CN105839057B - A kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure - Google Patents
A kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure Download PDFInfo
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- CN105839057B CN105839057B CN201610224706.5A CN201610224706A CN105839057B CN 105839057 B CN105839057 B CN 105839057B CN 201610224706 A CN201610224706 A CN 201610224706A CN 105839057 B CN105839057 B CN 105839057B
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- thermal barrier
- barrier coating
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- large strain
- strain tolerance
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/24—Vacuum evaporation
- C23C14/28—Vacuum evaporation by wave energy or particle radiation
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/08—Oxides
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/08—Oxides
- C23C14/083—Oxides of refractory metals or yttrium
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- Physical Vapour Deposition (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The present invention discloses a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure, which is presented the columnar structure with intercolumniation hole to have Large strain tolerance.This preparation method is at 10 5000Pa of chamber pressure, using the mixing line containing monatomic and/or elementide coating material particles as sedimentary origin, surface temperature maintains or keeps the temperature 0.2 times or more in coating material fusing point and is placed on intermittent more than the workpiece progress of the free path 2 times or more of mixing line coating material particulate minimum and/or successional deposition, and the thermal barrier coating of the Large strain tolerance columnar structure with intercolumniation hole is prepared.Compared with traditional thermal barrier, thermal barrier coating prepared by the present invention has the Large strain tolerance columnar structure with intercolumniation hole, can be released effectively the stress generated by thermal mismatching, strain tolerance is improved, to improve the service life of thermal barrier coating.
Description
Technical field
The invention belongs to Material Fields, and in particular to a kind of preparation method of thermal barrier coating.
Background technology
With the fast development of the industries such as aerospace, energy source and power, in today that science increasingly develops, these industries pair
The requirement of gas turbine is increasingly strict, it is desirable that its component can long service at higher operating temperatures, be provided simultaneously with it is corrosion-resistant,
The characteristics such as wear-resistant more directly require that turbine blade of gas turbine needs better high-temperature stability.Currently, improving combustion gas
The method of the operating temperature of turbine blade mainly has：Blade interior air-flow cooling technology, air film cooling technology and thermal barrier coating.
Thermal barrier coating has the good characteristic of low longitudinal thermal conductivity, high temperature resistance, can delay and obstruct combustion gas heat flow
It is conducted to high temperature alloy matrix, high temperature insulating is carried out to gas turbine blades, to reduce the operating temperature of blade.Currently, low
The utilization of the thermal barrier coating of thermal conductivity can improve fuel gas temperature, that is, reduce high-temperature alloy blades surface temperature, and then improve combustion
The thermal efficiency of gas-turbine, and extend the service life of gas turbine blades.
Currently, the main preparation process of thermal barrier coating have it is following two：Air plasma spraying and electron beam physical vapor
Deposition.Thermal barrier coating prepared by air plasma spraying has a large amount of interlayer holes, and longitudinal thermal conductivity is relatively low, and manufacturing cost is low,
But thermal stress and thermal strain energy force difference, service life are shorter.And electro beam physics vapour deposition prepare thermal barrier coating have it is good
The good columnar structure with intercolumniation hole, thermal stress and thermal strain ability to bear are good, have Large strain tolerance, service life
It is long.Studies have shown that the Large strain tolerance columnar structure that thermal barrier coating has intercolumniation hole is the coating thermal strain ability to bear good longevity
Order the main reason for long.
However, thermal barrier coating prepared by electro beam physics vapour deposition can only be tried out in flat flat work pieces, Wu Faying
For complicated workpiece.
Invention content
The purpose of the present invention is to provide a kind of preparation methods of the thermal barrier coating of Large strain tolerance columnar structure, can make
It obtains thermal barrier coating and has the Large strain tolerance columnar structure with intercolumniation hole, so as to increase substantially the use of thermal barrier coating
Service life.
In order to achieve the above objectives, the technical solution adopted by the present invention is：
A kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure, using containing monatomic and/or atomic group
The mixing line of coating material particles of cluster carries out interval in the workpiece surface that temperature is 0.2 times of sprayed on material fusing point or more
Property and/or successional deposition, workpiece surface obtain Large strain tolerance columnar structure thermal barrier coating.
Further, following steps are specifically included：
(1) by workpiece place in the deposition chamber, workpiece with away from spacing mix between line starting point be more than mix line
The 2 times or more of the minimum free path of coating material particulate；
(2) it is 10-5000Pa by deposition chambers air pressure adjustment；
(3) high energy beam current heating evaporation coating material powder is utilized to form corpuscullar flow, the coating material in corpuscullar flow
Particulate contains monatomic and/or elementide, and mix line with plasma (orifice) gas or carrier gas composition carries out interval to workpiece surface
Property or it is successional deposition obtain Large strain tolerance columnar structure thermal barrier coating.
Further, high energy beam current evaporates coating material to form coating material particles subflow, corpuscullar flow institute
Including it is monatomic include that narrow sense is monatomic, unimolecule or single ion, the elementide that the particulate is included include narrow
Adopted elementide, molecular cluster or ion cluster.
Further, high energy beam current evaporates powder raw material to form corpuscullar flow, monatomic sedimentation unit in corpuscullar flow
Percent by volume is 50%-99%, and elementide percent by volume is 1%-50%.
Further, coating material particles mixed in line has Characteristics of Flow Around jointly with plasma (orifice) gas or carrier gas,
When encountering pattern and blocking, gets around blocking position by the characteristic and deposited.
Further, when intermittent deposition, mixing line is swept on sample so that coating material particles sinks
Product can carry out in 0-180 ° of all angles, and random deposition forms surface undulation.
Further, the workpiece is the high temperature alloy matrix with adhesive layer.
Further, the coating material is YSZ powder, LZO powder, CeO2Powder or SZO powder.
Prepared by a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure, include the following steps：It will carry
The high temperature alloy matrix of adhesive layer is placed on away from mixing line starting point 950mm, and chamber pressure is controlled in 150Pa, to high temperature
Alloy surface is previously heated to 960 DEG C, and yttrium partially stabilized oxygen will be aoxidized by then utilizing power to be the high energy plasma line of 127kW
Change zirconium powder heating evaporation and form the corpuscullar flow containing zirconium ion, oxonium ion, zirconium oxonium ion and its cluster, with plasma gas Ar
Gas and He gas constitute mixing line and carry out continous way deposition to high temperature alloy matrix together, and sedimentation time is that 20min acquisition height is answered
Become the thermal barrier coating of tolerance columnar structure；Wherein plasma gas Ar gas and He gas air inflows is respectively 35NLPM and 60NLPM.
Compared with the existing technology, the invention has the advantages that：
The preparation method of the thermal barrier coating of Large strain tolerance columnar structure provided by the present invention is different from electro beam physics
Both regard linear process for vapor deposition and plasma spraying, this preparation method belongs to the sedimentation type of macroscopical non-line-of-sight, mix
Coating material particles closed in line has Characteristics of Flow Around jointly with plasma (orifice) gas or carrier gas, to have around plating characteristic,
When encountering pattern and blocking, gets around blocking position by the characteristic and deposited, macroscopically belonging to non-line-of-sight deposition.With good
It is good around plating characteristic so as to uniformly preparing high-performance thermal barrier coating in complex-shaped workpiece surface.By adjusting technique ginseng
Number, to control the free path of sedimentation unit, causes effective occlusion effect, to which Large strain tolerance columnar structure be prepared
Thermal barrier coating is of great significance to improving the thermal barrier coating service life.
Occlusion effect needed for the thermal barrier coating of formation Large strain tolerance columnar structure comes from coarse at nearly matrix surface
The coarse fluctuating on scale is spent, i.e. the deposition on nearly Substrate Surface Roughness scale is to regard linear deposit.
Description of the drawings
Fig. 1 is the surface texture figure of thermal barrier coating made from embodiment 1, wherein Fig. 1 (a), Fig. 1 (b), Fig. 1 (c), Fig. 1
(d) be respectively same sample from low power to high power under surface texture stereoscan photograph；
Fig. 2 is the fractography figure of thermal barrier coating made from embodiment 1, and wherein Fig. 2 (a) is section of the sample under low power
Tissue scanning electromicroscopic photograph, Fig. 2 (b) are fractography stereoscan photograph of the sample under high power；
Fig. 3 be polishing fractography Fig. 3, wherein Fig. 3 (a) of thermal barrier coating made from embodiment 1, Fig. 3 (b), Fig. 3 (c),
Fig. 3 (d) be respectively same sample from low power to high power under polishing fractography stereoscan photograph.
Specific implementation mode
Large strain tolerance column prepared by a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure of the present invention
The thermal barrier coating of shape tissue has the columnar structure with intercolumniation hole formed by heat barrier coat material powder, is applied in thermal boundary
During layer use, it can be released effectively the stress generated by thermal mismatching, strain tolerance is improved, to improve making for thermal barrier coating
Use the service life.
It is the specific embodiment of the preparation method of the thermal barrier coating for the Large strain tolerance columnar structure that the present invention provides below,
It should be noted that these embodiments are used for it will be understood by those skilled in the art that the present invention, but the invention is not limited in these
Embodiment.
Embodiment 1
Prepared by a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure, include the following steps：It will carry
The high temperature alloy matrix of adhesive layer is placed on away from mixing line starting point 950mm, and chamber pressure is controlled in 150Pa, to high temperature
Alloy surface is previously heated to 960 DEG C, and yttrium partially stabilized oxygen will be aoxidized by then utilizing power to be the high energy plasma line of 127kW
Change zirconium (YSZ) powder (M6700, ZrO2/Y2O3=87/13, -22+5 μm of powder size) heating evaporation formed containing zirconium ion, oxygen from
The corpuscullar flow of son, zirconium oxonium ion and its cluster constitutes mixing line together with plasma gas Ar gas and He gas.Its it is medium from
Sub- gas Ar gas and He gas air inflows are respectively 35NLPM and 60NLPM.Line carries out continous way deposition to high temperature alloy matrix,
Sedimentation time is 20min.
The surface texture of thermal barrier coating made from embodiment 1 is as shown in Figure 1, wherein (a) (b) (c) (d) is respectively same examination
Sample from low power to high power under surface texture stereoscan photograph.By Fig. 1 (a) (b) (c) (d) it is found that thermal barrier coating surface is contained
A large amount of dells.The fractography of thermal barrier coating obtained is as shown in Fig. 2, wherein (a) is that fractography of the sample under low power is swept
Electromicroscopic photograph is retouched, is (b) fractography stereoscan photograph of the sample under high power.It is found that thermal boundary obtained from Fig. 2 (a)
The columnar structure with intercolumniation hole is presented in coating, has Large strain tolerance.It is found that coating material in corpuscullar flow in Fig. 2 (b)
Material particulate contains larger elementide.The polishing fractography of thermal barrier coating obtained is as shown in figure 3, wherein (a) (b)
(c) (d) be respectively same sample from low power to high power under polishing fractography stereoscan photograph.From Fig. 3 (a) it is found that
The columnar structure with intercolumniation hole is presented in thermal barrier coating obtained, has Large strain tolerance.It is found that particle in Fig. 3 (c) (d)
Coating material particles in subflow contains larger elementide.
Embodiment 2
Prepared by a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure, include the following steps：It will carry
The high temperature alloy matrix of adhesive layer is placed on away from mixing line starting point 350mm, by chamber pressure control in 10Pa, is closed to high temperature
Gold surface is previously heated to 850 DEG C, then utilizes high energy laser beam by zirconic acid lanthanum La2Zr2O7(LZO) powder heating evaporation is formed
Corpuscullar flow containing lanthanum ion, zirconium ion, oxonium ion, zirconium oxonium ion and its cluster constitutes mixing line together with carrier gas Ar gas.
Finally the intermittent of formula is scanned to high temperature alloy matrix by the sweep speed of 1000mm/s to deposit.
Embodiment 3
Prepared by a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure, include the following steps：It will carry
The stainless steel base of adhesive layer is placed on away from mixing line starting point 900mm, and chamber pressure is controlled in 350Pa, to stainless steel
Surface is previously heated to 720 DEG C, then utilizes the plasma beam that power is 60kW by cerium oxide CeO2Powder heating evaporation shape
At the corpuscullar flow containing cerium ion, oxonium ion, cerium oxonium ion and its cluster, constituted together with plasma gas Ar gas and He gas mixed
Close line.Wherein plasma gas Ar gas and He gas air inflows is respectively 30NLPM and 55NLPM.Finally press the scanning of 500mm/s
Speed is scanned the intermittent of formula to stainless steel base and deposits.
Embodiment 4
Prepared by a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure, include the following steps：It will carry
The high temperature alloy matrix of aluminized coating is placed on away from mixing line starting point 900mm, and chamber pressure is controlled in 5000Pa, to high temperature
Alloy surface is previously heated to 870 DEG C, then utilizes high energy laser beam by samarium zirconate Sm2Zr2O7(SZO) powder heating evaporation shape
At the corpuscullar flow containing samarium ion, zirconium ion, oxonium ion, zirconium oxonium ion and its cluster, with carrier gas Ar gas.Finally press 200mm/s
Sweep speed the intermittent of formula be scanned to high temperature alloy matrix deposit；Then continous way deposition is carried out.
Claims (6)
1. a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure, which is characterized in that using containing monatomic and
The mixing line of coating material particles of elementide, the workpiece surface that temperature is 0.2 times of sprayed on material fusing point or more into
Row intermittence and/or successional deposition obtain the thermal barrier coating of Large strain tolerance columnar structure in workpiece surface；
Specifically include following steps：
(1) by workpiece place in the deposition chamber, workpiece with away from spacing mix between line starting point be more than mix line in apply
The 2 times or more of the minimum free path of layer material particulate；
(2) it is 10-5000Pa by deposition chambers air pressure adjustment；
(3) high energy beam current heating evaporation coating material powder is utilized to form corpuscullar flow, the coating material particles in corpuscullar flow
Son contains monatomic and elementide, and it is intermittent to workpiece surface progress or continuous to mix line with plasma (orifice) gas or carrier gas composition
Property deposition obtain Large strain tolerance columnar structure thermal barrier coating；
High energy beam current evaporates coating material to form coating material particles subflow, the monatomic packet that the corpuscullar flow is included
Monatomic narrow sense, unimolecule or single ion are included, the elementide that the particulate is included includes narrow sense elementide, molecule
Cluster or ion cluster；
Monatomic sedimentation unit percent by volume is 50%-99% in corpuscullar flow, and elementide percent by volume is 1%-
50%.
2. a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure according to claim 1, feature exist
In coating material particles mixed in line has Characteristics of Flow Around jointly with plasma (orifice) gas or carrier gas, is blocked encountering pattern
When, it gets around blocking position by the characteristic and is deposited.
3. a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure according to claim 1, feature exist
In, intermittence deposition when, mixing line swept on sample so that coating material particles be deposited on 0-180 ° it is each
It can be carried out in angle, random deposition forms surface undulation.
4. a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure according to claim 1, feature exist
In the workpiece is the high temperature alloy matrix with adhesive layer.
5. a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure according to claim 1, feature exist
In the coating material is YSZ powder, LZO powder, CeO2Powder or SZO powder.
6. a kind of preparation method of the thermal barrier coating of Large strain tolerance columnar structure according to claim 1, feature exist
In including the following steps：High temperature alloy matrix with adhesive layer is placed on away from mixing at line starting point 950mm, by chamber
Pressure is controlled in 150Pa, and 960 DEG C are previously heated to high-temperature alloy surface, and it is the high energy plasma of 127kW then to utilize power
Line forms yttrium oxide partially stabilized zirconia powder heating evaporation containing zirconium ion, oxonium ion, zirconium oxonium ion and its cluster
Corpuscullar flow, composition mixing line carries out continous way deposition to high temperature alloy matrix together with plasma gas Ar gas and He gas,
Sedimentation time is the thermal barrier coating that 20min obtains Large strain tolerance columnar structure；Wherein plasma gas Ar gas and He gas air inlets
Amount is respectively 35NLPM and 60NLPM.
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| CN104593767A (en) * | 2015-01-07 | 2015-05-06 | 上海交通大学 | Method for preparing thermal barrier coating bonding layer by utilizing laser powder deposition technology |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104593767A (en) * | 2015-01-07 | 2015-05-06 | 上海交通大学 | Method for preparing thermal barrier coating bonding layer by utilizing laser powder deposition technology |
Non-Patent Citations (2)
| Title |
|---|
| 等离子喷涂-物理气相沉积7YSZ热障涂层沉积机理及其CMAS腐蚀失效机制;张小锋等;《无机材料学报》;20150331;第30卷(第3期);第288页倒数第4-8行及表1，第289页第17-20行及右栏第10-21行，第290页右栏倒数第8-10行 * |
| 等离子喷涂-物理气相沉积7YSZ热障涂层的高温氧化行为;陈文龙等;《中国表面工程》;20151031;第28卷(第5期);49-56 * |
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