An erbium-cerium double rare earth modified europium zirconate thermal barrier coating material and a preparation method thereof

Abstract

This invention belongs to the field of thermal barrier coating technology for aero-engines, and relates to an erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material and its preparation method. The molecular formula of the thermal barrier coating material is (Er x Ce y Eu (1‑x‑y) The erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating is prepared by electron beam physical vapor deposition (EBPV) with x = 0.05~0.2 and y = 0.1~0.3. The deposition process parameters are: electron beam current intensity 1.5-1.7 A; sample temperature 950-1050℃; evaporation time 30-60 min. The evaporation time is controlled to obtain an erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating on a rotating sample. The thermal barrier coating material of this invention has a coefficient of thermal expansion close to that of YSZ and exhibits low thermal conductivity. Furthermore, the use of electron beam physical vapor deposition to prepare the erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating results in a columnar crystal structure and good lifespan. This invention can reduce the thermal conductivity of the coating, increase its service temperature, and address the problem of insufficient coating service life.

Description

Technical Field

[0001] This invention belongs to the field of thermal barrier coating technology for aero-engines, and relates to an erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material and its preparation method. Background Technology

[0002] Currently, with the continuous improvement of thrust and efficiency in aero-engines, the intake temperature of the exhaust gas is also increasing. The operating temperature of nickel-based superalloys used in turbine blades and other hot-end components is gradually approaching their service temperature limits. Thermal barrier coatings (TBCs) are a surface protection technology that utilizes the high-temperature resistance, erosion resistance, corrosion resistance, and low thermal conductivity of ceramic materials, combining them with metallic materials in the form of coatings. This aims to increase the operating temperature of metallic components, enhance the high-temperature resistance of hot-end components, extend the service life of hot-end components, and improve engine efficiency. Currently, the widely used YSZ (6~8 wt.% Y2O3 partially stabilized ZrO2) thermal barrier coating material has a long-term maximum operating temperature that cannot exceed 1200℃. During the cooling process, the volume expansion caused by the monoclinic phase generated during the phase transition leads to coating failure. Therefore, researching thermal barrier coating materials with a long-term operating temperature exceeding 1200℃ has become a key issue.

[0003] For novel thermal barrier coating ceramic layer materials, which are different from traditional YSZ thermal barrier coating materials, the basic design idea is to use ceramic layers with lower thermal conductivity and higher service temperature to protect high-temperature alloy samples. According to the novel thermal barrier coating ceramic layer material systems that have been extensively developed and verified abroad, they can be summarized into two categories: (1) Doping modification of traditional ZrO2 materials with one, two or more rare earth oxides / refractory metal oxides to increase the number of defects (oxygen holes or oxygen vacancies) in the ceramic coating, optimize the microstructure of the coating, and reduce the thermal conductivity of the material; (2) Developing novel thermal barrier coating materials with pyrochlore, fluorite, perovskite or magnetoplumb ore structures. This type of coating material system is completely different from traditional YSZ materials in terms of crystal structure, and directly achieves the purpose of reducing the thermal conductivity of existing materials. Summary of the Invention

[0004] The technical problem to be solved by this invention is to provide an erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating material and its preparation method. The aim is to solve the problems of insufficient service life of single zirconate thermal barrier coatings and the service temperature of YSZ not exceeding 1200℃ through erbium-cerium dual-rare-earth co-doping modification, while also addressing the insufficient thermal performance of single rare-earth element modification. By modifying europium zirconate with erbium-cerium dual-rare-earth elements, the thermal conductivity of the material is directly reduced, and the coefficient of thermal expansion is increased.

[0005] The technical solution of this invention is: On one hand, an erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating material is provided, wherein the molecular formula of the erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating material is (Er x Ce y Eu (1-x-y) The expression is: 2Zr₂O₇, where x = 0.05~0.2 and y = 0.1~0.3. For example, x can be 0.06, 0.07, 0.08, 0.09, 0.10, 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19; y can be 0.11, 0.12, 0.13, 0.14, 0.15, 0.16, 0.17, 0.18, 0.19, 0.20, 0.21, 0.22, 0.23, 0.24, 0.25, 0.26, 0.27, 0.28, 0.29. It should be understood that the above values ​​include, but are not limited to, the listed values, and any other value points within the range are also applicable.

[0006] On the other hand, a method for preparing the erbium-cerium dual rare earth modified europium zirconate thermal barrier coating is provided, comprising the following steps: Step 1: Er₂O₃, CeO₂, Eu₂O₃, and ZrO₂ are mixed according to their molecular formula ratios. Erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating targets are synthesized through chemical co-precipitation and calcination. The pH value of the chemical co-precipitation is controlled at 5-6, specifically 5.5±0.1, 5.5±0.2, 5.5±0.3, and 5.5±0.4. The calcination temperature is controlled at 1500-1700℃, specifically 1600±5℃. 10℃, 1600±15℃, 1600±20℃, 1600±25℃, 1600±30℃, 1600±35℃, 1600±40℃, 1600±45℃, 1600±50℃, 1600±55℃, 1600±60℃, 1600±65℃, 1600±70℃, 1600±75℃, 1600±80℃, 1600±85℃, 1600±90℃, 1600±95℃.

[0007] Step 2: Prepare a NiCrAlYSi metal underlayer as a thermal barrier coating on the sample using physical vapor deposition at a temperature of 950-1050℃, which can be 1000±5℃, 1000±10℃, 1000±15℃, 1000±20℃, 1000±25℃, 1000±30℃, 1000±35℃, 1000±40℃, or 1000±45℃; the electron beam current intensity is 1.20-1.40A, which can be 1.30±0.01A, 1.30±0.02A, 1.30±0.03A, 1.30±0.04A, 1.30±0.05A, 1.30±0.06A, 1.30±0.07A, 1.30±0.08A, or 1.30±0.09A. Step 3: The NiCrAlYSi metal substrate is shot peened with a shot peening intensity of 0.15-0.25 MPa and a shot size of 0.05-0.1 mm.

[0008] Step four involves loading the erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating target into an electron beam physical vapor deposition (EBPV) apparatus. The erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating target is evaporated by an electron beam, thus preparing the erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating on a NiCrAlYSi substrate. The electron beam current intensity is 1.5-1.7 A, specifically 1.60±0.01 A, 1.60±0.02 A, 1.60±0.03 A, or 1.60±0.04 A. 1.60±0.05A, 1.60±0.06A, 1.60±0.07A, 1.60±0.08A, 1.60±0.09A; the sample temperature is 950-1050℃, which can be 1000±5℃, 1000±10℃, 1000±15℃, 1000±20℃, 1000±25℃, 1000±30℃, 1000±35℃, 1000±40℃, 1000±45℃.

[0009] The sample matrix in step two is a nickel-based high-temperature alloy, such as CMSX-4, CMSX-10, PWA1484, DD90, etc.

[0010] The purity of the raw materials Er2O3, CeO2, Eu2O3, and ZrO2 in step one is ≥98%.

[0011] The raw material mixing in step one should be done by mechanical ball milling for a time of ≥24 hours.

[0012] The chemical coprecipitation time in step one is ≥12 hours.

[0013] In step two, the physical vapor deposition time is 30-60 minutes.

[0014] In step two, the vacuum level of the electron beam physical vapor deposition equipment is <1×10⁻⁶.-4 mbar.

[0015] In step three, the proportion of shot blasting particles is 15-25%.

[0016] In step four, the vacuum level of the electron beam physical vapor deposition equipment is <5×10⁻⁶. -4 mbar.

[0017] In step four, the evaporation time of the electron beam physical vapor deposition thermal barrier coating is 30-60 minutes.

[0018] In step four, the thermal barrier coating deposited by electron beam physical vapor deposition is cooled to below 100°C in the furnace, and the cooling is natural cooling.

[0019] The introduction of erbium (Er) and cerium (Ce) dual rare earth modified europium zirconate thermal barrier coating material is of great significance in exploring the ratio between x and y and their influence on coating performance. This allows for a deeper optimization of material properties, and the material exhibits excellent thermal shielding performance and thermal stability, further enhancing its effectiveness in practical applications.

[0020] Regarding thermal stability, the europium (Eu) content (1-xy) plays a crucial role in maintaining the material's thermal stability. Higher europium content generally improves thermal stability, while too low a content may negatively impact performance. For mechanical strength, the ratio of erbium to cerium affects the material's microstructure. An appropriate x-y ratio contributes to a uniform porosity distribution, enhancing the material's mechanical strength. Regarding thermal cycling resistance, thermal cycling tests show that a well-balanced combination of x and y provides optimal resistance, with the material exhibiting an extremely low failure rate under high-temperature cycling.

[0021] The beneficial effects of this invention are: The erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating of this invention exhibits high phase stability after long-term heat treatment at 1200℃ without phase transformation. By modifying europium zirconate with erbium-cerium dual-rare-earth, its coefficient of thermal expansion is made close to that of YSZ, while also possessing low thermal conductivity and good fracture toughness. Simultaneously, an erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating + NiCrAlYSi is prepared using electron beam physical vapor deposition (EBPV). EBPV vapor deposition vaporizes the erbium-cerium dual-rare-earth modified europium zirconate and NiCrAlYSi target, depositing vapor clouds on the sample surface. This results in a unique columnar crystal structure for the erbium-cerium dual-rare-earth modified europium zirconate and NiCrAlYSi coating. EBPV vapor deposition also enables the thermal barrier coating to possess good strain tolerance, improving its thermal cycling performance during thermal cycling. Figures 1 to 4 As shown. Attached Figure Description

[0022] To more clearly illustrate the technical solutions implemented in this invention, the accompanying drawings used in this invention will be briefly described below. Obviously, the drawings described below are merely some embodiments of this invention. Those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0023] Figure 1 This is a comparison chart showing the thermal conductivity results of various coatings in the example. Figure 2 This is a comparison chart of the thermal expansion coefficients of the various coatings in the example; Figure 3 This is a comparative graph showing the thermal life of various coatings in the example; Figure 4 This is a schematic diagram of columnar crystal and equiaxed crystal structures in Embodiment 2 of the present invention. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] The features of various aspects of the embodiments of the present invention will now be described in detail. In the following detailed description, numerous specific details are set forth to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention can also be practiced without these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples. The invention is not limited to any specific setups and methods provided below, but covers all improvements, substitutions, etc., to product structures and methods without departing from the spirit of the invention. In the various drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the invention.

[0026] The method flow of the present invention will now be described in detail with reference to the accompanying drawings and embodiments: The molecular formula of an erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material is (Er x Ce y Eu (1-x-y) )2Zr2O7, where x=0.05~0.2, y=0.1~0.3; The preparation method of erbium-cerium dual rare earth modified europium zirconate thermal barrier coating includes the following steps: Erbium-cerium dual rare earth modified europium zirconate thermal barrier coating target material was synthesized by mixing raw materials Er2O3, CeO2, Eu2O3 and ZrO2 according to the material molecular formula ratio, and by chemical coprecipitation and calcination. The purity of raw materials is ≥98%; the pH value of chemical coprecipitation is controlled at 5-6, and the precipitation time is ≥12 hours; the calcination temperature is controlled at 1500-1700℃, and the mechanical ball milling time is ≥24 hours.

[0027] In the embodiments and comparative examples of this invention, the sample substrate is a nickel-based superalloy, such as CMSX-4, PWA1484, DD90, or other nickel-based superalloys. NiCrAlYSi is prepared as the metal underlayer for the thermal barrier coating using physical vapor deposition at a temperature of 950-1050℃, an electron beam current of 1.2-1.4 A, a deposition time of 30-60 min, and a vacuum degree <1×10⁻⁶. - 4 mbar; the NiCrAlYSi metal substrate was shot-peened with an intensity of 0.15-0.25 MPa, a shot size of 0.1 mm, and a shot percentage of 15-25%. The prepared target was then loaded into an electron beam physical vapor deposition (EBV) system with a vacuum degree <5 × 10 mbar. - 4 mbar, electron beam current intensity 1.5-1.7A, sample temperature 950-1050℃, evaporation time 30-60min, to prepare thermal barrier coating, and then naturally cool to below 100℃ in the furnace.

[0028] The specific composition of the erbium-cerium dual rare earth modified europium zirconate thermal barrier coating is shown in Table 1 below: Table 1

[0029] The preparation process of the coating of the present invention is described below using examples 1#, 2#, and 3# in Table 1 as examples. In the examples and comparative examples of the present invention, the sample substrate is a nickel-based high-temperature alloy, which can be CMSX-4, PWA1484, DD90, or other nickel-based high-temperature alloys.

[0030] Example 1: (1) Raw material synthesis: According to the molecular formula of erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material (Er 0.05 Ce 0.1 Eu 0.85 Erbium-cerium dual rare earth modified europium zirconate thermal barrier coating target material was synthesized by chemical coprecipitation and calcination. The pH value of chemical coprecipitation was controlled at 5.2, the precipitation time was 15 hours, and the calcination temperature was controlled at 1550℃. (2) Preparation of metal substrate: NiCrAlYSi was prepared as the metal substrate for thermal barrier coating by physical vapor deposition. The deposition temperature of the sample was 950℃ and the electron beam intensity was 1.2A. (3) Shot peening strengthening treatment: The NiCrAlYSi metal substrate is shot peened with a shot peening intensity of 0.15MPa and a shot size of 0.1mm.

[0031] (4) Thermal barrier coating preparation: The erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating target was loaded into an electron beam physical vapor deposition (EBPV) apparatus. Deposition process parameters: vacuum degree <5×10⁻⁶ -4 mbar, electron beam current intensity 1.5A, evaporation time 40min, after cooling to below 100 degrees Celsius, the deposition equipment was turned on to obtain erbium-cerium dual rare earth modified europium zirconate thermal barrier coating.

[0032] Example 2: (1) Raw material synthesis: According to the molecular formula of erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material (Er 0.1 Ce 0.15 Eu 0.75 Erbium-cerium dual rare earth modified europium zirconate thermal barrier coating target material was synthesized by chemical coprecipitation and calcination. The pH value of chemical coprecipitation was controlled at 5.5, the precipitation time was 18 hours, and the calcination temperature was controlled at 1600℃. (2) Preparation of metal substrate: NiCrAlYSi was prepared as the metal substrate for thermal barrier coating by physical vapor deposition. The deposition temperature of the sample was 1000℃ and the electron beam intensity was 1.3A. (3) Shot peening strengthening treatment: The NiCrAlYSi metal substrate was shot peened with a shot peening intensity of 0.2MPa and a shot size of 0.1mm.

[0033] (4) Thermal barrier coating preparation: The erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating target was loaded into an electron beam physical vapor deposition (EBPV) apparatus. Deposition process parameters: vacuum degree <5×10⁻⁶ -4 mbar, electron beam intensity 1.6A, evaporation time 45min, after cooling to below 100 degrees Celsius, the deposition equipment was turned on to obtain erbium-cerium dual rare earth modified europium zirconate thermal barrier coating.

[0034] Example 3: (1) Raw material synthesis: According to the molecular formula of erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material (Er 0.15 Ce 0.2 Eu 0.65Erbium-cerium dual rare earth modified europium zirconate thermal barrier coating target material was synthesized by chemical coprecipitation and calcination. The pH value of chemical coprecipitation was controlled at 6, the precipitation time was 20 hours, and the calcination temperature was controlled at 1650℃. (2) Preparation of metal substrate: NiCrAlYSi was prepared as the metal substrate for thermal barrier coating by physical vapor deposition. The deposition temperature of the sample was 1050℃ and the electron beam intensity was 1.4A. (3) Shot peening strengthening treatment: The NiCrAlYSi metal substrate was shot peened with a shot peening intensity of 0.24MPa and a shot size of 0.1mm.

[0035] (4) Thermal barrier coating preparation: The erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating target was loaded into an electron beam physical vapor deposition (EBPV) apparatus. Deposition process parameters: vacuum degree <5×10⁻⁶ -4 mbar, electron beam current intensity 1.7A, evaporation time 50min, after cooling to below 100 degrees Celsius, the deposition equipment was turned on to obtain erbium-cerium dual rare earth modified europium zirconate thermal barrier coating.

[0036] To illustrate the effect of different component ratios on the performance of erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coatings, Comparative Example 1 was prepared; to illustrate the effect of process parameters such as beam current intensity on coating performance, Comparative Example 4 was prepared; Comparative Example 2 is a single erbium-modified europium zirconate thermal barrier coating; Comparative Example 3 is a YSZ thermal barrier coating in the prior art, as detailed below: Comparative Example 1: (1) Raw material synthesis: According to the molecular formula of erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material (Er 0.2 Ce 0.25 Eu 0.55 Erbium-cerium dual rare earth modified europium zirconate thermal barrier coating target material was synthesized by chemical coprecipitation and calcination. The pH value of chemical coprecipitation was controlled at 6, the precipitation time was 20 hours, and the calcination temperature was controlled at 1600℃. (2) Preparation of metal substrate: NiCrAlYSi was prepared as the metal substrate for thermal barrier coating by physical vapor deposition. The deposition temperature of the sample was 1050℃ and the electron beam intensity was 1.35A. (3) Shot peening strengthening treatment: The NiCrAlYSi metal substrate was shot peened with a shot peening intensity of 0.24MPa and a shot size of 0.1mm.

[0037] (4) Thermal barrier coating preparation: The erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating target was loaded into an electron beam physical vapor deposition (EBPV) apparatus. Deposition process parameters: vacuum degree <5×10⁻⁶-4 mbar, electron beam current intensity 1.85A, evaporation time 80min, after cooling to below 100 degrees Celsius, the deposition equipment was turned on to obtain erbium-cerium dual rare earth modified europium zirconate thermal barrier coating.

[0038] Comparative Example 2: A single erbium-modified europium zirconate thermal barrier coating, prepared as follows: (1) Raw material synthesis: According to the molecular formula of erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material (Er 0.2 Eu 0.8 Erbium-modified europium zirconate thermal barrier coating target material was synthesized by chemical coprecipitation and calcination. The pH value of the chemical coprecipitation was controlled at 5.6, the precipitation time was 20 hours, and the calcination temperature was controlled at 1650℃. (2) Preparation of metal substrate: NiCrAlYSi was prepared as the metal substrate for thermal barrier coating by physical vapor deposition. The deposition temperature of the sample was 1000℃ and the electron beam intensity was 1.3A. (3) Shot peening strengthening treatment: The NiCrAlYSi metal substrate was shot peened with a shot peening intensity of 0.22MPa and a shot size of 0.1mm.

[0039] (4) Thermal barrier coating preparation: The erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating target was loaded into an electron beam physical vapor deposition (EBPV) apparatus. Deposition process parameters: vacuum degree <5×10⁻⁶ -4 mbar, electron beam intensity 1.5A, evaporation time 50min, after cooling to below 100 degrees Celsius, the deposition equipment was turned on to obtain erbium-modified europium zirconate thermal barrier coating.

[0040] Comparative Example 3: The preparation process of the YSZ thermal barrier coating is as follows: (1) Raw material ratio: According to the molecular formula of YSZ thermal barrier coating material (Zr 0.92 Y 0.08 Weigh out raw materials ZrO2 and Y2O3.

[0041] (2) High-temperature solid-state synthesis: The raw materials were mechanically ball-milled for 20 hours, and europium-praseodymium dual-modified lanthanum zirconate target material was synthesized by high-temperature solid-state method at 1650℃ for 20 hours; (3) Substrate preparation: NiCoCrAlYHf was prepared as the metal substrate for the thermal barrier coating using chemical vapor deposition equipment, with a vacuum degree <1×10⁻⁶. -2 Pa, voltage 645V, current 14A, deposition time 150min; (4) Thermal barrier coating preparation: The YSZ target is loaded into an electron beam physical vapor deposition (EBPD) apparatus. Deposition process parameters: vacuum degree <5×10⁻⁶ -4mbar, electron beam current 1.65A, evaporation time 40 min, after cooling to below 100 degrees Celsius, the deposition equipment was turned on to obtain europium-praseodymium dual-modified lanthanum zirconate thermal barrier coating.

[0042] Comparative Example 4: (1) Raw material synthesis: According to the molecular formula of erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material (Er 0.1 Ce 0.15 Eu 0.75 Erbium-cerium dual rare earth modified europium zirconate thermal barrier coating target material was synthesized by chemical coprecipitation and calcination. The pH value of chemical coprecipitation was controlled at 5.5, the precipitation time was 18 hours, and the calcination temperature was controlled at 1600℃. (2) Preparation of metal substrate: NiCrAlYSi was prepared as the metal substrate for thermal barrier coating by physical vapor deposition. The deposition temperature of the sample was 1000℃ and the electron beam intensity was 1.3A. (3) Shot peening strengthening treatment: The NiCrAlYSi metal substrate was shot peened with a shot peening intensity of 0.3MPa and a shot size of 0.1mm.

[0043] (4) Thermal barrier coating preparation: The erbium-cerium dual-rare-earth modified europium zirconate thermal barrier coating target was loaded into an electron beam physical vapor deposition (EBPV) apparatus. Deposition process parameters: vacuum degree <5×10⁻⁶ -4 mbar, electron beam intensity 1.8A, evaporation time 45min, after cooling to below 100 degrees Celsius, the deposition equipment was turned on to obtain erbium-cerium dual rare earth modified europium zirconate thermal barrier coating.

[0044] Comparison of the performance of various coatings: Examples of Comparative Models: Performance Comparison of Each Coating Figures 1 to 3 As shown in the figure. A comparison of the results reveals that: (1) Using electron beam physical vapor deposition to prepare thermal barrier coatings will give the thermal barrier coatings a unique columnar crystal structure; using physical vapor deposition to prepare NiCrAlYSi as the metal underlayer of the thermal barrier coating, and then strengthening it with shot peening, will give the metal underlayer an equiaxed crystal structure (e.g., Figure 4 Left side), equiaxed crystal plus columnar crystal structure (such as Figure 4 The thermal barrier coating (on the right) exhibits better thermal cycling performance. The comparison results are as follows: Figure 1 , Figure 2 As shown.

[0045] (2) In terms of coating design, a uniform coating structure is obtained through erbium-cerium dual rare earth modification. This invention can both reduce the thermal conductivity of europium zirconate coating and improve the practical problem of insufficient service life of europium zirconate alone. Results Comparison Figure 3 As shown.

[0046] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be covered within the protection scope of the present invention.

Claims

1. An erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material, characterized in that: The molecular formula of the erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material is (Er x Ce y Eu (1-x-y) )2Zr2O7, where x=0.05~0.2, y=0.1~0.

3.

2. A method for preparing the erbium-cerium dual rare earth modified europium zirconate thermal barrier coating material as described in claim 1, characterized in that: Includes the following steps: Step 1: The raw materials Er2O3, CeO2, Eu2O3 and ZrO2 are mixed according to the material molecular formula ratio, and erbium-cerium dual rare earth modified europium zirconate thermal barrier coating target material is synthesized by chemical coprecipitation and calcination. The pH value of chemical coprecipitation is controlled at 5-6, and the calcination temperature is controlled at 1500-1700℃. Step 2: Prepare NiCrAlYSi as the metal underlayer for thermal barrier coating on the sample by physical vapor deposition at a temperature of 950-1050℃ and an electron beam current intensity of 1.2-1.4A. Step 3: The NiCrAlYSi metal substrate is shot peened to strengthen it. The shot peening intensity is 0.15-0.25 MPa, and the shot size is less than 0.1 mm and greater than 0.05 mm. Step four: The erbium-cerium dual rare earth modified europium zirconate thermal barrier coating target is loaded into an electron beam physical vapor deposition apparatus. The erbium-cerium dual rare earth modified europium zirconate thermal barrier coating target is evaporated by electron beam to prepare the erbium-cerium dual rare earth modified europium zirconate thermal barrier coating on the NiCrAlYSi substrate. The electron beam current intensity is 1.5-1.7A and the sample temperature is 950-1050℃.

3. The preparation method according to claim 2, characterized in that: The purity of the raw materials Er2O3, CeO2, Eu2O3, and ZrO2 in step one is ≥98%.

4. The preparation method according to claim 2, characterized in that: The raw material mixing in step one should be done by mechanical ball milling for a time of ≥24 hours.

5. The preparation method according to claim 2, characterized in that: The sedimentation time for step one is ≥12 hours.

6. The preparation method according to claim 2, characterized in that: In step two, the physical vapor deposition time is 30-60 minutes.

7. The preparation method according to claim 2, characterized in that: In step two, the vacuum level of the electron beam physical vapor deposition equipment is <1×10⁻⁶. -4 mbar.

8. The preparation method according to claim 2, characterized in that: In step three, the proportion of shot blasting particles is 15-25%.

9. The preparation method according to claim 2, characterized in that: In step four, the vacuum level of the electron beam physical vapor deposition equipment is <5×10⁻⁶. -4 mbar.

10. The preparation method according to claim 2, characterized in that: In step four, the evaporation time of the electron beam physical vapor deposition thermal barrier coating is 30-60 minutes.

11. The preparation method according to claim 2, characterized in that: In step four, the thermal barrier coating deposited by electron beam physical vapor deposition is cooled to below 100°C in the furnace, and the cooling is natural cooling.

12. The preparation method according to claim 2, characterized in that: The sample matrix described in steps two through four is a nickel-based high-temperature alloy.

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