CN107937858A - A kind of thermal barrier coating and preparation method thereof - Google Patents
A kind of thermal barrier coating and preparation method thereof Download PDFInfo
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- CN107937858A CN107937858A CN201711091866.8A CN201711091866A CN107937858A CN 107937858 A CN107937858 A CN 107937858A CN 201711091866 A CN201711091866 A CN 201711091866A CN 107937858 A CN107937858 A CN 107937858A
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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
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
- C23C4/11—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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
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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
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
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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
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/137—Spraying in vacuum or in an inert atmosphere
Abstract
The present invention relates to a kind of heat barrier coat material and preparation method thereof, belongs to ceramic composite technical field.The present invention sprays the NiCoCrAlYTa of one layer of Dy doping by low-voltage plasma spraying technique in matrix surface,The interface binding power of oxide-film is improved by Dy doping,Effectively eliminate the hole of oxide-film/coating interface,And crystal grain thinning,Change out of phase distribution in coating,And significantly improve the anti-cyclic oxidation ability of coating,Simultaneously because tack coat is polished to minute surface,To reduce surface geometry discontinuity position,Pre-oxidation treatment is carried out again forms one layer of fine and close thin and continuous oxide skin(coating),The speed of growth of oxide can be reduced,The polishing treatment of tie layer surface can also suppress the germinating and extension of ceramic layer/oxide/tie-layer interface and ceramic layer internal tiny crack,Ceramic layer is made with rare earth doped oxide ceramic with heat resistance powder powder feeding spraying again,The thermal conductivity of coating is greatly reduced,Extend its service life under thermal cycling.
Description
Technical field
The present invention relates to a kind of thermal barrier coating and preparation method thereof, belongs to heat-insulating technique field.
Background technology
As aero-engine is towards the development in high thrust-weight ratio direction, the operating temperature of combustion chamber is continuously improved, such as military
The fuel gas temperature of aircraft is up to 1600 DEG C, and the maximum operation (service) temperature for the nickel base superalloy for being used to manufacture turbine blade only has
1100 DEG C, the requirement of modern aeroengine is can not meet.Based on this, in addition to improving cooling structure system,
High-temperature alloy surface prepare thermal barrier coating become it is a kind of efficiently with efficiently method.Thermal barrier coating is generally by high heat-insulated, anticorrosive
Ceramic coating and metal bonding coating composition.The major function of ceramic coating is decrease biography of the heat to matrix under high temperature load
Send, it is anti-oxidant with erosion-resisting performance to improve matrix.The effect of metal bonding coating is to alleviate ceramic layer and matrix thermal expansion not
Matching, improves the high temperature oxidation resistance of matrix.
At present, TBC technologies are to be applied to the indispensable crucial skill in aero-engine high temperature-end part surfacecti proteon field
Art, with the development of science and technology, will obtain more extensive in various fields such as space flight, aviation, electric power, chemical industry, metallurgy
Research and application.For the heat insulation for making thermal barrier coating reach best, it is necessary to carry out structure design to thermal barrier coating system.Mesh
Before, the structure of thermal barrier coating is broadly divided into three kinds：Double-decker, sandwich construction and gradient-structure.Wherein, double-decker mainly by
Ceramic layer and tack coat are formed, and have the advantages that simple in structure and technical maturity.But the thermal expansion system of ceramic layer and tack coat
Number and elasticity modulus difference are larger, easy to fall off during elevated temperature thermal cycles.Therefore, in order to alleviate interface thermophysical property not
Matching, has developed sandwich construction, mainly by metal bonding coating, multilayer insulation, Al2O3Oxidation prevention layer and ceramic top layer etc. are formed.
Compared with double-decker, although which reduces oxide layer growth speed, improves coating antioxygenic property, but technique is answered
Miscellaneous, thermal shock resistance improves less, and the application in aero-engine field is subject to larger limitation.Therefore, in order to further improve
The resistance to high temperature oxidation and mechanical property of thermal barrier coating, carry out gradient-structure design to coating, make chemical composition, the knot of tissue of coating
Structure and mechanical property change in gradient along coating layer thickness direction, realize that ceramic layer is matched with the optimum performance of high temperature alloy, reduce
The residual stress of coating, effectively prevent the peeling of coating.
At present, thermal barrier coating system is generally as metal with MCrAlY (M=Ni, Co or NiCo) resistance to high temperature oxidation alloy
Tack coat, top layer are ceramic thermal barrier layer.The ceramic material that thermal barrier coating uses is needed with thermal coefficient of expansion and basis material phase
Matching and resistance to high temperature corrosion, lower thermal conductivity, mutually stablize the features such as.At present, common thermal barrier coating ceramic material mainly has
Al2O3、SiO2、ZrO2.Wherein, ZrO2With high-melting-point and lower thermal conductivity, and thermal coefficient of expansion is used extensively close to metal material
Make the ceramic material of thermal barrier coating.But ZrO at high temperature2With allotropic transformation, phase transformation makes volume change so as to produce
Structural stress, causes coating cracking or peeling, therefore the new thermal barrier coating for developing lower thermal conductivity and higher thermal expansion coefficient is used
Top layer ceramic material just seems particularly significant.
The content of the invention
The technical problems to be solved by the invention：For ZrO at high temperature2With allotropic transformation, phase transformation makes volume
A kind of the problem of change causes coating cracking or peeling so as to producing structural stress, and coating life reduces, there is provided thermal barrier coating
And preparation method thereof.
In order to solve the above technical problems, the technical solution adopted by the present invention is：
A kind of thermal barrier coating, including the nickel base superalloy matrix set, middle gluing layer and ceramic layer, the ceramic layer are folded successively
Chemical composition be (Sm0.5Gd0.3Yb0.2)2（CexZr1-x）2O7, wherein, 0.01≤x≤0.1.
The ceramic layer is that ceramic with heat resistance powder is carried out two-tube internal powder conveying spraying, and it is 20 ~ 25g/min to control powder feeding rate,
Ceramic layer thickness is sprayed into as 200 ~ 300 μm.
The ceramic with heat resistance powder is samaric nitrate, gadolinium nitrate, ytterbium nitrate, cerous nitrate, zirconium nitrate, in molar ratio 5：3：2：
（0.1~1）：（9.0~9.9）Mixing adds in deionized water and ammonia precipitation process is added dropwise, and is made through drying and calcining.
The middle gluing layer is the NiCoCrAlYTa of Dy doping, and the wherein percentage composition of each element is 22 ~ 24%Co,
19 ~ 21%Cr, 7.5 ~ 8.5%Al, 0.4 ~ 0.8%Y, 3.5 ~ 5.5%Ta, 0.01 ~ 0.05%Dy, nickel surplus.
The middle gluing layer also needs pre-oxidation treatment, and detailed process is that spraying is transferred to after being polished to minute surface with polishing machine very
In empty room, vacuum pump is opened spraying vacuum chamber to 100 ~ 150Pa, then oxygen is continually fed into 1 ~ 2L/min, and is added
Heat is to 400 ~ 500 DEG C, 20 ~ 30min of insulation pre-oxidation.
The nickel base superalloy matrix is nickel base superalloy K417.
The preparation method of a kind of thermal barrier coating, it is characterised in that concretely comprise the following steps：
（1）By samaric nitrate, gadolinium nitrate, ytterbium nitrate, cerous nitrate, zirconium nitrate, in molar ratio 5：3：2：（0.1~1）：（9.0~9.9）It is mixed
Close and add in deionized water and ammonia precipitation process is added dropwise, wash to obtain presoma；
（2）1 ~ 3h is calcined after presoma is dried at 1000 ~ 1200 DEG C, grinds to obtain ceramic with heat resistance powder；
（3）Take nickel base superalloy K417 to cut into the cylinder of Φ 20mm × 5mm, carried out after being cleaned by ultrasonic 2 ~ 3 times at sandblasting
Reason, it is 200 ~ 220 μm to control gravel average grain diameter, and blasting pressure is 1.5 × 105Pa, sandblasting angle are 45 ~ 60 °, sandblasting distance
For 80 ~ 100mm, then cleaned with compressed air purging, obtain pretreatment basis material；
（4）Using low-voltage plasma spraying technique, in pretreatment substrate material surface sprays a layer thickness as 100 ~ 150 μm
Between gluing layer, and be polished to after minute surface and be transferred in spraying vacuum chamber, be evacuated to 100 ~ 150Pa, then be passed through oxygen and be heated to
400 ~ 500 DEG C, insulation 20 ~ 30min of pre-oxidation, obtains pre-oxidation basis material；
（5）Be passed through argon gas and helium into spraying vacuum chamber, and be heated to 850 ~ 1000 DEG C, adjustment spray away from for 950 ~ 1000mm into
Row powder feeding sprays, and it is 20 ~ 25g/min to control powder feeding rate, is sprayed into ceramic layer thickness as 200 ~ 300 μm, obtains thermal barrier coating.
Compared with other methods, advantageous effects are the present invention：
The present invention sprays the NiCoCrAlYTa of one layer of Dy doping by low-voltage plasma spraying technique in matrix surface, passes through Dy
Doping improves the interface binding power of oxide-film, effectively eliminates the hole of oxide-film/coating interface, and crystal grain thinning, changes
Out of phase distribution in coating, and the anti-cyclic oxidation ability of coating is significantly improved, simultaneously because tack coat is thrown
Light is to minute surface, to reduce surface geometry discontinuity position, then carry out pre-oxidation treatment formed it is one layer fine and close thin and continuous
Oxide skin(coating), the speed of growth of oxide can be reduced, the polishing treatment of tie layer surface can also suppress ceramic layer/oxidation
The germinating and extension of thing/tie-layer interface and ceramic layer internal tiny crack, then with rare earth doped oxide ceramic with heat resistance powder
Ceramic layer is made in powder feeding spraying, and the thermal conductivity of coating is greatly reduced, extends its service life under thermal cycling.
Embodiment
Samaric nitrate, gadolinium nitrate, ytterbium nitrate, cerous nitrate, zirconium nitrate are taken, in molar ratio 5：3：2：（0.1~1）：（9.0~9.9）
Mixing is added in deionized water, stirs 20 ~ 30min with 300 ~ 400r/min, then ammonium hydroxide is added dropwise with 1 ~ 2mL/min and is produced to without precipitation
It is raw, filter residue is filtered to obtain after standing 1 ~ 2h, filter residue to cleaning solution is washed with deionized and is in neutrality, obtains presoma, presoma is put
In drying box, dry to constant weight, then be transferred in Muffle furnace at 105 ~ 110 DEG C, 1 ~ 3h is calcined at 1000 ~ 1200 DEG C, it is cold
But to 1 ~ 2h of grinding in grinder is fitted into after room temperature, ceramic with heat resistance powder is obtained, takes nickel base superalloy K417 to cut into Φ 20mm
The cylinder of × 5mm, and be cleaned by ultrasonic 2 ~ 3 times with kerosene and alcohol, then blasting treatment is carried out to its surface with corundum gravel, control
Gravel average grain diameter processed is 200 ~ 220 μm, and blasting pressure is 1.5 × 105Pa, sandblasting angle are 45 ~ 60 °, sandblasting distance for 80 ~
100mm, then cleaned with compressed air purging, pretreatment basis material is obtained, using low-voltage plasma spraying technique, in pretreatment base
Body material surface sprays a layer thickness and is 100 ~ 150 μm of middle gluing layer, and spraying is transferred to after being polished to minute surface with polishing machine
In vacuum chamber, open vacuum pump and spraying vacuum chamber is continually fed into oxygen to 100 ~ 150Pa, then with 1 ~ 2L/min, and
Be heated to 400 ~ 500 DEG C, insulation 20 ~ 30min of pre-oxidation, obtains pre-oxidation basis material, into spraying vacuum chamber respectively with 35 ~
40L/min is passed through argon gas and is passed through helium with 50 ~ 60L/min, and heats pre-oxidation basis material to 850 ~ 1000 DEG C, passes through machine
Ceramic with heat resistance powder is carried out two-tube internal powder conveying spraying, it is 20 ~ 25g/ to control powder feeding rate by the whole spray of tool hand adjustment away from for 950 ~ 1000mm
Min, is sprayed into ceramic layer thickness as 200 ~ 300 μm, obtains thermal barrier coating.
Example 1
Samaric nitrate, gadolinium nitrate, ytterbium nitrate, cerous nitrate, zirconium nitrate are taken, in molar ratio 5：3：2：0.1：9.0 mixing add deionization
In water, 20min is stirred with 300r/min, then ammonium hydroxide is added dropwise with 1mL/min and is produced to without precipitation, filter residue is filtered to obtain after standing 1h,
Filter residue to cleaning solution is washed with deionized to be in neutrality, obtains presoma, presoma is placed in drying box, it is dry at 105 DEG C
To constant weight, then it is transferred in Muffle furnace, 1h is calcined at 1000 DEG C, is fitted into after being cooled to room temperature in grinder and grinds 1h, obtain thermal boundary
Ceramic powders, take nickel base superalloy K417 to cut into the cylinder of Φ 20mm × 5mm, and are cleaned by ultrasonic 2 with kerosene and alcohol
Secondary, then carry out blasting treatment to its surface with corundum gravel, it is 200 μm to control gravel average grain diameter, blasting pressure for 1.5 ×
105Pa, sandblasting angle are 45 °, and sandblasting distance is 80mm, then is cleaned with compressed air purging, obtains pretreatment basis material, is used
Low-voltage plasma spraying technique, it is 100 μm of middle gluing layer to spray a layer thickness in pretreatment substrate material surface, and with throwing
Ray machine is transferred in spraying vacuum chamber after being polished to minute surface, opens vacuum pump spraying vacuum chamber to 100Pa, then with 1L/
Min is continually fed into oxygen, and is heated to 400 DEG C, and insulation pre-oxidation 20min, obtains pre-oxidation basis material, into spraying vacuum chamber
Argon gas is passed through with 35L/min respectively and helium is passed through with 50L/min, and heats pre-oxidation basis material to 850 DEG C, passes through machinery
Ceramic with heat resistance powder is carried out two-tube internal powder conveying spraying, it is 20g/min to control powder feeding rate, is sprayed into by the whole spray of hand adjustment away from for 950mm
Ceramic layer thickness is 200 μm, obtains thermal barrier coating.
Example 2
Samaric nitrate, gadolinium nitrate, ytterbium nitrate, cerous nitrate, zirconium nitrate are taken, in molar ratio 5：3：2：0.5：9.5 mixing add deionization
In water, 25min is stirred with 350r/min, then ammonium hydroxide is added dropwise with 1mL/min and is produced to without precipitation, filter residue is filtered to obtain after standing 1h,
Filter residue to cleaning solution is washed with deionized to be in neutrality, obtains presoma, presoma is placed in drying box, it is dry at 107 DEG C
To constant weight, then it is transferred in Muffle furnace, 2h is calcined at 1100 DEG C, is fitted into after being cooled to room temperature in grinder and grinds 1h, obtain thermal boundary
Ceramic powders, take nickel base superalloy K417 to cut into the cylinder of Φ 20mm × 5mm, and are cleaned by ultrasonic 2 with kerosene and alcohol
Secondary, then carry out blasting treatment to its surface with corundum gravel, it is 210 μm to control gravel average grain diameter, blasting pressure for 1.5 ×
105Pa, sandblasting angle are 52 °, and sandblasting distance is 90mm, then is cleaned with compressed air purging, obtains pretreatment basis material, is used
Low-voltage plasma spraying technique, it is 125 μm of middle gluing layer to spray a layer thickness in pretreatment substrate material surface, and with throwing
Ray machine is transferred in spraying vacuum chamber after being polished to minute surface, opens vacuum pump spraying vacuum chamber to 125Pa, then with 1L/
Min is continually fed into oxygen, and is heated to 450 DEG C, and insulation pre-oxidation 25min, obtains pre-oxidation basis material, into spraying vacuum chamber
Argon gas is passed through with 37L/min respectively and helium is passed through with 55L/min, and heats pre-oxidation basis material to 920 DEG C, passes through machinery
Ceramic with heat resistance powder is carried out two-tube internal powder conveying spraying, it is 22g/min to control powder feeding rate, is sprayed into by the whole spray of hand adjustment away from for 970mm
Ceramic layer thickness is 250 μm, obtains thermal barrier coating.
Example 3
Samaric nitrate, gadolinium nitrate, ytterbium nitrate, cerous nitrate, zirconium nitrate are taken, in molar ratio 5：3：2：1：9.9 mixing add deionized water
In, 30min is stirred with 400r/min, then ammonium hydroxide is added dropwise with 2mL/min and is produced to without precipitation, filter residue is filtered to obtain after standing 2h, is used
Deionized water washing filter residue to cleaning solution is in neutrality, and obtains presoma, presoma is placed in drying box, dried extremely at 110 DEG C
Constant weight, then be transferred in Muffle furnace, 3h is calcined at 1200 DEG C, is fitted into after being cooled to room temperature in grinder and grinds 2h, obtains thermal boundary pottery
Porcelain powder, takes nickel base superalloy K417 to cut into the cylinder of Φ 20mm × 5mm, and is cleaned by ultrasonic 3 times with kerosene and alcohol,
Blasting treatment is carried out to its surface with corundum gravel again, it is 220 μm to control gravel average grain diameter, blasting pressure for 1.5 ×
105Pa, sandblasting angle are 60 °, and sandblasting distance is 100mm, then is cleaned with compressed air purging, obtains pretreatment basis material, adopts
With low-voltage plasma spraying technique, the middle gluing layer that a layer thickness is 150 μm is sprayed in pretreatment substrate material surface, is used in combination
Polishing machine is transferred in spraying vacuum chamber after being polished to minute surface, opens vacuum pump spraying vacuum chamber to 150Pa, then with
2L/min is continually fed into oxygen, and is heated to 500 DEG C, and insulation pre-oxidation 30min, obtains pre-oxidation basis material, to spraying vacuum
Argon gas is passed through with 40L/min respectively in room and helium is passed through with 60L/min, and heats pre-oxidation basis material to 1000 DEG C, is led to
Manipulator adjustment spray is crossed away from for 1000mm, ceramic with heat resistance powder is subjected to two-tube internal powder conveying spraying, it is 25g/ to control powder feeding rate
Min, is sprayed into ceramic layer thickness as 300 μm, obtains thermal barrier coating.
Thermal barrier coating prepared by the present invention and the thermal barrier coating of Guangzhou company production are detected, specific detection knot
Fruit such as following table table 1：
1 thermal barrier coating performance characterization of table
The heat barrier coat material that as shown in Table 1 prepared by the present invention, thermal coefficient of expansion is low, and the high mechanical properties of material, product makes
Use long lifespan.
Claims (7)
1. a kind of thermal barrier coating, including fold the nickel base superalloy matrix set, middle gluing layer and ceramic layer, its feature successively and exist
In the chemical composition of the ceramic layer is (Sm0.5Gd0.3Yb0.2)2（CexZr1-x）2O7, wherein, 0.01≤x≤0.1.
2. a kind of thermal barrier coating as claimed in claim 1, it is characterised in that the ceramic layer is to carry out ceramic with heat resistance powder
Two-tube internal powder conveying spraying, it is 20 ~ 25g/min to control powder feeding rate, is sprayed into ceramic layer thickness as 200 ~ 300 μm.
3. a kind of thermal barrier coating as claimed in claim 2, it is characterised in that the ceramic with heat resistance powder is samaric nitrate, nitric acid
Gadolinium, ytterbium nitrate, cerous nitrate, zirconium nitrate, in molar ratio 5：3：2：（0.1~1）：（9.0~9.9）Mixing is added in deionized water and dripped
Water sedimentation is ammoniated, is made through drying and calcining.
4. a kind of thermal barrier coating as claimed in claim 1, it is characterised in that the middle gluing layer is Dy doping
The percentage composition of NiCoCrAlYTa, wherein each element are 22 ~ 24%Co, 19 ~ 21%Cr, 7.5 ~ 8.5%Al, 0.4 ~ 0.8%Y,
3.5 ~ 5.5%Ta, 0.01 ~ 0.05%Dy, nickel surplus.
5. a kind of thermal barrier coating as described in claim 1 or 4, it is characterised in that the middle gluing layer is also needed at pre-oxidation
Reason, detailed process are to be transferred to after being polished to minute surface with polishing machine in spraying vacuum chamber, open vacuum pump spraying vacuum chamber pumping is true
Sky is continually fed into oxygen to 100 ~ 150Pa, then with 1 ~ 2L/min, and is heated to 400 ~ 500 DEG C, 20 ~ 30min of insulation pre-oxidation.
6. a kind of thermal barrier coating as claimed in claim 1, it is characterised in that the nickel base superalloy matrix is nickel-base high-temperature
Alloy K417.
A kind of 7. preparation method of thermal barrier coating as described in claim 1 ~ 6 any one, it is characterised in that specific steps
For：
（1）By samaric nitrate, gadolinium nitrate, ytterbium nitrate, cerous nitrate, zirconium nitrate, in molar ratio 5：3：2：（0.1~1）：（9.0~9.9）It is mixed
Close and add in deionized water and ammonia precipitation process is added dropwise, wash to obtain presoma；
（2）1 ~ 3h is calcined after presoma is dried at 1000 ~ 1200 DEG C, grinds to obtain ceramic with heat resistance powder；
（3）Take nickel base superalloy K417 to cut into the cylinder of Φ 20mm × 5mm, carried out after being cleaned by ultrasonic 2 ~ 3 times at sandblasting
Reason, it is 200 ~ 220 μm to control gravel average grain diameter, and blasting pressure is 1.5 × 105Pa, sandblasting angle are 45 ~ 60 °, sandblasting distance
For 80 ~ 100mm, then cleaned with compressed air purging, obtain pretreatment basis material；
（4）Using low-voltage plasma spraying technique, in pretreatment substrate material surface sprays a layer thickness as 100 ~ 150 μm
Between gluing layer, and be polished to after minute surface and be transferred in spraying vacuum chamber, be evacuated to 100 ~ 150Pa, then be passed through oxygen and be heated to
400 ~ 500 DEG C, insulation 20 ~ 30min of pre-oxidation, obtains pre-oxidation basis material；
（5）Be passed through argon gas and helium into spraying vacuum chamber, and be heated to 850 ~ 1000 DEG C, adjustment spray away from for 950 ~ 1000mm into
Row powder feeding sprays, and it is 20 ~ 25g/min to control powder feeding rate, is sprayed into ceramic layer thickness as 200 ~ 300 μm, obtains thermal barrier coating.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109554656A (en) * | 2018-12-13 | 2019-04-02 | 西安交通大学 | The preparation method and system of ceramic of compact coating under a kind of room temperature atmospheric atmosphere |
| CN109663715A (en) * | 2018-12-17 | 2019-04-23 | 淄博水环真空泵厂有限公司 | A method of anti-tartar coating is prepared in large-scale water ring vacuum pump pump housing inner wall |
| CN109852846A (en) * | 2019-03-08 | 2019-06-07 | 北京矿冶科技集团有限公司 | A kind of MCrAlYX coating of achievable interface enhancing and preparation method thereof |
| CN113584419A (en) * | 2021-07-21 | 2021-11-02 | 中国科学院上海硅酸盐研究所 | Thermal barrier coating for TiAl alloy surface and preparation method thereof |
| CN113981381A (en) * | 2021-10-29 | 2022-01-28 | 昆明理工大学 | Light material surface coating for fuselage of low-altitude flight rescue unmanned aerial vehicle for fire disaster and preparation method thereof |
| CN114150254A (en) * | 2021-11-10 | 2022-03-08 | 中国科学院上海硅酸盐研究所 | Thermal barrier coating for TiAl alloy and preparation method thereof |
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| CN109554656A (en) * | 2018-12-13 | 2019-04-02 | 西安交通大学 | The preparation method and system of ceramic of compact coating under a kind of room temperature atmospheric atmosphere |
| CN109663715A (en) * | 2018-12-17 | 2019-04-23 | 淄博水环真空泵厂有限公司 | A method of anti-tartar coating is prepared in large-scale water ring vacuum pump pump housing inner wall |
| CN109852846A (en) * | 2019-03-08 | 2019-06-07 | 北京矿冶科技集团有限公司 | A kind of MCrAlYX coating of achievable interface enhancing and preparation method thereof |
| CN109852846B (en) * | 2019-03-08 | 2020-06-05 | 北京矿冶科技集团有限公司 | MCrAlYX coating capable of realizing interface strengthening and preparation method thereof |
| CN113584419A (en) * | 2021-07-21 | 2021-11-02 | 中国科学院上海硅酸盐研究所 | Thermal barrier coating for TiAl alloy surface and preparation method thereof |
| CN113981381A (en) * | 2021-10-29 | 2022-01-28 | 昆明理工大学 | Light material surface coating for fuselage of low-altitude flight rescue unmanned aerial vehicle for fire disaster and preparation method thereof |
| CN113981381B (en) * | 2021-10-29 | 2022-12-23 | 昆明理工大学 | Light material surface coating for fuselage of low-altitude flight rescue unmanned aerial vehicle for fire disaster and preparation method thereof |
| CN114150254A (en) * | 2021-11-10 | 2022-03-08 | 中国科学院上海硅酸盐研究所 | Thermal barrier coating for TiAl alloy and preparation method thereof |
| CN114150254B (en) * | 2021-11-10 | 2022-09-06 | 中国科学院上海硅酸盐研究所 | Thermal barrier coating for TiAl alloy and preparation method thereof |
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