CN105734500B - A kind of resistance to high temperature oxidation thermal barrier coating and preparation method thereof with composite construction - Google Patents
A kind of resistance to high temperature oxidation thermal barrier coating and preparation method thereof with composite construction Download PDFInfo
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- CN105734500B CN105734500B CN201610250748.6A CN201610250748A CN105734500B CN 105734500 B CN105734500 B CN 105734500B CN 201610250748 A CN201610250748 A CN 201610250748A CN 105734500 B CN105734500 B CN 105734500B
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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
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- 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
- C23C14/30—Vacuum evaporation by wave energy or particle radiation by electron bombardment
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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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- 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
- C23C14/14—Metallic material, boron or silicon
- C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
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Abstract
The present invention provides a kind of resistance to high temperature oxidation thermal barrier coatings with composite construction, including metal bonding coating, the first ceramic layer, the second ceramic layer, metal deposition layer, third ceramic layer and the 4th ceramic layer being sequentially deposited at the top of high temperature alloy matrix, first ceramic layer and third ceramic layer are isometric crystal structure, second ceramic layer and the 4th ceramic layer are columnar crystal structure, and wherein the ingredient of ceramic layer is Y2O3Stable ZrO2, the ingredient of metal bonding coating is MCrAlY, and the ingredient of metal deposition layer is MCrAlY or NiAl, and M is Ni or/and Co.The present invention also provides a kind of methods preparing the resistance to high temperature oxidation thermal barrier coating.Resistance to high temperature oxidation thermal barrier coating of the present invention has multiple-layer stacked equiax crystal and columnar crystal structure, has good oxygen barrier and thermal shock resistance, preparing technique process is simple, favorable repeatability, easily operated.
Description
Technical field
The invention belongs to high temperature coating protection technology fields, and in particular to a kind of resistance to high temperature oxidation heat with composite construction
Barrier coating and preparation method thereof.
Background technology
Thermal barrier coating is a kind of characteristics such as high-temperature resistant, low heat conduction and high thermal expansion coefficient using ceramics, by it with coating
Form and surface there is the high-temperature alloy base bluk recombination of metal bonding coating, to reduce high-temperature alloy surface temperature, improve its clothes
The surface protection technique for using as a servant the service life has been widely used dynamic in Aeronautics and Astronautics, sea ship, large-scale thermal power and automobile
Power etc..In actual use, the Service Environment of thermal barrier coating is extremely harsh, not only has strong high-temperature oxydation and high temperature
Corrosion is impacted also subject to frequent cold cycling, the failure behaviours such as is extremely easy to happen coating cracking, is removed, falls off, making its clothes
Use as a servant restricted lifetime.
The technology of preparing of thermal barrier coating is with air plasma spraying (APS) and electro beam physics vapour deposition (EB-PVD)
Main, coating prepared by APS is the layer structure with interstitial air voids, and oxygen barrier is preferable, but coating is low with the bond strength of matrix,
Thermal shock resistance is poor.The patent of invention that publication No. is CN103993313A handles YSZ prepared by APS using Laser Cladding and applies
Layer, makes it have closelypacked columnar crystal structure, but this method is easy to introduce thermal stress and vertical crack in the coating, leads
Cause coating premature failure.The column crystal being separated from each other by many compared to the thermal barrier coating that APS, EB-PVD are prepared forms, and has
Higher strain tolerance, good thermal shock, and the interface between coating and matrix based on chemical bonds, interface binding intensity compared with
Height, but the columnar crystal structure being separated from each other provides channel for the entrance of oxygen and corrosive medium, makes oxygen transmission rate height, the high temperature resistance of coating
Oxidation susceptibility and high temperature corrosion resistance reduce.In order to improve the high temperature oxidation resistance of coating, Publication No. CN103668191A
The YSZ surface ceramii layers that are prepared in EB-PVD using magnetically controlled sputter method of patent of invention deposit 5~30 μm of aluminum membranous layer, and very
Empty thermal barrier coating of the heat treatment with aluminium film makes one layer of fine and close aluminium oxide of its Surface Creation and stops the permeability of oxygen, improves
The high temperature oxidation resistance of coating.The patent of invention of Publication No. CN102719782A and CN103789715A are using strong current pulsed
Electron beam equipment seasoning metal adhesive layer, the remelted layer dense structure, refinement, hole and cavity are less, and the phase can be fast before oxidation
Speed forms thermal growth oxide (TGO) film, inhibits oxygen element diffusion, improves the antioxygenic property of coating.Document (Xu
H.B.,et al.Preparation of Al2O3-YSZ composite coating by EB-PVD.Materials
Science and Engineering A,2002,325:389-393] using EB-PVD co-depositions Al2O3- YSZ graded ceramics apply
The method of layer reduces the diffusion admittance of oxygen in the coating, and this method can reduce the thermal conductivity of coating, extend the use of coating
Service life.
However so far, not yet find a kind of simple preparation process, favorable repeatability, it is easily operated, there is multi-laminate
Add the composite heat resisting of equiax crystal/columnar crystal structure to aoxidize thermal barrier coating and is seen in report.
Invention content
It is a kind of with composite junction technical problem to be solved by the present invention lies in view of the above shortcomings of the prior art, providing
The resistance to high temperature oxidation thermal barrier coating of structure.The thermal barrier coating has multiple-layer stacked equiax crystal/columnar crystal structure, has good resistance oxygen
Property and thermal shock resistance, and preparing technique process is simple, favorable repeatability, it is easily operated.
In order to solve the above technical problems, the technical solution adopted by the present invention is：A kind of high temperature resistance oxygen with composite construction
Change thermal barrier coating, which is characterized in that the coating includes metal bonding coating, the first pottery being sequentially deposited at the top of high temperature alloy matrix
Enamel coating, the second ceramic layer, metal deposition layer, third ceramic layer and the 4th ceramic layer, first ceramic layer and third ceramic layer
It is isometric crystal structure, second ceramic layer and the 4th ceramic layer are columnar crystal structure；First ceramic layer, the second pottery
Enamel coating and the ingredient of third ceramic layer and the 4th ceramic layer are 6wt%~8wt%Y2O3Stable ZrO2, the metal bonding
The ingredient of layer is MCrAlY, and the ingredient of the metal deposition layer is MCrAlY or NiAl, and M is Ni or/and Co, and the high temperature refers to
Temperature is 1100 DEG C~1200 DEG C.
A kind of above-mentioned resistance to high temperature oxidation thermal barrier coating with composite construction, which is characterized in that the metal bonding coating
Thickness be 10 μm~100 μm, the thickness of first ceramic layer is 3 μm~7 μm, and the thickness of second ceramic layer is 10 μm
~50 μm, the thickness of the metal deposition layer is 2 μm~5 μm, and the thickness of the third ceramic layer is 3 μm~7 μm, the described 4th
The thickness of ceramic layer is 20 μm~200 μm.
A kind of above-mentioned resistance to high temperature oxidation thermal barrier coating with composite construction, which is characterized in that the high-temperature alloy base
The material of body is nickel base superalloy N5.
In addition, the present invention also provides a kind of sides preparing the above-mentioned resistance to high temperature oxidation thermal barrier coating with composite construction
Method, which is characterized in that this approach includes the following steps：
Step 1: polishing high temperature alloy matrix, then it is cleaned by ultrasonic clean；
It is cleaned by ultrasonic totally Step 2: MCrAlY is deposited in step 1 using the method for electro beam physics vapour deposition
High temperature alloy matrix surface, obtain metal bonding coating；The time of the electro beam physics vapour deposition be 20min~
150min, target evaporation current are 1.4A；
Step 3: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal bonding coating described in step 2 obtains the first ceramic layer and the second ceramic layer；The electron beam physical vapor is heavy
The long-pending time is 10min~60min, and target evaporation current is 1.2A；
Step 4: MCrAlY or NiAl are deposited on described in step 3 by the method using electro beam physics vapour deposition
The surface of two ceramic layers, obtains metal deposition layer；The time of the electro beam physics vapour deposition is 2min~8min, and target steams
Power generation stream is 1.4A；
Step 5: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal deposition layer described in step 4 obtains third ceramic layer and the 4th ceramic layer, finally on high temperature alloy matrix
Obtain the resistance to high temperature oxidation thermal barrier coating with composite construction；The time of the electro beam physics vapour deposition be 10min~
160min, target evaporation current are 1.2A.
Above-mentioned method, which is characterized in that the mesh number polished described in step 1 is the mesh of 80 mesh~1000.
Above-mentioned method, which is characterized in that the work of electro beam physics vapour deposition described in the step 2 to step 5
Skill parameter is：Settling chamber vacuum degree≤5 × 10-3Pa, heated current 0.2A~0.25A of high temperature alloy matrix, high temperature alloy
The rotating speed 20r/min of matrix, electron-beam voltage 20kV.
The present invention guiding theory be：First, it is prepared on metal bonding coating using electro beam physics vapour deposition method
Ceramic layer has equiax crystal and columnar crystal structure, compares column crystal, isometric crystal structure radial dimension bigger, crystal boundary in unit area
Quantity is less, can reduce atoms permeating channel.Therefore, the present invention is based on the principles, and one layer and ceramics are deposited in surface ceramii layer
The metal deposition layer that layer surface can differ greatly with polarity dispersive component, is prepared with multiple-layer stacked equiax crystal/column crystal knot
The thermal barrier coating of structure ceramic layer.Second, metal deposition layer can form oxidation barrier layer during high-temperature service, delay oxygen first
Element is spread to matrix.Third, under low oxygen concentration, metal bonding coating occurs diffusion reaction with ceramic layer and forms α-Al2O3, into one
The diffusion of step blocking oxygen, while improving the interface binding power for applying interlayer.
Compared with the prior art, the present invention has the following advantages：
1, there is coating of the present invention composite construction to utilize equiax crystal microstructure while ensureing column crystal advantage
Feature reduces the diffusion admittance of oxygen and corrosive medium, and the oxide resistance that metal deposition layer is formed during high-temperature service
Barrier can also delay diffusion of the oxygen element to matrix, and the oxygen transmission rate of thermal barrier coating is low, and high temperature oxidation resistance is excellent.
2, diffusion reaction occurs for interface of the present invention, improves the interface binding power for applying interlayer.
3, only with a kind of technology of preparing, simple for process, favorable repeatability is easily operated, adopts for the preparation of coating of the present invention
With electro beam physics vapour deposition prepare composite construction high temperature resistance thermal barrier coating can be widely applied to aerospace engine and
The thermal protection of ground gas turbine hot side metal component.
Invention is further described in detail with reference to the accompanying drawings and examples.
Description of the drawings
Fig. 1 is the structural schematic diagram for the resistance to high temperature oxidation thermal barrier coating that the present invention has composite construction.
Fig. 2 is the cross-sectional scans electron microscope for the resistance to high temperature oxidation thermal barrier coating that the embodiment of the present invention 1 has composite construction.
Fig. 3, which is the embodiment of the present invention 1, has the resistance to high temperature oxidation thermal barrier coating of composite construction under 1100 DEG C of hot conditions
Cross-sectional scans electron microscope after isothermal oxidation 500h.
Reference sign:
1-high temperature alloy matrix；2-metal bonding coatings；3-the first ceramic layer；
4-the second ceramic layer；5-metal deposition layers；6-third ceramic layers；
7-the four ceramic layer；Metal bonding coating after 2'-oxidation； 3'—Al2O3Layer；
4'-diffusion layer；5'-I layers of ceramics；6'-oxide skin(coating)；
7'-II layers of ceramics.
Specific implementation mode
Embodiment 1
As shown in Figure 1, there is the present embodiment the resistance to high temperature oxidation thermal barrier coating of composite construction to be deposited on high temperature alloy matrix 1
Top, and the coating includes the metal bonding coating 2 being sequentially depositing from top to bottom, the first ceramic layer 3, the second ceramic layer 4, metal
Sedimentary 5, third ceramic layer 6 and the 4th ceramic layer 7, first ceramic layer 3 and third ceramic layer 6 are isometric crystal structure,
Second ceramic layer, 4 and the 4th ceramic layer 7 is columnar crystal structure；First ceramic layer 3, the second ceramic layer 4 and third
The ingredient of ceramic layer 6 and the 4th ceramic layer 7 is 6wt%~8wt%Y2O3Stable ZrO2, the ingredient of the metal bonding coating 2
Ingredient for MCrAlY, the metal deposition layer 5 is MCrAlY, and M is Ni or/and Co.
In the present embodiment, M Ni；The thickness of the metal bonding coating 2 is 17 μm, and the thickness of first ceramic layer 3 is 5
μm, the thickness of second ceramic layer 4 is 36 μm, and the thickness of the metal deposition layer 5 is 3.5 μm, the third ceramic layer 6
Thickness is 5 μm, and the thickness of the 4th ceramic layer 7 is 36 μm.
In the present embodiment, the material of the high temperature alloy matrix 1 is nickel base superalloy N5.
In conjunction with Fig. 1, method that the present embodiment prepares the resistance to high temperature oxidation thermal barrier coating with composite construction include with
Lower step：
Step 1: being cleaned by ultrasonic totally after polishing high temperature alloy matrix 1, it is heavy to be then placed in electron beam physical vapor
In product equipment；The mesh number of the polishing is the mesh of 80 mesh~1000, and the mesh number polished in the present embodiment is followed successively by：80 mesh, 240 mesh,
600 mesh and 1000 mesh；
Step 2: MCrAlY is deposited on to the surface of high temperature alloy matrix 1 using the method for electro beam physics vapour deposition,
Obtain metal bonding coating 2；The time of the electro beam physics vapour deposition is 30min, and target evaporation current is 1.4A, settling chamber
Vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron beam electricity
Press 20kV；
Step 3: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal bonding coating 2 obtains the first ceramic layer 3 and the second ceramic layer 4；The time of the electro beam physics vapour deposition is
30min, target evaporation current are 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix are high
Temperature alloy matrix 1 rotating speed 20r/min, electron-beam voltage 20kV；
Step 4: MCrAlY to be deposited on to the surface of the second ceramic layer 4 using the method for electro beam physics vapour deposition, obtain
To metal deposition layer 5；The time of the electro beam physics vapour deposition is 3min, and target evaporation current is 1.4A, and settling chamber is true
Reciprocal of duty cycle≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron-beam voltage
20kV；
Step 5: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal deposition layer 5 obtains third ceramic layer 6 and the 4th ceramic layer 7, is finally had on high temperature alloy matrix 1
The resistance to high temperature oxidation thermal barrier coating of composite construction；The time of the electro beam physics vapour deposition is 30min, target evaporation current
For 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed of high temperature alloy matrix
20r/min, electron-beam voltage 20kV.
The present embodiment prepares a kind of resistance to high temperature oxidation thermal barrier coating with composite construction in high temperature alloy matrix surface,
Its cross-sectional scans Electronic Speculum is as shown in Fig. 2, the coating structure is fine and close as shown in Figure 2, well arranged, interface is continuous and is connect with matrix
Closely.For the high temperature oxidation resistance of testing coating, by the sample of the present embodiment and conventional double coating sample (high-temperature alloy base
Body/metal bonding coating/6 NiCrAlY~8wt%Y2O3-ZrO2Ceramic layer) while being put into 1100 DEG C of Muffle furnaces, atmospheric oxidn
500h.Carrying out Cross Section Morphology observation to the sample of the embodiment 1 after oxidation with scanning electron microscope and X-ray energy spectrum, (Cross Section Morphology is such as
Shown in Fig. 3), and analytical element ingredient and distribution are found：After high-temperature oxydation, the structure of the present embodiment high temperature alloy matrix 1 and
Ingredient does not change, and the structure of thermal barrier coating and ingredient have occurred that large change, wherein the metal in former coating bonds
Three-decker is presented after elements diffusion, oxidation and displacement reaction in layer 2：Metal bonding coating 2 ＇, Al after oxidation2O33 ＇ of layer and expansion
4 ＇ of layer is dissipated, the first ceramic layer 3 and the second ceramic layer 4 in former coating merge into ceramic 5 ＇ of I layers, the metal deposition layer in former coating
5 since oxidation reaction is converted into 6 ＇ of oxide skin(coating), and the third ceramic layer 6 and the 4th ceramic layer 7 in former coating merge into ceramic II
7 ＇ of layer.It is well arranged between each layer, be completely embedded, do not have crackle appearance.In oxidation process, the oxygen atom and metal deposit of diffusion
5 reaction of layer, which generates, contains Al2O3、Cr2O3With 6 ＇ of oxide skin(coating) of NiO mixtures, the formation of oxide skin(coating) and with isometric crystal structure
The first ceramic layer 3 and third ceramic layer 6 delayed diffusion of the oxygen atom to matrix, make in metal bonding coating 2 Al, Ni and Cr member
Element diffuses to form 4 ＇ of diffusion layer outward, with the extension of oxidization time, the Al of 2 external diffusion of metal bonding coating and the first ceramic layer 3 and
The ZrO spread in second ceramic layer 424Al+3ZrO has occurred2→2Al2O3The chemical reaction of+3Zr forms one layer continuously
Pellumina, generation aluminium oxide can be reacted by being at the same time diffused into the oxygen on metal bonding coating surface, and the two cooperatively forms
Al2O33 ＇ of layer.Al2O33 ＇ of layer can effectively stop diffusion of the oxygen element to matrix, extend the service life of coating.
After testing, after 1100 DEG C/500h oxidations, the TGO thickness of the present embodiment thermal barrier coating is 3~4.5 μm, is less than and passes
8~10 μm of the TGO thickness of system duplex coating sample illustrates that the high temperature oxidation resistance of coating prepared by the present invention is more preferable, is on active service
Time is longer.
Embodiment 2
As shown in Figure 1, there is the present embodiment the resistance to high temperature oxidation thermal barrier coating of composite construction to be deposited on high temperature alloy matrix 1
Top, and the coating includes the metal bonding coating 2 being sequentially depositing from top to bottom, the first ceramic layer 3, the second ceramic layer 4, metal
Sedimentary 5, third ceramic layer 6 and the 4th ceramic layer 7, first ceramic layer 3 and third ceramic layer 6 are isometric crystal structure,
Second ceramic layer, 4 and the 4th ceramic layer 7 is columnar crystal structure；First ceramic layer 3, the second ceramic layer 4 and third
The ingredient of ceramic layer 6 and the 4th ceramic layer 7 is 6wt%~8wt%Y2O3Stable ZrO2, the ingredient of the metal bonding coating 2
Ingredient for MCrAlY, the metal deposition layer 5 is MCrAlY, and M is Ni or/and Co.
In the present embodiment, M is Ni and Co；The thickness of the metal bonding coating 2 is 17 μm, the thickness of first ceramic layer 3
Degree is 5 μm, and the thickness of second ceramic layer 4 is 36 μm, and the thickness of the metal deposition layer 5 is 3.5 μm, the third ceramics
The thickness of layer 6 is 5 μm, and the thickness of the 4th ceramic layer 7 is 36 μm.
In the present embodiment, the material of the high temperature alloy matrix 1 is nickel base superalloy N5.
In conjunction with Fig. 1, method that the present embodiment prepares the resistance to high temperature oxidation thermal barrier coating with composite construction include with
Lower step：
Step 1: being cleaned by ultrasonic totally after polishing high temperature alloy matrix 1, it is heavy to be then placed in electron beam physical vapor
In product equipment；The mesh number of the polishing is the mesh of 80 mesh~1000, and the mesh number polished in the present embodiment is followed successively by：80 mesh, 240 mesh,
600 mesh and 1000 mesh；
Step 2: MCrAlY is deposited on to the surface of high temperature alloy matrix 1 using the method for electro beam physics vapour deposition,
Obtain metal bonding coating 2；The time of the electro beam physics vapour deposition is 30min, and target evaporation current is 1.4A, settling chamber
Vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron beam electricity
Press 20kV；
Step 3: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal bonding coating 2 obtains the first ceramic layer 3 and the second ceramic layer 4；The time of the electro beam physics vapour deposition is
30min, target evaporation current are 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix are high
Temperature alloy matrix 1 rotating speed 20r/min, electron-beam voltage 20kV；
Step 4: MCrAlY to be deposited on to the surface of the second ceramic layer 4 using the method for electro beam physics vapour deposition, obtain
To metal deposition layer 5；The time of the electro beam physics vapour deposition is 3min, and target evaporation current is 1.4A, and settling chamber is true
Reciprocal of duty cycle≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron-beam voltage
20kV；
Step 5: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal deposition layer 5 obtains third ceramic layer 6 and the 4th ceramic layer 7, is finally had on high temperature alloy matrix 1
The resistance to high temperature oxidation thermal barrier coating of composite construction；The time of the electro beam physics vapour deposition is 30min, target evaporation current
For 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed of high temperature alloy matrix
20r/min, electron-beam voltage 20kV.
By sample made from the present embodiment after 1100 DEG C of atmospheric environment high-temperature oxydation 500h, each interface connection of coating is tight
It is close, there is not crackle appearance, TGO thickness is about 4 μm after oxidation, is less than 8~10 μm of the TGO thickness of conventional double coating sample, says
The bright thermal barrier coating has good high temperature oxidation resistance.
Embodiment 3
As shown in Figure 1, there is the present embodiment the resistance to high temperature oxidation thermal barrier coating of composite construction to be deposited on high temperature alloy matrix 1
Top, and the coating includes the metal bonding coating 2 being sequentially depositing from top to bottom, the first ceramic layer 3, the second ceramic layer 4, metal
Sedimentary 5, third ceramic layer 6 and the 4th ceramic layer 7, first ceramic layer 3 and third ceramic layer 6 are isometric crystal structure,
Second ceramic layer, 4 and the 4th ceramic layer 7 is columnar crystal structure；First ceramic layer 3, the second ceramic layer 4 and third
The ingredient of ceramic layer 6 and the 4th ceramic layer 7 is 6wt%~8wt%Y2O3Stable ZrO2, the ingredient of the metal bonding coating 2
Ingredient for MCrAlY, the metal deposition layer 5 is MCrAlY, and M is Ni or/and Co.
In the present embodiment, M Co；The thickness of the metal bonding coating 2 is 17 μm, and the thickness of first ceramic layer 3 is 5
μm, the thickness of second ceramic layer 4 is 36 μm, and the thickness of the metal deposition layer 5 is 3.5 μm, the third ceramic layer 6
Thickness is 5 μm, and the thickness of the 4th ceramic layer 7 is 36 μm.
In the present embodiment, the material of the high temperature alloy matrix 1 is nickel base superalloy N5.
In conjunction with Fig. 1, method that the present embodiment prepares the resistance to high temperature oxidation thermal barrier coating with composite construction include with
Lower step：
Step 1: being cleaned by ultrasonic totally after polishing high temperature alloy matrix 1, it is heavy to be then placed in electron beam physical vapor
In product equipment；The mesh number of the polishing is the mesh of 80 mesh~1000, and the mesh number polished in the present embodiment is followed successively by：80 mesh, 240 mesh,
600 mesh and 1000 mesh；
Step 2: MCrAlY is deposited on to the surface of high temperature alloy matrix 1 using the method for electro beam physics vapour deposition,
Obtain metal bonding coating 2；The time of the electro beam physics vapour deposition is 30min, and target evaporation current is 1.4A, settling chamber
Vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron beam electricity
Press 20kV；
Step 3: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal bonding coating 2 obtains the first ceramic layer 3 and the second ceramic layer 4；The time of the electro beam physics vapour deposition is
30min, target evaporation current are 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix are high
Temperature alloy matrix 1 rotating speed 20r/min, electron-beam voltage 20kV；
Step 4: MCrAlY to be deposited on to the surface of the second ceramic layer 4 using the method for electro beam physics vapour deposition, obtain
To metal deposition layer 5；The time of the electro beam physics vapour deposition is 3min, and target evaporation current is 1.4A, and settling chamber is true
Reciprocal of duty cycle≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron-beam voltage
20kV；
Step 5: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal deposition layer 5 obtains third ceramic layer 6 and the 4th ceramic layer 7, is finally had on high temperature alloy matrix 1
The resistance to high temperature oxidation thermal barrier coating of composite construction；The time of the electro beam physics vapour deposition is 30min, target evaporation current
For 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed of high temperature alloy matrix
20r/min, electron-beam voltage 20kV.
By sample made from the present embodiment after 1100 DEG C of atmospheric environment high-temperature oxydation 500h, each interface connection of coating is tight
It is close, there are not crackle appearance, and the Al on metal bonding coating surface2O3Layer is fine and close, and oxygen element content is lower in diffusion layer, and TGO thickness is
2~4 μm, it is less than 7~8 μm of the TGO thickness of conventional double coating sample, illustrates that the thermal barrier coating reduces oxygen permeability, improves
The high-temperature oxidation resistance of high temperature alloy matrix, the service life of coating are longer.
Embodiment 4
As shown in Figure 1, there is the present embodiment the resistance to high temperature oxidation thermal barrier coating of composite construction to be deposited on high temperature alloy matrix 1
Top, and the coating includes the metal bonding coating 2 being sequentially depositing from top to bottom, the first ceramic layer 3, the second ceramic layer 4, metal
Sedimentary 5, third ceramic layer 6 and the 4th ceramic layer 7, first ceramic layer 3 and third ceramic layer 6 are isometric crystal structure,
Second ceramic layer, 4 and the 4th ceramic layer 7 is columnar crystal structure；First ceramic layer 3, the second ceramic layer 4 and third
The ingredient of ceramic layer 6 and the 4th ceramic layer 7 is 6wt%~8wt%Y2O3Stable ZrO2, the ingredient of the metal bonding coating 2
Ingredient for MCrAlY, the metal deposition layer 5 is MCrAlY, and M is Ni or/and Co.
In the present embodiment, M Ni；The thickness of the metal bonding coating 2 is 10 μm, and the thickness of first ceramic layer 3 is 3
μm, the thickness of second ceramic layer 4 is 10 μm, and the thickness of the metal deposition layer 5 is 2 μm, the thickness of the third ceramic layer 6
Degree is 3 μm, and the thickness of the 4th ceramic layer 7 is 20 μm.
In the present embodiment, the material of the high temperature alloy matrix 1 is nickel base superalloy N5.
In conjunction with Fig. 1, method that the present embodiment prepares the resistance to high temperature oxidation thermal barrier coating with composite construction include with
Lower step：
Step 1: being cleaned by ultrasonic totally after polishing high temperature alloy matrix 1, it is heavy to be then placed in electron beam physical vapor
In product equipment；The mesh number of the polishing is the mesh of 80 mesh~1000, and the mesh number polished in the present embodiment is followed successively by：80 mesh, 200 mesh,
400 mesh and 800 mesh；
Step 2: MCrAlY is deposited on to the surface of high temperature alloy matrix 1 using the method for electro beam physics vapour deposition,
Obtain metal bonding coating 2；The time of the electro beam physics vapour deposition is 20min, and target evaporation current is 1.4A, settling chamber
Vacuum degree≤5 × 10-3Pa, 1 heated current 0.2A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron beam electricity
Press 20kV；
Step 3: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal bonding coating 2 obtains the first ceramic layer 3 and the second ceramic layer 4；The time of the electro beam physics vapour deposition is
10min, target evaporation current are 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.2A of high temperature alloy matrix are high
Temperature alloy matrix 1 rotating speed 20r/min, electron-beam voltage 20kV；
Step 4: MCrAlY to be deposited on to the surface of the second ceramic layer 4 using the method for electro beam physics vapour deposition, obtain
To metal deposition layer 5；The time of the electro beam physics vapour deposition is 2min, and target evaporation current is 1.4A, and settling chamber is true
Reciprocal of duty cycle≤5 × 10-3Pa, 1 heated current 0.2A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron-beam voltage
20kV；
Step 5: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal deposition layer 5 obtains third ceramic layer 6 and the 4th ceramic layer 7, is finally had on high temperature alloy matrix 1
The resistance to high temperature oxidation thermal barrier coating of composite construction；The time of the electro beam physics vapour deposition is 10min, target evaporation current
For 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.2A of high temperature alloy matrix, 1 rotating speed 20r/ of high temperature alloy matrix
Min, electron-beam voltage 20kV.
By sample made from the present embodiment after 1100 DEG C of atmospheric environment high-temperature oxydation 100h, each interface connection of coating is tight
It is close, there are not crackle appearance, and the Al on metal bonding coating surface2O3Layer is fine and close, and oxygen element content is lower in diffusion layer, and TGO thickness is
3~4 μm, it is less than 5~6 μm of the TGO thickness of conventional double coating sample, illustrates that the thermal barrier coating reduces oxygen permeability, improves
The high-temperature oxidation resistance of high temperature alloy matrix, the service life of coating are longer.
Embodiment 5
As shown in Figure 1, there is the present embodiment the resistance to high temperature oxidation thermal barrier coating of composite construction to be deposited on high temperature alloy matrix 1
Top, and the coating includes the metal bonding coating 2 being sequentially depositing from top to bottom, the first ceramic layer 3, the second ceramic layer 4, metal
Sedimentary 5, third ceramic layer 6 and the 4th ceramic layer 7, first ceramic layer 3 and third ceramic layer 6 are isometric crystal structure,
Second ceramic layer, 4 and the 4th ceramic layer 7 is columnar crystal structure；First ceramic layer 3, the second ceramic layer 4 and third
The ingredient of ceramic layer 6 and the 4th ceramic layer 7 is 6wt%~8wt%Y2O3Stable ZrO2, the ingredient of the metal bonding coating 2
It is Ni or/and Co for MCrAlY, M, the ingredient of the metal deposition layer 5 is MCrAlY.
In the present embodiment, the thickness of M Ni, the metal bonding coating 2 are 100 μm, and the thickness of first ceramic layer 3 is
7 μm, the thickness of second ceramic layer 4 is 50 μm, and the thickness of the metal deposition layer 5 is 5 μm, the third ceramic layer 6
Thickness is 7 μm, and the thickness of the 4th ceramic layer 7 is 200 μm.
In the present embodiment, the material of the high temperature alloy matrix 1 is nickel base superalloy N5.
In conjunction with Fig. 1, method that the present embodiment prepares the resistance to high temperature oxidation thermal barrier coating with composite construction include with
Lower step：
Step 1: being cleaned by ultrasonic totally after polishing high temperature alloy matrix 1, it is heavy to be then placed in electron beam physical vapor
In product equipment；The mesh number of the polishing is the mesh of 80 mesh~1000, and the mesh number polished in the present embodiment is followed successively by：80 mesh, 300 mesh,
600 mesh and 1000 mesh；
Step 2: MCrAlY is deposited on to the surface of high temperature alloy matrix 1 using the method for electro beam physics vapour deposition,
Obtain metal bonding coating 2；The time of the electro beam physics vapour deposition is 150min, and target evaporation current is 1.4A, deposition
Room vacuum degree≤5 × 10-3Pa, 1 heated current 0.25A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron beam
Voltage 20kV；
Step 3: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal bonding coating 2 obtains the first ceramic layer 3 and the second ceramic layer 4；The time of the electro beam physics vapour deposition is
60min, target evaporation current are 1.2A, settling chamber vacuum degree≤3~5 × 10-3Pa, 1 heated current of high temperature alloy matrix
0.25A, high temperature alloy matrix 1 rotating speed 20r/min, electron-beam voltage 20kV；
Step 4: MCrAlY to be deposited on to the surface of the second ceramic layer 4 using the method for electro beam physics vapour deposition, obtain
To metal deposition layer 5；The time of the electro beam physics vapour deposition is 8min, and target evaporation current is 1.4A, and settling chamber is true
Reciprocal of duty cycle≤5 × 10-3Pa, 1 heated current 0.25A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron-beam voltage
20kV；
Step 5: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal deposition layer 5 obtains third ceramic layer 6 and the 4th ceramic layer 7, is finally had on high temperature alloy matrix 1
The resistance to high temperature oxidation thermal barrier coating of composite construction；The time of the electro beam physics vapour deposition is 160min, target evaporation electricity
Stream is 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.25A of high temperature alloy matrix, 1 rotating speed of high temperature alloy matrix
20r/min, electron-beam voltage 20kV.
By sample made from the present embodiment after 1100 DEG C of atmospheric environment high-temperature oxydation 500h, each interface connection of coating is tight
It is close, there are not crackle appearance, and the Al on metal bonding coating surface2O3Layer is fine and close, and oxygen element content is lower in diffusion layer, and TGO thickness is
2 μm, it is less than 4~5 μm of the TGO thickness of conventional double coating sample, illustrates that the thermal barrier coating reduces oxygen permeability, improve height
The service life of the high-temperature oxidation resistance of temperature alloy matrix, coating is longer.
Embodiment 6
As shown in Figure 1, there is the present embodiment the resistance to high temperature oxidation thermal barrier coating of composite construction to be deposited on high temperature alloy matrix 1
Top, and the coating includes the metal bonding coating 2 being sequentially depositing from top to bottom, the first ceramic layer 3, the second ceramic layer 4, metal
Sedimentary 5, third ceramic layer 6 and the 4th ceramic layer 7, first ceramic layer 3 and third ceramic layer 6 are isometric crystal structure,
Second ceramic layer, 4 and the 4th ceramic layer 7 is columnar crystal structure；First ceramic layer 3, the second ceramic layer 4 and third
The ingredient of ceramic layer 6 and the 4th ceramic layer 7 is 6wt%~8wt%Y2O3Stable ZrO2, the ingredient of the metal bonding coating 2
It is Ni or/and Co for MCrAlY, M, the ingredient of the metal deposition layer 5 is NiAl.
In the present embodiment, M Ni；The thickness of the metal bonding coating 2 is 17 μm, and the thickness of first ceramic layer 3 is 5
μm, the thickness of second ceramic layer 4 is 36 μm, and the thickness of the metal deposition layer 5 is 4 μm, the thickness of the third ceramic layer 6
Degree is 5 μm, and the thickness of the 4th ceramic layer 7 is 36 μm.
In the present embodiment, the material of the high temperature alloy matrix 1 is nickel base superalloy N5.
In conjunction with Fig. 1, method that the present embodiment prepares the resistance to high temperature oxidation thermal barrier coating with composite construction include with
Lower step：
Step 1: being cleaned by ultrasonic totally after polishing high temperature alloy matrix 1, it is heavy to be then placed in electron beam physical vapor
In product equipment；The mesh number of the polishing is the mesh of 80 mesh~1000, and the mesh number polished in the present embodiment is followed successively by：80 mesh, 240 mesh,
600 mesh and 1000 mesh；
Step 2: MCrAlY is deposited on to the surface of high temperature alloy matrix 1 using the method for electro beam physics vapour deposition,
Obtain metal bonding coating 2；The time of the electro beam physics vapour deposition is 30min, and target evaporation current is 1.4A, settling chamber
Vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron beam electricity
Press 20kV；
Step 3: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal bonding coating 2 obtains the first ceramic layer 3 and the second ceramic layer 4；The time of the electro beam physics vapour deposition is
30min, target evaporation current are 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix are high
Temperature alloy matrix 1 rotating speed 20r/min, electron-beam voltage 20kV；
Step 4: NiAl to be deposited on to the surface of the second ceramic layer 4 using the method for electro beam physics vapour deposition, obtain
Metal deposition layer 5；The time of the electro beam physics vapour deposition is 5min, and target evaporation current is 1.4A, settling chamber's vacuum
Degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed 20r/min of high temperature alloy matrix, electron-beam voltage
20kV；
Step 5: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on
The surface of metal deposition layer 5 obtains third ceramic layer 6 and the 4th ceramic layer 7, is finally had on high temperature alloy matrix 1
The resistance to high temperature oxidation thermal barrier coating of composite construction；The time of the electro beam physics vapour deposition is 30min, target evaporation current
For 1.2A, settling chamber vacuum degree≤5 × 10-3Pa, 1 heated current 0.23A of high temperature alloy matrix, 1 rotating speed of high temperature alloy matrix
20r/min, electron-beam voltage 20kV.
By sample made from the present embodiment after 1100 DEG C of atmospheric environment high-temperature oxydation 500h, coating interface is completely embedded,
There is not crackle appearance, Al content is higher in NiAl, can form one layer of comparatively dense aluminium oxide, blocking oxygen member in layer on surface of metal
Element penetrates；The Al on metal bonding coating surface2O3Layer is fine and close, and the thickness of TGO is 2~3 μm, is less than the TGO of conventional double coating sample
7~8 μm of thickness, thermal barrier coating have low oxygen transmission rate and good high temperature oxidation resistance.
The above is only presently preferred embodiments of the present invention, is not imposed any restrictions to the present invention.It is every according to invention skill
Art essence still falls within technical solution of the present invention to any simple modification, change and equivalence change made by above example
Protection domain in.
Claims (6)
1. a kind of resistance to high temperature oxidation thermal barrier coating with composite construction, which is characterized in that the coating includes being sequentially deposited to height
Metal bonding coating (2), the first ceramic layer (3), the second ceramic layer (4), metal deposition layer (5) at the top of temperature alloy matrix (1),
Three ceramic layers (6) and the 4th ceramic layer (7), first ceramic layer (3) and third ceramic layer (6) are isometric crystal structure, institute
It is columnar crystal structure to state the second ceramic layer (4) and the 4th ceramic layer (7)；First ceramic layer (3), the second ceramic layer (4)
Ingredient with third ceramic layer (6) and the 4th ceramic layer (7) is 6wt%~8wt%Y2O3Stable ZrO2, the metal is viscous
The ingredient for tying layer (2) is MCrAlY, and the ingredient of the metal deposition layer (5) is MCrAlY or NiAl, and M is Ni or/and Co, described
High temperature refers to that temperature is 1100 DEG C~1200 DEG C.
2. a kind of resistance to high temperature oxidation thermal barrier coating with composite construction according to claim 1, which is characterized in that described
The thickness of metal bonding coating (2) is 10 μm~100 μm, and the thickness of first ceramic layer (3) is 3 μm~7 μm, second pottery
The thickness of enamel coating (4) is 10 μm~50 μm, and the thickness of the metal deposition layer (5) is 2 μm~5 μm, the third ceramic layer (6)
Thickness be 3 μm~7 μm, the thickness of the 4th ceramic layer (7) is 20 μm~200 μm.
3. a kind of resistance to high temperature oxidation thermal barrier coating with composite construction according to claim 1, which is characterized in that described
The material of high temperature alloy matrix (1) is nickel base superalloy N5.
4. a kind of method preparing the resistance to high temperature oxidation thermal barrier coating with composite construction as described in claim 1, feature exist
In this approach includes the following steps：
Step 1: polishing high temperature alloy matrix (1), then it is cleaned by ultrasonic clean；
Step 2: MCrAlY is deposited on using the method for electro beam physics vapour deposition be cleaned by ultrasonic clean height in step 1
Temperature alloy matrix (1) surface, obtains metal bonding coating (2)；The time of the electro beam physics vapour deposition be 20min~
150min, target evaporation current are 1.4A；
Step 3: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on step
The surface of metal bonding coating described in two (2) obtains the first ceramic layer (3) and the second ceramic layer (4)；The electron-beam qi-regulating
Mutually the time of deposition is 10min~60min, and target evaporation current is 1.2A；
Step 4: MCrAlY or NiAl are deposited on the second pottery described in step 3 by the method using electro beam physics vapour deposition
The surface of enamel coating (4) obtains metal deposition layer (5)；The time of the electro beam physics vapour deposition is 2min~8min, target
Evaporation current is 1.4A；
Step 5: using the method for electro beam physics vapour deposition by 6wt%~8wt%Y2O3Stable ZrO2It is deposited on step
The surface of metal deposition layer described in four (5) obtains third ceramic layer (6) and the 4th ceramic layer (7), finally in high-temperature alloy base
The resistance to high temperature oxidation thermal barrier coating with composite construction is obtained on body (1)；The time of the electro beam physics vapour deposition is
10min~160min, target evaporation current are 1.2A.
5. according to the method described in claim 4, it is characterized in that, the mesh number polished described in step 1 is 80 mesh~1000
Mesh.
6. according to the method described in claim 4, it is characterized in that, electron-beam qi-regulating described in the step 2 to step 5
Mutually the technological parameter of deposition is：Settling chamber vacuum degree≤5 × 10-3Pa, the heated current 0.2A of high temperature alloy matrix (1)~
0.25A, the rotating speed 20r/min of high temperature alloy matrix (1), electron-beam voltage 20kV.
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| CN106567077B (en) * | 2016-11-15 | 2019-04-12 | 东莞市联洲知识产权运营管理有限公司 | A kind of preparation method of high-temp. alloy surface heat barrier |
| CN106435489B (en) * | 2016-11-30 | 2019-01-11 | 西北有色金属研究院 | A kind of preparation method of the anti-oxidant self-healing Cr/NiCr coating of niobium primary surface |
| CN109608176B (en) * | 2018-12-18 | 2021-11-05 | 辽宁省轻工科学研究院有限公司 | Ablation fiber-shaped coating and preparation and construction methods thereof |
| CN110144554A (en) * | 2019-05-23 | 2019-08-20 | 西北有色金属研究院 | The preparation method of the laser modified YSZ thermal barrier coating of high-temperature alloy surface NiCrAlY/YSZ/ |
| CN110129729A (en) * | 2019-06-28 | 2019-08-16 | 西北有色金属研究院 | Nickel-base alloy surface NiCrAlY/NiCrAlY-YSZ/YSZ thermal barrier coating and preparation method thereof |
| CN112063959B (en) * | 2020-08-06 | 2022-02-11 | 西安交通大学 | Column-layer/tree composite structure thermal barrier coating and preparation method thereof |
| CN113981366B (en) * | 2021-12-28 | 2022-03-18 | 北京航空航天大学 | Preparation method of thermal barrier coating, thermal barrier coating and turbine rotor blade |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1605460A (en) * | 2003-10-10 | 2005-04-13 | 通用电气公司 | Nano-multilayered structures, components and associated methods of manufacture |
| CN102181860A (en) * | 2011-03-25 | 2011-09-14 | 上海大学 | Method for forming Pt-modified NiAl+Ni3Al thermal barrier adhering layer on surface of nickel-based super alloy |
| 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 |
| CN103993254A (en) * | 2014-05-07 | 2014-08-20 | 江苏大学 | Thermal barrier coating material with closed surface layer and preparation method thereof |
| CN105463453A (en) * | 2015-11-25 | 2016-04-06 | 沈阳黎明航空发动机(集团)有限责任公司 | Thermal barrier coating with stable interface and manufacturing method of thermal barrier coating |
-
2016
- 2016-04-21 CN CN201610250748.6A patent/CN105734500B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1605460A (en) * | 2003-10-10 | 2005-04-13 | 通用电气公司 | Nano-multilayered structures, components and associated methods of manufacture |
| CN102181860A (en) * | 2011-03-25 | 2011-09-14 | 上海大学 | Method for forming Pt-modified NiAl+Ni3Al thermal barrier adhering layer on surface of nickel-based super alloy |
| 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 |
| CN103993254A (en) * | 2014-05-07 | 2014-08-20 | 江苏大学 | Thermal barrier coating material with closed surface layer and preparation method thereof |
| CN105463453A (en) * | 2015-11-25 | 2016-04-06 | 沈阳黎明航空发动机(集团)有限责任公司 | Thermal barrier coating with stable interface and manufacturing method of thermal barrier coating |
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