CN105886994B - A method of preparing high-performance level thermal barrier coating system - Google Patents
A method of preparing high-performance level thermal barrier coating system Download PDFInfo
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- CN105886994B CN105886994B CN201610228040.0A CN201610228040A CN105886994B CN 105886994 B CN105886994 B CN 105886994B CN 201610228040 A CN201610228040 A CN 201610228040A CN 105886994 B CN105886994 B CN 105886994B
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/18—After-treatment
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Coating By Spraying Or Casting (AREA)
Abstract
The present invention discloses a kind of method preparing high-performance level thermal barrier coating system, includes the following steps：The first step prepares alloy adhesive linkage in matrix surface；Second step carries out surface modification treatment using supersonic speed plasma jet to alloy adhesive linkage；Third walks, and alloy bonding layer surface after modification prepares single-layer or multi-layer ceramic coating, obtains thermal barrier coating system.The present invention obtains the level thermal barrier coating system being made of high temperature alloy adhesive linkage and ceramic surface using internal powder conveying supersonic speed air plasma spraying method, compared with traditional thermal barrier preparation method, efficiently avoid the problems such as coating preparation efficiency is low, quality lot stability is poor because caused by being converted technique, the high-temperature service service life to improving thermal barrier coating has important application value, it has broad application prospects in the national defence sophisticated industry such as aero-turbine and heavy duty gas turbine, there is huge economic and social benefit.
Description
Technical field
The present invention relates to Thermal Barrier Coating Technologies field, more particularly to a kind of side preparing high-performance level thermal barrier coating system
Method.
Background technology
There is an urgent need for a kind of high-performance thermal barrier coating systems to reduce alloy substrate for aero-turbine and heavy duty gas turbine
Temperature is to ensure its normal use under the high temperature conditions.Thermal barrier coating system includes alloy adhesive linkage, ceramic layer and by closing
The thermally grown oxide layer (TGOs) of golden adhesive linkage oxidation and formation.This thermal growth oxide is in early growth period mainly with oxidation
Aluminium (Al2O3) based on, fine and close Al2O3Film is to preventing the further oxidation of alloy coat from playing certain positive effect.But
Al2O3Film is while forming, some other oxides such as chromium oxide (Cr2O3), nickel oxide (NiO) and spinelle
(NiAl2O4、NiCr2O4、CoAl2O4、CoCr2O4) etc. also simultaneously grown.These oxides and Al2O3Compared to higher
The speed of growth, cause to generate a large amount of growth stress in TGOs/ ceramic layers interface, especially when TGOs reaches certain thickness
When, the germinating and extension of crackle are caused inside above-mentioned interface and TGOs, eventually leads to the peeling of ceramic surface, i.e. thermal barrier coating
Failure.At present the common preparation process of alloy adhesive linkage have vacuum plasma spray coating (Vacuum Plasma Spraying,
VPS), low-voltage plasma spraying (Low-Pressure Plasma Spraying, LPPS), supersonic flame spraying (High
Velocity Oxygen Fuel, HVOF), cold air power spraying and coating (Cold Gas Dynamic Spraying, CGDS or CS).
And the preparation process of ceramic layer is then electro beam physics vapour deposition (Electron Beam Physical Vapor
Deposition, EB-PVD) and two kinds of air plasma spraying (Air Plasma Spraying, APS).There it can be seen that
Existing thermal barrier coating system needs differently to prepare alloy adhesive linkage and ceramic layer, this will necessarily be related to turning because of technique
The problem of production efficiency changed and brought reduces, is unfavorable for continuous production.It is viscous also to easily lead to alloy for the conversion of spraying process simultaneously
Connect layer surface pollution.
Invention content
It is steady to obtain quality the purpose of the present invention is to provide a kind of method preparing high-performance level thermal barrier coating system
Fixed thermal barrier coating system reliable, high temperature oxidation resistance is excellent, thermal shock resistance is excellent, by designing different no cofusing particles
It the alloy adhesive linkage of ratio and surface modification treatment is carried out to alloy adhesive linkage improves its high temperature oxidation resistance, finally changing
Property after alloy bonding layer surface deposition single layer or double-layer ceramic layer to form complete thermal barrier coating system.
To achieve the above objectives, the technical solution adopted by the present invention is that：
A method of high-performance level thermal barrier coating system is prepared, is included the following steps：The first step, in matrix surface system
Standby alloy adhesive linkage；Second step carries out surface modification treatment using supersonic speed plasma jet to alloy adhesive linkage；Third
Step, alloy bonding layer surface after modification prepare single-layer or multi-layer ceramic coating, obtain thermal barrier coating system.
Further, the first step specifically includes following steps：It is sprayed using internal powder conveying supersonic speed air plasma spraying spray gun
Alloy adhesive linkage is applied, power regulation is to 25-70kW in spraying process, spray distance ranging from 80-140mm, is controlled in spraying process
Alloyage flying speed of partcles ranging from 350-550m/s, temperature range are 1900-2600 DEG C, obtain no cofusing particle content in 5-
60% alloy adhesive linkage；The alloy that internal powder conveying supersonic speed air plasma spraying spray gun is sprayed is bonded layer material
CoNiCrAlY, NiCoCrAlY or NiCrAlY.
Further, second step specifically includes following steps：Existed using internal powder conveying supersonic speed air plasma spraying spray gun
Continuous scanning, power 30-100kW are carried out to established alloy bonding layer surface under no powder feeding state, distance is 70-
150mm, number are 10-50 times.
Further, in second step using during internal powder conveying supersonic speed air plasma spraying high temperature, high speed it is super
Velocity of sound plasma jet is by alloy adhesive linkage surface melting and forms fine and close oxide skin(coating), while will be adhered to alloy bonding
The no cofusing particle of layer surface removes.
Further, the alloy bonding layer surface in third step after modification prepares ceramic layer, and ceramic layer is：Yttrium oxide portion
Divide stable zirconium dioxide single-layer ceramic layer, YSZ- lanthanum cerate double-layer ceramic layers or YSZ- lanthanum magnalium oxygen (LaMA) double-layer ceramic
Layer.
Further, power when ceramic layer is prepared in third step using internal powder conveying supersonic speed air plasma spraying method
Select the control ceramic particle flying speed ranging from 340- in 30-80kW, spray distance ranging from 80-120mm, spraying process
800m/s, temperature range are 2000-3600 DEG C.
Compared with the existing technology, the invention has the advantages that：The method according to the invention, can high-efficiency and continuous deposition
The thermal barrier coating system that stable quality is reliable, high temperature oxidation resistance is excellent, thermal shock resistance is excellent starts in aeroturbine
It has broad application prospects in the national defence sophisticated industry such as machine and heavy duty gas turbine.
Description of the drawings
Fig. 1 is the alloy adhesive linkage section erosion profile that 1 no cofusing particle content of embodiment is 35%；
Fig. 2 is that embodiment 1 sprays state alloy adhesive linkage surface topography；
Fig. 3 is the 1 modified alloy adhesive linkage surface topography in supersonic speed plasma jet surface of embodiment；
Fig. 4 is 1 thermal barrier coating system section pattern of embodiment；
Fig. 5 is the oxidizing dynamics curve at 1100 DEG C of 1 coating of embodiment；
Fig. 6 is the surface topography under 1100 DEG C of 1 coating of embodiment, different thermal shock numbers.
Specific implementation mode
Below in conjunction with specific embodiment, the present invention is described in further detail.
Embodiment 1
A method of high-performance level thermal barrier coating system is prepared, uses CoNiCrAlY alloy powders for raw material, is used
Internal powder conveying supersonic speed air plasma spraying spray gun spraying alloy adhesive linkage, power regulation is to 54.8kW, spraying in spraying process
Distance is 110mm, using in high-speed photography and dual wavelength radiation intensity rate method plasma jet stream in spraying process
Alloy powder flying speed of partcles and temperature carry out on-line measurement, and obtained flying speed of partcles is 420ms-1, temperature is
2330 DEG C, scanning electron microscopic observation is carried out after corroding to alloy adhesive linkage, obtained coating profile pattern is as shown in Figure 1, surface shape
Looks are as shown in Figure 2.Image processing software is used to analyze in coating no cofusing particle content as 35%.It is penetrated using supersonic speed plasma
Stream handles alloy adhesive linkage surface (power 50kW, distance are 90mm, laser heating 50 times), treated coating table
Face pattern adds shown in Fig. 3, and comparison diagram 2 and Fig. 3 are it can be found that supersonic speed plasma jet can remove spraying state alloy bonding
The no cofusing particle of layer surface adherency, improves the surface smoothness of alloy adhesive linkage.In the modified alloyed layer spray in surface
YSZ ceramic layers are applied, constitute complete thermal barrier coating system, sectional view is as shown in Figure 4.1100 DEG C of high temperature are carried out to coating system
Oxidation experiment and thermal shock experiment, it is as a result as shown in Figures 5 and 6 respectively, therefrom it can be found that changing to alloy adhesive linkage surface
After property, the high temperature oxidation resistance of coating can be significantly improved, it is relatively low to show as its increasing weight of oxidation, the thermal barrier coating body
Tie up to 1100 DEG C heat preservation 5 points after hardening, 846 rear surfaces only have 9.3% area peel off, with long time without surface modification treatment
Coating is compared and shows good thermal shock resistance.
1 alloy adhesive linkage spray parameters of table and corresponding flying speed of partcles, surface temperature and no cofusing particle content
Internal powder conveying supersonic speed air plasma spraying is a kind of novel plasma spraying technology, and basic principle is to utilize spray
Gun system is elongated electric arc by mechanical compression, hot compression and magnetic compression, and then obtains the supersonic speed with very high energies density
Plasma jet, and make to enter the fusing of the raw material powder particle heated fast in jet stream and hit matrix and form coating.Profit
With internal powder conveying supersonic speed atmospheric plasma spraying technology deposit alloy adhesive linkage and ceramic layer, technique conversion is not needed, to pole
The earth improves spray efficiency.At the same time, at this stage alloy adhesive linkage be surface-treated and mostly use heating in vacuum greatly
Method, it is therefore an objective to which its surface forms the oxide skin(coating) based on aluminium oxide, to reduce alloy adhesive linkage in high-temperature service condition
Under oxidation rate.Using vacuum processing, accessory size will be limited by vacuum chamber, greatly limit the application of this method.
Using supersonic speed plasma jet high temperature and high speed feature, surface modification treatment is carried out to alloy adhesive linkage in atmospheric conditions,
While so that its surface is formed oxide, and the no cofusing particle of surface adhesion can be removed.In short, big using internal powder conveying supersonic speed
Gas plasma spraying can with deposit alloy adhesive linkage, to alloy adhesive linkage surface be modified processing and prepare ceramic layer, can connect
Continuous metaplasia production, coating quality are reliable and stable.
Through the invention, finally acquisition stable quality is reliable, high temperature oxidation resistance is excellent, thermal shock resistance is excellent
Thermal barrier coating system, before there is wide application in the national defence sophisticated industry such as aero-turbine and heavy duty gas turbine
Scape.
Claims (4)
1. a kind of method preparing high-performance level thermal barrier coating system, which is characterized in that include the following steps：
The first step prepares alloy adhesive linkage using internal powder conveying supersonic speed air plasma spraying spray gun in matrix surface；
Second step carries out surface modification treatment using supersonic speed plasma jet to alloy adhesive linkage；
Third walks, and alloy bonding layer surface after modification prepares single-layer or multi-layer ceramic coating, obtains complete thermal boundary
Coating system；
The first step specifically includes following steps：Using internal powder conveying supersonic speed air plasma spraying spray gun spraying alloy adhesive linkage,
Power regulation is to 25-70kW in spraying process, spray distance ranging from 80-140mm, control alloy particle flight in spraying process
Velocity interval is 350-550m/s, and temperature range is 1900-2600 DEG C, and the alloy for obtaining no cofusing particle content in 5-60% is bonded
Layer；The alloy bonding layer material that internal powder conveying supersonic speed air plasma spraying spray gun is sprayed is CoNiCrAlY, NiCoCrAlY
Or NiCrAlY；
Power selection when using internal powder conveying supersonic speed air plasma spraying method to prepare ceramic layer in third step is in 30-
80kW, spray distance ranging from 80-120mm control ceramic particle flying speed ranging from 340-800m/s, temperature in spraying process
Ranging from 2000-3600 DEG C of degree.
2. a kind of method preparing high-performance level thermal barrier coating system according to claim 1, which is characterized in that second
Step specifically includes following steps：Using internal powder conveying supersonic speed air plasma spraying spray gun to established under no powder feeding state
Alloy is bonded layer surface and carries out continuous scanning, power 30-100kW, and distance is 70-150mm, and number is 10-50 times.
3. a kind of method preparing high-performance level thermal barrier coating system according to claim 2, which is characterized in that second
Using the supersonic speed plasma jet of high temperature, high speed during internal powder conveying supersonic speed air plasma spraying by alloy in step
Adhesive linkage surface melting simultaneously forms fine and close oxide skin(coating), while the no cofusing particle for being adhered to alloy bonding layer surface being removed.
4. a kind of method preparing high-performance level thermal barrier coating system according to claim 1, which is characterized in that third
Alloy bonding layer surface in step after modification prepares ceramic layer, and ceramic layer is：Aoxidize yttrium partially stabilized zirconium dioxide single layer
Ceramic layer, YSZ- lanthanum cerate double-layer ceramic layers or YSZ- lanthanum magnalium oxygen (LaMA) double-layer ceramic layer.
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20190032189A1 (en) * | 2017-07-31 | 2019-01-31 | General Electric Company | Adhesion of thermal spray coatings over a smooth surface |
| CN108060384B (en) * | 2017-12-12 | 2020-04-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Double-ceramic-layer thermal barrier coating system and composite preparation process thereof |
| CN108728786A (en) * | 2018-04-11 | 2018-11-02 | 中国人民解放军陆军装甲兵学院 | A method of preparing silumin coating |
| CN108950461A (en) * | 2018-06-30 | 2018-12-07 | 黑龙江科技大学 | A kind of preparation method suitable for iron base high-temperature alloy surface thermal barrier coating |
| CN110541138A (en) * | 2019-10-09 | 2019-12-06 | 西安热工研究院有限公司 | Interlayer metallurgical bonding thermal spraying coating for boiler heating surface and preparation method |
| CN111962005A (en) * | 2020-09-09 | 2020-11-20 | 上海电气集团股份有限公司 | Preparation method of thermal barrier coating |
| CN114438435B (en) * | 2022-01-24 | 2023-08-25 | 西南科技大学 | Thermal barrier coating and preparation method thereof |
| CN115354268A (en) * | 2022-08-31 | 2022-11-18 | 西安航空学院 | Method for involuting Jin Nianjie layer surface modification by supersonic plasma jet |
| CN116254496B (en) * | 2022-09-09 | 2023-12-15 | 北京金轮坤天特种机械有限公司 | Preparation method of thermal barrier coating |
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| CN103789715A (en) * | 2014-02-10 | 2014-05-14 | 江苏大学 | Anti-oxidization thermal barrier coating material with long service life and preparation method thereof |
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| CN103789715A (en) * | 2014-02-10 | 2014-05-14 | 江苏大学 | Anti-oxidization thermal barrier coating material with long service life and preparation method thereof |
Non-Patent Citations (1)
| Title |
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| 热障涂层体系中MCrAlY 合金粘接层结构设计及高温氧化行为研究;唐健江等;《热喷涂技术》;20150630;第7卷(第2期);第23页右栏第2-15行，第24页左栏第7-22行，第31页倒数第1行至第32页第12行，以及第25页表2和表4 * |
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