CN104529535A - A high-temperature and oxidation-resistant coating material used for C/C-SiC composites - Google Patents
A high-temperature and oxidation-resistant coating material used for C/C-SiC composites Download PDFInfo
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- CN104529535A CN104529535A CN201410597033.9A CN201410597033A CN104529535A CN 104529535 A CN104529535 A CN 104529535A CN 201410597033 A CN201410597033 A CN 201410597033A CN 104529535 A CN104529535 A CN 104529535A
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Abstract
The embodiment of the invention provides a high-temperature and oxidation-resistant coating material used for C/C-SiC composites, and relates to the high-temperature and oxidation-resistant coating materials technology. The coating material is composed of the following chemical compounds in parts by weight: boron phenolic resin 12-14 parts, boron carbide 3-5 parts, oct-zirconium tri-disilicide alloy powder 84-86 parts, silicon carbide powder 1-3 parts, zirconium carbide powder 2-4 parts, uni-zirconium di-boride powder 2-4 parts and absolute ethanol 15-21 parts. The coating material can effectively solve the problem that the high-temperature and oxidation-resistant coating material of the current aircrafts has high costs, complex operation and difficult repair and patch technique. The material is mainly used for high temperature and oxidation-resistant coating.
Description
Technical field
The present invention relates to high-temperature oxidation resistant coating material technology, particularly relate to a kind of high-temperature oxidation resistant coating material for C/SiC matrix material.
Background technology
Aircraft high temperature oxidation position uses C/SiC matrix material usually, as hypersonic aircraft, the leading edge of reentry vehicle and near space vehicle, the high temperature oxidation section positions such as passive heat protection face board and engine chamber, and oxidation resistance temperature is no more than 1650 DEG C time long without the C/SiC matrix material of anti-oxidant modification, when temperature exceedes this temperature, C/SiC matrices of composite material and the loss of fiber rapid oxidation, material mechanical performance sharply declines, therefore, prepare anti-oxidant at C/SiC composite material surface, the coated material of resistance to erosion is the effective means improving matrix material use temperature.At present, generally use chemical vapour deposition and plasma spraying technology for the preparation of the oxidation resistant coating material of spacecraft, coated material is directly coated on aircraft surface through the process such as high temperature, high pressure by these two kinds of processes before vehicle launch, but these two kinds of technology all need to drop into accurate complicated main equipment, cost is high, complicated operation, and coating is once after having prepared, it has been repaired to repair and will become and difficulty, cannot realize even at all.
Summary of the invention
In order to solve the problems of the technologies described above, the embodiment of the present invention provides a kind of high-temperature oxidation resistant coating material for C/SiC matrix material, effectively can solve that current aircraft fire-resistant oxidation resistant coating cost is high, complicated operation, repairs the problem of repairing difficulty.
Concrete technical solution scheme is:
A kind of high-temperature oxidation resistant coating material for C/SiC matrix material, be made up of following compound and weight proportion: 12 to 14 parts, boron phenolic aldehyde, boron carbide 3 to 5 parts, three 84 to 86 parts, silication seven zirconium alloy powder, carborundum powder 1 to 3 part, carbonization zirconium powder 2 to 4 parts, two boronation one zirconium powders 2 to 4 parts, dehydrated alcohol 15 to 21 parts.
The high-temperature oxidation resistant coating material for C/SiC matrix material that the embodiment of the present invention provides, exists in coating on the one hand and generates ZrC, ZrB
2with SiC tri-kinds of ceramic compositions, three defines a more suitable proportional amount, makes the ZrO that it generates under high-temperature oxidation environment
2, SiO
2and ZrSiO
4can form a kind of densification, stablize and have the mixture compared with high bond strength with base material, this mixture can effectively stop penetrating into of oxygen, thus the material of protection inside is not oxidized, therefore has very excellent antioxidant property; On the other hand, boron phenolic aldehyde, norbide (B is contained in this coating
4and Zr C)
7si
3alloy powder three kinds of activeconstituentss, make coating can generate ZrC, ZrB by reaction in－situ in applied at elevated temperature process
2with SiC and its corresponding oxidation products, realize the high-temperature oxidation resistance that it is good, can say that the including high temperature processes needed for coating preparation in use completes, therefore before component uses, the repairing of coating defect does not need to melt down again carries out pyroprocessing, and patching coating is simple and convenient.Therefore, this coated material has a ultrahigh-temperature (> 2000 DEG C) antioxidant property is good, cost is low, preparation is simple and is easy to the remarkable advantage repaired.
Embodiment
To be described in detail to specific embodiments of the invention below.In the following description, the nonrestrictive object for explanation, has set forth detail, to help to understand the present invention all sidedly.But, it will be apparent to those skilled in the art that and also can put into practice the present invention in other embodiment having departed from these details.
The embodiment of the present invention provides a kind of high-temperature oxidation resistant coating material for C/SiC matrix material, be made up of following compound and weight proportion: 12 to 14 parts, boron phenolic aldehyde, boron carbide 3 to 5 parts, three 84 to 86 parts, silication seven zirconium alloy powder, carborundum powder 1 to 3 part, carbonization zirconium powder 2 to 4 parts, two boronation one zirconium powders 2 to 4 parts, dehydrated alcohol 15 to 21 parts.
Several specific embodiment and experimental data are provided below:
Embodiment 1
Take 12 grams of boron phenolic aldehyde, 3/ gram of norbide (B
4c) powder, 84 grams of Zr
7si
3alloy powder, 1 gram of SiC powder, 2 grams of ZrC powder, 2 grams of ZrB
2powder, 15 grams of dehydrated alcohols, mix and obtain high-temperature oxidation resistant coating material.
Embodiment 2
Take 13 grams of boron phenolic aldehyde, 4 grams of norbide (B
4c) powder, 85 grams of Zr
7si
3alloy powder, 2 grams of SiC powder, 3 grams of ZrC powder, 3 grams of ZrB
2powder, 18 grams of dehydrated alcohols, mix and obtain high-temperature oxidation resistant coating material.
Embodiment 3
Take 14 grams of boron phenolic aldehyde, 5 grams of norbide (B
4c) powder, 86 grams of Zr
7si
3alloy powder, 3 grams of SiC powder, 4 grams of ZrC powder, 4 grams of ZrB
2powder, 21 grams of dehydrated alcohols, mix and obtain high-temperature oxidation resistant coating material.
The C/SiC composite material flat plate employing coated material prepared by embodiment 3 is carried out to 600 seconds certification tests of Tt2500K/Pt0.6MPa/Ma0.6 state arc tunnel, after test, line ablation amount only has 0.01mm, embodiment 1, embodiment 2 experimental result are similar, repeat no more herein, there is well high temperature resistant, antioxidant effect.
The high-temperature oxidation resistant coating material for C/SiC matrix material that the embodiment of the present invention provides, exist in coating on the one hand and generate ZrC, ZrB
2with SiC tri-kinds of ceramic compositions, three defines a more suitable proportional amount, makes the ZrO that it generates under high-temperature oxidation environment
2, SiO
2and ZrSiO
4can form a kind of densification, stablize and have the mixture compared with high bond strength with base material, this mixture can effectively stop penetrating into of oxygen, thus the material of protection inside is not oxidized, therefore has very excellent antioxidant property; On the other hand, boron phenolic aldehyde, norbide (B is contained in this coating
4and Zr C)
7si
3alloy powder three kinds of activeconstituentss, make coating can generate ZrC, ZrB by reaction in－situ in applied at elevated temperature process
2with SiC and its corresponding oxidation products, realize the high-temperature oxidation resistance that it is good, can say that the including high temperature processes needed for coating preparation in use completes, therefore before component uses, the repairing of coating defect does not need to melt down again carries out pyroprocessing, and patching coating is simple and convenient.Therefore, this coated material has a ultrahigh-temperature (> 2000 DEG C) antioxidant property is good, cost is low, preparation is simple and is easy to the remarkable advantage repaired.
As above the feature described for a kind of embodiment and/or illustrate can use in one or more other embodiment in same or similar mode, and/or combines with the feature in other embodiment or the feature substituted in other embodiment uses.
Should emphasize, term " comprises/comprises " existence referring to feature, one integral piece, step or assembly when using herein, but does not get rid of one or more further feature, one integral piece, step, assembly or its existence of combining or additional.
Many feature and advantage of these embodiments are clearly according to this detailed description, and therefore claims are intended to all these feature and advantage fallen in its true spirit and scope covering these embodiments.In addition, owing to those skilled in the art will find apparent that a lot of amendment and changing, therefore not embodiments of the invention to be limited to precision architecture that is illustrated and that describe and operation, but can contain and fall into all suitable modifications within the scope of it and equivalent.
The unspecified part of the present invention is known to the skilled person technology.
Claims (1)
1. the high-temperature oxidation resistant coating material for C/SiC matrix material, it is characterized in that, be made up of following compound and weight proportion: 12 to 14 parts, boron phenolic aldehyde, boron carbide 3 to 5 parts, three 84 to 86 parts, silication seven zirconium alloy powder, carborundum powder 1 to 3 part, carbonization zirconium powder 2 to 4 parts, two boronation one zirconium powders 2 to 4 parts, dehydrated alcohol 15 to 21 parts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410597033.9A CN104529535B (en) | 2014-10-31 | 2014-10-31 | A high-temperature and oxidation-resistant coating material used for C/C-SiC composites |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410597033.9A CN104529535B (en) | 2014-10-31 | 2014-10-31 | A high-temperature and oxidation-resistant coating material used for C/C-SiC composites |
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|---|---|
| CN104529535A true CN104529535A (en) | 2015-04-22 |
| CN104529535B CN104529535B (en) | 2017-02-22 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107257451A (en) * | 2017-06-20 | 2017-10-17 | 舟山市普陀金色阳光网络科技有限公司 | A kind of remote security supervising device component |
| CN113402298A (en) * | 2021-07-03 | 2021-09-17 | 西北工业大学 | Repairing agent and repairing method for surface damage of silicon carbide ceramic matrix composite |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1062961A (en) * | 1990-12-26 | 1992-07-22 | 华兴航空机轮公司 | Carbon/carbon compound material brake disc high-temperature oxidation resistant coating |
| CN103540936A (en) * | 2012-07-16 | 2014-01-29 | 苏州宏久航空防热材料科技有限公司 | High temperature resistant antioxidative metal ceramic composite coating and preparation method thereof |
-
2014
- 2014-10-31 CN CN201410597033.9A patent/CN104529535B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1062961A (en) * | 1990-12-26 | 1992-07-22 | 华兴航空机轮公司 | Carbon/carbon compound material brake disc high-temperature oxidation resistant coating |
| CN103540936A (en) * | 2012-07-16 | 2014-01-29 | 苏州宏久航空防热材料科技有限公司 | High temperature resistant antioxidative metal ceramic composite coating and preparation method thereof |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107257451A (en) * | 2017-06-20 | 2017-10-17 | 舟山市普陀金色阳光网络科技有限公司 | A kind of remote security supervising device component |
| CN113402298A (en) * | 2021-07-03 | 2021-09-17 | 西北工业大学 | Repairing agent and repairing method for surface damage of silicon carbide ceramic matrix composite |
| CN113402298B (en) * | 2021-07-03 | 2022-07-26 | 西北工业大学 | Repairing agent and repairing method for surface layer damage of silicon carbide ceramic matrix composite |
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|---|---|
| CN104529535B (en) | 2017-02-22 |
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| CB03 | Change of inventor or designer information |
Inventor after: Pei Yuchen Inventor after: Yu Xinmin Inventor after: Wang Tao Inventor after: Liu Junpeng Inventor after: Sun Tongchen Inventor after: Zhan Wanchu Inventor before: Yu Xinmin Inventor before: Wang Tao Inventor before: Liu Junpeng Inventor before: Sun Tongchen Inventor before: Zhan Wanchu Inventor before: Pei Yuchen |