CN103722823A - C-C-SiC-ZrC ceramic matrix composite and preparation method thereof - Google Patents
C-C-SiC-ZrC ceramic matrix composite and preparation method thereof Download PDFInfo
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- CN103722823A CN103722823A CN201310412248.4A CN201310412248A CN103722823A CN 103722823 A CN103722823 A CN 103722823A CN 201310412248 A CN201310412248 A CN 201310412248A CN 103722823 A CN103722823 A CN 103722823A
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Abstract
The invention discloses a C-C-SiC-ZrC ceramic matrix composite and a preparation method thereof. The C-C-SiC-ZrC ceramic matrix composite comprises C fiber, a C matrix, an SiC matrix and a ZrC matrix, and is characterized in that the SiC matrix exists between a C/C framework and the ZrC matrix. The preparation method comprises the steps as follows: the C fiber is woven or laminated to form an enhancement structure, pyrolytic carbon is deposited with a chemical vapor infiltration method, then the synthesized C/C framework is subjected to high-temperature graphitization, an SiC densified composite is introduced through liquid-phase infiltration and pyrolysis of polycarbosilane, boron-containing phenolic resin is soaked, C is formed through pyrolysis, metal Zr is infiltrated with an infiltration method, and high-temperature heat treatment is performed to obtain the C-C-SiC-ZrC ceramic matrix composite. The C-C-SiC-ZrC ceramic matrix composite has excellent performance including high strength, superhigh temperature resistance, antioxidation, thermal shock resistance and the like.
Description
Technical field
The present invention relates to ceramic matric composite and preparation method thereof, particularly relate to a kind of C/C-SiC-ZrC ceramic matric composite and preparation method thereof.
Technical background
Superelevation velocity of sound aircraft flying for long time, atmosphere reenter, Trans-atmospheric flight and rocket propulsion system have extremely proposed very harsh requirement to high temperature thermal structure material, in these environment, high temperature thermal structure material not only requires to bear the test of 2000 ℃ and even higher temperature, also will bear washing away and the corrosion of oxidizing gas of high velocity air.Existing C/SiC composite and C/C composite can not meet the instructions for use of the parts such as supersonic vehicle nose cone, the leading edge of a wing, long-life engine combustion chamber.It is poor that C/SiC composite is mainly limited to its heat resistance, and the best serviceability temperature of this material is 1300～1650 ℃; Although the serviceability temperature of C/C composite can reach 2800 ℃, the serviceability temperature of its ORC is no more than 1650 ℃.
Document " ZrC based composites and Micro-Structure Analysis, army Zhidan, Liu Yufu, Zhong Wenjing. Southeast China University's journal, 42 (2): 350-354 " introduce a kind of infiltration method and successfully prepared ZrC based composites.Document " number of patent application is 200910227195.2 Chinese invention patent " discloses a kind of C/ZrC ceramic matric composite and preparation method thereof, the method is take prefabricated carbon fiber part as basis, by chemical vapour deposition technique or resin liquid-phase impregnation cracking process, prepare C/C composite, again take the alloy of metallic Z r or Zr as penetration enhancer, by melting, ooze reaction and obtain C/ZrC ceramic matric composite.
The composite that more than invention obtains has the premium properties such as superhigh temperature resistant, resistance to oxidation, resistance to ablation, anti-thermal shock.But owing to easily damaging C fiber melting metallic Z r in infiltrate journey, the mechanical property of material is significantly reduced.
Summary of the invention
Object of the present invention is intended to overcome the defect of prior art, and a kind of high performance composite superhigh temperature resistant, resistance to oxidation, anti-thermal shock and preparation method thereof that has in the situation that not destroying C fiber is provided.
For realizing the technical scheme that object of the present invention adopts, be: a kind of C/C-SiC-ZrC ceramic matric composite is provided, by C fiber, C matrix, SiC matrix and ZrC matrix composition, it is characterized in that SiC matrix is present between C/C skeleton and ZrC matrix.The shared volume fraction of described C fiber is that the shared volume fraction of 45～55%, C matrix is that the shared volume fraction of 5～10%, SiC matrix is that the shared volume fraction of 5～10%, ZrC matrix is 25～45%.
The present invention also provides a kind of preparation method of C/C-SiC-ZrC ceramic matric composite, it is characterized in that comprising the step of following order:
(1) C fibrage or lamination preparation are strengthened to structure, the shared volume fraction of C fiber is 45～55%;
(2) by the method deposition RESEARCH OF PYROCARBON of chemical vapor infiltration, then carry out high temperature graphitization and process synthetic C/C skeleton, 1500～2500 ℃ of temperature;
(3) by the cracking of Polycarbosilane liquid impregnation, introduce SiC density composite again;
(4) then soak and put boron bakelite resin, Pintsch process forms C;
(5) by melting, ooze method metallic cementation zirconium, 1900～2200 ℃ of temperature, reaction generates ZrC;
(6) melt after oozing and carry out high-temperature heat treatment, heat treatment temperature is 1500～1800 ℃;
(7) obtain C/C-SiC-ZrC ceramic matric composite.
Beneficial effect of the present invention: (1), owing to having prepared one deck SiC matrix on C/C skeleton, can provide protection for C fiber, prevents from melting in the back in metallic cementation Zr process the destruction of metallic Z r to matrix; (2) this material have that intensity is high, the premium properties such as superhigh temperature resistant, anti-oxidant, anti-thermal shock; (3) adopt boron bakelite resin dipping pyrolysis meeting to form loose porous RESEARCH OF PYROCARBON, be easy to melting of metallic Z r and ooze.
The specific embodiment
Below in conjunction with specific embodiment, further illustrate the present invention, should understand these embodiment is only not used in and limits the scope of the invention for the present invention is described, after having read the present invention, those skilled in the art all fall within the application's claims to the modification of the various equivalent form of values of the present invention and limit.
Embodiment
A kind of C/C-SiC-ZrC ceramic matric composite, by C fiber, C matrix, SiC matrix and ZrC matrix composition, is characterized in that SiC matrix is present between C/C skeleton and ZrC matrix.The shared volume fraction of described C fiber is that the shared volume fraction of 50%, C matrix is that the shared volume fraction of 10%, SiC matrix is that the shared volume fraction of 10%, ZrC matrix is 30%.
The present invention also provides a kind of preparation method of C/C-SiC-ZrC ceramic matric composite, it is characterized in that comprising the step of following order:
(1) C fibrage or lamination preparation are strengthened to structure, the shared volume fraction of C fiber is 50%;
(2) by the method deposition RESEARCH OF PYROCARBON of chemical vapor infiltration, then carry out high temperature graphitization and process synthetic C/C skeleton, 2000 ℃ of temperature;
(3) by the cracking of Polycarbosilane liquid impregnation, introduce SiC density composite again;
(4) then soak and put boron bakelite resin, Pintsch process forms C;
(5) by melting, ooze method metallic cementation zirconium, 1950 ℃ of temperature, reaction generates ZrC;
(6) melt after oozing and carry out high-temperature heat treatment, heat treatment temperature is 1600 ℃;
(7) obtain C/C-SiC-ZrC ceramic matric composite.
Claims (6)
1. a C/C-SiC-ZrC ceramic matric composite, by C fiber, C matrix, SiC matrix and ZrC matrix composition, is characterized in that SiC matrix is present between C/C skeleton and ZrC matrix.
2. composite according to claim 1, is characterized in that the described shared volume fraction of C fiber is 45～55%.
3. composite according to claim 1, is characterized in that the described shared volume fraction of C matrix is 5～10%.
4. composite according to claim 1, is characterized in that the described shared volume fraction of SiC matrix is 5～10%.
5. composite according to claim 1, is characterized in that the described shared volume fraction of ZrC matrix is 25～45%.
6. a preparation method for C/C-SiC-ZrC ceramic matric composite, is characterized in that comprising the step of following order:
(1) C fibrage or lamination preparation are strengthened to structure, the shared volume fraction of C fiber is 45～55%;
(2) by the method deposition RESEARCH OF PYROCARBON of chemical vapor infiltration, then carry out high temperature graphitization and process synthetic C/C skeleton, 1500～2500 ℃ of temperature;
(3) by the cracking of Polycarbosilane liquid impregnation, introduce SiC density composite again;
(4) then soak and put boron bakelite resin, Pintsch process forms C;
(5) by melting, ooze method metallic cementation zirconium, 1900～2200 ℃ of temperature, reaction generates ZrC;
(6) melt after oozing and carry out high-temperature heat treatment, heat treatment temperature is 1500～1800 ℃;
(7) obtain C/C-SiC-ZrC ceramic matric composite.
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104003746A (en) * | 2014-05-14 | 2014-08-27 | 西北工业大学 | Preparation method of fiber enhanced ceramics base composite material sharp leading edge |
| CN104446580A (en) * | 2014-12-16 | 2015-03-25 | 中国人民解放军国防科学技术大学 | Method for preparing continuous fiber cloth reinforced silica ceramic-based composite material |
| CN104496506A (en) * | 2014-11-21 | 2015-04-08 | 青岛麦特瑞欧新材料技术有限公司 | A C / C-TaC-ZrB2 ceramic matrix composite and preparation method thereof |
| CN104671815A (en) * | 2015-01-19 | 2015-06-03 | 中南大学 | ZrC-TiC modified C/C-SiC composite material and preparation method thereof |
| CN104671814A (en) * | 2015-01-19 | 2015-06-03 | 中南大学 | C/C-SiC-ZrC-TiC composite material and preparation method thereof |
| CN106045550A (en) * | 2016-05-31 | 2016-10-26 | 西北工业大学 | Preparing method of SiC-ZrC gradient modified carbon/carbon composite material |
| CN106830968A (en) * | 2017-02-24 | 2017-06-13 | 中南大学 | A kind of modified C/C composites of compound interface layer and its preparation method and application |
| CN109851381A (en) * | 2019-04-23 | 2019-06-07 | 航天特种材料及工艺技术研究所 | A kind of C/SiC-ZrC-TiC-Cu composite material and preparation method |
| CN110028329A (en) * | 2018-01-11 | 2019-07-19 | 航天特种材料及工艺技术研究所 | A kind of high heat-conducting ceramic based composites and preparation method thereof |
| CN110776320A (en) * | 2019-10-12 | 2020-02-11 | 航天材料及工艺研究所 | C/SiC-ZrC complex phase ceramic matrix composite and preparation method thereof |
| CN111099911A (en) * | 2020-01-02 | 2020-05-05 | 航天特种材料及工艺技术研究所 | Carbon fiber reinforced carbon-silicon carbide-zirconium carbide composite material and preparation method thereof |
| CN111499401A (en) * | 2020-05-13 | 2020-08-07 | 湖南东映碳材料科技有限公司 | High-thermal-conductivity C/SiC composite material and preparation method thereof |
| CN112110739A (en) * | 2020-08-28 | 2020-12-22 | 湖南东映碳材料科技有限公司 | Preparation method of three-dimensional high-thermal-conductivity C/C-ZrC-SiC composite material |
| CN112358307A (en) * | 2020-08-28 | 2021-02-12 | 湖南东映碳材料科技有限公司 | Preparation method of three-dimensional high-thermal-conductivity C/C-SiC-ZrC composite material |
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| CN101709421A (en) * | 2009-12-11 | 2010-05-19 | 中国人民解放军国防科学技术大学 | W-ZrC-SiC metal ceramic and preparation method thereof |
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| CN101709421A (en) * | 2009-12-11 | 2010-05-19 | 中国人民解放军国防科学技术大学 | W-ZrC-SiC metal ceramic and preparation method thereof |
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Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104003746B (en) * | 2014-05-14 | 2015-12-30 | 西北工业大学 | A kind of preparation method of FRCMC sharp leading edge |
| CN104003746A (en) * | 2014-05-14 | 2014-08-27 | 西北工业大学 | Preparation method of fiber enhanced ceramics base composite material sharp leading edge |
| CN104496506A (en) * | 2014-11-21 | 2015-04-08 | 青岛麦特瑞欧新材料技术有限公司 | A C / C-TaC-ZrB2 ceramic matrix composite and preparation method thereof |
| CN104446580A (en) * | 2014-12-16 | 2015-03-25 | 中国人民解放军国防科学技术大学 | Method for preparing continuous fiber cloth reinforced silica ceramic-based composite material |
| CN104671815A (en) * | 2015-01-19 | 2015-06-03 | 中南大学 | ZrC-TiC modified C/C-SiC composite material and preparation method thereof |
| CN104671814A (en) * | 2015-01-19 | 2015-06-03 | 中南大学 | C/C-SiC-ZrC-TiC composite material and preparation method thereof |
| CN104671814B (en) * | 2015-01-19 | 2016-10-26 | 中南大学 | A kind of C/C-SiC-ZrC-TiC composite and preparation method thereof |
| CN106045550A (en) * | 2016-05-31 | 2016-10-26 | 西北工业大学 | Preparing method of SiC-ZrC gradient modified carbon/carbon composite material |
| CN106045550B (en) * | 2016-05-31 | 2018-08-07 | 西北工业大学 | The preparation method of SiC-ZrC gradient modifying carbon/carbon composite materials |
| CN106830968A (en) * | 2017-02-24 | 2017-06-13 | 中南大学 | A kind of modified C/C composites of compound interface layer and its preparation method and application |
| CN110028329B (en) * | 2018-01-11 | 2021-10-29 | 航天特种材料及工艺技术研究所 | High-thermal-conductivity ceramic matrix composite and preparation method thereof |
| CN110028329A (en) * | 2018-01-11 | 2019-07-19 | 航天特种材料及工艺技术研究所 | A kind of high heat-conducting ceramic based composites and preparation method thereof |
| CN109851381A (en) * | 2019-04-23 | 2019-06-07 | 航天特种材料及工艺技术研究所 | A kind of C/SiC-ZrC-TiC-Cu composite material and preparation method |
| CN110776320A (en) * | 2019-10-12 | 2020-02-11 | 航天材料及工艺研究所 | C/SiC-ZrC complex phase ceramic matrix composite and preparation method thereof |
| CN111099911A (en) * | 2020-01-02 | 2020-05-05 | 航天特种材料及工艺技术研究所 | Carbon fiber reinforced carbon-silicon carbide-zirconium carbide composite material and preparation method thereof |
| CN111099911B (en) * | 2020-01-02 | 2020-11-13 | 航天特种材料及工艺技术研究所 | Carbon fiber reinforced carbon-silicon carbide-zirconium carbide composite material and preparation method thereof |
| CN111499401A (en) * | 2020-05-13 | 2020-08-07 | 湖南东映碳材料科技有限公司 | High-thermal-conductivity C/SiC composite material and preparation method thereof |
| CN111499401B (en) * | 2020-05-13 | 2022-05-10 | 湖南东映碳材料科技有限公司 | High-thermal-conductivity C/SiC composite material and preparation method thereof |
| CN112110739A (en) * | 2020-08-28 | 2020-12-22 | 湖南东映碳材料科技有限公司 | Preparation method of three-dimensional high-thermal-conductivity C/C-ZrC-SiC composite material |
| CN112358307A (en) * | 2020-08-28 | 2021-02-12 | 湖南东映碳材料科技有限公司 | Preparation method of three-dimensional high-thermal-conductivity C/C-SiC-ZrC composite material |
| CN112110739B (en) * | 2020-08-28 | 2022-04-22 | 湖南东映碳材料科技有限公司 | Preparation method of three-dimensional high-thermal-conductivity C/C-ZrC-SiC composite material |
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Application publication date: 20140416 |