A high-emissivity rare-earth doped thermal barrier coating material and a method of making the same
Patent Information
- Application Number
- CN202611312598.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-08-27
- Publication Date
- 2026-11-03
AI Technical Summary
Existing rare earth zirconate thermal barrier coating materials suffer from severe radiative heat transfer at high temperatures due to their infrared transparency or translucency, resulting in reduced thermal shielding efficiency. Current technologies lack effective rare earth element doping strategies to simultaneously reduce lattice thermal conductivity and suppress high-temperature radiative heat transfer.
A single-phase solid solution is formed by doping La2(Zr0.7Ce0.3)2O7 with rare earth elements Pr, Eu, Tb, Er, and Yb. By introducing lattice distortion and changes in oxygen vacancy concentration, phonon scattering and electron transition are enhanced, infrared emissivity is increased, and radiative heat transfer is suppressed.
It significantly improves the infrared emissivity of the material at high temperatures, reduces the lattice thermal conductivity, suppresses radiative heat transfer, and enhances the thermal shielding performance. In particular, Pr doping has the best effect, reducing the thermal conductivity to 1.49 W·m⁻¹·K⁻¹ at 1000℃ and increasing the infrared emissivity by about 45%.
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Abstract
Description
Technical Field
[0001] This invention relates to the field of thermal barrier coating materials technology, and in particular to a rare earth-doped thermal barrier coating material with high infrared emissivity and its preparation method. Background Technology
[0002] As the service temperatures of hot-end components in aero-engines and gas turbines continue to rise, thermal barrier coating materials face increasingly demanding high-temperature service environments. Traditional yttrium-stabilized zirconia (YSZ) ceramic thermal barrier coatings suffer from phase transformation and sintering densification issues during long-term service at temperatures above 1200℃, making them unsuitable for the higher requirements of next-generation high thrust-to-weight ratio engines. Rare-earth zirconates (Re2Zr2O7) with a pyrochlore structure (A2B2O7) are considered one of the most promising alternatives to YSZ due to their lower intrinsic thermal conductivity, higher phase transformation temperature (>1600℃), and excellent high-temperature phase stability.
[0003] Among many rare earth zirconates, La2(Zr) 0.7 Ce 0.3 Rare earth zirconates (LZC) have demonstrated good overall performance, exhibiting relatively excellent thermal expansion properties and stronger sintering resistance. However, a fatal flaw is common among rare earth zirconates: they exhibit infrared transparency or translucency at high temperatures, leading to severe radiative heat transfer. When the temperature rises to 800℃ or even higher, the thermal radiation in the service environment becomes increasingly significant and approaches the infrared band. Rare earth zirconates are almost transparent or translucent in this band, resulting in intensified radiative heat transfer and a significant reduction in the high-temperature thermal shielding efficiency of the thermal barrier coating. For example, the thermal conductivity of the LZC matrix can reach as high as 3.03 W·m at 1000℃ due to intensified radiative heat transfer. -1 ·K -1 When thermal radiation interacts with a material, its reflectivity + absorptivity + transmittance = 1. The reflectivity is generally a constant value. The higher the emissivity of a material to thermal radiation, the higher its absorptivity and the lower its transmittance, the better the material's thermal shielding effect.
[0004] Currently, improving the infrared emissivity of materials by doping with oxides of high infrared emissivity is a common strategy. Existing technologies mainly focus on single-doped systems and emphasize phonon thermal conductivity modulation, lacking a systematic comparison of the different mechanisms of high-temperature radiative heat transfer modulation by different rare earth ions. In particular, there is a lack of understanding on how to synergistically optimize both reducing lattice thermal conductivity and suppressing high-temperature radiative heat transfer through rare earth element doping. Therefore, researching a thermal barrier coating material with both low thermal conductivity and high infrared emissivity to address the severe radiative heat transfer problem of existing rare earth zirconate materials at high temperatures is of great significance. Summary of the Invention
[0005] The purpose of this invention is to provide a rare earth-doped thermal barrier coating material with high infrared emissivity and its preparation method, so as to solve the problem that rare earth zirconate thermal barrier coating materials in the prior art suffer from severe radiative heat transfer and reduced thermal insulation performance at high temperatures due to infrared transparency or semi-transparency.
[0006] To achieve the above-mentioned objectives, the present invention provides the following technical solution: This invention provides a rare-earth-doped thermal barrier coating material with high infrared emissivity, wherein the chemical formula of the rare-earth-doped thermal barrier coating material is (La... 1-x M x )2(Zr 0.7 Ce 0.3 )2O7, where M is selected from one or more of Pr, Eu, Tb, Er and Yb, 0 <x≤0.5。
[0007] Preferably, in the chemical formula of the rare earth-doped thermal barrier coating material, M is Pr.
[0008] Preferably, in the chemical formula of the rare earth-doped thermal barrier coating material, 0.2 ≤ x ≤ 0.5.
[0009] Preferably, in the chemical formula of the rare earth-doped thermal barrier coating material, 0.3 ≤ x ≤ 0.5.
[0010] This invention provides a method for preparing the above-described high infrared emissivity rare-earth-doped thermal barrier coating material, comprising the following steps: (1) After mixing the various oxide raw materials and dispersant, the mixture is ball-milled, ground, and sieved to obtain the sieved powder; (2) The sieved powder is pre-sintered, ball-milled a second time, pre-pressed, cold isostatically pressed and sintered to obtain a rare earth doped thermal barrier coating material with high infrared emissivity.
[0011] Preferably, the dispersant is anhydrous ethanol; the total mass ratio of the oxide raw materials to the dispersant is 1:1~3; the rotation speed of the first ball mill and the second ball mill are independently 400~600 rpm, and the time is independently 12~24h.
[0012] Preferably, the pre-sintering temperature is 1200~1400℃ and the time is 6~8h.
[0013] Preferably, the pre-compression molding pressure is 2~5MPa and the holding time is 50~70s.
[0014] Preferably, the pressure of the cold isostatic pressing treatment is 150~250MPa, and the holding time is 80~100s.
[0015] Preferably, the sintering treatment is performed at a temperature of 1500~1700℃ for 8~10 hours.
[0016] The beneficial effects of this invention are: (1) La2(Zr) used in the prior art 0.7 Ce 0.3 La₂(Zr₂)₇ thermal barrier coated ceramic materials suffer from drawbacks such as increased radiative heat transfer and a sharp increase in thermal conductivity at high temperatures due to their infrared transparency or translucency. This invention utilizes La₂(Zr₂)₇ thermal barrier coated ceramic materials. 0.7 Ce 0.3 Using La₂(Zr)₂O₇ as the matrix material, rare earth oxides such as Pr, Eu, Tb, Er, and Yb are dissolved in La₂(Zr)₂O₇. 0.7 Ce 0.3 In the 2O7 lattice, a single-phase solid solution is formed. Rare earth element doping, on the one hand, enhances phonon scattering by introducing lattice distortion and mass fluctuations, effectively reducing the lattice thermal conductivity of the material; on the other hand, multivalent rare earth elements (such as Pr³⁺) can also enhance phonon scattering. + / Pr 4+ Coexistence, Tb³ + / Tb 4+ Coexistence (in the process of doping) causes changes in oxygen vacancy concentration and introduces impurity energy levels, effectively narrowing the band gap of the material, promoting electronic transitions, and significantly improving the infrared emissivity of the material at high temperatures, thereby effectively suppressing radiative heat transfer. Taking Pr doping as an example, analysis shows that Pr³ + After LZC doping, the oxygen vacancy concentration increased from 36% to 44%. The coexistence of multivalent Pr and oxygen vacancies introduced impurity energy levels, narrowed the band gap, and promoted electronic transitions, thereby improving infrared emissivity. This invention, by doping rare earth elements at the A-site, simultaneously suppresses phonon thermal conductivity and radiative thermal conductivity, effectively solving the problem of severe radiative heat transfer in rare earth zirconates at high temperatures.
[0017] (2) The (La) prepared by this invention 0.6 Pr 0.4 )2(Zr 0.7 Ce 0.3 The thermal conductivity of O2O7 ceramic materials can be as low as 1.49 W·m at 1000℃. - ¹·K - ¹, much lower than La2(Zr 0.7 Ce 0.3 3.03 W·m⁻² of 2O₇ matrix - ¹·K -¹; The average infrared emissivity at 1000℃ within the 3–5 μm wavelength range reaches 0.94, an improvement of approximately 45% compared to the substrate (0.65). At the same doping concentration (10 at.%), Pr doping shows the best effect (average infrared emissivity of 0.88), followed by Eu (approximately 0.83), while Tb, Er, and Yb also show significant improvements (all ≥0.76). The average coefficient of thermal expansion is 11.14 × 10⁻⁶. -6 K - ¹, with 8YSZ (approximately 11.70 × 10⁻⁶) -6 K - ¹) They are close together and have good thermal compatibility.
[0018] (3) Unlike other thermal barrier coating ceramic material systems, the high infrared emissivity rare earth doped thermal barrier coating material proposed in this invention is constructed based on the currently widely used lanthanum cerium zirconate-based coating, possessing significant advantages in technical feasibility and relatively low technical risk. The ceramic materials doped with the five rare earth elements can all maintain a single cubic pyrochlore structure, indicating that the doping system described in this invention has good structural compatibility.
[0019] (4) The ceramic materials prepared by the solid-state reaction method of the present invention have high purity, uniform composition, simple process and low cost, and are suitable for large-scale production. Attached Figure Description
[0020] Figure 1 La2(Zr) prepared for Comparative Example 1 0.7 Ce 0.3 XRD pattern of 2O7 thermal barrier coating material; Figure 2 (La) prepared in Examples 1-5 1-x Pr x )2(Zr 0.7 Ce 0.3 XRD pattern of 2O7 thermal barrier coating material; Figure 3 The (La) prepared in Examples 1 and 6-9 0.9 Re 0.1 )2(Zr 0.7 Ce 0.3 XRD pattern of 2O7 (Re = Pr, Eu, Tb, Er, Yb) thermal barrier coating material; Figure 4 The infrared emissivity test results of the thermal barrier coating materials prepared in Comparative Example 1 and Examples 1-5 at 1000°C are shown. Figure 5 Infrared emissivity test results of the thermal barrier coating materials prepared in Comparative Example 1, Example 1, and Examples 6-9 at 1000°C; Figure 6Thermal conductivity diagrams of the thermal barrier coating materials prepared in Comparative Example 1 and Examples 1-5; Figure 7 The thermal conductivity diagrams are for the thermal barrier coating materials prepared in Comparative Example 1, Example 1, and Examples 6-9. Detailed Implementation
[0021] This invention provides a rare-earth-doped thermal barrier coating material with high infrared emissivity, wherein the chemical formula of the rare-earth-doped thermal barrier coating material is (La... 1-x M x )2(Zr 0.7 Ce 0.3 )2O7, where M is selected from one or more of Pr, Eu, Tb, Er and Yb, 0 <x≤0.5。
[0022] In this invention, M is Pr in the chemical formula of the rare earth-doped thermal barrier coating material.
[0023] In this invention, the chemical formula of the rare earth-doped thermal barrier coating material is 0.2≤x≤0.5.
[0024] In this invention, the chemical formula of the rare earth-doped thermal barrier coating material is 0.3≤x≤0.5.
[0025] This invention provides a method for preparing the above-described high infrared emissivity rare-earth-doped thermal barrier coating material, comprising the following steps: (1) After mixing the various oxide raw materials and dispersant, the mixture is ball-milled, ground, and sieved to obtain the sieved powder; (2) The sieved powder is pre-sintered, ball-milled a second time, pre-pressed, cold isostatically pressed and sintered to obtain a rare earth doped thermal barrier coating material with high infrared emissivity.
[0026] In this invention, the oxide raw material is preferably calcined to remove moisture from the raw material. The calcination temperature is 600~800℃, specifically 600℃, 700℃, or 800℃, and the time is 3~5h, specifically 3h, 4h, or 5h.
[0027] In this invention, the purity of each oxide raw material is independently ≥99.90%.
[0028] In this invention, the dispersant is anhydrous ethanol; the total mass ratio of the oxide raw materials to the dispersant is 1:1 to 3, preferably 1:2; the rotation speed of the first ball mill and the second ball mill is independently 400 to 600 rpm, preferably 450 to 550 rpm, and more preferably 500 rpm; the time is independently 12 to 24 hours, specifically 12 hours, 14 hours, 16 hours, 18 hours, 20 hours, 22 hours, and 24 hours.
[0029] In this invention, the ball-to-material ratio during the first and second ball milling is 1:2, and the milling beads are zirconia balls. Preferably, the zirconia balls are composed of three diameters of 3mm, 5mm, and 8mm in a mass ratio of 3:4:3.
[0030] In this invention, the pre-sintering temperature is 1200~1400℃, preferably 1250~1350℃, and more preferably 1300℃; the time is 6~8h, preferably 7~8h, and more preferably 8h.
[0031] In this invention, the pre-compression pressure is 2~5MPa, specifically 2MPa, 3MPa, 4MPa, or 5MPa, and the holding time is 50~70s, preferably 55~65s, and more preferably 60s.
[0032] In this invention, the pressure of the cold isostatic pressing treatment is 150~250MPa, preferably 180~220MPa, more preferably 200MPa, and the holding time is 80~100s, preferably 85~95s, more preferably 90s.
[0033] In this invention, the sintering temperature is 1500~1700℃, specifically 1500℃, 1550℃, 1600℃, 1650℃, or 1700℃, and the time is 8~10h, specifically 8h, 9h, or 10h.
[0034] The technical solutions provided by the present invention will be described in detail below with reference to the embodiments, but they should not be construed as limiting the scope of protection of the present invention.
[0035] Example 1
[0036] Preparation (La 0.9 Pr 0.1 )2(Zr 0.7 Ce 0.3 )2O7 thermal barrier coating material: La2O3, ZrO2, CeO2 and Pr6O 11The raw material was calcined in a muffle furnace at 800℃ for 5 hours to remove moisture and obtain powder. The powder and anhydrous ethanol were then placed in a nylon polyester ball mill jar according to a predetermined stoichiometric ratio and wet-milled at 500 rpm for 24 hours. The milling balls consisted of zirconia balls with diameters of 3 mm, 5 mm, and 8 mm in a mass ratio of 3:4:3, with a ball-to-material ratio of 1:2. The mass ratio of anhydrous ethanol to the powder was 2:1. The milled slurry was dried in an 80℃ constant-temperature oven to constant weight. The dried powder was then ground and passed through an 80-mesh sieve. The sieved powder was then placed in a muffle furnace and pre-sintered at 1300℃ for 8 hours to obtain pre-sintered powder.
[0037] Pre-sintered powder and anhydrous ethanol were placed in a nylon polyester ball mill jar and subjected to secondary ball milling at 500 rpm. The milling balls consisted of zirconia balls with diameters of 3 mm, 5 mm, and 8 mm in a mass ratio of 3:4:3, with a ball-to-material ratio of 1:2. The mass ratio of anhydrous ethanol to powder raw materials was 2:1. The slurry after secondary ball milling was dried in an 80°C constant temperature oven to constant weight. The dried powder was then placed in a mold and pre-pressed under a pressure of 5 MPa for 60 s, followed by cold isostatic pressing under a pressure of 200 MPa for 90 s to obtain a ceramic green body. Finally, the ceramic green body was placed in a muffle furnace and sintered at 1600°C for 8 h to obtain (La) 0.9 Pr 0.1 )2(Zr 0.7 Ce 0.3 The thermal barrier coating material is denoted as Yb-LZC.
[0038] Example 2
[0039] (La) was prepared according to the method in Example 1. 0.8 Pr 0.2 )2(Zr 0.7 Ce 0.3 The difference between the 2O7 thermal barrier coating material and the 2O7 thermal barrier coating material lies in the stoichiometric ratio of the raw materials, while all other conditions are the same.
[0040] Example 3
[0041] (La) was prepared according to the method in Example 1. 0.7 Pr 0.3 )2(Zr 0.7 Ce 0.3 The difference between the 2O7 thermal barrier coating material and the 2O7 thermal barrier coating material lies in the stoichiometric ratio of the raw materials, while all other conditions are the same.
[0042] Example 4
[0043] (La) was prepared according to the method in Example 1. 0.6 Pr 0.4)2(Zr 0.7 Ce 0.3 The difference between the 2O7 thermal barrier coating material and the 2O7 thermal barrier coating material lies in the stoichiometric ratio of the raw materials, while all other conditions are the same.
[0044] Example 5
[0045] (La) was prepared according to the method in Example 1. 0.5 Pr 0.5 )2(Zr 0.7 Ce 0.3 The difference between the 2O7 thermal barrier coating material and the 2O7 thermal barrier coating material lies in the stoichiometric ratio of the raw materials, while all other conditions are the same.
[0046] Example 6
[0047] Preparation (La 0.9 Eu 0.1 )2(Zr 0.7 Ce 0.3 The preparation method of the 2O7 thermal barrier coating material differs from that in Example 1 in that the raw materials used are La2O3, ZrO2, CeO2, and Eu2O3, while all other conditions remain the same. 0.9 Eu 0.1 )2(Zr 0.7 Ce 0.3 )2O7 is denoted as Eu-LZC.
[0048] Example 7
[0049] Preparation (La 0.9 Tb 0.1 )2(Zr 0.7 Ce 0.3 The preparation method of the 2O7 thermal barrier coating material differs from that in Example 1 in that the raw materials used are La2O3, ZrO2, CeO2, and Tb2O3, while all other conditions remain the same. 0.9 Tb 0.1 )2(Zr 0.7 Ce 0.3 )2O7 is denoted as Tb-LZC.
[0050] Example 8
[0051] Preparation (La 0.9 Er 0.1 )2(Zr 0.7 Ce 0.3 The preparation method of the 2O7 thermal barrier coating material differs from that in Example 1 in that the raw materials used are La2O3, ZrO2, CeO2, and Er2O3, while all other conditions remain the same. 0.9 Er 0.1 )2(Zr 0.7 Ce0.3 )2O7 is denoted as Er-LZC.
[0052] Example 9
[0053] Preparation (La 0.9 Yb 0.1 )2(Zr 0.7 Ce 0.3 The preparation method of the 2O7 thermal barrier coating material differs from that in Example 1 in that the raw materials used are La2O3, ZrO2, CeO2, and Yb2O3, while all other conditions remain the same. 0.9 Yb 0.1 )2(Zr 0.7 Ce 0.3 )2O7 is denoted as Yb-LZC.
[0054] Comparative Example 1
[0055] Preparation of La2(Zr) 0.7 Ce 0.3 The preparation method of the 2O7 thermal barrier coating material differs from that in Example 1 in that the raw materials used are La2O3, ZrO2, and CeO2, while all other conditions remain the same. 0.7 Ce 0.3 )2O7 is denoted as LZC.
[0056] The performance of the thermal barrier coating materials of Examples 1-9 and Comparative Example 1 was verified and characterized: (I) Crystal Structure Analysis Figure 1 La2(Zr) prepared for Comparative Example 1 0.7 Ce 0.3 XRD pattern of 2O7 thermal barrier coating material. Figure 2 (La) prepared in Examples 1-5 1-x Pr x )2(Zr 0.7 Ce 0.3 XRD pattern of 2O7 thermal barrier coating material. Figure 3 The (La) prepared in Examples 1 and 6-9 0.9 Re 0.1 )2(Zr 0.7 Ce 0.3 XRD pattern of 2O7 (Re=Pr, Eu, Tb, Er, Yb) thermal barrier coating material.
[0057] Depend on Figure 1 and Figure 2 , Figure 3 It can be seen that Comparative Example 1 and Examples 1-9 all synthesized a single cubic pyrochlore structure, and no second phase formation was observed, indicating that Pr 3+ Eu3+ 、Tb 3+ Er 3+ Yb 3+ All of them were successfully dissolved into the LZC lattice.
[0058] (ii) Infrared emissivity test
[0059] Figure 4 The infrared emissivity test results of the thermal barrier coating materials prepared in Comparative Example 1 and Examples 1-5 are shown at 1000°C. Figure 5 The infrared emissivity test results of the thermal barrier coating materials prepared in Comparative Example 1, Example 1, and Examples 6-9 are shown at 1000°C.
[0060] Depend on Figure 5 It can be seen that doping with the five rare earth elements significantly improves the infrared emissivity of LZC ceramics at 1000℃, especially in the 3~5μm wavelength range. Among them, Pr doping has the best effect (average infrared emissivity of 0.88), followed by Eu (approximately 0.83), while Tb, Er, and Yb also show significant improvements (all ≥0.76), indicating that the five rare earth elements can effectively improve the high-temperature radiation shielding performance of thermal barrier coating materials.
[0061] Depend on Figure 4 It can be seen that as the Pr doping concentration increases, the infrared emission of the material first increases and then decreases slightly. When x=0.4 (Example 4), the average infrared emissivity in the 3~5μm band reaches the highest value of 0.94, which is about 45% higher than that of the LZC matrix (0.65) in Comparative Example 1.
[0062] (III) Thermal conductivity test
[0063] Figure 6 The thermal conductivity diagrams are for the thermal barrier coating materials prepared in Comparative Example 1 and Examples 1-5. Figure 7 The thermal conductivity diagrams are for the thermal barrier coating materials prepared in Comparative Example 1, Example 1, and Examples 6-9.
[0064] Depend on Figure 7 It can be seen that the thermal barrier coating materials prepared in Examples 1-5 significantly reduced the thermal conductivity across the entire temperature range compared to the conventional La2(Zr0.7Ce0.3)2O7 thermal barrier coating material in Comparative Example 1. Within the temperature range of room temperature to 600℃, all five rare earth dopants effectively reduced the lattice thermal conductivity of LZC, with Yb doping exhibiting the lowest lattice thermal conductivity due to the greatest mass difference. However, when the temperature exceeds 600℃, the LZC substrate in Comparative Example 1 exhibits a sharp increase in thermal conductivity (reaching 3.03 W·m⁻¹ at 1000℃) due to the intensified radiative heat transfer caused by its infrared translucency. - ¹·K -¹); while rare earth-doped samples effectively suppressed high-temperature radiative heat transfer, and no sharp increase in thermal conductivity was observed throughout the temperature range.
[0065] Depend on Figure 6 It can be seen that Pr doping has the most significant effect, with Pr-LZC with x=0.1 exhibiting a thermal conductivity of 1.63 W·m at 1000℃. - ¹·K - ¹; After further optimization of the doping concentration, Example 4 with x=0.4 exhibited the lowest thermal conductivity at 1000℃, at only 1.49 W·m. - ¹·K - ¹.
[0066] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.
Claims
1. A rare-earth-doped thermal barrier coating material with high infrared emissivity, characterized in that, The chemical formula of the rare earth-doped thermal barrier coating material is (La 1-x M x )2(Zr 0.7 Ce 0.3 )2O7, where M is selected from one or more of Pr, Eu, Tb, Er and Yb, 0 <x≤0.5。 2. The high infrared emissivity rare-earth-doped thermal barrier coating material according to claim 1, characterized in that, In the chemical formula of the thermal barrier coating material, M stands for Pr.
3. The high infrared emissivity rare-earth-doped thermal barrier coating material according to claim 1 or 2, characterized in that, In the chemical formula of the rare earth-doped thermal barrier coating material, 0.2 ≤ x ≤ 0.
5.
4. The high infrared emissivity rare-earth-doped thermal barrier coating material according to claim 3, characterized in that, In the chemical formula of the rare earth-doped thermal barrier coating material, 0.3 ≤ x ≤ 0.
5.
5. The method for preparing the high infrared emissivity rare earth-doped thermal barrier coating material according to any one of claims 1 to 4, characterized in that, Includes the following steps: (1) After mixing the various oxide raw materials and dispersant, the mixture is ball-milled, ground, and sieved to obtain the sieved powder; (2) The sieved powder is pre-sintered, ball-milled a second time, pre-pressed, cold isostatically pressed and sintered to obtain a rare earth doped thermal barrier coating material with high infrared emissivity.
6. The method for preparing a high infrared emissivity rare-earth-doped thermal barrier coating material according to claim 5, characterized in that, The dispersant is anhydrous ethanol; the total mass ratio of the oxide raw materials to the dispersant is 1:1~3; the rotation speed of the first ball mill and the second ball mill are independently 400~600 rpm, and the time is independently 12~24h.
7. The method for preparing a high infrared emissivity rare-earth-doped thermal barrier coating material according to claim 5 or 6, characterized in that, The pre-sintering temperature is 1200~1400℃, and the time is 6~8h.
8. The method for preparing a high infrared emissivity rare-earth-doped thermal barrier coating material according to claim 7, characterized in that, The pre-compression molding pressure is 2~5MPa, and the holding time is 50~70s.
9. The method for preparing a high infrared emissivity rare-earth-doped thermal barrier coating material according to claim 6 or 8, characterized in that, The pressure of the cold isostatic pressing process is 150~250MPa, and the holding time is 80~100s.
10. The method for preparing a high infrared emissivity rare-earth-doped thermal barrier coating material according to claim 9, characterized in that, The sintering process is carried out at a temperature of 1500~1700℃ for 8~10 hours.