CN115418599A - Thermal barrier coating of engine impeller and surface treatment method - Google Patents
Thermal barrier coating of engine impeller and surface treatment method Download PDFInfo
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- CN115418599A CN115418599A CN202211021034.XA CN202211021034A CN115418599A CN 115418599 A CN115418599 A CN 115418599A CN 202211021034 A CN202211021034 A CN 202211021034A CN 115418599 A CN115418599 A CN 115418599A
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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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C29/00—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides
- C22C29/02—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides
- C22C29/06—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds
- C22C29/067—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds comprising a particular metallic binder
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C29/00—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides
- C22C29/02—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides
- C22C29/06—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds
- C22C29/08—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds based on tungsten carbide
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C30/00—Alloys containing less than 50% by weight of each constituent
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/0005—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with at least one oxide and at least one of carbides, nitrides, borides or silicides as the main non-metallic constituents
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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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
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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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
- C23C4/11—Oxides
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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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/18—After-treatment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
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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
Abstract
The invention relates to B23P6, in particular to a thermal barrier coating of an engine impeller and a surface treatment method. The thermal barrier coating of the engine impeller comprises a first coating, a second coating and a third coating; the thickness of the first coating is 87-97 μm, the thickness of the second coating is 360-380 μm, and the thickness of the third coating is 360-400 μm. In the first coating, the weight ratio of nickel powder, chromium carbide, aluminum oxide and yttrium oxide is controlled to be (13-17): (15-20): (15-20): (5-10), not only has improved the cavitation erosion resisting effect of the coating, has improved the thermal shock resisting effect of the coating, the coating is difficult to split and strip, the thermal barrier coating of the engine impeller that the invention provides, under certain current, use plasma equipment to spray, after processing with the laser remelting machine, not only the quality of the coating is improved, have also improved the reliability of the aircraft engine work.
Description
Technical Field
The invention relates to B23P6, in particular to a thermal barrier coating of an engine impeller and a surface treatment method.
Background
The engine impeller is an important component part of an aircraft engine. The impeller is connected with the blades, and the blades rotate at a high speed to suck high-temperature and high-pressure gas into the combustor assembly to provide power for the operation of the engine. In such a harsh environment with high temperature and high pressure, in order to ensure stable operation of the engine impeller and the engine blade, some means such as boundary layer cooling, thermal barrier coating, etc. are generally required to be used in the surface treatment process of the impeller and the engine blade.
Patent No. CN113102145A provides a surface treatment method for turbine engine impeller production, which improves the structure of surface treatment equipment, so that scattered coating is taken away by water during spraying, the coating is not easy to accumulate, and the quality of the impeller is ensured. Patent No. CN103205607B provides an anti-cavitation coating material and a high-speed fuel centrifugal pump with an anti-cavitation coating, in which elements such as carbon, boron, silicon and the like are doped in a specific ratio, and the thickness of the coating is controlled to 200um, so that the component can resist cavitation.
When the impeller is coated, the quality of the coating must be improved, which not only requires that the impeller has the capability of cavitation erosion resistance, but also requires that the coating can further improve the reliability of the engine operation.
Disclosure of Invention
In order to solve the above problems, a first aspect of the present invention provides a thermal barrier coating of an engine impeller, the thermal barrier coating of the engine impeller comprising a first coating, a second coating and a third coating; the thickness of the first coating is 87-97 μm, the thickness of the second coating is 360-380 μm, and the thickness of the third coating is 360-400 μm.
Preferably, the thickness of the first coating layer is 90-95 μm, the thickness of the second coating layer is 370 μm, and the thickness of the third coating layer is 370-390 μm.
Further preferably, the surface of the engine impeller is in contact with a first coating, and the thermal barrier coating comprises the first coating, a second coating and a third coating from inside to outside in sequence.
In a preferred embodiment of the present invention, the raw material of the first coating layer includes one or more of chromium, aluminum, nickel, yttrium, cadmium, and palladium.
Preferably, the raw material of the first coating layer includes nickel element, chromium element, aluminum element, and yttrium element.
More preferably, the nickel element is derived from nickel powder; the chromium element is derived from chromium carbide, wherein the chromium carbide contains 80-90wt% of Cr and 10-17wt% of C; the aluminum element is derived from aluminum oxide, and the particle size is less than 50um; the yttrium element is derived from yttrium oxide, the particle diameter of yttrium oxide is 15-25 μm, and the specific surface area is 30-49m 2 /g。
More preferably, the weight ratio of the nickel powder, the chromium carbide, the aluminum oxide and the yttrium oxide is (13-17): (15-20): (15-20): (5-10).
More preferably, the weight ratio of nickel powder, chromium carbide, aluminum oxide and yttrium oxide is 15:18:16:7.
in order to improve the coating quality of the aircraft engine impeller, through a large number of experiments, the applicant found that the first coating contains nickel, chromium, aluminum and yttrium elements, and the proportion of the elements is controlled, in particular the weight ratio of nickel powder, chromium carbide, aluminum oxide and yttrium oxide is (13-17): (15-20): (15-20): and (5-10), the cavitation erosion resistance effect of the coating is improved, and the thermal shock resistance effect of the coating is also improved. When the coating is sprayed by plasma, the Cr content is 80-90wt%, the C content is 10-17wt%, the chromium carbide, the alumina with the grain diameter less than 50um, the grain diameter is 15-25 μm, and the specific surface area is 30-49m 2 The specific contact between the raw materials occurs under the combined action of/g yttrium oxide and nickel powder, and meanwhile, part of new particle impurities are generated due to high temperature, so that the first coating forms a unique structure, the porosity and the roughness are influenced, specific agglomeration occurs between particles, the matching effect with the sprayed base material and the second coating is improved, the cavitation resistance and the thermal shock resistance of the coating are improved, and the coating is not easy to crack and peel.
As a preferable technical solution of the present invention, the raw material of the second coating layer includes one or more of carbon, zirconium, silicon, tin, aluminum, tungsten, cobalt, and chromium.
Preferably, the raw material of the second coating layer includes carbon element, tungsten element and cobalt element.
Further preferably, the raw material of the second coating is WC-10Co-4Cr and WC-12Co.
More preferably, the weight ratio of WC-10Co-4Cr to WC-12Co is (5-8): (3-6).
As a preferred technical solution of the present invention, the third coating is a nano coating.
As a preferred technical solution of the present invention, the raw material of the nano coating is selected from one or more of nano titanium dioxide, nano yttrium oxide, nano zirconium oxide and nano zirconium hydroxide.
As a preferable technical scheme of the invention, the raw material of the nano coating is nano zirconium hydroxide, the particle size of the nano zirconium hydroxide is 10-40nm, and the nano zirconium hydroxide contains iron and silicon.
Preferably, the content of iron in the nano zirconium hydroxide is less than 0.005wt%, and the content of silicon in the nano zirconium hydroxide is less than 0.005wt%.
In a preferred embodiment of the present invention, the first coating layer has a spraying current of 700 to 710A during spraying.
As a preferable technical scheme of the invention, the spraying current of the second coating during spraying is 900-915A.
In a preferred embodiment of the present invention, the spray current of the third coating layer during spraying is 930-950A.
Preferably, the application method of the thermal barrier coating of the engine impeller comprises the following steps: and the first coating, the second coating and the third coating are sprayed by plasma equipment and processed by a laser remelting machine after spraying.
The invention provides a surface treatment method of a thermal barrier coating of an engine impeller, which is applied to an aeroengine surface treatment method.
Compared with the prior art, the invention has the following beneficial effects:
in the first coating, the weight ratio of nickel powder, chromium carbide, aluminum oxide and yttrium oxide is controlled to be (13-17): (15-20): (15-20): (5-10), not only the cavitation erosion resistance effect of the coating is improved, but also the thermal shock resistance effect of the coating is improved, and the coating is not easy to crack and strip; controlling the weight ratio of the second coating WC-10Co-4Cr to WC-12Co to be (5-8): (3-6), the matching of the second coating and the first coating is further improved, and meanwhile, the matching of the second coating and the third coating is improved, so that the coatings are further not easy to crack, especially the service life of the coating close to the outer side is prolonged, and the coatings are not easy to wear; the thermal barrier coating of the engine impeller provided by the invention is sprayed by using plasma equipment under a certain current, and is processed by using a laser remelting machine, so that the quality of the coating is improved, and the working reliability of an aircraft engine is also improved.
Detailed Description
Examples
In the examples, nickel powder is purchased from a new melting material, chromium carbide is purchased from a long bridge, wherein the content of Cr is 84-87wt%, the content of C is 12-14wt%, aluminum oxide is purchased from a super primary, the grain diameter is 15-45um, the sources of yttrium oxide in the example 1 and the example 2 are different, yttrium oxide in the example 1 is purchased from a new Begal material, and the model is B-Y 2 O 3 18, particle size 18 μm, specific surface area 30-40m 2 Per g, yttrium oxide from Begal New materials, type B-Y, in example 2 2 O 3 25, particle size 25 μm, specific surface area 30-40m 2 The nano zirconium hydroxide contains iron and silicon, wherein the iron content is 0.002wt%, the silicon content is 0.002wt%, and the nano yttrium oxide is purchased from Andi, and the particle size is 20nm.
Example 1
The example provides a thermal barrier coating of an engine impeller, which comprises a first coating, a second coating and a third coating; the thickness of the first coating was 95 μm, the thickness of the second coating was 370 μm and the thickness of the third coating was 390 μm.
The surface of the engine impeller is in contact with the first coating, and the thermal barrier coating comprises the first coating, the second coating and the third coating from inside to outside in sequence.
The raw material of the first coating comprises nickel element, chromium element, aluminum element and yttrium element.
The nickel element is derived from nickel powder; the chromium element is derived from chromium carbide; the aluminum element is derived from aluminum oxide; the yttrium element is derived from yttrium oxide.
The weight ratio of nickel powder, chromium carbide, aluminum oxide and yttrium oxide is 15:18:16:7.
the raw material of the second coating comprises carbon element, tungsten element and cobalt element. The raw materials of the second coating are WC-10Co-4Cr and WC-12Co. The weight ratio of WC-10Co-4Cr to WC-12Co is 7:5.
the third coating is a nano-coating. The raw material of the nano coating is nano zirconium hydroxide.
The spraying current of the first coating during spraying is 700A; the spraying current of the second coating during spraying is 910A; the third coating layer was sprayed at a spray current of 940A.
The application method of the thermal barrier coating of the engine impeller comprises the following steps: and the first coating, the second coating and the third coating are sprayed by plasma equipment and processed by a laser remelting machine after being sprayed.
Example 2
This example provides a thermal barrier coating for an engine impeller, differing from example 1 in that the source of yttria in the first coating is different, the weight ratio of nickel powder, chromium carbide, alumina and yttria being 14:19:15:8.
example 3
This example provides a thermal barrier coating for an engine impeller, the difference being that the third coating is 380 μm thick. The third coating is a nano coating, and the raw material of the nano coating is nano yttrium oxide.
Example 4
The present example provides a thermal barrier coating for an engine impeller, differing from example 1 in that the weight ratio of WC-10Co-4Cr and WC-12Co in the second coating is 3:5.
example 5
This example provides a thermal barrier coating for an engine impeller, differing from example 1 in that the first coating comprises nickel powder, chromium carbide, alumina and yttrium oxide in a weight ratio of 14:22:19:9.
and (3) performance testing:
1. and (3) testing thermal shock resistance: thermal shock experiments were conducted according to HB7269-96 on the thermal barrier coatings of the engine impellers obtained in examples 1-5, and the number of thermal shock failures at which cracks started to appear was measured, with the results shown in Table 1:
TABLE 1
| Examples | Number of thermal shock failures |
| 1 | 53 |
| 2 | 53 |
| 3 | 51 |
| 4 | 46 |
| 5 | 47 |
2. And (3) appearance testing: thermal shock experiments were performed on the thermal barrier coatings of the engine impellers obtained in examples 1 to 5 according to HB7269 to 96, and the mass loss percentage of the thermal barrier coatings of the engine impellers was measured after 180 thermal shock cycle times, with the results shown in table 2:
TABLE 2
| Examples | Percentage mass loss (%) |
| 1 | 11 |
| 2 | 12 |
| 3 | 15 |
| 4 | 15 |
| 5 | 23 |
Claims (10)
1. A thermal barrier coating of an engine wheel, comprising a first coating, a second coating, and a third coating; the thickness of the first coating is 87-97 μm, the thickness of the second coating is 360-380 μm, and the thickness of the third coating is 360-400 μm.
2. The thermal barrier coating of an engine impeller of claim 1, wherein the raw material of the first coating comprises one or more of chromium, aluminum, nickel, yttrium, cadmium, palladium.
3. The thermal barrier coating of an engine impeller of claim 1, wherein the raw material of the second coating comprises one or more of elemental carbon, elemental zirconium, elemental silicon, elemental tin, elemental aluminum, elemental tungsten, elemental cobalt, and elemental chromium.
4. The thermal barrier coating of an engine impeller of claim 1, wherein the third coating is a nanocoating.
5. The thermal barrier coating of an engine impeller of claim 4, wherein the nano coating is made from one or more materials selected from nano titania, nano yttria, nano zirconia, and nano zirconia hydroxide.
6. The thermal barrier coating of an engine impeller as claimed in claim 5, wherein the nano coating is made of nano zirconium hydroxide, the nano zirconium hydroxide has a particle size of 10-40nm, and the nano zirconium hydroxide contains iron and silicon.
7. The thermal barrier coating of an engine impeller of claim 1, wherein the first coating when sprayed has a spray current of 700-710A.
8. The thermal barrier coating of an engine impeller of claim 7, wherein the second coating when sprayed has a spray current of 900-915A.
9. The thermal barrier coating of an engine impeller of any of claims 1-8, wherein the third coating when sprayed has a spray current of 930-950A.
10. A method for the surface treatment of a thermal barrier coating of an engine wheel according to claims 1 to 9, characterized in that it is applied in an aeroengine surface treatment method.
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| CN112176275A (en) * | 2020-10-26 | 2021-01-05 | 中国人民解放军陆军装甲兵学院 | Thermal barrier coating and preparation method and application thereof |
| CN112481577A (en) * | 2020-11-18 | 2021-03-12 | 东北大学 | Thermal shock resistant thermal barrier coating material and preparation method thereof |
| CN113388801A (en) * | 2021-06-18 | 2021-09-14 | 北京理工大学 | Thermal barrier coating with composite double-ceramic-layer structure and preparation method thereof |
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2022
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| CN1178204A (en) * | 1996-09-19 | 1998-04-08 | 株式会社东芝 | Thermal insulation coating components, their manufacture and gas turbine parts using them |
| CN1221067A (en) * | 1997-11-26 | 1999-06-30 | 联合技术公司 | Columnar zirconium oxide abrasive coating for gas turbine engine seal system |
| CN101748402A (en) * | 2009-12-10 | 2010-06-23 | 南昌航空大学 | Method of laser induction composite cladding gradient function thermal barrier coating |
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| CN103789715A (en) * | 2014-02-10 | 2014-05-14 | 江苏大学 | Anti-oxidization thermal barrier coating material with long service life and preparation method thereof |
| CN206071650U (en) * | 2016-07-20 | 2017-04-05 | 上海电气（集团）总公司 | A kind of turbine blade of gas turbine |
| CN109706418A (en) * | 2019-02-28 | 2019-05-03 | 北京金轮坤天特种机械有限公司 | A kind of double ceramic layer structure 8YSZ thermal barrier coatings and preparation method |
| CN112176275A (en) * | 2020-10-26 | 2021-01-05 | 中国人民解放军陆军装甲兵学院 | Thermal barrier coating and preparation method and application thereof |
| CN112481577A (en) * | 2020-11-18 | 2021-03-12 | 东北大学 | Thermal shock resistant thermal barrier coating material and preparation method thereof |
| CN113388801A (en) * | 2021-06-18 | 2021-09-14 | 北京理工大学 | Thermal barrier coating with composite double-ceramic-layer structure and preparation method thereof |
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