CN114182191B - Thermal barrier coating and preparation method thereof - Google Patents
Thermal barrier coating and preparation method thereof Download PDFInfo
- Publication number
- CN114182191B CN114182191B CN202111498240.5A CN202111498240A CN114182191B CN 114182191 B CN114182191 B CN 114182191B CN 202111498240 A CN202111498240 A CN 202111498240A CN 114182191 B CN114182191 B CN 114182191B
- Authority
- CN
- China
- Prior art keywords
- bonding layer
- layer
- thermal barrier
- barrier coating
- metal oxide
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000012720 thermal barrier coating Substances 0.000 title claims abstract description 30
- 238000002360 preparation method Methods 0.000 title abstract description 11
- 238000004942 thermal barrier coating method Methods 0.000 title description 2
- 239000010410 layer Substances 0.000 claims abstract description 142
- 239000002245 particle Substances 0.000 claims abstract description 42
- 229910052751 metal Inorganic materials 0.000 claims abstract description 33
- 239000002184 metal Substances 0.000 claims abstract description 33
- 229910044991 metal oxide Inorganic materials 0.000 claims abstract description 33
- 150000004706 metal oxides Chemical class 0.000 claims abstract description 33
- 238000010438 heat treatment Methods 0.000 claims abstract description 29
- 239000012790 adhesive layer Substances 0.000 claims abstract description 24
- 229910052702 rhenium Inorganic materials 0.000 claims abstract description 7
- 229910052741 iridium Inorganic materials 0.000 claims abstract description 4
- 238000005507 spraying Methods 0.000 claims description 27
- 239000000919 ceramic Substances 0.000 claims description 20
- 239000000758 substrate Substances 0.000 claims description 13
- 230000003647 oxidation Effects 0.000 claims description 12
- 238000007254 oxidation reaction Methods 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 11
- 239000000843 powder Substances 0.000 claims description 9
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 8
- 230000008569 process Effects 0.000 claims description 8
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 7
- 239000007921 spray Substances 0.000 claims description 5
- PNEYBMLMFCGWSK-UHFFFAOYSA-N Alumina Chemical compound [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 4
- 229910000428 cobalt oxide Inorganic materials 0.000 claims description 4
- IVMYJDGYRUAWML-UHFFFAOYSA-N cobalt(ii) oxide Chemical compound [Co]=O IVMYJDGYRUAWML-UHFFFAOYSA-N 0.000 claims description 4
- 229910000480 nickel oxide Inorganic materials 0.000 claims description 4
- GNRSAWUEBMWBQH-UHFFFAOYSA-N oxonickel Chemical compound [Ni]=O GNRSAWUEBMWBQH-UHFFFAOYSA-N 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 claims description 3
- 229910052753 mercury Inorganic materials 0.000 claims description 3
- 238000004321 preservation Methods 0.000 claims description 3
- QDOXWKRWXJOMAK-UHFFFAOYSA-N dichromium trioxide Chemical compound O=[Cr]O[Cr]=O QDOXWKRWXJOMAK-UHFFFAOYSA-N 0.000 claims description 2
- 239000011159 matrix material Substances 0.000 abstract description 22
- 238000002844 melting Methods 0.000 abstract description 10
- 230000002401 inhibitory effect Effects 0.000 abstract description 5
- 230000008018 melting Effects 0.000 abstract description 5
- 238000009826 distribution Methods 0.000 abstract description 2
- 238000009792 diffusion process Methods 0.000 description 12
- 230000002829 reductive effect Effects 0.000 description 8
- 239000000203 mixture Substances 0.000 description 6
- 239000003963 antioxidant agent Substances 0.000 description 5
- 230000003078 antioxidant effect Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000005336 cracking Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 239000004576 sand Substances 0.000 description 3
- WGLPBDUCMAPZCE-UHFFFAOYSA-N Trioxochromium Chemical compound O=[Cr](=O)=O WGLPBDUCMAPZCE-UHFFFAOYSA-N 0.000 description 2
- 229910000423 chromium oxide Inorganic materials 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000000873 masking effect Effects 0.000 description 2
- SIWVEOZUMHYXCS-UHFFFAOYSA-N oxo(oxoyttriooxy)yttrium Chemical compound O=[Y]O[Y]=O SIWVEOZUMHYXCS-UHFFFAOYSA-N 0.000 description 2
- 230000002028 premature Effects 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000003213 activating effect Effects 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 229910052593 corundum Inorganic materials 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006355 external stress Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000000670 limiting effect Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- DYIZHKNUQPHNJY-UHFFFAOYSA-N oxorhenium Chemical compound [Re]=O DYIZHKNUQPHNJY-UHFFFAOYSA-N 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 229910003449 rhenium oxide Inorganic materials 0.000 description 1
- 238000005488 sandblasting Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 238000004506 ultrasonic cleaning Methods 0.000 description 1
- 229910001845 yogo sapphire Inorganic materials 0.000 description 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
-
- 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
-
- 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
- C23C4/129—Flame spraying
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The invention provides a thermal barrier coating, wherein the bonding layer comprises a first bonding layer and a second bonding layer, the distance between the first bonding layer and a metal matrix is from near to far, and the first bonding layer comprises MCrAlY particles and metal oxide particles; the total amount of the metal oxide particles in the first adhesive layer is 15% or more in terms of area percentage; the second bonding layer comprises 95.5-99.2% of MCrAlY and 0.8-4.5% of high-melting-point elements by mass percent; the high melting point element is one or more of Re, ru, ta, dy, hf and Ir. The invention also provides a preparation method of the thermal barrier coating. The invention has the advantages that: and introducing metal oxide particles into the first bonding layer, inhibiting longitudinal expansion of cracks in the bonding layer, and removing the heat treatment step on the second bonding layer, so that the distribution of high-melting-point elements such as Re, ru, ir and the like in the bonding layer is more uniform, the growth speed of TGO is inhibited, and the crack origin caused by the TGO is inhibited.
Description
Technical Field
The invention relates to the technical field of thermal barrier coatings, in particular to a thermal barrier coating and a preparation method thereof.
Background
The development of aerospace, energy power and other industries puts higher and higher requirements on aeroengines and gas turbines, and particularly brings great challenges to the heat insulation performance of turbine blade coatings and the long-term service stability of blades along with the continuous increase of the design temperature before the turbine. The most widely used thermal barrier coating (Thermal Barrier Coatings, TBC) at present is made up of a top layer of partially yttria doped zirconia (PYSZ) and a bonding layer of MCrAlY (M stands for Co and/or Ni elements).
After actual service, the surface of the turbine blade can generate local cracks, and the cracks can continuously expand inwards after forming, thereby influencing the safe operation of the unit. The external reasons for the generation of cracks are mainly fatigue of part of the blade in the service process, the internal reasons are that the adhesive layer coated on the surface of the blade matrix is poor in toughness and easy to crack, and the external reasons are mainly attributed to the following aspects: 1) The crack is originated from a thermally grown oxide layer (TGO) on the surface of the bonding layer, and after the bonding layer reaches a certain thickness, the crack is easy to crack to form a crack source under the effects of internal stress and external high-low cycle fatigue; 2) Because the toughness of the bonding layer is poor, cracks can be rapidly expanded to the interface of the metal matrix and the bonding layer under the action of external stress after the cracks are formed; 3) Because the composition of the bonding layer and the metal matrix are generally greatly different, high-temperature interdiffusion can occur in the service process, an interdiffusion layer is formed between the surface of the metal matrix and the bottom of the bonding layer, brittle sheet-shaped structures are easy to generate in the interdiffusion layer, so that the toughness is reduced, and part of cracks which are diffused to the interface between the interdiffusion layer and the bonding layer can be promoted to expand into the metal matrix.
Based on the consideration of mechanical properties, the heat treatment process and the structure composition of the superalloy substrate cannot be changed at will, so that in combination, the reduction of cracks on the surface of the service metal substrate is required from two aspects, one is to reduce stress concentration in design and avoid local premature cracking, and the other is to improve the design and preparation method of the bonding layer, and the related design or improvement is carried out from the aspects of TGO generation speed, crack expansion in the bonding layer, crack expansion in the metal substrate and the like.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a thermal barrier coating which can suppress crack propagation and has a long service life.
The invention provides a thermal barrier coating, which comprises a bonding layer and a ceramic layer, wherein the bonding layer is sprayed on the outer surface of a metal matrix, the bonding layer comprises a first bonding layer and a second bonding layer, the distance between the first bonding layer and the metal matrix is from near to far, the first bonding layer comprises MCrAlY particles and metal oxide particles, and M in the MCrAlY represents Co and/or Ni elements; the total amount of the metal oxide particles in the first adhesive layer is 15% or more in terms of area percentage; the second bonding layer comprises 95.5-99.2% of MCrAlY and 0.8-4.5% of high-melting-point elements in percentage by mass, wherein M represents Co and/or Ni elements; the high-melting-point element is one or more of Re, ru, ta, dy, hf and Ir.
Preferably, the ceramic layer is spray coated from a partially yttria-doped zirconia powder.
Preferably, the ceramic layer has a thickness of 250-550 μm.
Preferably, the metal oxide particles include alpha-alumina, chromia, nickel oxide, and cobalt oxide.
Preferably, the thickness of the first adhesive layer in the adhesive layer is 50-70%, and the thickness of the second adhesive layer in the adhesive layer is 30-50%.
Preferably, the total amount of metal oxide particles in the second adhesive layer is 3% or less in terms of area percentage.
The invention also provides a preparation method of the thermal barrier coating, which comprises the following steps:
s1, spraying a first bonding layer on the outer surface of a metal matrix, forming metal oxide particles among MCrAlY particles by adjusting the oxidation degree of powder in the spraying process, and ensuring that the area percentage of the metal oxide particles in the first bonding layer is more than 15% by controlling parameters;
s2, carrying out vacuum heat treatment on the first bonding layer;
s3, spraying a second bonding layer on the surface of the first bonding layer after the heat treatment is finished;
s4, spraying a ceramic layer on the surface of the second bonding layer.
Preferably, in the S2, the vacuum heat treatment includes: the vacuum degree of heat treatment is not less than 0.3Pa (2 micrometer mercury injection), the heat treatment temperature is 1080+/-10 ℃, the heat preservation time is 1h, the heating rate is less than 10-25K/min, the cooling rate is 20-40K/min, and the vacuum heat treatment is carried out on the first bonding layer.
The invention improves the environment of inhibiting crack generation and propagation, and is beneficial in that: 1, introducing metal oxide particles into a first bonding layer, inhibiting longitudinal expansion of cracks in the bonding layer and interdiffusion of bonding layer components and a metal matrix, thereby reducing the growth speed of an interdiffusion layer and further inhibiting the expansion of the cracks in the metal matrix; 2, removing the heat treatment step of the second bonding layer, so that the high-melting-point elements such as Re, ru, ta, dy, hf, ir and the like are distributed more uniformly in the bonding layer, and the growth speed of TGO is restrained, thereby restraining the crack origin caused by the TGO; and 3, changing the existing bonding layer into a combination of the first bonding layer and the second bonding layer, so that the method can be applied to conventional spraying without carrying out large process modification, and can inhibit crack growth in all directions, thereby inhibiting cracking of the serving part.
Drawings
FIG. 1 is a schematic structural view of a thermal barrier coating of the present invention;
FIG. 2 is a schematic illustration of two distribution patterns of high melting point elements in a bonding layer;
FIG. 3 is a flow chart of a vacuum thermal diffusion process performed on a first bonding layer in one embodiment.
Description of element numbers:
1. metal matrix
2. Inter-diffusion layer
3. First adhesive layer
4. Second adhesive layer
5. Ceramic layer
Detailed Description
The following describes the embodiments of the present invention in further detail with reference to the accompanying drawings. These embodiments are merely illustrative of the present invention and are not intended to be limiting.
As shown in fig. 1, the conventional thermal barrier coating mainly comprises a bonding layer and a ceramic layer 5, wherein the bonding layer and the ceramic layer are sprayed on the outer surface of a metal substrate 1, and can play a role in resisting oxidation corrosion and matching thermal expansion coefficients, and can generate high-temperature interdiffusion in the high-temperature service process, so that an interdiffusion layer 2 is formed between the surface of the metal substrate 1 and the bottom of the bonding layer. The thermal barrier coating of the present invention is based on a conventional thermal barrier coating, the bond coat comprising a first bond coat 3 and a second bond coat 4 at a distance from the metal substrate 1 from near to far.
The first bond coat 3 comprises MCrAlY particles and metal oxide particles, M in MCrAlY representing Co and/or Ni elements; the total amount of the metal oxide particles in the first adhesive layer 3 is 15% or more in terms of area percentage. The second bonding layer 4 comprises 95.5-99.2% of MCrAlY and 0.8-4.5% of high melting point elements by mass percent, wherein M represents Co and/or Ni elements; the high melting point element is one or more of Re, ru, ta, dy, hf and Ir. The total amount of the metal oxide particles in the second adhesive layer 4 is 3% or less in terms of area percentage.
In the first binder layer 3, the metal oxide particles are generally a mixture mainly composed of α -alumina and containing chromium oxide, nickel oxide, and cobalt oxide, and the specific composition varies depending on the MCrAlY powder composition selected. In a specific embodiment of the invention, the metal oxide in the first adhesive layer 3 has the following composition in mass percent: 25.39% of aluminum oxide, 19.78% of chromium oxide, 21.85% of cobalt oxide, 32.69% of nickel oxide, and 0.29% of the sum of rhenium oxide, yttrium oxide and other impurity oxides. The upper limit of the area percentage of the metal oxide particles takes the bonding strength of the bonding layer after heat treatment as an examination standard, the single bonding strength is not lower than 40MPa, and the average value of 5 times of testing is not lower than 50MPa.
Since Al in the bonding layer reacts with oxygen diffused from the ceramic layer 5 in a high temperature environment, a layer of TGO, whose main component is α -Al2O3, is formed between the bonding layer/ceramic layer 5 interface, which can effectively prevent oxidation of the metal substrate 1 as an oxidation-resistant film. However, cracks also easily originate from the TGO and eventually propagate into the metal matrix 1. To solve this problem, the present invention provides two adhesive layers. The presence of the metal oxide particles can lead the crack which is extended into the first bonding layer 3 to be prone to be transversely extended, so that the longitudinal extension of the crack in the first bonding layer 3 and the induction effect of the crack on the metal matrix 1 are restrained, meanwhile, the mutual diffusion of elements between the first bonding layer 3 and the metal matrix 1 is restrained through the total amount of the metal oxide particles, the cracking tendency of the mutual diffusion layer 2 is reduced, and the loss of oxidation resistant element Al in the first bonding layer 3 can be effectively slowed down. In the present invention, therefore, the area percentage of the metal oxide particles in the first adhesive layer 3 is set to 15% or more. For the second bonding layer 4 adjacent to the ceramic layer 5, the addition of the high melting point element Re, ru, ta, dy, hf, ir and the like can slow down the diffusion speed of the antioxidant element Al and avoid the premature failure of the antioxidant film, but too many metal oxide particles can prevent the diffusion of the antioxidant element Al in the second bonding layer 4, so that the antioxidant film cannot be generated in time, therefore, the invention controls the area percentage of the metal oxide particles in the second bonding layer 4 to be below 3 percent and ensures the stable existence of the antioxidant film.
In a specific implementation, the thickness of the first adhesive layer 3 in the adhesive layer is 50-70%, and the thickness of the second adhesive layer 4 in the adhesive layer is 30-50%. The thickness ratio of the first adhesive layer 3 and the second adhesive layer 4 in the adhesive layers can be adjusted according to actual needs by those skilled in the art. The ceramic layer 5 is formed by spraying a part of yttrium oxide doped zirconia (PYSZ) or other ceramic materials, and the spraying mode can be common ceramic layer preparation modes such as APS, EB-PVD and the like. The thickness of the ceramic layer 5 is 250-550 μm.
The invention also provides a preparation method of the thermal barrier coating, which comprises the following steps:
s1, spraying a first bonding layer 3 on the outer surface of the metal matrix 1, forming metal oxide particles among MCrAlY particles by adjusting the oxidation degree of powder in the spraying process, and ensuring that the area percentage of the metal oxide particles in the first bonding layer 3 is more than 15% by controlling parameters.
S2, carrying out vacuum heat treatment on the first bonding layer 3, so that interfaces among particles in the first bonding layer 3 disappear and are homogenized, elements at the interfaces between the first bonding layer 3 and the metal matrix 1 are diffused, and the thermal shock resistance of the thermal barrier coating is improved.
And S3, spraying a second bonding layer 4 on the surface of the first bonding layer 3 after the heat treatment, and controlling parameters to ensure that the area percentage of the metal oxide particles in the second bonding layer 4 is less than 3%.
As shown in figure 2, before the bonding layer is sprayed and heat treatment is carried out on the bonding layer, the high-melting elements are in an unsteady state, so that the high-melting elements can be uniformly distributed in the bonding layer, the diffusion speed of the oxidation resistant element Al in the bonding layer is reduced, the growth speed of TGO is reduced, and the overall oxidation performance of the thermal barrier coating is improved. However, after high-temperature heat treatment, the high-melting point elements generally reach a steady state, and are agglomerated to form a phase rich in the high-melting point elements, so that the total amount of the high-melting point elements in other areas is reduced, the diffusion speed of elements such as Al is increased, and the oxidation resistance is reduced.
Therefore, in the preparation method of the thermal barrier coating, the second bonding layer 4 added with the high-melting-point element is not subjected to vacuum heat treatment, and meanwhile, the total amount of metal oxide particles in the second bonding layer 4 is strictly controlled, so that the oxidation performance of the whole thermal barrier coating is ensured to meet the requirement.
And S4, spraying a ceramic layer 5 on the surface of the second bonding layer 4.
In summary, the bonding layer in the thermal barrier coating is divided into two parts, the first bonding layer 3 is close to the metal substrate 1, an oxide layer is introduced into the first bonding layer 3 and is subjected to vacuum heat treatment, the oxide layer can slow down the longitudinal expansion speed of cracks in the bonding layer, so that the cracks tend to deflect transversely, meanwhile, the high-temperature diffusion between the bonding layer and the metal substrate can be restrained, the inter-diffusion of the surface of the metal substrate is reduced, the growth speed of 2 is increased, the toughness of the inter-diffusion layer 2 is prevented from being reduced, and therefore the crack diffusion is further restrained, and meanwhile, the operability and the production cost are both considered; the second bonding layer 4 is close to the ceramic layer 5, and a vacuum heat treatment step is removed in the preparation process of the second bonding layer 4 added with the high-melting-point element, so that the high-melting-point element is uniformly distributed in the bonding layer in an unsteady state, and the oxidation resistance of the bonding layer is further improved.
In connection with fig. 1, one specific preparation example of the thermal barrier coating of the present invention is as follows:
step 1: cleaning, namely cleaning the surface of the metal matrix 1 to be sprayed, checking whether oil stains exist on the surface of the metal matrix 1 or not, and performing ultrasonic cleaning on the surface;
step 2: masking: masking the non-spraying area of the metal matrix 1 by a tool or an adhesive tape, and visually detecting whether the non-spraying area is masked;
step 3: sand blasting: spraying sand on the shielded spraying area of the metal matrix 1, activating the surface, wherein the sand spraying adopts 30 mesh silicon carbide sand, the pressure is 2bar, and the roughness of the sprayed surface reaches Ra (alpha) 5-6 mu m;
step 4: spraying a first bonding layer 3: the first bonding layer 3 is sprayed by supersonic flame, the spraying thickness is between 50-70% of the total thickness of the bonding layer and is 100-140 micrometers (calculated according to the total thickness of 200 micrometers), the total amount of metal oxide particles in the first bonding layer 3 is controlled to be more than 15%, such as 18%, by controlling parameters, the bonding strength is not lower than 40MPa in a single time, and the average value of 5 times of testing is not lower than 50MPa. The porosity is controlled within 2%.
Step 5: the vacuum heat treatment is as shown in fig. 3: the first adhesive layer 3 is vacuum heat-treated at a heat treatment vacuum degree of 0.3Pa (2 μm mercury injection) or more, a heat treatment temperature of 1080 ℃ + -10 ℃, a heat preservation time of 1h, a heating rate of less than 10-25K/min, and a cooling rate of 20-40K/min.
Step 6: spraying a second bonding layer 4: the second bonding layer 4 is sprayed by supersonic flame, the spraying thickness is between 30 and 50 percent of the total thickness of the bonding layer, and is 60 to 100 microns (calculated according to the total thickness of 200 microns), the total amount of metal oxide particles is controlled within 3 percent by adjusting parameters, the porosity is controlled within 2 percent, and the surface roughness is Ra is 9 to 14 microns.
Step 7: and (3) spraying a ceramic layer 5: and (3) spraying a 250-550 mu m YSZ surface layer by using a plasma spraying technology, wherein the porosity is controlled to be 8-15%.
The following materials and equipment were used in this example:
the metal matrix 1 adopts a sheet material of Rene80 high-temperature alloy Ni60Cr14Co9.5Ti5Mo4W4Al3, with the diameter of 25mm and the thickness of 5 mm.
Supersonic flame gun: JER KOAT spray gun.
YSZ plasma flame spray gun: and F4, spraying gun.
The MCrAlY powder used for the first bond coat 3 and the second bond coat 4 was commercially available under the trade designation SICOAT 2464. Powder particle size range 22-45 microns, re content wt%:1 to 1.8 percent.
The YSZ material is preferably ZrO 2 7Y 2 O 3 (Metro 234A), powder particle size 16-90 μm, spray thickness 300 μm, porosity 15%.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications and substitutions can be made by those skilled in the art without departing from the technical principles of the present invention, and these modifications and substitutions should also be considered as being within the scope of the present invention.
Claims (8)
1. A thermal barrier coating comprising a bonding layer and a ceramic layer (5) sprayed on the outer surface of a metal substrate (1), characterized in that the bonding layer comprises a first bonding layer (3) and a second bonding layer (4) which are arranged at a distance from the metal substrate (1) from near to far,
the first binding layer (3) comprises MCrAlY particles and metal oxide particles, wherein M in the MCrAlY represents Co and/or Ni elements; the total amount of the metal oxide particles in the first adhesive layer (3) is 15% or more in terms of area percentage;
the second bonding layer (4) comprises 95.5-99.2% of MCrAlY and 0.8-4.5% of high-melting-point elements in percentage by mass, wherein M represents Co and/or Ni elements; the high-melting-point element is one or more of Re, ru, ta, dy, hf and Ir.
2. Thermal barrier coating according to claim 1, characterized in that the ceramic layer (5) is spray-coated from a partly yttria-doped zirconia powder.
3. Thermal barrier coating according to claim 1 or 2, characterized in that the thickness of the ceramic layer (5) is 250-550 μm.
4. The thermal barrier coating of claim 1, wherein the metal oxide particles comprise alpha-alumina, chromia, nickel oxide, and cobalt oxide.
5. The thermal barrier coating according to claim 1, characterized in that the thickness of the first bonding layer (3) in the bonding layer is 50-70% and the thickness of the second bonding layer (4) in the bonding layer is 30-50%.
6. The thermal barrier coating according to claim 1, characterized in that the total amount of metal oxide particles in the second bond coat layer (4) is 3% or less in area percent.
7. A method of preparing a thermal barrier coating as claimed in claim 1, comprising the steps of:
s1, spraying a first bonding layer (3) on the outer surface of a metal substrate (1), forming metal oxide particles among MCrAlY particles by adjusting the oxidation degree of powder in the spraying process, and ensuring that the area percentage of the metal oxide particles in the first bonding layer (3) is more than 15% by controlling parameters;
s2, carrying out vacuum heat treatment on the first bonding layer (3);
s3, spraying a second bonding layer (4) on the surface of the first bonding layer (3) after the heat treatment is finished;
s4, spraying a ceramic layer (5) on the surface of the second bonding layer (4).
8. The method according to claim 7, wherein in S2, the vacuum heat treatment comprises: the vacuum degree of heat treatment is not less than 0.3Pa (2 micrometer mercury injection), the heat treatment temperature is 1080+/-10 ℃, the heat preservation time is 1h, the heating rate is less than 10-25K/min, the cooling rate is 20-40K/min, and the first bonding layer (3) is subjected to vacuum heat treatment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111498240.5A CN114182191B (en) | 2021-12-09 | 2021-12-09 | Thermal barrier coating and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111498240.5A CN114182191B (en) | 2021-12-09 | 2021-12-09 | Thermal barrier coating and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114182191A CN114182191A (en) | 2022-03-15 |
| CN114182191B true CN114182191B (en) | 2023-12-08 |
Family
ID=80604036
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111498240.5A Active CN114182191B (en) | 2021-12-09 | 2021-12-09 | Thermal barrier coating and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114182191B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1999043861A1 (en) * | 1998-02-28 | 1999-09-02 | General Electric Company | Multilayer bond coat for a thermal barrier coating system and process therefor |
| CN103668191A (en) * | 2013-12-09 | 2014-03-26 | 广州有色金属研究院 | Preparation method for thermal-barrier coating |
| CN106119760A (en) * | 2016-07-28 | 2016-11-16 | 西安石油大学 | A kind of thermal barrier coating with double-deck tack coat and preparation method thereof |
| JP2020033589A (en) * | 2018-08-29 | 2020-03-05 | 株式会社ディ・ビー・シー・システム研究所 | Heat resistant alloy member and method for manufacturing the same, high temperature apparatus and method for manufacturing the same, and member for manufacturing heat resistant alloy member |
| CN212451590U (en) * | 2020-06-23 | 2021-02-02 | 中国航发商用航空发动机有限责任公司 | Thermal barrier coating for a gradient cte bond coat |
-
2021
- 2021-12-09 CN CN202111498240.5A patent/CN114182191B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1999043861A1 (en) * | 1998-02-28 | 1999-09-02 | General Electric Company | Multilayer bond coat for a thermal barrier coating system and process therefor |
| CN103668191A (en) * | 2013-12-09 | 2014-03-26 | 广州有色金属研究院 | Preparation method for thermal-barrier coating |
| CN106119760A (en) * | 2016-07-28 | 2016-11-16 | 西安石油大学 | A kind of thermal barrier coating with double-deck tack coat and preparation method thereof |
| JP2020033589A (en) * | 2018-08-29 | 2020-03-05 | 株式会社ディ・ビー・シー・システム研究所 | Heat resistant alloy member and method for manufacturing the same, high temperature apparatus and method for manufacturing the same, and member for manufacturing heat resistant alloy member |
| CN212451590U (en) * | 2020-06-23 | 2021-02-02 | 中国航发商用航空发动机有限责任公司 | Thermal barrier coating for a gradient cte bond coat |
Non-Patent Citations (3)
| Title |
|---|
| 中国科学技术协会 主编.《材料腐蚀学科发展报告》.中国科学技术出版社,2012,第62页. * |
| 沈承金 等编.《材料热处理与表面工程》.中国矿业大学出版社,2017,第283页. * |
| 王振廷 等主编.《材料表面工程技术》.哈尔滨工业大学出版社,2011,第35-36页. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114182191A (en) | 2022-03-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1640477B2 (en) | High temperature component with thermal barrier coating and gas turbine using the same | |
| JP4645030B2 (en) | Heat resistant member with thermal barrier coating | |
| JP5561733B2 (en) | Gas turbine component having thermal barrier coating and gas turbine using the same | |
| EP2053141A1 (en) | Alumina-based protective coatings for thermal barrier coatings | |
| US20120251777A1 (en) | Component for a turbomachine and method for manufacturing such a component | |
| JP2013515171A (en) | Coating system and coating product for protecting substrates exposed to high temperatures and harsh environments | |
| JP2008095193A (en) | Segmented abradable coating and process for applying the same | |
| JP7232295B2 (en) | Adhesion-promoting layer for bonding high-temperature protective layer onto substrate, and method for producing same | |
| KR101681195B1 (en) | Thermal Barrier Coating System with Self-Healing Ability | |
| US11852078B2 (en) | Reflective coating and coating process therefor | |
| US11319829B2 (en) | Geometrically segmented abradable ceramic thermal barrier coating with improved spallation resistance | |
| CN112176275B (en) | Thermal barrier coating and preparation method and application thereof | |
| JP5905354B2 (en) | Thermal barrier coating on power generation gas turbine blades and power generation gas turbine using the same | |
| US20150284834A1 (en) | Method for applying a high-temperature stable coating layer on the surface of a component and component with such a coating layer | |
| US20110086163A1 (en) | Method for producing a crack-free abradable coating with enhanced adhesion | |
| JP2013249487A (en) | Gas turbine blade for power generation and gas turbine for power generation | |
| CN110527940B (en) | High-bonding-strength high-temperature-oxidation-resistant porous MCrAlY abradable coating and preparation method thereof | |
| JP2002339052A (en) | Heat-insulating film coated member and thermal-spray powder | |
| WO2012029540A1 (en) | Heat-masking coating film, process for production thereof, and heat-resistant alloy members using the same | |
| CN114182191B (en) | Thermal barrier coating and preparation method thereof | |
| JP5702749B2 (en) | Gas turbine blade, combustor, shroud, and gas turbine using them | |
| JP2018003103A (en) | Thermal barrier coating method, thermal barrier coating film and turbine member | |
| CN114592164B (en) | DVC thermal barrier coating and preparation method and application thereof | |
| Wortman et al. | Bond coat development for thermal barrier coatings | |
| CN113789496A (en) | Preparation method of self-healing gradient thermal barrier coating |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |