CN103572191A - Four-phase ceramic matrix high-temperature wearable sealing coating - Google Patents
Four-phase ceramic matrix high-temperature wearable sealing coating Download PDFInfo
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- CN103572191A CN103572191A CN201310540999.4A CN201310540999A CN103572191A CN 103572191 A CN103572191 A CN 103572191A CN 201310540999 A CN201310540999 A CN 201310540999A CN 103572191 A CN103572191 A CN 103572191A
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Abstract
The invention belongs to the technical field of sealing coating materials and particularly relates to a four-phase ceramic matrix high-temperature wearable sealing coating. The coating is composed of four phases including a ceramic matrix phase, a lubricating phase, a pore-forming phase and a high-temperature antioxidant nanophase. A certain proportion of high-temperature antioxidant nanophase is added on the basis of the traditional two-phase or three-phase ceramic matrix high-temperature wearable sealing coating to coat the ceramic matrix phase, so that the four-phase ceramic matrix high-temperature wearable sealing coating with multi-sealing antioxidant barriers is formed. The ceramic matrix phase is ZrO2 with part of stable Dy2O3, the lubricating phase is h-BN, the pore-forming phase is polyester, and the high-temperature antioxidant nanophase is nano SiO2 or Al2O3 or Cr2O3. The four-phase ceramic matrix high-temperature wearable sealing coating has the advantages that the diffusion of oxygen towards the inside of the coating or a coating/matrix interface can be effectively stopped due to the addition of the high-temperature antioxidant nanophase, so that the high temperature stability and interface integrity of the coating are effectively enhanced, and the thermal shock resistance of the wearable sealing coating at high temperature is remarkably improved.
Description
Technical field
The invention belongs to sealing coating material technical field, be specifically related to a kind of four phase ceramics base high-temperature abradable seal coatings.
Background technology
Developing rapidly of aircraft industry proposed more and more higher requirement to aircraft engine, and high thrust, high-level efficiency, low oil consumption have become the overall goal of engine design and manufacture.Yet, in the manufacture and operational process of engine, due to the thermal expansion of engine pack, the thermal distortion of axle and high speed rotating centrifugal force cause the factors such as blade elongation, radius clearance cannot be controlled is zero, reserve always the gap of 2～3mm, and excessive gap will make gas leak in a large number, cause motor efficiency to reduce.Therefore, for reducing the abradable seal coating technology in gap between pneumatic plant, turbine blade tip and casing, just become the important means that improves motor performance.Scraping action by blade tip in operational process to abradable coating, can reduce radial air flow gap effectively, thereby obtains maximum differential pressure, significantly improves motor efficiency and reduces oil consumption.
Conventional abradable seal coating is generally comprised of base phase, lubricated phase and a certain amount of small hole.The Main Function of base phase is as supporter, with guarantee coating self intensity and with the bonding strength of matrix.According to the difference of use temperature, base can be metallographic phase or ceramic phase mutually, and conventional metallographic phase has nickel, aluminium, copper and alloy thereof etc., and conventional ceramic phase is mainly yttria-stabilized zirconia; The Main Function of lubricated phase is abradability and the block resistance that reduces hardness, improves coating, and conventional lubricated phase material has graphite, diatomite, wilkinite, hexagonal boron nitride etc.; Small hole can or add specific pore-creating to form mutually by preparation process, its Main Function is to reduce coating hardness, alleviate coating stress, improve the abradability of coating and make coating have certain heat-insulating capability, conventional pore-creating is the high molecular polymers such as polyester mutually.Researchdevelopment through many decades, at present formed the multiple sealing coating material that is applicable to differing temps, different sites requirement both at home and abroad, comprised that being applicable to 350～650 ℃ take the low temperature abradable seal coating that AlSi-polybenzoate, AlSi-graphite and Ni-graphite is representative; Be applicable to 650～950 ℃ and take middle temperature abradable seal coating that Ni-diatomite, NiCrAl-wilkinite and NiCrAlY-BN be representative and being applicable to more than 1000 ℃ with ZrO
2ceramic base high-temperature abradable seal coating for base phase.Wherein, the multiple abradable seal coating that is applicable to middle low-temperature zone has been realized commodity market and has been used widely.
Current, aircraft engine is to high flow capacity ratio, high thrust-weight ratio and high inlet gas temperature direction development, the working temperature at high-pressure turbine position has reached more than 1100 ℃, this has just proposed more and more higher requirement to the high-temperature behavior of high-pressure turbine outer shroud position abradable seal coating, especially coating is meeting under the condition of suitable abradability energy, and thermal shock resistance and the high-temperature stability of coating under hot conditions just becomes particularly important.At present the more high-temperature abradable seal coating of research is to take ZrO2 as ceramic base phase, by itself and lubricated phase h-BN and mutually compound two-phase or the three-phase ceramic base abradable seal coating of pore-creating phase polyester.Yet, in this coating system, because ZrO2 can not hinder oxygen to the diffusion of coating inside as a kind of oxygen ion conductor, and in coating compared with the existence of multiple hole also for the rapid diffusion of oxygen provides approach.Oxygen can impel the Fast Growth of interface TGO layer and the generation of defect to the rapid diffusion of coating inside and coating/tie-layer interface, thereby cause seal coating, too early generation cracking peels off and lost efficacy.Therefore the ceramic base high-temperature abradable seal coating that, research and development can be born higher temperature and be had superior high-temperature stability and a thermal shock resistance on the basis of existing seal coating system has important theory and using value.
Summary of the invention
The problem that the present invention solves is to provide a kind of four phase ceramics base high-temperature abradable seal coatings, this coating is by hindering oxygen to the diffusion of coating inside and coating/tie-layer interface adding of high-temperature oxidation resistant nanophase, thereby effectively improve the globality of coating and the interfacial state of coating/tack coat, significantly improve high-temperature stability and the thermal shock resistance of ceramic base high-temperature abradable seal coating.
The present invention solves its technical problem by the following technical solutions:
This coating is by ceramic base phase, lubricated phase, pore-creating phase and high-temperature oxidation resistant four phase composites mutually, dusty spray used by mass percentage, wherein: ceramic base is the Dy of 80～90wt% mutually
2o
3partially stabilized ZrO
2, granularity is 30～150 μ m; Lubricated is 0.5～5wt%h-BN mutually; Pore-creating is 4.5～20wt% polyester mutually; High-temperature oxidation resistant is the nanometer SiO of 5wt%～20wt% mutually
2or Al
2o
3or Cr
2o
3, granularity is 5～100nm; Wherein high-temperature oxidation resistant nanophase exists to be coated the structure of micron order ceramic base phase, adopts plasma spraying to prepare coating, and processing parameter is: electric current 500～650A, voltage 60～80V, spray distance 90～120mm, powder feeding rate 25～40g/min, thickness 800～1500 μ m of spray-on coating.
Described ceramic base is Dy mutually
2o
3partially stabilized ZrO
2, Dy wherein
2o
3massfraction be 8～10%, the granularity of powder is 60～100 μ m.
The granularity of described lubricated phase h-BN is 1～3 μ m.
The granularity of described pore-creating phase polyester is 50～80 μ m.
Described high-temperature oxidation resistant phase SiO
2or Al
2o
3or Cr
2o
3granularity be 10～60nm.
Four described phase ceramics base high-temperature abradable seal coatings, before preparation coating, also need be at alloy substrate surface spraying or deposition one deck bond coating, bond coating material is NiCrAlY or NiCoCrAlY, thickness is 100～150 μ m.
Compare with existing high-temperature abrasive sealing coating material, the present invention has following useful technique effect:
First, the Dy that the present invention selects
2o
3partially stabilized ZrO
2compare Y
2o
3stablize ZrO
2there is higher phase stability, be conducive to improve the high-temperature stability of Bulk coat.
Secondly, the 4th phase high-temperature oxidation resistant nanophase that the present invention adds forms clad structure mutually with DySZ ceramic base, thereby in coating, form the anti-oxidant barrier of multiple sealing, hinder oxygen to the diffusion of coating inside and coating/tie-layer interface, effectively improve the globality of coating and the interfacial state of coating/tack coat, the high-temperature stability of ceramic base high-temperature abradable seal coating and thermal shock resistance are significantly improved.
Finally, the 4th phase high-temperature oxidation resistant nanophase that the present invention adds can be brought into play its nano effect, the mechanical property of Bulk coat is improved, thus the thermal stresses that effectively lax coating produces in cold cycling, the thermal shock resistance of raising abradable seal coating.
Accompanying drawing explanation
Fig. 1: four phase ceramics base high-temperature abradable seal coating structural representations of the present invention.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in further detail.
First, by the partially stabilized ZrO2(DySZ of Dy2O3, lower with) ceramic base mutually 1, lubricated mutually 2, the polyester pore-creating of cubic boron nitride (h-BN) mutually 3 and SiO2 or Al2O3 or Cr
2o
3high-temperature oxidation resistant nanophase 4 carries out compound preparation according to predetermined granularity and ratio, and wherein high-temperature oxidation resistant nanophase exists to be coated the structure of micron order ceramic base phase;
Then, before preparing ceramic base abradable seal coating, at alloy substrate 6 surface sprayings or deposition one deck bond coating 5, bond coating material is NiCrAlY or NiCoCrAlY, and thickness is 100～150 μ m;
Finally, adopt plasma spraying to prepare ceramic base abradable seal coating, processing parameter is: electric current 500～650A, voltage 60～80V, spray distance 90～120mm, powder feeding rate 25～40g/min, thickness 800～1500 μ m of spray-on coating.
The Al that is 20～40nm by 10wt% granularity
2o
3powder and DySZ+h-BN+ polyester three-phase can wear away powder mechanically mixing 12 hours, and obtaining four, mutually can to wear away composite powder stand-by.Adopt 46 order emergies to treat sprayed surface and carry out sandblast roughening treatment.Adopt hypersonic flame spraying technique to prepare bond coating at the matrix surface spraying NiCoCrAlY of alligatoring powdered alloy, thickness is about 150 μ m.Adopt plasma spray coating process on bond coating, to spray Doped n m-Al
2o
3four phase ceramics base high-temperature abradable seal coatings, spray parameters is: electric current 620A, voltage 70V, spray distance 120mm, spray-on coating thickness is about 1000 μ m.To DySZ+h-BN+ polyester three-phase abradable seal coating and Doped n m-Al
2o
3four phase abradable seal coatings show the thermal shock resistance test result of 1150 ℃: add 10wt% the 4th phase nanometer Al
2o
3three-phase abradable seal coating was increased to 1900 times by 100～200 times the anti-thermal shock life-span of 1150 ℃.
Embodiment 2
The SiO that is 20nm by 5wt% granularity
2powder and DySZ+h-BN+ polyester three-phase can wear away powder mechanically mixing 8 hours, and obtaining four, mutually can to wear away composite powder stand-by.Adopt 46 order emergies to treat sprayed surface and carry out sandblast roughening treatment.Adopt detonation flame spraying technique to prepare bond coating at the matrix surface spraying NiCrAlY of alligatoring powdered alloy, thickness is about 150 μ m.Adopt plasma spray coating process on bond coating, to spray Doped n m-SiO
2four phase ceramics base high-temperature abradable seal coatings, spray parameters is: electric current 600A, voltage 70V, spray distance 100mm, spray-on coating thickness is about 1000 μ m.To DySZ+h-BN+ polyester three-phase abradable seal coating and Doped n m-Al
2o
3four phase abradable seal coatings show the thermal shock resistance test result of 1150 ℃: add 5wt% the 4th phase nanometer SiO
2three-phase abradable seal coating was increased to 2200 times by 100～200 times the anti-thermal shock life-span of 1150 ℃.
Above content is in conjunction with concrete preferred implementation further description made for the present invention; but protection scope of the present invention is not limited to this; anyly be familiar with those skilled in the art in the technical scope that the present invention discloses; the variation that can expect easily or replacement, within all should being encompassed in protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claims.
Claims (6)
1. four phase ceramics base high-temperature abradable seal coatings, is characterized in that, this coating is by ceramic base phase, lubricated phase, pore-creating phase and high-temperature oxidation resistant four phase composites mutually, dusty spray used by mass percentage, wherein: ceramic base is the Dy of 80～90wt% mutually
2o
3partially stabilized ZrO
2, granularity is 30～150 μ m; Lubricated is 0.5～5wt%h-BN mutually; Pore-creating is 4.5～20wt% polyester mutually; High-temperature oxidation resistant is the nanometer SiO of 5wt%～20wt% mutually
2or Al
2o
3or Cr
2o
3, granularity is 5～100nm; Wherein high-temperature oxidation resistant nanophase exists to be coated the structure of micron order ceramic base phase, adopts plasma spraying to prepare coating, and processing parameter is: electric current 500～650A, voltage 60～80V, spray distance 90～120mm, powder feeding rate 25～40g/min, thickness 800～1500 μ m of spray-on coating.
2. four phase ceramics base high-temperature abradable seal coatings according to claim 1, is characterized in that, described ceramic base is Dy mutually
2o
3partially stabilized ZrO
2, Dy wherein
2o
3massfraction be 8～10%, the granularity of powder is 60～100 μ m.
3. four phase ceramics base high-temperature abradable seal coatings according to claim 1, is characterized in that, the granularity of described lubricated phase h-BN is 1～3 μ m.
4. four phase ceramics base high-temperature abradable seal coatings according to claim 1, is characterized in that, the granularity of described pore-creating phase polyester is 50～80 μ m.
5. four phase ceramics base high-temperature abradable seal coatings according to claim 1, is characterized in that, described high-temperature oxidation resistant phase SiO
2or Al
2o
3or Cr
2o
3granularity be 10～60nm.
6. four phase ceramics base high-temperature abradable seal coatings according to claim 1, it is characterized in that, before preparation four phase ceramics based wearable sealing coatings, also need be at alloy substrate surface spraying or deposition one deck bond coating, described bond coating material is NiCrAlY or NiCoCrAlY, and thickness is 100～150 μ m.
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| CN201310540999.4A CN103572191A (en) | 2013-11-05 | 2013-11-05 | Four-phase ceramic matrix high-temperature wearable sealing coating |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103588469A (en) * | 2013-11-05 | 2014-02-19 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing ceramic-based high temperature abradable seal coating layer based on sol-gel |
| CN104498861A (en) * | 2014-12-17 | 2015-04-08 | 中国航空工业集团公司北京航空制造工程研究所 | Preparation method of sealing coating with high peeling failure resistance |
| CN108950454A (en) * | 2018-08-24 | 2018-12-07 | 中国航空制造技术研究院 | A kind of refractory ceramics base abradable seal coating structure and preparation method thereof |
| CN109023205A (en) * | 2018-08-30 | 2018-12-18 | 昆明理工大学 | A kind of preparation method of thermal spraying thermal barrier coating |
| CN110359968A (en) * | 2019-06-26 | 2019-10-22 | 辽宁福鞍燃气轮机有限公司 | A kind of abradable coating in high temperature combustion environment |
| CN111286690A (en) * | 2020-03-16 | 2020-06-16 | 清华大学 | Thermal spraying powder with ceramic ablation-resistant shell coating lubricating phase and preparation device and method thereof |
| CN112048696A (en) * | 2020-09-10 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Double-layer anti-oxidation bonding bottom layer high-temperature sealing coating and preparation method thereof |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103588469A (en) * | 2013-11-05 | 2014-02-19 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing ceramic-based high temperature abradable seal coating layer based on sol-gel |
| CN104498861A (en) * | 2014-12-17 | 2015-04-08 | 中国航空工业集团公司北京航空制造工程研究所 | Preparation method of sealing coating with high peeling failure resistance |
| CN104498861B (en) * | 2014-12-17 | 2017-02-22 | 中国航空工业集团公司北京航空制造工程研究所 | Preparation method of sealing coating with high peeling failure resistance |
| CN108950454A (en) * | 2018-08-24 | 2018-12-07 | 中国航空制造技术研究院 | A kind of refractory ceramics base abradable seal coating structure and preparation method thereof |
| CN109023205A (en) * | 2018-08-30 | 2018-12-18 | 昆明理工大学 | A kind of preparation method of thermal spraying thermal barrier coating |
| CN110359968A (en) * | 2019-06-26 | 2019-10-22 | 辽宁福鞍燃气轮机有限公司 | A kind of abradable coating in high temperature combustion environment |
| CN111286690A (en) * | 2020-03-16 | 2020-06-16 | 清华大学 | Thermal spraying powder with ceramic ablation-resistant shell coating lubricating phase and preparation device and method thereof |
| CN111286690B (en) * | 2020-03-16 | 2021-06-25 | 清华大学 | Thermal spraying powder with ceramic ablation-resistant shell coating lubricating phase and preparation device and method thereof |
| CN112048696A (en) * | 2020-09-10 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Double-layer anti-oxidation bonding bottom layer high-temperature sealing coating and preparation method thereof |
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Application publication date: 20140212 |