or more selected from a raw material group consisting of a layered body using continuous fibers, a layered body using chopped fibers, a 2D woven fabric, and a layered body using felt.
- the present invention it is possible to improve the thermal conductivity in the stacking direction at room temperature while improving the bending strength and the interlaminar shear strength.
- a PAN-based carbon fiber tow (single fiber diameter of about 7 ⁇ m, tensile strength of about 5 GPa, number of filaments of about 12,000) is made, and then a plurality of PAN-based carbon fiber tows are bundled in a hook shape using nylon fibers.
- a carbon fiber unidirectional cloth was produced. This carbon fiber unidirectional cloth has high bending strength and high thermal conductivity in the extending direction of the PAN-based carbon fiber tow. However, when these are laminated, the heat conduction in the laminating direction between adjacent carbon fiber unidirectional cloths. The degree is lowered.
- the same PAN-based carbon fiber was cut to about 25 mm to produce a felt (bulk density: about 0.1 g / cm 3 ) in which the carbon fibers were randomly oriented.
- a C / C composite in which a felt is impregnated with a matrix component is inferior in bending strength or the like, but has high thermal conductivity in all directions.
- the two felts 10 and the two carbon fiber unidirectional cloths 11 and 12 are arranged in order from the top, the felt 10, the carbon fiber unidirectional cloth 12, the felt 10, A layered body 1 was produced by laminating carbon fiber unidirectional cloths 11.
- the extending direction of the carbon fibers in one carbon fiber unidirectional cloth 11 is arranged so as to be perpendicular to the extending direction of the carbon fibers in the other carbon fiber unidirectional cloth 12.
- each layer is formed by penetrating all layers with a needle having a reverse barb and entangled with the carbon fiber of the felt.
- a carbon fiber preform having a thickness of about 10 mm and a bulk density of about 0.6 g / cm 3 (a laminated body, hereinafter sometimes referred to as a 2.5D preform) was produced.
- the needle punch provided opening holes with a diameter of 0.3 to 0.6 mm at an average interval of about 2 mm.
- the carbon fibers of the felt are arranged so as to penetrate the carbon fiber unidirectional cross in the laminating direction, so that the thermal conductivity in the laminating direction at room temperature can be improved.
- the layers are firmly bonded, the bending strength and interlayer shear strength of the C / C composite material can be increased.
- the 2.5D preform was CVI-treated. Specifically, under the condition that the temperature is about 1000 ° C. and the pressure is 10 Torr, the above 2 in the mixed gas flow of hydrogen and propane (the volume ratio of hydrogen to propane is about 90:10). The 5D preform was held for about 1000 hours to deposit the gas phase pyrolytic carbon as a matrix component in the 2.5D preform. As a result, a C / C composite material having a bulk density increased to about 1.7 g / cm 3 was obtained. Finally, the C / C composite material was heat-treated at about 2000 ° C. The C / C composite material had a thickness of about 10 mm.
- the carbon fiber preform has a relatively small thickness of about 10 mm, so that the needle is penetrated through all layers by needle punching, but the needle is penetrated through all layers.
- Example 1 As Example 1, the C / C composite material shown in the above embodiment was used.
- the C / C composite material thus produced is hereinafter referred to as the present invention material A1.
- Example 2 Same as Example 1 except that heat treatment was performed at about 1000 ° C. for about 1 hour in a nitrogen atmosphere after removing 2.5D preform and before CVI treatment to remove nylon fibers in the 2.5D preform. Thus, a C / C composite material was produced.
- the C / C composite material thus produced is hereinafter referred to as the present invention material A2.
- Example 3 A C / C composite material was produced in the same manner as in Example 1 except that the C / C composite material was further heat-treated (at about 3000 ° C. for about 24 hours) using an Acheson graphitization furnace.
- the C / C composite material thus produced is hereinafter referred to as the present invention material A3.
- Example 4 A C / C composite material was produced in the same manner as in Example 2 except that the C / C composite material was further heat-treated (at about 3000 ° C. for about 24 hours) using an Acheson graphitization furnace.
- the C / C composite material thus produced is hereinafter referred to as the present invention material A4.
- Example 5 When forming the matrix on the 2.5D preform, a C / C composite material was produced in the same manner as in Example 1 above, except that pitch-derived carbon was used instead of vapor-phase pyrolytic carbon. Specifically, the same 2.5D preform as in Example 1 above was impregnated with a phenol resin and fired in a nitrogen atmosphere at about 1000 ° C. for about 1 hour to obtain a low-density C / C composite material. Next, this low density C / C composite material is impregnated with coal pitch and fired at about 1000 ° C. for about 1 hour five times to increase the bulk density to about 1.6 g / cm 3. A C / C composite material was obtained. Finally, this was heat-treated at about 2000 ° C.
- the matrix component is mainly composed of carbon derived from pitch.
- the C / C composite material thus produced is hereinafter referred to as the present invention material A5.
- a plain weave cloth is produced using a tow composed of about 12,000 carbon fiber filaments, impregnated with a phenol resin, and laminated with a hot platen press to form a laminate (a low-density C / C composite material).
- a laminate a low-density C / C composite material
- it may be referred to as a 2D cloth laminate.
- the laminate is fired at about 1000 ° C. for about 1 hour in a nitrogen atmosphere and then impregnated with petroleum pitch and fired at about 1000 ° C. for about 1 hour, the bulk density is about 1 A C / C composite material increased to 0.6 g / cm 3 was obtained. Finally, this was heat-treated at about 2000 ° C. for about 1 hour.
- the C / C composite material thus produced is hereinafter referred to as a comparative material Z1.
- Comparative Example 2 A C / C composite material was produced in the same manner as in Comparative Example 1 except that the C / C composite material was further heat-treated (at about 3000 ° C. for about 1 hour) using an Acheson graphitization furnace.
- the C / C composite material thus produced is hereinafter referred to as a comparative material Z2.
- Comparative Example 3 After sandwiching the laminate obtained by laminating 40 layered bodies used in Example 1 between two metal plates with a distance of about 10 mm without needle punching, impregnating with phenol resin and further curing, A laminate having a thickness of about 10 mm was obtained. This laminate was fired in a nitrogen atmosphere at about 1000 ° C. for about 1 hour to produce a low density C / C composite. A C / C composite material having a bulk density increased to about 1.6 g / cm 3 was obtained by repeating the process of impregnating the coal pitch and firing at about 1000 ° C. for about 1 hour 5 times. Finally, this was heat-treated at about 2000 ° C. for about 1 hour. The C / C composite material thus produced is hereinafter referred to as comparative material Z3.
- thermal conductivity // the thermal conductivity in the plane direction (the thermal conductivity in the direction perpendicular to the stacking direction, which may be hereinafter referred to as thermal conductivity //), was examined by the following method. Is shown in Table 1. The experiment was performed at room temperature (23 ° C.). 3 and 4 show the relationship between the bending strength and the thermal conductivity ⁇ of these materials and the relationship between the thermal conductivity ⁇ ⁇ and the interlaminar shear strength, respectively.
- ILSS internal shear strength
- Thermal conductivity ⁇ , Thermal conductivity // A test piece having a diameter of about 10 ⁇ and a thickness of 3 mm (measurement direction is the thickness direction) was prepared, and the thermal diffusivity was measured using a laser flash method. This results in the bulk density (using the value of the graphite.
- Inventive materials A1 and A2 obtained by densifying the 2.5D preform by CVI treatment have a bending strength of 100 Mpa or more, an interlayer shear strength of 10 MPa or more, and a thermal conductivity of 30 W / (m ⁇ K) or more.
- the present invention materials A3 and A4 which differ from the present invention materials A1 and A2 in that heat treatment (graphitization treatment) of about 3000 ° C. is applied, respectively, in comparison with the present invention materials A1 and A2, the bending strength and interlaminar shear strength. are slightly decreased (however, the bending strength is 100 Mpa or more and the interlaminar shear strength is 10 MPa or more). It is recognized that the material is greatly improved as compared with the materials A1 and A2.
- the present invention material A5 which is different from the present invention material A1 in that the matrix component is composed of pitch-derived carbon, has a slightly lower thermal conductivity than the present invention material A1 (however, heat conduction).
- the rate is 30 W / (m ⁇ K) or more), but it is recognized that the bending strength and the interlaminar shear strength are substantially the same as the material A1 of the present invention. From the above, it can be seen that all of the inventive materials A1 to A5 have a bending strength of 100 Mpa or more, an interlayer shear strength of 10 MPa or more, and a thermal conductivity of 30 W / (m ⁇ K) or more.
- the comparative materials Z1 and Z2 which are different from the material A1 of the present invention in that a laminate of 2D cloth is used instead of the 2.5D preform, have a bending strength of 100 Mpa or more, but both have thermal conductivity. It is recognized that the soot is less than 30 W / (m ⁇ K), and that the interlaminar shear strength is less than 10 MPa in the comparative material Z2. Further, in the comparative material Z3 different from the material A5 of the present invention in that the preform is not subjected to needle punching, the bending strength is 100 Mpa or more, but the thermal conductivity ⁇ ⁇ is less than 30 W / (m ⁇ K). It is recognized that the interlaminar shear strength is also less than 10 MPa.
- the bending strength is 100 MPa or more and the thermal conductivity in the stacking direction is 30 W / (m ⁇ K) or more, or the interlayer shear strength is 10 MPa or more and the thermal conductivity in the stacking direction is It can be seen that the configuration of the present invention is desirable in order to achieve 30 W / (m ⁇ K) or more. This is apparent from FIGS. 3 and 4.
- the layered body 1 is not limited to the above structure.
- the extending direction of the carbon fiber in one carbon fiber unidirectional cloth 11 is the other carbon fiber unidirectional.
- the cross fiber 12 may not be perpendicular to the extending direction of the carbon fibers.
- three carbon fiber unidirectional crosses 11, 12, and 13 may be arranged, and the extending directions of these carbon fibers may be different from each other (in FIG. 6, adjacent carbon fiber unidirectional
- the angle formed by the extending direction of the carbon fibers in the cloth is 60 °).
- FIG. 7 when the strength in one direction (for example, the A direction in FIG.
- the extending direction of the carbon fibers in the carbon fiber unidirectional cloths 11 and 12 is set together.
- the direction A may be adopted, and only the carbon fiber unidirectional cross 13 may be a direction other than the A direction.
- the felt 10 in the layered body 1 is not limited to one as described above, and may be two or more, and the carbon fiber unidirectional cloth and felt as shown in FIG. It is good also as a form laminated
- the laminate 2 is not limited to the one having the above-described structure.
- a 2D woven fabric 22 is disposed between laminates 21 and 21 made of 2.5D preform.
- the structure may be a structure in which a 2D woven fabric 22 is arranged on one surface of a laminate 21 made of 2.5D preform.
- at least two raw materials selected from a raw material group consisting of a layered body using continuous fibers, a layered body using chopped fibers, a 2D woven fabric, and a layered body using felt are used as the laminate 2.
- the bending strength is 100 MPa or more and the thermal conductivity in the stacking direction is 30 W / (m ⁇ K) or more, or the interlayer shear strength is 10 MPa or more and the thermal conductivity in the stacking direction is 30 W / ( Any structure may be used as long as it is m ⁇ K) or more.
- the diameter of the carbon fiber tow and the single fiber constituting the carbon fiber felt is not limited as described above, but is preferably about 5 to 20 ⁇ m. If the diameter of the single fiber is less than 5 ⁇ m, the strength per single fiber becomes too low and the strength may decrease. On the other hand, if the diameter of the single fiber exceeds 20 ⁇ m, it may be difficult to handle or needle There may be a disadvantage that the fiber is easily broken during punching.
- the carbon fiber length of the carbon fiber felt is preferably about 10 to 100 mm. When the carbon fiber length is less than 10 mm, the fibers are not easily entangled with each other, and there is a disadvantage that the shape of the felt as a fiber aggregate is difficult to be formed. On the other hand, there may be a disadvantage that it is difficult to manufacture the felt.
- the size of the hole formed by the needle punch is not limited as described above, but the diameter is preferably about 0.1 to 1.0 mm. If the hole diameter is less than 0.1 mm, the amount of felt fibers penetrating the cloth in the laminating direction decreases, and the thermal conductivity in the laminating direction at normal temperature may not be sufficiently improved. If the diameter of the hole exceeds 1.0 mm, the area of the hole becomes too large, and the strength of the C / C composite material may be reduced.
- the C / C composite material of the present invention can be used for aerospace use, semiconductor and solar cell panel production, nuclear materials, metal heat treatment jig applications, and the like.
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Abstract
Description
また、目的は異なるが、C/Cコンポジット材の強度特性と熱伝導率との最適化を図るため、曲げ強度と、積層方向の熱伝導率とを規制するような提案がなされている(下記特許文献2参照)。
また、特許文献2に記載の技術では、低温(常温)での熱伝導率を所望の値にまで向上させることはできない。
上記構成であれば、曲げ強度の向上を図りつつ、常温での積層方向の熱伝導度を向上させることができる。
ここで、連続繊維を用いた層状体とは、例えば面方向両端に至るまで一方向に配置された一体の長炭素繊維を平行に並べて形成させた層状体をいい、チョップド繊維を用いた層状体とは、例えば短炭素繊維を二次元でランダムに隙間無く薄く面状に敷き詰めて、プレスして層状体としたものをいい、2D織布とは、例えば長炭素繊維を平行に配置して短冊状に形成したトウを縦横に配置し、該トウを互いに交差させて織布状に形成したものをいい、フェルトを用いた層状体とは、例えば短炭素繊維を三次元にランダムに集合させ、ある程度の圧力でプレスして層状体としたものをいう。
上記構成であれば、層間せん断強度の向上を図りつつ、常温での積層方向の熱伝導度を向上させることができる。
このような構成であればマトリックスを容易に作製でき、曲げ強度や層間せん断強度の更なる向上、及び、常温における積層方向の熱伝導度の更なる向上を図ることができる。
このような構成であれば、炭素繊維により熱伝導がなされるため、常温における積層方向の熱伝導度を一層向上させることができる。
上記構成であれば、曲げ強度と層間せん断強度(以下、両強度と称するときがある)の高い連続繊維から成るクロスが存在しているので、C/Cコンポジット材の両強度を高めることができる。また、熱伝導度の高いフェルトの繊維の一部がクロスを積層方向に貫通していることにより、C/Cコンポジット材において、常温での積層方向の熱伝導度を向上させることができる。更に、フェルトの繊維がクロスを積層方向に貫通することにより、各層が強固に結合されるので、C/Cコンポジット材の両強度を一層高めることができる。また、層状体における少なくとも1のクロスは他のクロスと異なる方向に繊維が延設されているので、一方向ではなく、多方向において、C/Cコンポジット材の両強度を高めることができる。加えて、積層体の内部にマトリックス成分を含んでいるので、C/Cコンポジット材の両強度を更に高めることができる。
1の繊維の延設方向は他の繊維の延設方向とは直角となるように構成されていれば、何れの方向においても、C/Cコンポジット材の両強度を高めることができる。
このような構成が望ましいのは、上述した理由と同様の理由である。
このような方法であれば、上記C/Cコンポジット材を容易に作製することができる。また、ニードルパンチを用いれば、積層体の積層方向に炭素繊維を容易に配することができるので、常温における積層方向の熱伝導度の向上を低コストで実施することができ、しかも、各層が強固に結合されるので、C/Cコンポジット材の強度が高くなる。
先ず、PAN系炭素繊維トウ(単繊維直径約7μm、引っ張り強度約5GPa、フィラメント数約12000本)を作製した後、ナイロン繊維を用いて、複数のPAN系炭素繊維トウを筏状に束ねることにより炭素繊維一方向クロスを作製した。この炭素繊維一方向クロスは曲げ強度は高く、PAN系炭素繊維トウの延設方向における熱伝導率は高いが、これを積層した場合には隣接する炭素繊維一方向クロス同士の積層方向の熱伝導度は低くなる。
これと並行して、上記同じPAN系炭素繊維を約25mmにカットし、炭素繊維がランダムに配向したフェルト(かさ密度:約0.1g/cm3)を作製した。このフェルトにマトリックス成分を含浸させたC/Cコンポジットは曲げ強度等には劣っているが、あらゆる方向において熱伝導度は高い。
実施例1としては、上記形態で示したC/Cコンポジット材を用いた。
このようにして作製したC/Cコンポジット材を、以下、本発明材料A1と称する。
2.5Dプリフォーム中のナイロン繊維を除去するため、2.5Dプリフォーム作製後CVI処理前に、窒素雰囲気下約1000℃で約1時間の熱処理を行なった以外は、上記実施例1と同様にしてC/Cコンポジット材を作製した。
このようにして作製したC/Cコンポジット材を、以下、本発明材料A2と称する。
アチェソン黒鉛化炉を用いて、C/Cコンポジット材に更に熱処理(約3000℃で約24時間)を施した以外は、上記実施例1と同様にしてC/Cコンポジット材を作製した。
このようにして作製したC/Cコンポジット材を、以下、本発明材料A3と称する。
アチェソン黒鉛化炉を用いて、C/Cコンポジット材に更に熱処理(約3000℃で約24時間)を施した以外は、上記実施例2と同様にしてC/Cコンポジット材を作製した。
このようにして作製したC/Cコンポジット材を、以下、本発明材料A4と称する。
2.5Dプリフォームにマトリックスを形成する際、気相熱分解炭素を用いずピッチ由来の炭素を用いた以外は、上記実施例1と同様にしてC/Cコンポジット材を作製した。
具体的には、上記実施例1と同様の2.5Dプリフォームにフェノール樹脂を含浸し、窒素雰囲気中約1000℃で約1時間焼成して低密度のC/Cコンポジット材を得た。次に、この低密度のC/Cコンポジット材に石炭ピッチを含浸して約1000℃で約1時間焼成するという工程を5回繰り返すことにより、かさ密度が約1.6g/cm3まで高められたC/Cコンポジット材を得た。最後に、これを約2000℃で約1時間熱処理した。尚、上述の如く、2.5Dプリフォームに石炭ピッチを含浸して焼成するという工程を繰り返しているので、マトリックス成分は主にピッチ由来の炭素により構成されることになる。
このようにして作製したC/Cコンポジット材を、以下、本発明材料A5と称する。
先ず、約12000本の炭素繊維フィラメントからなるトウを用いて平織りクロス作製し、これにフェノール樹脂を含浸し、積層後に熱盤プレスで成形して積層体(低密度のC/Cコンポジット材であって、以下、2Dクロスの積層体と称することがある)を得た。次に、この積層体を窒素雰囲気中約1000℃で約1時間焼成した後、石油ピッチを含浸して約1000℃で約1時間焼成するという工程を5回繰り返すことにより、かさ密度が約1.6g/cm3まで高められたC/Cコンポジット材を得た。最後に、これを約2000℃で約1時間熱処理した。
このようにして作製したC/Cコンポジット材を、以下、比較材料Z1と称する。
アチェソン黒鉛化炉を用いて、C/Cコンポジット材に更に熱処理(約3000℃で約1時間)を施した以外は、上記比較例1と同様にしてC/Cコンポジット材を作製した。
このようにして作製したC/Cコンポジット材を、以下、比較材料Z2と称する。
実施例1で用いた層状体を40枚積層した積層体をニードルパンチせずに、間隔を約10mmとした2枚の金属板間に挟んだ後、フェノール樹脂を含浸し、更に硬化させて、厚さ約10mmの積層体を得た。この積層体を、窒素雰囲気中約1000℃で約1時間焼成し、低密度のC/Cコンポジットを作製した。これに、石炭ピッチを含浸して約1000℃で約1時間焼成するという工程を5回繰り返すことにより、かさ密度が約1.6g/cm3まで高められたC/Cコンポジット材を得た。最後に、これを約2000℃で約1時間熱処理した。
このようにして作製したC/Cコンポジット材を、以下、比較材料Z3と称する。
上記本発明材料A1~A5及び比較材料Z1~Z3のかさ密度と、曲げ強度と、層間せん断強度(ILSS)と、積層方向の熱伝導率(以下、熱伝導率⊥と表示することがある)と、平面方向の熱伝導率(積層方向と垂直方向の熱伝導率であって、以下、熱伝導率//と表示することがある)とを、以下に示す方法により調べたので、その結果を表1に示す。尚、実験は常温(23℃)で行った。また、これら材料の曲げ強度と熱伝導率⊥との関係、及び、熱伝導率⊥と層間せん断強度との関係について、それぞれ図3及び図4に示す。
長さ60mm、幅10mm、高さ3mm(積層方向を高さとする)である直方体形状のテストピースを準備し、スパン間距離40mm、クロスヘッドスピードを0.5mm/分として3点曲げ試験を行い、最大荷重より下記(1)式を用いて曲げ強度を算出した。
曲げ強度=3PL/(2wh2)・・・(1)
尚、(1)式において、Pは荷重、Lはスパン間距離、wは幅、hは高さである。
長さ50mm、幅10mm、高さ6mm(積層方向を高さとする)である直方体形状のテストピースを準備し、スパン間距離30mm、クロスヘッドスピードを0.5mm/分として3点曲げ試験を行い、最大荷重より下記(2)式を用いて層間せん断強度を算出した。
ILSS=3P/(4wh)・・・(2)
尚、(2)式において、Pは荷重、wは幅、hは高さである。
直径約10φ、厚さ3mm(測定方向は厚さ方向)のテストピースを準備し、レーザーフラッシュ法を用いて熱拡散率を測定した。これと、かさ密度、比熱(黒鉛の値を使用した。尚、出典は、JANAF Thermochemical Tables,3rded.等である)を乗ずることにより熱伝導率を算出した。
2.5DプリフォームにCVI処理を施して緻密化した本発明材料A1、A2は、曲げ強度が100Mpa以上、層間せん断強度が10MPa以上、熱伝導率⊥が30W/(m・K)以上となっていることが認められる。
また、それぞれ約3000℃の熱処理(黒鉛化処理)を加えた点において本発明材料A1、A2と異なる本発明材料A3、A4は、本発明材料A1、A2に比べて、曲げ強度と層間せん断強度とが若干が低下している(但し、曲げ強度が100Mpa以上で、層間せん断強度が10MPa以上である)が、両熱伝導率(熱伝導率⊥と熱伝導率//)については、本発明材料A1、A2に比べて大幅に向上していることが認められる。
以上のことから、本発明材料A1~A5では、全て、曲げ強度が100Mpa以上、層間せん断強度が10MPa以上、熱伝導率⊥が30W/(m・K)以上となっていることがわかる。
また、プリフォームの形成においてニードルパンチを施していない点において本発明材料A5と異なる比較材料Z3では、曲げ強度は100Mpa以上であるが、熱伝導率⊥が30W/(m・K)未満であり、層間せん断強度も10MPa未満となっていることが認められる。
(1)上記層状体1としては上記の構造に限定するものではなく、例えば図5に示すように、一の炭素繊維一方向クロス11における炭素繊維の延設方向は、他の炭素繊維一方向クロス12における炭素繊維の延設方向とは直角でなくても良い。
また、図6に示すように、炭素繊維一方向クロス11,12,13を3枚配置し、これらの炭素繊維の延設方向をそれぞれ異ならしめても良い(図6では、隣接する炭素繊維一方向クロスにおける炭素繊維の延設方向の成す角度は60°となっている)。
更に、図7に示すように、一の方向(例えば、図7ではA方向)における強度が特に必要とされる場合には、炭素繊維一方向クロス11,12における炭素繊維の延設方向を共にA方向とし、炭素繊維一方向クロス13のみをA方向以外の方向としても良い。
加えて、層状体1におけるフェルト10は、上記の如く1枚に限定するものではなく、2枚以上であっても良く、また図1に示したような炭素繊維一方向クロスとフェルトとを交互に積層する形態としても良い。
また、炭素繊維フェルトの炭素繊維長は、10~100mm程度であることが好ましい。炭素繊維長が10mm未満であると、繊維同士が絡みにくく繊維集合体としてのフェルトの形状が形成されにくいという不都合が生じることがある一方、炭素繊維長が100mmを超えると、繊維同士が絡まり過ぎて逆にフェルトの製造が困難になるという不都合が生じることがある。
10 フェルト
11 炭素繊維一方向クロス
12 炭素繊維一方向クロス
Claims (10)
- 連続繊維を用いた層状体、チョップド繊維を用いた層状体、2D織布、及び、フェルトを用いた炭素繊維を含む層状体から成る原料群から選択される少なくとも2以上の原料が積層された積層体を有し、且つ、当該積層体の内部にマトリックス成分を含むC/Cコンポジット材であって、
常温において、曲げ強度が100MPa以上で、且つ、積層方向の熱伝導度が30W/(m・K)以上であることを特徴とするC/Cコンポジット材。 - 連続繊維を用いた層状体、チョップド繊維を用いた層状体、2D織布、及び、フェルトを用いた炭素繊維を含む層状体から成る原料群から選択される少なくとも2以上の原料が積層された積層体を有し、且つ、当該積層体の内部にマトリックス成分を含むC/Cコンポジット材であって、
層間せん断強度が10MPa以上で、且つ積層方向の熱伝導度が30W/(m・K)以上であることを特徴とするC/Cコンポジット材。 - 上記マトリックス成分の一部もしくは全部が気相熱分解炭素により構成される、請求項1又は2に記載のC/Cコンポジット材。
- 上記マトリックス成分の一部もしくは全部がピッチ由来の炭素により構成される、請求項1又は2に記載のC/Cコンポジット材。
- 上記積層体の積層方向に炭素繊維が配されている、請求項1~4の何れか1項に記載のC/Cコンポジット材。
- 連続繊維から成るクロスを2枚以上とフェルトとを有する炭素繊維を含む層状体が2以上積層された構造の積層体を有し、且つ、当該積層体の内部にマトリックス成分を含むC/Cコンポジット材であって、
上記クロスの繊維は、積層方向とは垂直の平面内における1方向に延設され、且つ、上記層状体における少なくとも1のクロスは他のクロスと異なる方向に繊維が延設され、しかも、上記フェルトの繊維の一部は、上記クロスを積層方向に貫通していることを特徴とするC/Cコンポジット材。 - 上記1のクロスにおける繊維の延設方向と上記他のクロスにおける繊維の延設方向とが、直角となるように構成される、請求項6に記載のC/Cコンポジット材。
- 上記マトリックス成分の一部もしくは全部が気相熱分解炭素により構成される、請求項6又は7に記載のC/Cコンポジット材。
- 上記マトリックス成分の一部もしくは全部がピッチ由来の炭素により構成される、請求項6又は7に記載のC/Cコンポジット材。
- 連続繊維を用いた層状体、チョップド繊維を用いた層状体、2D織布、及び、フェルトを用いた層状体から成る原料群から選択される少なくとも2以上の原料が積層された積層体を作製するステップと、
ニードルパンチを用いて、積層体の積層方向に炭素繊維を配するステップを有する、
上記積層体の内部にマトリックス成分を配置するステップと、
を有することを特徴とするC/Cコンポジット材の製造方法。
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