WO2005066098A1 - 複合材料及びその製造方法 - Google Patents
複合材料及びその製造方法 Download PDFInfo
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- WO2005066098A1 WO2005066098A1 PCT/JP2004/019518 JP2004019518W WO2005066098A1 WO 2005066098 A1 WO2005066098 A1 WO 2005066098A1 JP 2004019518 W JP2004019518 W JP 2004019518W WO 2005066098 A1 WO2005066098 A1 WO 2005066098A1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249924—Noninterengaged fiber-containing paper-free web or sheet which is not of specified porosity
- Y10T428/249927—Fiber embedded in a metal matrix
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249924—Noninterengaged fiber-containing paper-free web or sheet which is not of specified porosity
- Y10T428/249928—Fiber embedded in a ceramic, glass, or carbon matrix
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/249921—Web or sheet containing structurally defined element or component
- Y10T428/249924—Noninterengaged fiber-containing paper-free web or sheet which is not of specified porosity
- Y10T428/249928—Fiber embedded in a ceramic, glass, or carbon matrix
- Y10T428/249931—Free metal or alloy fiber
Definitions
- the present invention relates to a composite material and a method for producing the same.
- a ceramic-based composite material in which a matrix phase having silicon carbide force is adhered to a fiber woven fabric made of silicon carbide has been known.
- a ceramic-based composite material hereinafter referred to as siczsic
- siczsic is used as a material for forming a rocket injection nozzle or the like because of its light weight and high heat resistance.
- the matrix phase in the siczsic is obtained by subjecting a heated fiber woven fabric surface to a CVI (Chemical Vapor Infiltration) treatment and a PIP (Polymer Infiltration and Pyrolysis retreatment). It is formed by combination.
- silicon carbide has high heat resistance, it has a characteristic that its strength is reduced in a high-temperature atmosphere. Therefore, the strength of siczsic having a fiber woven fabric composed of silicon carbide and a matrix phase composed of silicon carbide also decreases in a high-temperature atmosphere. Specifically, the strength of SiCZSiC is reduced to about half in an atmosphere at a temperature of about 1400 ° C compared to an atmosphere at room temperature. For this reason, siczsic has a problem that its strength is not sufficient when it is constantly exposed to a high-temperature atmosphere. As a method for solving such a problem, there is a method for removing impurities such as oxygen in silicon carbide fibers.
- CZSiC has higher strength in a high-temperature atmosphere than SiCZSiC, but has a difference in thermal elongation between carbon fiber and a matrix phase formed of silicon carbide. Therefore, in an environment having a thermal cycle, the matrix phase (especially, High residual stress may be applied to the dense phase formed by the CVI method) and the matrix phase may crack. In addition, as described above, the matrix phase adheres to the surface of the fiber woven fabric at a high temperature of about 1000 ° C. Therefore, after the formation of the matrix phase, a high residual stress is applied to the matrix phase even when the matrix phase is cooled. There is a problem that the matrix phase is broken.
- the present invention has been made in view of the above-described problems, and has as its object to improve characteristics in a high-temperature atmosphere and prevent the matrix phase from being destroyed.
- a composite material of the present invention is a composite material comprising a fiber woven fabric made of predetermined fibers, and a matrix phase adhered to the fiber woven fabric.
- the woven fabric employs a configuration that includes main constituent fibers and auxiliary fibers that compensate for (eg, decrease in strength) when the main constituent fibers are exposed to a high-temperature atmosphere.
- the auxiliary fibers are such that the residual stress exerted on the matrix phase due to the difference in thermal elongation between the fiber fabric and the matrix phase is equal to or less than the destructive stress of the matrix phase. If it is included in, it may be configured ⁇ .
- the auxiliary fibers are formed in such a ratio that the stress during use exerted on the matrix phase due to the difference in thermal elongation between the fiber fabric and the matrix phase is equal to or less than the destructive stress of the matrix phase. If it is included in textiles!
- the main constituent fibers may be formed of any one of silicon carbide, carbon, silicon nitride, silicon oxide, aluminum oxide, YAG, and a heat-resistant metal.
- the auxiliary fiber has a composition different from that of the main constituent fiber, and is formed of any one of silicon carbide, carbon, silicon nitride, silicon oxide, aluminum oxide, YAG, and a heat-resistant metal. It may be configured.
- the fiber woven fabric includes a plurality of types of the auxiliary fibers having different compositions! Good.
- the matrix phase is formed of any one of silicon carbide, carbon, zirconium carbide, silicon nitride, silicon oxide, aluminum oxide, zirconium oxide, hafnium oxide, YAG, and a heat-resistant metal. It may be.
- a configuration in which a plurality of types of the matrix phases having different compositions may be provided.
- the main constituent fibers are formed of silicon carbide
- the auxiliary fibers are formed of carbon
- the matrix phase is formed of silicon carbide
- a mixing ratio of the auxiliary fibers to the main constituent fibers is set. May be less than 90%.
- a configuration may be adopted in which the auxiliary fibers are contained in the fiber fabric at a predetermined density distribution.
- a configuration may be adopted in which the density distribution of the auxiliary fibers with respect to the fiber fabric is gradually changed in the thickness direction.
- the method for producing a composite material according to the present invention is a method for producing a composite material comprising a fiber woven fabric made of predetermined fibers and a matrix phase adhered to the fiber woven fabric. Forming a fiber woven fabric containing auxiliary fibers that supplement the properties of the main constituent fibers when exposed to a high-temperature atmosphere; and attaching and forming the matritus phase to the fiber woven fabric. .
- At least a part of the matrix phase may be formed by a CVI method.
- At least a part of the matrix phase may be formed by a PIP method.
- At least a part of the matrix phase may be formed by a slurry method.
- At least a part of the matrix phase may be formed by a reaction sintering method.
- the bundle of the main constituent fibers and the bundle of the auxiliary fibers are combined and then combined to form the fiber woven fabric.
- the fiber fabric may be formed by dispersing and mixing the main constituent fibers and the auxiliary fibers with each other and then twisting the fibers to form the fiber fabric.
- the configuration may be such that the bundle of the main constituent fibers and the bundle of the auxiliary fibers are arranged at a predetermined ratio to form the fiber fabric.
- the fiber woven fabric includes auxiliary fibers that supplement characteristics relating to temperature changes of the main constituent fibers, for example, characteristics when the main constituent fibers are exposed to a high-temperature atmosphere. Therefore, the characteristics of the composite material in a high-temperature atmosphere can be compensated for, and the destruction of the matrix phase can be prevented.
- FIG. 1 is a partially enlarged schematic configuration view of a ceramic-based composite material 1 according to one embodiment of the present invention.
- FIG. 2 is a view for explaining a simulation result of the ceramic-based composite material 1 according to one embodiment of the present invention.
- FIG. 3 is a view for explaining a simulation result of the ceramic-based composite material 1 according to one embodiment of the present invention.
- FIG. 4 is a view for explaining experimental data of the ceramic-based composite material 1 according to one embodiment of the present invention.
- FIG. 5A is a view for explaining an experimental result of the ceramic-based composite material 1 according to one embodiment of the present invention.
- FIG. 5B is a view for explaining an experimental result of the ceramic-based composite material 1 according to one embodiment of the present invention.
- FIG. 6 is a flowchart for explaining a method for producing a ceramic-based composite material 1 according to one embodiment of the present invention. Explanation of symbols
- FIG. 1 is a schematic configuration diagram showing an enlarged part of a ceramic-based composite material 1 (composite material) according to the present embodiment.
- reference numeral 2 is a fiber fabric
- 3 is a matrix phase.
- Fiber woven fabric 2 is formed by three-dimensionally weaving silicon carbide fibers 21 (main constituent fibers) and carbon fibers 22 (auxiliary fibers) together.
- the carbon fiber 22 is an auxiliary fiber that compensates for a decrease in strength (characteristics) when the silicon carbide fiber 21 is exposed to a high-temperature atmosphere. It is woven into the fiber woven fabric 2 at a rate such that the remaining residual stress or the stress during use is less than or equal to the destructive stress of the matrix phase 3.
- the stress to be destroyed as used herein indicates a threshold value of residual stress or stress during use in which the matrix phase 3 can withstand without being destroyed. Phase 3 breaks such as cracks.
- the residual stress referred to here is a stress applied to the matrix phase 3 when the ceramic-based composite material 1 is moved from a high-temperature atmosphere to a low-temperature atmosphere during the formation of the matrix phase. Is a stress that is uniformly exerted for each type.
- the stress during use is the stress applied to the matrix phase 3 due to the temperature distribution inside the ceramic matrix composite 1 when the ceramic matrix composite 1 is placed in the use environment. In each part of the matrix phase 3, the stress has a different strength. In general, the stress in matrix phase 3 during use is smaller than the residual stress.
- the carbon fibers 22 are applied to the fiber fabric 2 at such a ratio that the residual stress applied to the matrix phase 3 due to the difference in thermal elongation between the fiber fabric 2 and the matrix phase 3 becomes equal to or less than the destructive stress of the matrix phase 3.
- it is woven.
- the matrix phase 3 is formed to adhere to the fiber fabric 2, and is formed by silicon carbide.
- the matrix phase 3 is formed on the silicon carbide (hereinafter referred to as CVI matrix) densely formed around the fiber fabric 2 and on the silicon carbide formed densely.
- silicon carbide having pores hereinafter referred to as a PIP matrix.
- the ceramic-based composite material 1 since the fiber fabric 2 contains the carbon fibers 22, the ceramic-based composite material 1 was exposed to a high-temperature atmosphere. Even in this case, it is possible to suppress a decrease in the strength of the ceramic-based composite material 1.
- the carbon fibers 22 are contained in the fiber fabric 2 within a range in which the residual stress applied to the matrix phase 3 or the stress during use is equal to or less than the destructive stress of the matrix phase 3, the ceramic-based composite material At the time of molding and use of 1, the matrix phase 3 is subjected only to stress equal to or less than the crushing stress. Therefore, it is possible to prevent the matrix phase 3 from being broken due to a difference in thermal elongation between the fiber fabric 2 and the matrix phase 3.
- a silicon carbide fiber formed of silicon carbide is used as a main constituent fiber of the present invention.
- the present invention is not limited to this.
- carbon, silicon nitride, silicon oxide It is acceptable to use the main constituent fibers of aluminum oxide, YAG (yttrium aluminum garnet) and heat-resistant metal, which are formed by slippage.
- the force of using carbon fibers formed of carbon as the auxiliary fibers of the present invention is not limited to this.
- silicon carbide having a composition different from that of the main constituent fibers Auxiliary fibers formed of any of carbon, silicon nitride, silicon oxide, aluminum oxide, YAG and heat-resistant metal may be used.
- a plurality of types of auxiliary fibers need not be used as the auxiliary fibers.
- the force using the one formed of silicon carbide as the matrix phase of the present invention is not limited to this.
- carbon, zirconium carbide, silicon nitride, silicon oxide , Aluminum oxide, zirconium oxide, hafnium oxide, YAG and heat-resistant metal It is not necessary to use one type of matrix phase, and a plurality of types of matrix phases may be used.
- the carbon fiber ratio indicates the ratio of the carbon fiber 22 to the fiber fabric 2 as a whole
- the volume ratio is the ceramic-based composite material. 1 indicates the percentage of the fiber fabric 2 contained
- strength CVI indicates the strength of the CVI matrix
- strength PIP indicates the strength of the PIP matrix
- volume ratio CVI indicates the CVI matrix with the ceramic-based composite material 1 as 1.
- the volume ratio PIP indicates the ratio of the ceramic-based composite material 1 to 1 and the PIP matrix is included, and the CVI residual stress of the ceramic-based composite material 1 from 1000 ° C to room temperature (23 ° C)
- the residual stress applied to the CVI matrix is shown when the temperature is changed, and the PIP residual stress is the residual stress applied to the PIP matrix when the temperature of the ceramic-based composite material 1 is increased from 1000 ° C to room temperature.
- Tirano (registered trademark) ZMI fiber manufactured by Ube Industries, Ltd. was used as the silicon carbide fiber 21, and T300 manufactured by Toray was used as the carbon fiber 22.
- the volume ratio of the fiber fabric 2 was 0.4 regardless of the carbon fiber ratio.
- the strength CVI ie the residual fracture stress of the CVI matrix
- the strength PIP ie the residual fracture stress of the PIP matrix
- the volume ratio CVI and the volume ratio PIP were set to 0.22 regardless of the carbon fiber ratio.
- the carbon fiber ratio increases from 0.1 to 1
- the CVI residual stress changes to 0.09 GPa force and 0.89 GPa
- the PIP residual stress increases to 0.0. It changes up to 07GPa.
- the CVI residual stress is higher than the PIP residual stress because the CVI matrix is denser than the PIP matrix and has a higher modulus as a matrix.
- the carbon fiber ratio was 0.9 or 1.0
- the matrix stress 3 was broken by residual stress. That is, Table 1 shows that when the carbon fiber ratio is less than 0.9, the matrix phase 3 is not broken. Therefore, when the main constituent fibers are formed of silicon carbide, the auxiliary fibers are formed of carbon, and the matrix phase is formed of silicon carbide, the mixing ratio of the auxiliary fibers to the main constituent fibers is 90%. It is understood that it is preferable to be less than.
- FIGS. 2 and 3 are diagrams showing how the strength S of the ceramic-based composite material 1 changes with a change in the carbon fiber ratio.
- the horizontal axis represents the carbon fiber ratio
- the vertical axis represents the carbon fiber ratio. Indicates the strength of the ceramic-based composite material 1.
- FIG. 2 is a diagram showing the strength of the ceramic-based composite material 1 at room temperature (23 ° C.)
- FIG. 3 is a diagram showing the strength of the ceramic-based composite material 1 at 1600 ° C. (high-temperature atmosphere). .
- the strength of the ceramic-based composite material 1 is about 250 MPa, which hardly changes with respect to the carbon fiber ratio. This is because ZMI as the silicon carbide fiber 21 and T300 as the carbon fiber 22 have almost the same strength at room temperature. Therefore, for example, when a fiber having a higher strength than T-300 (for example, T-1000) is used as the carbon fiber 22, the strength of the ceramic-based composite material 1 increases as the carbon fiber ratio increases.
- the strength of the ceramic-based composite material 1 increases as the carbon fiber ratio increases. This is because the fiber fabric 2 contains a large amount of the carbon fibers 22 whose strength does not decrease much even in a high-temperature atmosphere, and a decrease in the strength of the ceramic-based composite material 1 in a high-temperature atmosphere is suppressed.
- FIG. 2 and FIG. 3 according to the present embodiment, it is It is understood that it is preferable to set the carbon fiber ratio to the fiber woven fabric 2 to about 0.7 in order to suppress the strength reduction of the mixed matrix composite material 1 and prevent the matrix phase 3 from being broken.
- Table 2 and FIG. 4 are experimental data for supporting the above-described simulation.
- Table 2 shows actual measured values
- FIG. 4 is a graph of the actual measured values in Table 2.
- ZMI + (T-300) ZSiC carbon fiber ratio: 0.5
- ZMlZSiC is a fiber woven fabric made of silicon carbide. It is a ceramic-based composite material made of only Table 2 and Fig. 4 also show, for comparison, the strength of a ceramic-based composite material ( ⁇ -300 / SiC) in which the fiber fabric was formed of carbon only.
- the strength of “ZMlZSiC” has been reduced from 250 MPa to 100 MPa by changing from room temperature (23 ° C) to a high-temperature atmosphere (1600 ° C).
- the strength of “ZMI + (T-300) ZSiC” with a carbon fiber ratio of 0.5 changes from 260 MPa to 186 MPa.
- “T-300ZSiC” changes its strength from 252MPa to 235MPa! / ⁇ .
- FIGS. 5A and 5B are enlarged photographs of the matrix phase when the ceramic-based composite material is returned from a high-temperature atmosphere to room temperature
- FIG. 5A is an enlarged photograph of the matrix phase of “T300ZSiC”.
- FIG. 5B is an enlarged photograph of the matrix phase of the ceramic-based composite material (ZMI + (T-300) ZSiC) according to the present embodiment.
- matrix cracks can be observed in the matrix phase of “T 300 / SiC”, whereas no matrix cracks can be observed in the matrix phase of the ceramic-based composite material according to the present embodiment. No. From this, it was confirmed that the ceramic-based composite material according to the present embodiment can prevent the matrix phase from being broken.
- the method for producing the ceramic-based composite material 1 includes fiber production 1, weaving 2, desize 3, C CVI4, SiC-CVI5, jig separation 6, SiC-CVI7. It is used as part of each process of density measurement 8, PIP9, density measurement 10, machining 11, SiC-CVI12 and inspection 13. The jig separation 6, SiC-CVI7, and others can be omitted.
- the fiber woven fabric 2 is formed by molding the silicon carbide fibers 21 and the carbon fibers 22 into a predetermined shape at a predetermined ratio. Specifically, for example, a fiber bundle in which 300 silicon carbide fibers 21 are bundled with a fiber bundle in which 700 carbon fibers 22 are bundled and then combined to form a fiber fabric 2 may be formed. Alternatively, the fiber woven fabric 2 may be formed after dispersing and mixing the fibers at a ratio of 300 silicon carbide fibers 21 and 700 carbon fibers 22 and twisting them.
- the shape to be formed in the weaving step 2 is preferably, for example, a three-dimensional shape suitable for an injection nozzle of a rocket engine to which the ceramic-based composite material 1 is applied. A step of splitting the plied yarn as described above to have a predetermined thickness may be further performed.
- Machining process 11 is to perform machining and surface grinding on the ceramic-based composite material 1 completed by a hybrid process combining CVI (Chemical Vapor Infiltration) process and PIP (Polymer Infiltration and Pyrolysis) process. This is the process of manufacturing the parts.
- the workpiece is processed into a predetermined shape by using, for example, diamond ganite.
- the main steps of the present embodiment are the above-described hybrid treatment, that is, the CVI treatment for forming a silicon carbide matrix phase on the surface of the formed fiber fabric 2 in a reduced pressure atmosphere, and the gap between the formed matrix phases.
- PIP treatment of impregnating and firing an organic silicon polymer as a base material.
- the CVI treatment includes CC CVI step 4 and three SiC-CVI steps 5, 7, and 12.
- C CVI Step 4 is a step of coating the formed fiber fabric 2 with carbon (preferably graphite carbon) or BN.
- the thickness of the coating is preferably about 0.1-1 O / z m.
- This coating phase separates the matrix phase 3 from the silicon carbide fibers 21 and enhances the toughness of the silicon carbide fibers 21 as disclosed in JP-A-63-12671.
- the SiC-CVI processes 5, 7, and 12 are processes in which the so-called CVI process (gas phase impregnation process) is performed.
- the fiber fabric 2 fixed in a furnace with a special jig is heated to a reduced pressure atmosphere. Then, for example, methyltrichlorosilane is introduced to synthesize the above-mentioned CVI matrix.
- the first steps 5 and 7 are repeated as necessary to bring the volume ratio of the matrix synthesized by the CVI treatment to about 5% or more and about 80% or less.
- the last step 12 is a step of forming a dense matrix on the surface of the PIP matrix formed by the PIP processing. Step 12 is not essential and may be omitted in some cases.
- PIP treatment 9 is a step of performing treatment by the V, so-called PIP method (liquid phase impregnation method), and an impregnation step of impregnating a matrix phase formed by CVI treatment with an organic silicon polymer as a base material. It is followed by a firing step. The impregnation step and the firing step are repeated as necessary.
- the organosilicon polymer used in the impregnation step is preferably a polycarbosilane solution, polyvinyl silane, polymetacarbosilane or the like, or a mixture of these and silicon carbide powder.
- the PIP process in which the organic silicon polymer is impregnated and fired can form a PIP matrix in a short time.
- the impregnation in the PIP treatment may be immersion, reduced pressure impregnation, or pressure impregnation !, a deviation, or a combination thereof.
- immersion a large amount of the organosilicon polymer can be impregnated in a short time.
- vacuum impregnation an organic silicon polymer Can be impregnated.
- pressure impregnation airtightness can be improved by impregnating by impregnating in the direction of pressure during use.
- the matrix phase 3 is attached to the fiber fabric 2, and the ceramic-based composite material 1 according to the present embodiment is manufactured.
- a step for measuring whether or not the density of the matrix phase 3 formed in each immediately preceding step has a desired density is performed. This is a step of inspecting whether the completed ceramic-based composite material 1 has desired performance.
- the thermal conductivity or the Young's modulus may be focused on when the main constituent fibers are exposed to a high-temperature atmosphere. In this case, it is possible to prevent the matrix phase from being broken even if attention is paid to any of the characteristics, in which the auxiliary fiber is selected so as to supplement the respective characteristics.
- the present invention is not limited to this, and the density distribution of the auxiliary fibers with respect to the ceramic-based composite material 1 may be biased.
- the shape of the ceramic-based composite material is set according to the wall shape of the injection nozzle.
- the inner wall surface of the ceramic-based composite material (the center side of the injection nozzle) is exposed to a higher temperature atmosphere, and the outer wall surface of the ceramic-based composite material is exposed to a lower temperature atmosphere than the inner wall surface. Therefore, the density distribution of the auxiliary fiber to the fiber It is preferable to gradually increase the height from the side toward the inner wall surface side, that is, gradually change in the thickness direction.
- the matrix phase 3 made of silicon carbide was formed by the CVI method and the PIP method.
- the present invention is not limited to this.
- the matrix phase may be formed by a slurry method or a reaction sintering method.
- the slurry method is a method in which a slurry is generated by pouring a powder into a solvent, and the slurry is sintered to form a matrix phase.
- the reaction sintering method is a method in which a plurality of kinds of powders or powders are mixed with each other. This is a method of forming a matrix phase by reacting with a molten metal at a high temperature. Industrial applicability
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Abstract
Description
Claims
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DE102008022289B4 (de) * | 2008-04-25 | 2010-07-29 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Flugkörper |
FR2933970B1 (fr) * | 2008-07-21 | 2012-05-11 | Snecma Propulsion Solide | Procede de fabrication d'une piece en materiau composite thermostructural et piece ainsi obtenue |
US20110071014A1 (en) * | 2009-09-24 | 2011-03-24 | United Technologies Corporation | Hybred polymer cvi composites |
US20110071013A1 (en) * | 2009-09-24 | 2011-03-24 | United Technologies Corporation | Ceramic matrix composite system and method of manufacture |
JP2016141581A (ja) * | 2015-01-30 | 2016-08-08 | イビデン株式会社 | 流体用整流部材 |
JP6441700B2 (ja) * | 2015-01-30 | 2018-12-19 | イビデン株式会社 | 流体用整流部材 |
JP6441701B2 (ja) * | 2015-01-30 | 2018-12-19 | イビデン株式会社 | 流体用整流部材 |
JP2016141582A (ja) * | 2015-01-30 | 2016-08-08 | イビデン株式会社 | 流体用整流部材 |
JP6441699B2 (ja) * | 2015-01-30 | 2018-12-19 | イビデン株式会社 | 流体用整流部材 |
JP6484047B2 (ja) * | 2015-01-30 | 2019-03-13 | イビデン株式会社 | 流体用整流部材 |
RU2603330C2 (ru) * | 2015-03-13 | 2016-11-27 | Государственное бюджетное образовательное учреждение высшего образования Московской области "Технологический университет" | Способ получения многофункциональных керамоматричных композиционных материалов (варианты) |
JP2017105662A (ja) * | 2015-12-08 | 2017-06-15 | イビデン株式会社 | セラミック複合材 |
CN105788890B (zh) * | 2016-05-10 | 2019-05-31 | 湖南艾华集团股份有限公司 | 一种电容器素子的含浸方法 |
CN106738202A (zh) * | 2016-12-12 | 2017-05-31 | 浙江嘉华晶体纤维有限公司 | 一种纤维异型件的制造工艺 |
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JP3211203B2 (ja) * | 1999-03-29 | 2001-09-25 | 川崎重工業株式会社 | 高強度繊維強化複合材料及びその製造方法 |
DE19944345A1 (de) * | 1999-09-16 | 2001-03-22 | Sgl Technik Gmbh | Mit Fasern und/oder Faserbündeln verstärkter Verbundwerkstoff mit keramischer Matrix |
DE10001995A1 (de) * | 2000-01-19 | 2001-07-26 | Alstom Power Schweiz Ag Baden | Verfahren zur Einstellung bzw. Regelung der Dampftemperatur des Frischdampfes und/oder Zwischenüberhitzerdampfers in einem Verbundkraftwerk sowie Verbundkraftwerk zur Durchführung des Verfahrens |
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2004
- 2004-01-08 JP JP2004002904A patent/JP4517334B2/ja not_active Expired - Lifetime
- 2004-12-27 EP EP20040807873 patent/EP1702908B1/en active Active
- 2004-12-27 CA CA 2552364 patent/CA2552364C/en active Active
- 2004-12-27 WO PCT/JP2004/019518 patent/WO2005066098A1/ja not_active Application Discontinuation
- 2004-12-27 CN CNB2004800399529A patent/CN100564319C/zh not_active Expired - Fee Related
- 2004-12-27 US US10/585,289 patent/US7754319B2/en active Active
Patent Citations (2)
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JPH10194856A (ja) * | 1997-01-14 | 1998-07-28 | Toshiba Corp | セラミック複合材料とその部品 |
JP2003020287A (ja) * | 2001-07-04 | 2003-01-24 | Ishikawajima Harima Heavy Ind Co Ltd | セラミックス複合部材の製造方法 |
Non-Patent Citations (1)
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See also references of EP1702908A4 * |
Also Published As
Publication number | Publication date |
---|---|
EP1702908A4 (en) | 2009-11-04 |
US20070166525A1 (en) | 2007-07-19 |
CA2552364C (en) | 2010-07-13 |
CN100564319C (zh) | 2009-12-02 |
JP2005194141A (ja) | 2005-07-21 |
US7754319B2 (en) | 2010-07-13 |
CN1902143A (zh) | 2007-01-24 |
EP1702908A1 (en) | 2006-09-20 |
JP4517334B2 (ja) | 2010-08-04 |
EP1702908B1 (en) | 2014-03-26 |
CA2552364A1 (en) | 2005-07-21 |
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