CN104529535B - 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
- Publication number
- CN104529535B CN104529535B CN201410597033.9A CN201410597033A CN104529535B CN 104529535 B CN104529535 B CN 104529535B CN 201410597033 A CN201410597033 A CN 201410597033A CN 104529535 B CN104529535 B CN 104529535B
- Authority
- CN
- China
- Prior art keywords
- parts
- temperature
- coating material
- powder
- resistant coating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Ceramic Products (AREA)
- Laminated Bodies (AREA)
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, more particularly, to a kind of high-temperature oxidation resistant coating material for C/SiC composite.
Background technology
Aircraft high-temperature oxydation position is usually used C/SiC composite, as hypersonic aircraft, reentry vehicle and the leading edge of near space vehicle, the passive high temperature oxidation section such as thermal protection panel and engine chamber position, and without antioxidation modification C/SiC composite long when oxidation resistance temperature be less than 1650 DEG C, when temperature exceedes this temperature, C/SiC matrices of composite material and the loss of fiber rapid oxidation, material mechanical performance drastically declines, therefore, prepare antioxidation in C/SiC composite material surface, the coating material of resistance to erosion is to improve the effective means that composite uses temperature.At present, commonly use chemical vapor deposition and plasma spraying technology prepares the ORC material for spacecraft, coating material is directly coated on aircraft surface through processes such as high temperature, high pressure before vehicle launch by both processes, but both technology are required for putting into the main equipment of accurate complexity, high cost, complex operation, and after the completion of coating is once prepare, it repairs repairing will become and its difficult, or even cannot realize at all.
Content of the invention
In order to solve above-mentioned technical problem, the embodiment of the present invention provides a kind of high-temperature oxidation resistant coating material for C/SiC composite, can effectively solve the problem that current aircraft fire-resistant oxidation resistant coating high cost, complex operation, repairs and repairs difficult problem.
Specifically solving technical scheme is：
A kind of high-temperature oxidation resistant coating material for C/SiC composite, is made up of following compound and weight proportion：12 to 14 parts of boron phenolic, 3 to 5 parts of boron carbide, 84 to 86 parts of three silication, seven zircaloy powder, 1 to 3 part of carborundum powder, 2 to 4 parts of carbonization zirconium powder, 2 to 4 parts of two boronations, one zirconium powder, 15 to 21 parts of dehydrated alcohol.
High-temperature oxidation resistant coating material for C/SiC composite provided in an embodiment of the present invention, exists in one side coating and generates ZrC, ZrB2With tri- kinds of ceramic compositions of SiC, three define an appropriate proportional amount so as under high-temperature oxidation environment generate ZrO2、SiO2And ZrSiO4Can be formed a kind of fine and close, stable and with base material, there is the mixture compared with high bond strength, this mixture can effectively stop penetrating into of oxygen, thus protecting internal material not oxidized, therefore has very excellent antioxygenic property；On the other hand, boron phenolic, boron carbide (B are contained in this coating4) and Zr C7Si3Three kinds of active component of alloyed powder, make coating can generate ZrC, ZrB by reaction in-situ during applied at elevated temperature2With SiC and its corresponding oxidation product, realize its good high-temperature oxidation resistance it may be said that the required including high temperature processes of coating preparation complete in use, therefore before component use, the repairing of coating defect does not need to melt down again and carries out high-temperature process, and patching coating is simple and convenient.Therefore, this coating material has that superhigh temperature (2000 DEG C of ＞) antioxygenic property is good, low cost, preparation is simple and is easy to the remarkable advantage repaired.
Specific embodiment
The specific embodiment of the present invention will be described in detail below.In the following description, the nonrestrictive purpose for explanation, elaborates detail, to help be apparent from the present invention.It is however obvious for a person skilled in the art that it is also possible to putting into practice the present invention in the other embodiments departing from these details.
The embodiment of the present invention provides a kind of high-temperature oxidation resistant coating material for C/SiC composite, is made up of following compound and weight proportion：12 to 14 parts of boron phenolic, 3 to 5 parts of boron carbide, 84 to 86 parts of three silication, seven zircaloy powder, 1 to 3 part of carborundum powder, 2 to 4 parts of carbonization zirconium powder, 2 to 4 parts of two boronations, one zirconium powder, 15 to 21 parts of dehydrated alcohol.
Several specific embodiments and experimental data are provided below：
Embodiment 1
Weigh 12 grams of boron phenolics, 3/ gram of boron carbide (B4C) powder, 84 grams of Zr7Si3Alloyed powder, 1 gram of SiC powder, 2 grams of ZrC powder, 2 grams of ZrB2Powder, 15 grams of dehydrated alcohol, mix homogeneously obtains final product high-temperature oxidation resistant coating material.
Embodiment 2
Weigh 13 grams of boron phenolics, 4 grams of boron carbide (B4C) powder, 85 grams of Zr7Si3Alloyed powder, 2 grams of SiC powder, 3 grams of ZrC powder, 3 grams of ZrB2Powder, 18 grams of dehydrated alcohol, mix homogeneously obtains final product high-temperature oxidation resistant coating material.
Embodiment 3
Weigh 14 grams of boron phenolics, 5 grams of boron carbide (B4C) powder, 86 grams of Zr7Si3Alloyed powder, 3 grams of SiC powder, 4 grams of ZrC powder, 4 grams of ZrB2Powder, 21 grams of dehydrated alcohol, mix homogeneously obtains final product high-temperature oxidation resistant coating material.
600 seconds certification tests of Tt2500K/Pt0.6MPa/Ma0.6 state arc tunnel have been carried out to the C/SiC composite material flat plate of the coating material employing embodiment 3 preparation, after test, line ablation amount only has 0.01mm, embodiment 1, embodiment 2 experimental result are similar to, here is omitted, has high temperature resistant, antioxidant effect well.
High-temperature oxidation resistant coating material for C/SiC composite provided in an embodiment of the present invention, exist in one side coating and generate ZrC, ZrB2With tri- kinds of ceramic compositions of SiC, three define an appropriate proportional amount so as under high-temperature oxidation environment generate ZrO2、SiO2And ZrSiO4Can be formed a kind of fine and close, stable and with base material, there is the mixture compared with high bond strength, this mixture can effectively stop penetrating into of oxygen, thus protecting internal material not oxidized, therefore has very excellent antioxygenic property；On the other hand, boron phenolic, boron carbide (B are contained in this coating4) and Zr C7Si3Three kinds of active component of alloyed powder, make coating can generate ZrC, ZrB by reaction in-situ during applied at elevated temperature2With SiC and its corresponding oxidation product, realize its good high-temperature oxidation resistance it may be said that the required including high temperature processes of coating preparation complete in use, therefore before component use, the repairing of coating defect does not need to melt down again and carries out high-temperature process, and patching coating is simple and convenient.Therefore, this coating material has that superhigh temperature (2000 DEG C of ＞) antioxygenic property is good, low cost, preparation is simple and is easy to the remarkable advantage repaired.
The feature describing as described above for a kind of embodiment and/or illustrating can be used in one or more other embodiments in same or similar mode, and/or combine with the feature in other embodiments or substitute the feature use in other embodiments.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, one integral piece, step or assembly herein when using, but it is not precluded from the presence of one or more further features, one integral piece, step, assembly or a combination thereof or additional.
The many features of these embodiments and advantage are clearly according to this detailed description, and therefore claims are intended to cover all these feature and advantage falling in its true spirit and scope of these embodiments.Further, since those skilled in the art is readily apparent that a lot of modifications and changes, therefore it is not meant to for embodiments of the invention to be limited to precision architecture that is illustrated and describing and operation, but all suitable modifications and the equivalent falling in the range of it can be covered.
Unspecified part of the present invention is known to the skilled person technology.
Claims (1)
1. a kind of high-temperature oxidation resistant coating material for C/SiC composite is it is characterised in that by following
Compound and weight proportion composition：12 to 14 parts of boron phenolic, 3 to 5 parts of boron carbide, three silication seven
84 to 86 parts of zircaloy powder, 1 to 3 part of carborundum powder, 2 to 4 parts of carbonization zirconium powder, two boronation one zirconium powder
2 to 4 parts, 15 to 21 parts of dehydrated alcohol.
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104529535A CN104529535A (en) | 2015-04-22 |
| CN104529535B true CN104529535B (en) | 2017-02-22 |
Family
ID=52845222
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410597033.9A Active CN104529535B (en) | 2014-10-31 | 2014-10-31 | A high-temperature and oxidation-resistant coating material used for C/C-SiC composites |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104529535B (en) |
Families Citing this family (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 |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1025575C (en) * | 1990-12-26 | 1994-08-03 | 华兴航空机轮公司 | High-temp. anti-oxydation coating of carbon/carbon composition braking wheel |
| 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
Also Published As
| Publication number | Publication date |
|---|---|
| CN104529535A (en) | 2015-04-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105967759B (en) | A kind of rare-earth oxide modified Si-Mo-O gradient antioxidant coating and preparation method | |
| Vinci et al. | Oxidation behaviour of a continuous carbon fibre reinforced ZrB2–SiC composite | |
| US9126873B2 (en) | Process for producing a self-healing layer on a part made of a C/C composite | |
| EP3094490B1 (en) | Silicon oxycarbide environmental barrier coating | |
| US7638178B2 (en) | Protective coating for ceramic components | |
| Jiang et al. | Oxidation and ablation protection of multiphase Hf0. 5Ta0. 5B2-SiC-Si coating for graphite prepared by dipping-pyrolysis and reactive infiltration of gaseous silicon | |
| US8475945B2 (en) | Composite article including silicon oxycarbide layer | |
| ZhongLiu et al. | Thermal cycling behavior and oxidation resistance of SiC whisker-toughened-mullite/SiC coated carbon/carbon composites in burner rig tests | |
| CN102757260B (en) | Repairing method of ceramic-based composite material coating with utilization temperature of being more than or equal to 1400 DEG C | |
| CN105623506B (en) | Ceramic base composite coating and preparation method thereof | |
| Wang et al. | Improving oxidation resistance of MoSi2 coating by reinforced with Al2O3 whiskers | |
| WO2021001466A1 (en) | High emissivity cerium oxide coating | |
| CN103764594A (en) | Ultra-refractory material that is stable in a wet environment and process for manufacturing same | |
| US20220081750A1 (en) | Silicon oxycarbide-based environmental barrier coating | |
| CN104529535B (en) | A high-temperature and oxidation-resistant coating material used for C/C-SiC composites | |
| CN107201171A (en) | A kind of boron bakelite resin/epoxy modified silicone resin coating of resistance to ablation protection and preparation method thereof | |
| Shirani et al. | ZrB2-SiC-WC coating with SiC diffusion bond coat on graphite by spark plasma sintering process | |
| CN108947588A (en) | A kind of C/SiC composite material and the antioxidant coating for the material and preparation method thereof | |
| CN106866162A (en) | A kind of coating material for carbon fiber reinforced silicon carbide matrix composite | |
| Li et al. | The anti-oxidation behavior and infrared emissivity property of SiC/ZrSiO 4–SiO 2 coating | |
| Wang et al. | Microstructure and ablation properties of SiC/ZrB2–SiC/ZrB2/SiC multilayer coating on graphite | |
| Zou et al. | Thermal properties, oxidation corrosion behavior, and the in situ ceramization mechanism of SiB6@ BPR/HF composites under high-temperature corrosion | |
| Jiang et al. | Oxidation and ablation protection of graphite materials by monolayer MoSi2–CrSi2–SiC–Si multiphase coating | |
| Li et al. | Mo–Si–Al–C multiphase oxidation protective coating for carbon/carbon composites | |
| US11472750B2 (en) | Barrier coating resin formulations, and related methods |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information | ||
| 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 |