CN103722822A - SiC/ZrC laminated ceramic matrix composite - Google Patents
SiC/ZrC laminated ceramic matrix composite Download PDFInfo
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- CN103722822A CN103722822A CN201310412232.3A CN201310412232A CN103722822A CN 103722822 A CN103722822 A CN 103722822A CN 201310412232 A CN201310412232 A CN 201310412232A CN 103722822 A CN103722822 A CN 103722822A
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Abstract
A SiC/ZrC laminated ceramic matrix compositen is characterized by comprising a matrix C/C composite, a SiC layer, a C layer and a ZrC layer from inside to outside. The SiC/ZrC ceramic matrix composite can adopt a plate shape, a round pipe, a blind pipe and a cover, the C/C composite is formed by filling a C fiber fabric body with C, the aperture ratio of one side provided with a ceramic coating is 30%-45%, and the aperture ratio of one side without the ceramic coating is 3%-5%. The SiC layer is located between the C/C composite and the C layer, so that inward diffusion of oxygen is prevented effectively. ZrC has high-temperature ablation resistance, and the melting point of generated ZrO2 reaches up to 2,680 DEG C, so that the ablation resistance and the antioxidant capacity of the ceramic matrix composite with the SiC surface layer and the ZrC inner layer are improved.
Description
Technical field
The present invention relates to a kind of ceramic matric composite, particularly relate to the ceramic matric composite that a kind of SiC/ZrC lamination distributes.
Background technology
C/C composite not only has good electrical and thermal conductivity corrosion resistance and heat endurance, but also there is the high-temperature behavior of a series of excellences, as resistance to ablation, good elevated temperature strength conservation rate and thermal shock resistance etc., although be that a kind of desirable lightweight high-temperature structural material C/C composite has good high temperature ablation resistance, yet the application demand in extreme environment (as the Throat Materials for Solid Rocket Motors of Gao Chongzhi ratio, guided missile nose cone etc.), has higher requirement to the anti-oxidant resistance to ablation ability of C/C composite.In addition,, as the desirable lightweight thermal protection struc ture material of aircraft of new generation combustion chamber, nose cone and the leading edge of a wing etc., ablation resistance is also the key factor that determines its reliability, accuracy and operability.Therefore,, for meeting the needs of high-performance Aerospace Products development of new generation, urgently further improve high temperature resistant ablation and the flushing resistance of C/C composite.
In recent years, the countries such as the United States, Russia, method add TaC in C/C composite, ZrC, and the refractory carbides such as HfC improve the resistance to ablation ability of antiscour of C/C composite, to bear higher fuel gas temperature or longer active time.ZrC has high-melting-point (3540 ℃), high strength and high hardness and good high temperature thermal shock resistance energy, is a kind of corrosion-resistant, high-temperature structural material that chemical stability is good.In high-temperature oxidation environment, its oxidation product ZrO
2fusing point high (2770 ℃) not only, and there is relatively low vapour pressure and thermal conductivity.Again or by adding SiC, improve the oxidation resistance of C/C composite, SiC high-temperature oxydation product is SiO
2, this has been known the most oxidation resistant material.
Document adopts liquid-phase vaporization thermal gradient CVI legal system for C/C material in " reaction infiltration method is prepared institutional framework and the performance of C/C-SiC material; Tang Rui; Wang Jiping; Long Chongsheng, Jin Zhihao, Nuclear Power Engineering; 2009.2; the 30th volume, the 1st phase ", by reaction infiltration method, prepare density 2.13～2.28g/cm
3c/C-SiC composite.C/C-SiC composite prepared by reaction infiltration method is comprised of C, SiC, Si, and density is higher, then after graphitization processing, bending strength and compressive strength decrease, but fracture toughness obviously improves.
Document " Yonggang Tong; Shuxin Bai; Hong Zhang; Ke Chen.C/C-SiC composite prepared by Si-10Zr alloyed melt infiltration.2012; 38:3301-3307 " has been prepared containing the C/C-SiC composite of free Si to infiltration Si-Zr alloy in porous C/C precast body by reaction infiltration method, and the Zr in alloy reacts formation ZrC and ZrSi with C and Si in C/C porous body
2, the composite that obtains has higher intensity, good non-oxidizability and Burning corrosion resistance.
Summary of the invention
The technical problem to be solved in the present invention is to overcome the deficiencies in the prior art, and the ceramic matric composite that provides a kind of SiC/ZrC lamination to distribute is characterized in that described ceramic matric composite comprises base material C/C composite, SiC layer, C layer, ZrC layer.Be followed successively by from inside to outside C/C composite, SiC layer, C layer, ZrC layer.C/C composite volume integral number is that 70%～88%, C layer volume fraction is 2～10%, ZrC volume fraction 5%～10%, and SiC volume fraction is 5%～10%.
For the problems referred to above, the invention provides the ceramic matric composite that a kind of SiC/ZrC lamination distributes, described ceramic matric composite is tabular, pipe, blind pipe, cover.Be followed successively by from inside to outside C/C composite, SiC layer, C layer, ZrC layer.SiC has good antioxidation, the SiO of generation
2be the most oxidation resistant known material, SiC is between C/C composite and C layer and ZrC layer, effectively stops the inside diffusion of oxygen, protects C/C composite by external environment, not to be oxidized when high temperature.C layer reacts with melting Zr under high temperature.ZrC layer directly contacts with flame, ablation that ZrC is high temperature resistant, the ZrO of generation
2fusing point is up to 2680 ℃.So by adding SiC and ZrC, the antioxygenic property of composite and anti-ablation ability are well improved.
Composite of the present invention is characterized in that described C/C composite is in C fibrage body, to fill the composite that C forms, and having a STH rate of ceramic coating is 30%～45%, without a STH rate 3%～5% of ceramic coating.
The present invention has advantages of: in (1) composite, not containing free Si, high-temperature behavior is more excellent; (2) interpolation of SiC and ZrC is improved the anti-oxidant and anti-ablation ability of composite; (3) material has good heat, chemical stability; (4) SiC density is 3.21g/cm
3, ZrC density is 6.70g/cm
3, the quality of reduction integral material.
Accompanying drawing explanation
Fig. 1 is the sectional view of the ceramic matric composite of tabular SiC/ZrC lamination distribution
10 is C/C composite; 20 is SiC layer; 30 is C layer; 40 is ZrC layer
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 1
With reference to Fig. 1, the sectional view of the ceramic matric composite that tabular SiC/ZrC lamination distributes, wherein 10 is C/C composite, and 20 is SiC layer, and 30 is C layer, and 40 is ZrC layer.C/C composite volume integral number is that 80%, SiC volume fraction is that 9%, C layer volume fraction is that 5%, ZrC volume fraction is 6%.Ceramic matric composite is tabular, comprises base material C/C composite, SiC layer, and C layer, ZrC layer, is followed successively by C/C composite from inside to outside, SiC layer, C layer, ZrC layer.C/C composite is in C fibrage body, to fill the composite that C forms, and having a STH rate of ceramic coating is 30%, without a STH rate 3% of ceramic coating.
Embodiment 2
With reference to Fig. 1, the sectional view of the ceramic matric composite that tabular SiC/ZrC lamination distributes, wherein 10 is C/C composite, and 20 is SiC layer, and 30 is C layer, and 40 is ZrC layer.C/C composite volume integral number is that 78%, SiC volume fraction is that 10%, C layer volume fraction is that 5%, ZrC volume fraction is 7%.Ceramic matric composite is tabular, comprises base material C/C composite, SiC layer, and C layer, ZrC layer, is followed successively by C/C composite from inside to outside, SiC layer, C layer, ZrC layer.C/C composite is in C fibrage body, to fill the composite that C forms, and having a STH rate of ceramic coating is 40%, without a STH rate 5% of ceramic coating.
Above are only two specific embodiment of the present invention, but design concept of the present invention is not limited to this, allly utilizes this design to carry out the change of unsubstantiality to the present invention, all should belong to the behavior of invading the scope of protection of the invention.In every case be the content that does not depart from technical solution of the present invention, any type of simple modification, equivalent variations and the remodeling above embodiment done according to technical spirit of the present invention, still belong to the protection domain of technical solution of the present invention.
Claims (4)
1. the ceramic matric composite that SiC/ZrC lamination distributes, is characterized in that described ceramic matric composite comprises base material C/C composite, SiC layer, and C layer, ZrC layer, is followed successively by C/C composite from inside to outside, SiC layer, C layer, ZrC layer.
2. the ceramic matric composite that SiC/ZrC lamination according to claim 1 distributes, it is characterized in that, C/C composite volume integral number is that 70%～88%, C layer volume fraction is 2～10%, ZrC volume fraction is that 5%～10%, SiC volume fraction is 5%～10%.
3. composite according to claim 1, is characterized in that described C/C composite is in C fibrage body, to fill the composite that C forms, and having a STH rate of ceramic coating is 30%～45%, without a STH rate 3%～5% of ceramic coating.
4. composite according to claim 1, is characterized in that described composite shape can be tabular, pipe, blind pipe, cover.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310412232.3A CN103722822A (en) | 2013-09-11 | 2013-09-11 | SiC/ZrC laminated ceramic matrix composite |
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| CN201310412232.3A CN103722822A (en) | 2013-09-11 | 2013-09-11 | SiC/ZrC laminated ceramic matrix composite |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112457056A (en) * | 2020-11-30 | 2021-03-09 | 中南大学 | Preparation method of component gradient controllable multi-element ultrahigh-temperature ceramic modified C/C composite material |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102417375A (en) * | 2011-08-18 | 2012-04-18 | 西北工业大学 | Charcoal / charcoal composite material SiC / ZrB2-SiC / SiC coating and preparation method thereof |
-
2013
- 2013-09-11 CN CN201310412232.3A patent/CN103722822A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102417375A (en) * | 2011-08-18 | 2012-04-18 | 西北工业大学 | Charcoal / charcoal composite material SiC / ZrB2-SiC / SiC coating and preparation method thereof |
Non-Patent Citations (4)
| Title |
|---|
| 但奇善等: "反应熔渗法制备C/C-ZrC复合材料的微观结构与烧蚀性能", 《粉末冶金材料科学与工程》 * |
| 冉宏基等: "炭基体结构状态对C/C复合材料抗烧蚀性能的影响", 《炭素》 * |
| 李照谦等: "C/C复合材料ZrC/SiC抗烧蚀涂层性能研究", 《固体火箭技术》 * |
| 李贺军等: "C/C复合材料高温抗氧化涂层的研究现状与展望", 《无机材料学报》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112457056A (en) * | 2020-11-30 | 2021-03-09 | 中南大学 | Preparation method of component gradient controllable multi-element ultrahigh-temperature ceramic modified C/C composite material |
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Application publication date: 20140416 |