CN113373408A - Dysprosium-doped gadolinium zirconate thermal barrier coating material and preparation method of coating - Google Patents

Dysprosium-doped gadolinium zirconate thermal barrier coating material and preparation method of coating Download PDF

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CN113373408A
CN113373408A CN202110531588.3A CN202110531588A CN113373408A CN 113373408 A CN113373408 A CN 113373408A CN 202110531588 A CN202110531588 A CN 202110531588A CN 113373408 A CN113373408 A CN 113373408A
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thermal barrier
dysprosium
barrier coating
doped gadolinium
gadolinium zirconate
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CN113373408B (en
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申造宇
王立哲
刘冠熙
牟仁德
何利民
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AECC Beijing Institute of Aeronautical Materials
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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
    • 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
    • C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
    • 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
    • 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
    • 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 aeroengines, and relates to a dysprosium-doped gadolinium zirconate thermal barrier coating material and a preparation method of the coating, wherein the chemical molecular formula of the dysprosium-doped gadolinium zirconate thermal barrier coating material is (Dy)xGd1‑x)2Zr2O7Wherein x is 0.05-0.20; the thermal expansion coefficient of the thermal barrier coating material is closer to that of YSZ, the thermal barrier coating material has lower thermal conductivity, and meanwhile, the dysprosium-doped gadolinium zirconate thermal barrier coating is prepared by utilizing an electron beam physical vapor deposition technology, so that the dysprosium-doped gadolinium zirconate thermal barrier coating has a unique columnar crystal structure and has 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 coatingAnd the practical problems of short service life and low thermal expansion coefficient of the coating can be solved.

Description

Dysprosium-doped gadolinium zirconate thermal barrier coating material and preparation method of coating
Technical Field
The invention belongs to the technical field of thermal barrier coatings of aeroengines, and relates to a dysprosium-doped gadolinium zirconate thermal barrier coating material and a preparation method of the coating.
Background
At present, with the continuous improvement of the thrust and the working efficiency of the gas turbine, the gas inlet temperature is higher and higher, and the working temperature of the nickel-based high-temperature alloy used for the turbine blade and other hot-end components is gradually close to the service temperature limit. Thermal Barrier Coatings (TBCs) are a surface protection technology which combines ceramic materials with a metal substrate in the form of a coating by utilizing the high temperature resistance, scouring resistance, corrosion resistance and low Thermal conductivity of the ceramic materials, so as to improve the working temperature of metal components, enhance the high temperature resistance of hot end components, prolong the service life of the hot end components and improve the working efficiency of an engine. Currently, the YSZ (6-8 wt.% Y) is widely used2O3Partially stabilized ZrO2) The thermal barrier coating material has high thermal conductivity. However, the next generation of high performance aircraft engine thermal barrier coating materials require more excellent thermal insulation effects, i.e., low thermal conductivity. Therefore, the research on new thermal barrier coating materials has become a key issue for the development of the next generation of high performance aeroengines.
Disclosure of Invention
The invention provides a dysprosium-doped gadolinium zirconate thermal barrier coating material and a preparation method thereof aiming at the defects of the prior art, aims to dope rare earth dysprosium element, and solves the problems of short service life and high YSZ thermal conductivity of a single gadolinium zirconate thermal barrier coating.
The purpose of the invention is realized by the following technical measures:
a dysprosium-doped gadolinium zirconate thermal barrier coating material is characterized in that: the chemical molecular formula of the dysprosium doped gadolinium zirconate thermal barrier coating material is (Dy)xGd1-x)2Zr2O7Wherein x is 0.05-0.20.
The preparation method of the dysprosium doped gadolinium zirconate thermal barrier coating material coating is characterized by comprising the following steps of: the method comprises the following steps:
step one, raw material Dy2O3、Gd2O3、ZrO2Mixing according to the molecular formula proportion of the material, and synthesizing the dysprosium doped gadolinium zirconate target by a high-temperature solid-phase method at the synthesis temperature of 1400-1600 ℃;
step two, preparing a NiCoCrAlYHf metal bottom layer as a thermal barrier coating by adopting vacuum arc plating equipment, wherein the voltage is 600-650V, and the current is 10-20A;
and step three, the dysprosium-doped gadolinium zirconate target is loaded into electron beam physical vapor deposition equipment, the dysprosium-doped gadolinium zirconate target is evaporated through electron beams, and a dysprosium-doped gadolinium zirconate thermal barrier coating is prepared on the NiCoCrAlYHf bottom layer, wherein the beam intensity of the electron beams is 1.3-1.5A.
Step one raw material Dy2O3、Gd2O3、ZrO2The purity of the product is more than or equal to 99.9 percent.
In the first step, the raw material mixing is mechanical ball milling for more than or equal to 6 hours.
The synthesis time of the step I by a high-temperature solid phase method is more than or equal to 12 hours.
Vacuum degree of vacuum arc plating equipment in the second step<1×10-2Pa。
And in the second step, the deposition time of the vacuum arc plating equipment is more than or equal to 100 min.
Vacuum degree of electron beam physical vapor deposition equipment in the third step<2×10-2Pa。
In the third step, the evaporation time of the electron beam physical vapor deposition thermal barrier coating is more than or equal to 30 min.
And in the third step, the thermal barrier coating deposited by the electron beam physical vapor deposition is cooled to below 200 ℃ along with the furnace, and the cooling is natural cooling.
The invention has the advantages and beneficial effects that the thermal barrier coating material as a novel thermal barrier coating material has a thermal expansion coefficient which is closer to that of YSZ and has lower thermal conductivity. Meanwhile, the dysprosium-doped gadolinium zirconate thermal barrier coating is prepared by utilizing an electron beam physical vapor deposition technology, so that the dysprosium-doped gadolinium zirconate thermal barrier coating has a unique columnar crystal structure and has a better service life; the invention can not only ensure to reduce the heat conductivity of the coating, but also improve the service temperature of the coating, and also improve the practical problems of short service life and low thermal expansion coefficient of the coating.
Drawings
FIG. 1 is a schematic view of thermal conductivity of example 2
FIG. 2 is a schematic view showing the thermal expansion coefficient in example 2
FIG. 3 is a schematic view of thermal life in example 2
FIG. 4 is a schematic view of a columnar crystal structure of the present invention
Detailed Description
The technical scheme of the invention is further detailed in the following by combining the drawings and the embodiment:
the chemical molecular formula of the dysprosium doped gadolinium zirconate thermal barrier coating material is (Dy)xGd1-x)2Zr2O7Wherein x is 0.05-0.20.
The preparation method of the dysprosium doped gadolinium zirconate thermal barrier coating material coating comprises the following steps:
dy as a raw material2O3、Gd2O3、ZrO2Mixing according to the molecular formula ratio of the material, wherein the purity of the raw material is more than or equal to 99.9 percent, the mixing mode is mechanical ball milling, and the time is more than or equal to 6 hours; synthesizing the target material by a high-temperature solid-phase method, wherein the synthesis temperature is 1400 ℃ and 1600 ℃, and the synthesis time is more than or equal to 12 hours; preparing NiCoCrAlYHf as a metal bottom layer of a thermal barrier coating by adopting vacuum arc plating equipment, wherein the vacuum degree<1×10-2Pa, voltage of 600-650V, current of 10-20A, and deposition time of 100min or more; the prepared target material is loaded into electron beam physical vapor deposition equipment with vacuum degree<2×10-2P, the beam intensity of the electron beam is 1.3-1.5A, the evaporation time is more than or equal to 30min, a thermal barrier coating is prepared, and the thermal barrier coating is naturally cooled to below 200 ℃ along with the furnace.
Example 1:
the method comprises the following steps of: weighing raw materials Dy2O3, Gd2O3 and ZrO2 according to the molecular formula (Dy0.08Gd0.92)2Zr2O7 of the dysprosium-doped gadolinium zirconate thermal barrier coating material.
The method comprises the following steps of: mechanically ball-milling the raw materials for 8 hours, and synthesizing the dysprosium doped gadolinium zirconate target by a high-temperature solid phase method at 1400 ℃ for 20 hours;
(3) preparing a bottom layer: preparing a NiCoCrAlYHf metal bottom layer serving as a thermal barrier coating by adopting vacuum arc plating equipment, wherein the vacuum degree is less than 1 multiplied by 10 < -2 > Pa, the voltage is 600V, the current is 10A, and the deposition time is 200 min;
(4) and preparing a thermal barrier coating: and (3) loading the dysprosium doped gadolinium zirconate target into electron beam physical vapor deposition equipment. Deposition process parameters: the vacuum degree is less than 2 multiplied by 10 < -2 > Pa, the electron beam current intensity is 1.35A, the evaporation time is 60min, and after cooling to below 200 ℃, deposition equipment is opened to obtain the dysprosium-doped gadolinium zirconate thermal barrier coating.
The thermal conductivity of the prepared dysprosium-doped gadolinium zirconate thermal barrier coating at 1000 ℃ is 1.03W/(mK); the thermal expansion coefficient is 10.56 multiplied by 10-6K-1; the thermal life was 670 hours.
Example 2:
the method comprises the following steps of: weighing raw materials Dy2O3, Gd2O3 and ZrO2 according to the molecular formula (Dy0.12Gd0.88)2Zr2O7 of the dysprosium-doped gadolinium zirconate thermal barrier coating material.
The method comprises the following steps of: mechanically ball-milling the raw materials for 10 hours, and synthesizing the dysprosium doped gadolinium zirconate target by a 1500 ℃ high-temperature solid phase method for 16 hours;
(3) preparing a bottom layer: preparing a NiCoCrAlYHf metal bottom layer serving as a thermal barrier coating by adopting vacuum arc plating equipment, wherein the vacuum degree is less than 1 multiplied by 10 < -2 > Pa, the voltage is 625V, the current is 15A, and the deposition time is 150 min;
(4) and preparing a thermal barrier coating: and (3) loading the dysprosium doped gadolinium zirconate target into electron beam physical vapor deposition equipment. Deposition process parameters: the vacuum degree is less than 2 multiplied by 10 < -2 > Pa, the electron beam current intensity is 1.45A, the evaporation time is 40min, and after cooling to below 200 ℃, deposition equipment is opened to obtain the dysprosium-doped gadolinium zirconate thermal barrier coating.
The thermal conductivity of the prepared dysprosium-doped gadolinium zirconate thermal barrier coating at 1000 ℃ is 0.97W/(mK); the thermal expansion coefficient is 10.75 multiplied by 10-6K-1; the thermal life was 750 hours.
Example 3:
the method comprises the following steps of: weighing raw materials Dy2O3, Gd2O3 and ZrO2 according to the molecular formula (Dy0.18Gd0.82)2Zr2O7 of the dysprosium-doped gadolinium zirconate thermal barrier coating material.
The method comprises the following steps of: mechanically ball-milling the raw materials for 12 hours, and synthesizing the dysprosium doped gadolinium zirconate target by a 1600 ℃ high-temperature solid phase method for 14 hours;
(3) preparing a bottom layer: preparing a NiCoCrAlYHf metal bottom layer as a thermal barrier coating by adopting vacuum arc plating equipment, wherein the voltage is 650V, the current is 20A, and the deposition time is 100 min;
(4) and preparing a thermal barrier coating: and (3) loading the dysprosium doped gadolinium zirconate target into electron beam physical vapor deposition equipment. Deposition process parameters: the vacuum degree is less than 2 multiplied by 10 < -2 > Pa, the electron beam current intensity is 1.55A, the evaporation time is 30min, and after cooling to below 200 ℃, deposition equipment is opened to obtain the dysprosium-doped gadolinium zirconate thermal barrier coating.
The thermal conductivity of the prepared dysprosium-doped gadolinium zirconate thermal barrier coating at 1000 ℃ is 0.98W/(mK); the thermal expansion coefficient is 10.68 multiplied by 10-6K-1; the thermal life was 725 hours.
As can be seen from the above embodiments, compared with the prior art, the technical scheme of the invention has the advantages that:
(1) in the preparation method, the thermal barrier coating is prepared by using the electron beam physical vapor deposition technology, so that the thermal barrier coating has a unique columnar crystal structure and a longer service life.
(2) In the design of the coating, through dysprosium doping modification, the thermal conductivity of the coating can be reduced, and the practical problem of low thermal expansion coefficient of single gadolinium zirconate can be solved.

Claims (10)

1. A dysprosium-doped gadolinium zirconate thermal barrier coating material is characterized in that: the chemical molecular formula of the dysprosium doped gadolinium zirconate thermal barrier coating material is (Dy)xGd1-x)2Zr2O7Wherein x is 0.05-0.20.
2. The method for preparing the coating of the dysprosium-doped gadolinium zirconate thermal barrier coating material according to claim 1, characterized in that: the method comprises the following steps:
step one, raw material Dy2O3、Gd2O3、ZrO2Mixing according to the molecular formula proportion of the material, and synthesizing the dysprosium doped gadolinium zirconate target by a high-temperature solid-phase method at the synthesis temperature of 1400-1600 ℃;
step two, preparing a NiCoCrAlYHf metal bottom layer as a thermal barrier coating by adopting vacuum arc plating equipment, wherein the voltage is 600-650V, and the current is 10-20A;
and step three, the dysprosium-doped gadolinium zirconate target is loaded into electron beam physical vapor deposition equipment, the dysprosium-doped gadolinium zirconate target is evaporated through electron beams, and a dysprosium-doped gadolinium zirconate thermal barrier coating is prepared on the NiCoCrAlYHf bottom layer, wherein the beam intensity of the electron beams is 1.3-1.5A.
3. The method for preparing the coating of the dysprosium-doped gadolinium zirconate thermal barrier coating material according to claim 2, characterized in that: step one raw material Dy2O3、Gd2O3、ZrO2The purity of the product is more than or equal to 99.9 percent.
4. The method for preparing the coating of the dysprosium-doped gadolinium zirconate thermal barrier coating material according to claim 2, characterized in that: in the first step, the raw material mixing is mechanical ball milling for more than or equal to 6 hours.
5. The method for preparing the coating of the dysprosium-doped gadolinium zirconate thermal barrier coating material according to claim 2, characterized in that: the synthesis time of the step I by a high-temperature solid phase method is more than or equal to 12 hours.
6. The method for preparing the coating of the dysprosium-doped gadolinium zirconate thermal barrier coating material according to claim 2, characterized in that: vacuum degree of vacuum arc plating equipment in the second step<1×10-2Pa。
7. The method for preparing the coating of the dysprosium-doped gadolinium zirconate thermal barrier coating material according to claim 2, characterized in that: and in the second step, the deposition time of the vacuum arc plating equipment is more than or equal to 100 min.
8. The method for preparing the coating of the dysprosium-doped gadolinium zirconate thermal barrier coating material according to claim 2, characterized in that: vacuum degree of electron beam physical vapor deposition equipment in the third step<2×10-2Pa。
9. The method for preparing the coating of the dysprosium-doped gadolinium zirconate thermal barrier coating material according to claim 2, characterized in that: in the third step, the evaporation time of the electron beam physical vapor deposition thermal barrier coating is more than or equal to 30 min.
10. The method for preparing the coating of the dysprosium-doped gadolinium zirconate thermal barrier coating material according to claim 2, characterized in that: and in the third step, the thermal barrier coating deposited by the electron beam physical vapor deposition is cooled to below 200 ℃ along with the furnace, and the cooling is natural cooling.
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114560697A (en) * 2022-03-14 2022-05-31 清华大学 Double-rare-earth zirconate thermal barrier coating material and preparation method thereof
WO2024021527A1 (en) * 2022-07-29 2024-02-01 中国航发北京航空材料研究院 Lanthanum-gadolinium-samarium-based high-entropy thermal barrier coating and preparation method therefor

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1621556A (en) * 2004-12-15 2005-06-01 北京航空航天大学 High sintering -resistant thermal barrier coating with high thermal stability and low thermal conductivity
CN101255515A (en) * 2008-04-08 2008-09-03 北京航空航天大学 Pyrogenic oxidation resistant nickel-aluminium-dysprosium coat bond material and preparation of hot screening coating
US20100104764A1 (en) * 2005-07-12 2010-04-29 Mohamed Youssef Nazmy Method of forming a ceramic thermal barrier coating
CN102212786A (en) * 2011-05-27 2011-10-12 中国航空工业集团公司北京航空制造工程研究所 Method for preparing thermal barrier coating
CN104891990A (en) * 2015-05-08 2015-09-09 清华大学 Thermal barrier coating material of eutectic structure and method for manufacturing thermal spraying powder particles by utilizing material
JP2016222992A (en) * 2015-06-02 2016-12-28 株式会社東芝 Thermal barrier coating, thermal barrier member, and steam device
CN107245687A (en) * 2017-06-09 2017-10-13 天津大学 A kind of toughness rare earth phosphate/zirconates composite thermal barrier coating and preparation method thereof
CN108101533A (en) * 2017-12-25 2018-06-01 北京有色金属研究总院 A kind of preparation method of thermal barrier coating ceramic target
CN110129729A (en) * 2019-06-28 2019-08-16 西北有色金属研究院 Nickel-base alloy surface NiCrAlY/NiCrAlY-YSZ/YSZ thermal barrier coating and preparation method thereof
CN110144554A (en) * 2019-05-23 2019-08-20 西北有色金属研究院 The preparation method of the laser modified YSZ thermal barrier coating of high-temperature alloy surface NiCrAlY/YSZ/

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1621556A (en) * 2004-12-15 2005-06-01 北京航空航天大学 High sintering -resistant thermal barrier coating with high thermal stability and low thermal conductivity
US20100104764A1 (en) * 2005-07-12 2010-04-29 Mohamed Youssef Nazmy Method of forming a ceramic thermal barrier coating
CN101255515A (en) * 2008-04-08 2008-09-03 北京航空航天大学 Pyrogenic oxidation resistant nickel-aluminium-dysprosium coat bond material and preparation of hot screening coating
CN102212786A (en) * 2011-05-27 2011-10-12 中国航空工业集团公司北京航空制造工程研究所 Method for preparing thermal barrier coating
CN104891990A (en) * 2015-05-08 2015-09-09 清华大学 Thermal barrier coating material of eutectic structure and method for manufacturing thermal spraying powder particles by utilizing material
JP2016222992A (en) * 2015-06-02 2016-12-28 株式会社東芝 Thermal barrier coating, thermal barrier member, and steam device
CN107245687A (en) * 2017-06-09 2017-10-13 天津大学 A kind of toughness rare earth phosphate/zirconates composite thermal barrier coating and preparation method thereof
CN108101533A (en) * 2017-12-25 2018-06-01 北京有色金属研究总院 A kind of preparation method of thermal barrier coating ceramic target
CN110144554A (en) * 2019-05-23 2019-08-20 西北有色金属研究院 The preparation method of the laser modified YSZ thermal barrier coating of high-temperature alloy surface NiCrAlY/YSZ/
CN110129729A (en) * 2019-06-28 2019-08-16 西北有色金属研究院 Nickel-base alloy surface NiCrAlY/NiCrAlY-YSZ/YSZ thermal barrier coating and preparation method thereof

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114560697A (en) * 2022-03-14 2022-05-31 清华大学 Double-rare-earth zirconate thermal barrier coating material and preparation method thereof
WO2024021527A1 (en) * 2022-07-29 2024-02-01 中国航发北京航空材料研究院 Lanthanum-gadolinium-samarium-based high-entropy thermal barrier coating and preparation method therefor

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