CN115341174B - Lanthanum zirconium praseodymium oxygen thermal barrier coating material and preparation method thereof - Google Patents
Lanthanum zirconium praseodymium oxygen thermal barrier coating material and preparation method thereof Download PDFInfo
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- CN115341174B CN115341174B CN202210913423.7A CN202210913423A CN115341174B CN 115341174 B CN115341174 B CN 115341174B CN 202210913423 A CN202210913423 A CN 202210913423A CN 115341174 B CN115341174 B CN 115341174B
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- 239000012720 thermal barrier coating Substances 0.000 title claims abstract description 59
- -1 Lanthanum zirconium praseodymium oxygen Chemical compound 0.000 title claims abstract description 45
- 239000000463 material Substances 0.000 title claims abstract description 31
- 238000002360 preparation method Methods 0.000 title claims abstract description 11
- 239000013077 target material Substances 0.000 claims abstract description 13
- 238000001704 evaporation Methods 0.000 claims abstract description 9
- 230000008021 deposition Effects 0.000 claims abstract description 8
- 238000010894 electron beam technology Methods 0.000 claims abstract description 8
- 230000008020 evaporation Effects 0.000 claims abstract description 7
- 239000002994 raw material Substances 0.000 claims description 12
- 238000005328 electron beam physical vapour deposition Methods 0.000 claims description 11
- 238000007747 plating Methods 0.000 claims description 9
- 238000010532 solid phase synthesis reaction Methods 0.000 claims description 9
- 238000000151 deposition Methods 0.000 claims description 7
- 238000002156 mixing Methods 0.000 claims description 7
- 229910021193 La 2 O 3 Inorganic materials 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 238000000498 ball milling Methods 0.000 claims description 5
- 230000015572 biosynthetic process Effects 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims description 5
- 238000003786 synthesis reaction Methods 0.000 claims description 5
- 238000011049 filling Methods 0.000 claims description 3
- 239000000126 substance Substances 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 abstract description 9
- 238000000576 coating method Methods 0.000 abstract description 9
- 239000013078 crystal Substances 0.000 abstract description 4
- 238000005137 deposition process Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 7
- 239000012071 phase Substances 0.000 description 4
- 230000002194 synthesizing effect Effects 0.000 description 4
- 238000013329 compounding Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 229910052746 lanthanum Inorganic materials 0.000 description 3
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 description 3
- 230000007774 longterm Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000006467 substitution reaction Methods 0.000 description 3
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000011068 loading method Methods 0.000 description 2
- 229910052761 rare earth metal Inorganic materials 0.000 description 2
- 238000005303 weighing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 150000002910 rare earth metals Chemical class 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 229910052727 yttrium Inorganic materials 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/08—Oxides
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/24—Vacuum evaporation
- C23C14/28—Vacuum evaporation by wave energy or particle radiation
- 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
- C23C14/22—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
- C23C14/32—Vacuum evaporation by explosion; by evaporation and subsequent ionisation of the vapours, e.g. ion-plating
- C23C14/325—Electric arc evaporation
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention belongs to the technical field of thermal barrier coatings of aero-engines, and relates to a lanthanum-zirconium-praseodymium-oxygen thermal barrier coating material and a preparation method thereof, wherein the molecular formula of a lanthanum-zirconium-praseodymium-oxygen target material is La 2 (Zr x Pr 1‑x ) 2 O 7 Wherein x=0.1-0.3; selecting deposition process parameters: vacuum degree of deposition chamber<5×10 ‑4 Torr; the beam intensity of the electron beam is 1.3-1.5A; the temperature of the sample is 800-1000 ℃; the evaporation time is 30-80min; and controlling the evaporation time of the seed target, and finally obtaining the lanthanum-zirconium-praseodymium-oxygen thermal barrier coating on the rotating sample. The thermal barrier coating material has a thermal expansion coefficient which is close to that of YSZ, has lower thermal conductivity, and has a unique columnar crystal structure and a better service life; the invention can not only ensure the reduction of the heat conductivity of the coating, but also improve the service temperature of the coating, and can also improve the practical problems of insufficient service life and low thermal expansion coefficient of the coating.
Description
Technical Field
The invention belongs to the technical field of thermal barrier coatings of aeroengines, and relates to a lanthanum-zirconium-praseodymium-oxygen thermal barrier coating material and a preparation method thereof.
Background
At present, with the continuous improvement of the thrust and the working efficiency of a gas turbine, the gas inlet temperature is also higher and higher, and the turbine blades and other hot end components are usedThe operating temperature of nickel-base superalloys has gradually approached its service temperature limit. The thermal barrier coating (Thermal Barrier Coatings, TBCs) is a surface protection technology for compounding a ceramic material with a metal matrix in a coating mode by utilizing the high temperature resistance, scouring resistance, corrosion resistance and low thermal conductivity of the ceramic material, so as to improve the working temperature of the metal component, enhance the high temperature resistance of the hot end component, prolong the service life of the hot end component and improve the working efficiency of an engine. Currently, the widely used YSZ (6-8 wt.% Y) 2 O 3 Partially stabilized ZrO 2 ) The long-term maximum service temperature of the thermal barrier coating material cannot exceed 1200 ℃, and volume expansion occurs due to monoclinic phase generation caused by phase change during cooling, thereby leading to coating failure. However, the long-term service temperature of the thermal barrier coating materials of the next generation of high performance aeroengines must exceed 1200 ℃. Therefore, research on novel thermal barrier coating materials has become a key topic for developing next-generation high-performance aeroengines.
Disclosure of Invention
The invention provides a lanthanum zirconium praseodymium oxygen thermal barrier coating material and a preparation method thereof, which aim to solve the problems that the service life of a single lanthanum zirconate thermal barrier coating is insufficient and the service temperature of YSZ is not higher than 1200 ℃ by rare earth compounding, simultaneously reduce the thermal conductivity of the material and improve the thermal expansion coefficient of the material.
In order to solve the technical problem, the technical scheme of the invention is as follows:
in one aspect, a lanthanum zirconium praseodymium oxygen thermal barrier coating material is provided, and the chemical molecular formula of the lanthanum zirconium praseodymium oxygen thermal barrier coating material is La 2 (Zr x Pr 1-x ) 2 O 7 Wherein x=0.1-0.3.
On the other hand, the preparation method of the lanthanum-zirconium praseodymium-oxygen thermal barrier coating comprises the following steps:
step one, raw material La 2 O 3 、PrO 2 、ZrO 2 Mixing according to the molecular formula ratio of the materials, and synthesizing a lanthanum-zirconium-praseodymium-oxygen target material by a high-temperature solid-phase method at 1800-2000 ℃;
preparing a metal bottom layer with NiCoCrAlYHf serving as a thermal barrier coating by adopting vacuum arc plating equipment, wherein the voltage is 600-650V, and the current is 10-20A;
step three, filling a lanthanum-zirconium-praseodymium-oxygen target material into electron beam physical vapor deposition equipment, evaporating the lanthanum-zirconium-praseodymium-oxygen target material by using an electron beam, preparing a lanthanum-zirconium-praseodymium-oxygen thermal barrier coating on a NiCoCrAlYHf bottom layer, wherein the beam intensity of the electron beam is 1.3-1.5A, and the temperature of a sample is 800-1000 ℃;
step one raw material La 2 O 3 、PrO 2 、ZrO 2 The purity of the product is more than or equal to 99.9 percent.
Step one, the raw material mixing is mechanical ball milling, and the time is more than or equal to 8 hours.
The synthesis time of the step one high-temperature solid phase method is more than or equal to 12 hours.
Vacuum degree of vacuum arc plating equipment in the second step<1×10 -2 Pa; the deposition time of the vacuum arc plating equipment is more than or equal to 100min.
Vacuum degree of electron beam physical vapor deposition equipment in step three<5×10 -2 Pa, the evaporation time of the thermal barrier coating is 30-80min, and the deposited thermal barrier coating is naturally cooled to below 200 ℃ along with a furnace.
The beneficial effects of the invention are as follows: as a novel thermal barrier coating material, the lanthanum-zirconium-praseodymium-oxygen thermal barrier coating has no phase change after long-term heat treatment at 1200 ℃, has stable tissue structure (shown in figure 4) and has high phase stability. Their thermal expansion coefficients are relatively close to YSZ (as shown in fig. 2), and have lower thermal conductivity (as shown in fig. 1) and better fracture toughness. Meanwhile, the lanthanum-zirconium-praseodymium-oxygen thermal barrier coating is prepared by utilizing an electron beam physical vapor deposition technology, so that the lanthanum-zirconium-praseodymium-oxygen thermal barrier coating has a unique columnar crystal structure (shown in figure 4) and has good thermal cycle performance (shown in figure 3).
Drawings
FIG. 1 is a schematic view of the thermal conductivity of example 2;
FIG. 2 is a schematic diagram of the thermal expansion coefficient of example 2;
FIG. 3 is a schematic diagram of thermal life of example 2;
FIG. 4 is a schematic diagram of the columnar crystal structure of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without making any inventive effort are intended to fall within the scope of the present invention.
Features of various aspects of embodiments of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely for a better understanding of the invention by showing examples of the invention. The present invention is not limited to any particular arrangement and method provided below, but covers any modifications, substitutions, etc. of all product constructions, methods, and the like covered without departing from the spirit of the invention.
Well-known structures and techniques have not been shown in detail in the various drawings and the following description in order not to unnecessarily obscure the present invention.
Lanthanum zirconium praseodymium oxygen thermal barrier coating material, wherein the chemical molecular formula of the lanthanum zirconium praseodymium oxygen thermal barrier coating material is La 2 (Zr x Pr 1-x ) 2 O 7 Wherein x=0.1-0.3.
The preparation method of the lanthanum-zirconium-praseodymium-oxygen thermal barrier coating material coating comprises the following steps:
by mixing La as raw material 2 O 3 、PrO 2 、ZrO 2 Mixing according to the molecular formula ratio of the materials, wherein the purity of the raw materials is more than or equal to 99.9%, and the mixing mode is mechanical ball milling for more than or equal to 8 hours; synthesizing a lanthanum zirconium praseodymium oxygen target material by a high-temperature solid phase method, wherein the synthesis temperature is 1600-1800 ℃, and the synthesis time is more than or equal to 12 hours; preparation of a metallic underlayer with NiCoCrAlYHf as a thermal barrier coating by vacuum arc plating equipmentVacuum degree<1×10 -2 Pa, the voltage is 600-650V, the current is 10-20A, and the deposition time is more than or equal to 100min; filling the prepared target material into electron beam physical vapor deposition equipment, and vacuum degree<5×10 -2 P, the beam intensity of the electron beam is 1.3-1.5A, the evaporation time is 30-80min, the thermal barrier coating is prepared, and the thermal barrier coating is naturally cooled to below 200 ℃ along with a furnace.
Example 1:
the preparation method comprises the following steps: molecular formula La of lanthanum zirconium praseodymium oxygen thermal barrier coating material 2 (Zr 0.85 Pr 0.15 ) 2 O 7 Weighing raw material La 2 O 3 、PrO 2 、ZrO 2 。
And (3) carrying out high-temperature solid phase synthesis: mechanically ball-milling the raw materials for 10 hours, and synthesizing a lanthanum-zirconium-praseodymium-oxygen target material by a high-temperature solid-phase method at 1950 ℃ for 16 hours;
(3) Preparing a bottom layer: vacuum arc plating equipment is adopted to prepare a metal bottom layer with NiCoCrAlYHf as a thermal barrier coating, and the vacuum degree is high<1×10 -2 Pa, the voltage is 625V, the current is 12A, and the deposition time is 150min;
(4) Preparing a thermal barrier coating: and loading the lanthanum-zirconium-praseodymium-oxygen target material into electron beam physical vapor deposition equipment. Deposition process parameters: vacuum degree<5×10 -2 Pa, the electron beam intensity is 1.35A, the evaporation time is 60min, and after cooling to below 200 ℃, the deposition equipment is opened to obtain the lanthanum zirconium praseodymium oxygen thermal barrier coating.
The thermal conductivity of the prepared lanthanum zirconium praseodymium oxygen thermal barrier coating is 1.35W/(mK) at the temperature of 1000 ℃; the thermal expansion coefficient is 10.76 multiplied by 10 -6 K -1 The method comprises the steps of carrying out a first treatment on the surface of the The thermal life was 750 hours.
Example 2:
the preparation method comprises the following steps: molecular formula La of lanthanum zirconium praseodymium oxygen thermal barrier coating material 2 (Zr 0.75 Pr 0.25 ) 2 O 7 Weighing raw material La 2 O 3 、PrO 2 、ZrO 2 。
And (3) carrying out high-temperature solid phase synthesis: mechanically ball-milling the raw materials for 16 hours, and synthesizing a lanthanum-zirconium-praseodymium-oxygen target material by a 1850 ℃ high-temperature solid phase method for 20 hours;
(3) Preparing a bottom layer: by usingVacuum arc plating equipment for preparing metal bottom layer with NiCoCrAlYHf as thermal barrier coating, vacuum degree<1×10 -2 Pa, voltage 645V, current 14A, deposition time 175min;
(4) Preparing a thermal barrier coating: and loading the lanthanum-zirconium-praseodymium-oxygen target material into electron beam physical vapor deposition equipment. Deposition process parameters: vacuum degree<5×10 -2 Pa, the electron beam intensity is 1.45A, the evaporation time is 45min, and after cooling to below 200 ℃, the deposition equipment is opened to obtain the lanthanum-zirconium-praseodymium-oxygen thermal barrier coating.
Under the condition of the process method, the thermal conductivity of the prepared lanthanum-zirconium-praseodymium-oxygen thermal barrier coating is 1.28W/(mK) at the temperature of 1000 ℃; coefficient of thermal expansion of 10.62X10 -6 K -1 The method comprises the steps of carrying out a first treatment on the surface of the The thermal life was 850 hours.
As can be seen from the above embodiments in combination with the accompanying drawings, the technical scheme of the present invention: (1) The thermal barrier coating prepared by utilizing the electron beam physical vapor deposition technology can have a unique columnar crystal structure and good thermal cycle performance. (2) In the design of the coating, the uniform coating structure is obtained by compounding rare earth elements, and the invention can reduce the heat conductivity of the lanthanum zirconate coating and improve the practical problem of insufficient service life of single lanthanum zirconate.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think about various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered in the scope of the present invention.
Claims (9)
1. A lanthanum zirconium praseodymium oxygen thermal barrier coating material is characterized in that: the chemical molecular formula of the lanthanum zirconium praseodymium oxygen thermal barrier coating material is La 2 (Zr 0.85 Pr 0.15 ) 2 O 7 ；
The preparation method of the thermal barrier coating comprises the following steps:
step one, raw material La 2 O 3 、PrO 2 、ZrO 2 Mixing according to the molecular formula ratio of the materialsSynthesizing a lanthanum zirconium praseodymium oxygen target material by a high-temperature solid phase method, wherein the synthesis temperature is 1800-2000 ℃;
preparing a metal bottom layer with NiCoCrAlYHf serving as a thermal barrier coating by adopting vacuum arc plating equipment, wherein the voltage is 600-650V, and the current is 10-20A;
step three, filling a lanthanum-zirconium-praseodymium-oxygen target material into an electron beam physical vapor deposition device, evaporating the lanthanum-zirconium-praseodymium-oxygen target material by using an electron beam, preparing a lanthanum-zirconium-praseodymium-oxygen thermal barrier coating on a NiCoCrAlYHf bottom layer, wherein the beam intensity of the electron beam is 1.3-1.5A, and the temperature of a sample is 800-1000 ℃.
2. The lanthanum zirconium praseodymium oxygen thermal barrier coating material according to claim 1, characterized in that: the step one is that the raw material La 2 O 3 、PrO 2 、ZrO 2 The purity of the product is more than or equal to 99.9 percent.
3. The lanthanum zirconium praseodymium oxygen thermal barrier coating material according to claim 1, characterized in that: the step one of raw material mixing is mechanical ball milling, and the time is more than or equal to 8 hours.
4. The lanthanum zirconium praseodymium oxygen thermal barrier coating material according to claim 1, characterized in that: the synthesis time of the step one high-temperature solid phase method is more than or equal to 12 hours.
5. The lanthanum zirconium praseodymium oxygen thermal barrier coating material according to claim 1, characterized in that: vacuum degree of the vacuum arc plating equipment in the second step<1×10 -2 Pa。
6. The lanthanum zirconium praseodymium oxygen thermal barrier coating material according to claim 1, characterized in that: and in the second step, the deposition time of the vacuum arc plating equipment is more than or equal to 100min.
7. The lanthanum zirconium praseodymium oxygen thermal barrier coating material according to claim 1, characterized in that: vacuum degree of electron beam physical vapor deposition equipment in the third step<5×10 -2 Pa。
8. The lanthanum zirconium praseodymium oxygen thermal barrier coating material according to claim 1, characterized in that: and in the third step, the evaporation time of the electron beam physical vapor deposition thermal barrier coating is 30-80min.
9. The lanthanum zirconium praseodymium oxygen thermal barrier coating material according to claim 1, characterized in that: and in the third step, the electron beam physical vapor deposition thermal barrier coating is cooled to below 200 ℃ along with the furnace, and the cooling is natural cooling.
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| Title |
|---|
| Pan Yang等.Thermal shock resistance and failure analysis of La2(Zr0.75Ce0.25)2O7-based TBCs produced by atmospheric plasma spraying.《Surface & Coatings Technology》.2021,第第409卷卷摘要，第2.1节. * |
| Thermal shock resistance and failure analysis of La2(Zr0.75Ce0.25)2O7-based TBCs produced by atmospheric plasma spraying;Pan Yang等;《Surface & Coatings Technology》;第第409卷卷;摘要，第2.1节 * |
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