CN105132908A - Gas turbine blade thermal barrier coating bonding layer and preparation method thereof - Google Patents
Gas turbine blade thermal barrier coating bonding layer and preparation method thereof Download PDFInfo
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- CN105132908A CN105132908A CN201510676900.2A CN201510676900A CN105132908A CN 105132908 A CN105132908 A CN 105132908A CN 201510676900 A CN201510676900 A CN 201510676900A CN 105132908 A CN105132908 A CN 105132908A
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- Prior art keywords
- bonding layer
- barrier coating
- gas turbine
- turbine blades
- coating bonding
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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
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
-
- 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
-
- 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
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
A gas turbine blade thermal barrier coating bonding layer is composed of powdery Co, Ni, Cr, Al and Y. The optimal range of the powder particle size is 10-50 micrometers. A preparation method comprises the steps that 1, oil removal, washing and drying are performed on the surface of a matrix before spraying is performed, 40-80-mesh corundum is used for sand-blasting roughening, and floating dust is removed to form the rough surface; 2, the powder forming the bonding layer is kept at the temperature of 200-300 DEG C for 4 h before spraying is performed, and the powder is sufficiently softened; 3, a cold spraying method is adopted for preparing the bonding layer on the surface of the matrix; 4, the surface of the bonding layer is sprayed through the plasma technology to obtain an 8YSZ ceramic surface layer; 5, a complete thermal barrier coating is kept at the temperature of 900-1100 DEG C in a vacuum heat treatment furnace for 4 h, and the vacuum degree is lower than 10<-3>Pa. The technology is simple and low in cost; the porosity of the bonding layer is controlled to be smaller than 1%, and the structure is compact; pressure stress exists inside the coating, and the thermal expansion matching in the coating service process can be relieved; the bonding strength of the coating is improved, and the oxidation resistance of the coating is improved.
Description
Technical field
The present invention relates to a kind of Composition Design of CoNiCrAlY heat barrier coating bonding layer of gas turbine blades.The invention still further relates to the CoNiCrAlY heat barrier coating bonding layer preparation method of described gas turbine blades.
Background technology
Gas turbine blades is the important hot-end component of internal combustion turbine, and its working temperature decides the thermo-efficiency of internal combustion turbine, and therefore it subjects the harshest Working environment.How to improve gas turbine blades and comprise the Main way that the thermo-efficiency under the harsh Service Environment such as corrosion and oxidation is internal combustion turbine development.The technology generally adopted at present is that blade surface prepares thermal barrier coating.Typical thermal barrier coating is made up of stable zirconium white (YSZ) ceramic topcoats of partial oxidation yttrium and MCrAlY tack coat, and tack coat quality decides the quality of whole thermal barrier coating high-temperature oxidation resistance.Generally adopt low-voltage plasma spraying (LPPS) or hypersonic flame spraying (HVOF) in conventional art, its composition and advanced preparation technology are grasped by external.
Existing thermospray prepares that heat barrier coating bonding layer porosity is high, coating compactness is inadequate.
Cold spray technique (GasDynamicSpray, GDS) is a kind of coat preparing technology that development in recent years is got up; The theoretical basis of cold spraying is: pressurized gas (air, N
2, He) be heated to certain temperature (being less than 600 DEG C), and by pressurized gas accelerate metallics to critical velocity (supersonic speed), there is severe plastic deformation after striking matrix surface in metallics.Metallics hits flat at matrix surface and firm attachment, and whole process metallics is not melted; The coating compactness obtained is good, and porosity is low, and thickness is easy to control.
Summary of the invention
First technical problem to be solved by this invention, is just to provide a kind of CoNiCrAlY heat barrier coating bonding layer of gas turbine blades.
Second technical problem to be solved by this invention, is just to provide the preparation method of the CoNiCrAlY heat barrier coating bonding layer of above-mentioned gas turbine blades.
The CoNiCrAlY heat barrier coating bonding layer of the gas turbine blades adopting the inventive method to prepare, by suitable heat treating regime, improve the combination of tack coat and matrix, and prepare oxide film in tie layer surface, further increase its high-temperature oxidation resistance, reduce heat barrier coating bonding layer porosity, be extremely suitable for being applied on gas-turbine blade.
Solve above-mentioned first technical problem, the technical solution used in the present invention is as follows:
A kind of gas turbine blades heat barrier coating bonding layer, is characterized in that: be made up of pulverous Co, Ni, Cr, Al and Y.
Preferred version is: Ni31 ~ 33%, Cr31 ~ 33%, Al7 ~ 9%, Y0.5 ~ 0.8%, Co surplus, and described each component percentages refers to mass percent.
The powder diameter preferable range of described each component 10 ~ 50 μm.
Spraying base material refers in particular to GTD111 or MGA1400 superalloy, and adhesive layer thickness is at 100 ~ 150 μm.
Solve above-mentioned second technical problem, the technical solution used in the present invention is as follows:
Above-mentioned heat barrier coating bonding layer preparation method, is characterized in that: adopt cold spray process preparation, comprise the following steps:
(1) matrix surface oil removing before spraying, washing, oven dry, with the capable sandblasting roughening treatment of 40-80 order corundum, removes floating dust, forms uneven surface;
(2) before spraying, each powder of composition tack coat is incubated 4h at 200 ~ 300 DEG C, fully softening powder;
(3) cold spray-coating method is adopted to prepare tack coat at matrix surface;
(4) tie layer surface adopts plasma process spraying to obtain 8YSZ ceramic topcoats;
(5) by complete thermal barrier coating 900-1100 DEG C of insulation 4h under vacuum heat treatment furnace, low vacuum is in 10
-3pa.
The design parameter that described step (3) adopts is: working gas N
2, spray pressure 2.5-3MPa, temperature 500-600 DEG C, spray distance is 10mm, and spray gun translational speed is 80mm/s, and powder feeding rate is at 18-20gmin
-1.
The design parameter that described step (4) adopts is: spraying current 650A, voltage 36V, main Ar flow 30psi, auxiliary H
2flow 20psi, powder feeding rate 2.3rpm, spray distance 80mm, spray 9 passages; Surface ceramic layer thickness 200 μm.
Compared with coating prepared by the thermal barrier coating that the present invention obtains and prior art, there is following advantage and effect:
(1) cold spray technique technique is simple, and cost is low;
(2) the tack coat porosity that prepared by cold spraying controls below 1%, compact structure;
(3) coat inside prepared has stress, can alleviate the thermal expansion matching of coating military service process;
(4) after thermal treatment, tack coat and matrix form diffusion layer, improve anchoring strength of coating;
(5) after thermal treatment, tie layer surface forms layer oxide film, and coating antioxidant property improves.
Tack coat prepared by the present invention overcomes the hole defect that traditional hot-spraying techniques is brought, again by thermal treatment, improve tissue and the structure of coating, high-temperature oxidation resistance is improved, thermal barrier coating life, can promote the use of on large-scale gas turbine blade.
Accompanying drawing explanation
Fig. 1 is complete structure schematic diagram after the thermal barrier coating thermal treatment prepared of this technique;
Fig. 2 is used for the original SEM pattern of heat barrier coating bonding layer Co32Ni32Cr8Al0.5Y powder of the present invention;
Fig. 3 is used for the original SEM pattern of thermal barrier coating YSZ ceramic layer powder of the present invention.
Reference numeral in figure: 1-8YSZ ceramic layer, 2-α-Al
2o
3oxide film, 3-Co32Ni32Cr8Al0.5Y tack coat, 4-diffusion layer, 5-GTD111 or MGA1400 high temperature matrix.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
Gas turbine blades heat barrier coating bonding layer embodiment of the present invention, the metal-powder meeting tack coat component requirements that tack coat component is prepared by German ALD company vacuum aerosolization technology, composition is respectively:
Ni31 ~ 33%, Cr31 ~ 33%, Al7 ~ 9%, Y0.5 ~ 0.8%, Co surplus, described each component percentages refers to mass percent.
Preferred version is: Ni32%, Cr32%, Al8%, Y0.5%, Co surplus, and described each component percentages refers to mass percent, and powdered material particle diameter is at 10 ~ 50 μm, prepared by vacuum aerosolization technology.
As shown in Figure 2, spheroidal particle, even particle size distribution, major part is spherical to its pattern, and good fluidity is incubated 4h at spraying first 200 DEG C.
Surface ceramic composition of layer is 8YSZ, and the original SEM pattern of powder as shown in Figure 3.
The implementation step preparing heat barrier coating bonding layer and ceramic layer on surface comprises following 4 steps:
(1) matrix alloy surface degreasing, washing, oven dry, 40-80 order corundum sand washing process, removes floating dust;
(2) before spraying, each powder of composition tack coat is incubated 4h at 200 ~ 300 DEG C, fully softening powder; Cold spray technique prepares tack coat, and thickness is at 100 μm, and main spray parameters is: working gas N
2, spray pressure 2.7MPa, temperature 550 DEG C, spray distance is 10mm, and spray gun translational speed is 80mm/s, and powder feeding rate is at 18gmin
-1;
(3) plasma spray coating process prepares 8YSZ surface ceramic coat, and processing parameter is mainly, spraying current 650A, voltage 36V, main Ar flow 30psi, auxiliary H
2flow 20psi, powder feeding rate 2.3rpm, spray distance 80mm, spray 9 passages.
(4) structure that thermal barrier coating is complete is placed in vacuum heat treatment furnace, constant temperature 4h at 1050 DEG C, vacuum tightness 10
-3pa.
Claims (7)
1. a gas turbine blades heat barrier coating bonding layer, is characterized in that: be made up of pulverous Co, Ni, Cr, Al and Y.
2. gas turbine blades heat barrier coating bonding layer according to claim 1, is characterized in that: the preferred version of described each component is Ni31 ~ 33%, Cr31 ~ 33%, Al7 ~ 9%, Y0.5 ~ 0.8%, Co surplus, described each component percentages refers to mass percent.
3. gas turbine blades heat barrier coating bonding layer according to claim 2, is characterized in that: the powder diameter scope of described each component 10 ~ 50 μm.
4. gas turbine blades heat barrier coating bonding layer according to claim 3, is characterized in that: spraying base material is GTD111 or MGA1400 superalloy, adhesive layer thickness 100 ~ 150 μm.
5. the gas turbine blades heat barrier coating bonding layer as described in claim 1-4 any one obtains a preparation method, it is characterized in that: adopt cold spray process preparation, comprise the following steps:
(1) substrate surface oil removing before spraying, washing, oven dry, with the capable sandblasting roughening treatment of 40-80 order corundum, removes floating dust, forms uneven surface;
(2) before spraying, each powder of composition tack coat is incubated 4h at 200 ~ 300 DEG C, fully softening powder;
(3) cold spray-coating method is adopted to prepare tack coat at matrix surface;
(4) tie layer surface adopts plasma process spraying to obtain 8YSZ ceramic topcoats;
(5) by complete thermal barrier coating 900-1100 DEG C of insulation 4h under vacuum heat treatment furnace, low vacuum is in 10
-3pa.
6. the preparation method of gas turbine blades heat barrier coating bonding layer according to claim 5, is characterized in that: the design parameter that described step (3) adopts is: working gas N
2, spray pressure 2.5-3MPa, temperature 500-600 DEG C, spray distance is 10mm, and spray gun translational speed is 80mm/s, and powder feeding rate is at 18-20gmin
-1.
7. gas turbine blades heat barrier coating bonding layer according to claim 5 obtains preparation method, it is characterized in that: the design parameter that described step (4) adopts is: spraying current 650A, voltage 36V, main Ar flow 30psi, auxiliary H
2flow 20psi, powder feeding rate 2.3rpm, spray distance 80mm, spray 9 passages; Surface ceramic layer thickness 200 μm.
Priority Applications (1)
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|---|---|---|---|
| CN201510676900.2A CN105132908A (en) | 2015-10-16 | 2015-10-16 | Gas turbine blade thermal barrier coating bonding layer and preparation method thereof |
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|---|---|---|---|
| CN201510676900.2A CN105132908A (en) | 2015-10-16 | 2015-10-16 | Gas turbine blade thermal barrier coating bonding layer and preparation method thereof |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106498335A (en) * | 2016-11-22 | 2017-03-15 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of preparation technology of hot-end component burner inner liner high temperature coating |
| CN107354418A (en) * | 2017-06-23 | 2017-11-17 | 广东技术师范学院 | A kind of Wear-resistant heat insulation coating and preparation method thereof |
| CN108754495A (en) * | 2018-06-25 | 2018-11-06 | 广东省新材料研究所 | A kind of composite thermal barrier coating and the preparation method and application thereof |
| CN108950461A (en) * | 2018-06-30 | 2018-12-07 | 黑龙江科技大学 | A kind of preparation method suitable for iron base high-temperature alloy surface thermal barrier coating |
| CN109972133A (en) * | 2019-05-10 | 2019-07-05 | 兰州理工大学 | The method that induction fabricated in situ prepares NiCoCrAlY alloy coating at high temperature |
| CN110632048A (en) * | 2019-09-19 | 2019-12-31 | 西安交通大学 | Method for improving fluorescence transmittance of thermal barrier coating sprayed by plasma |
| CN110643951A (en) * | 2019-10-14 | 2020-01-03 | 四川大学 | High-temperature oxidation resistant aluminum-chromium-silicon-nitrogen-aluminum oxide multilayer composite coating and preparation method thereof |
| CN110643953A (en) * | 2019-10-14 | 2020-01-03 | 四川大学 | Aluminum oxide/titanium aluminum nitrogen composite coating suitable for milling and preparation method thereof |
| CN110643936A (en) * | 2019-10-14 | 2020-01-03 | 四川大学 | Multilayer composite coating suitable for milling and preparation method thereof |
| CN110643935A (en) * | 2019-10-14 | 2020-01-03 | 四川大学 | Anti-crater wear titanium aluminum nitride/aluminum oxide composite coating and preparation method thereof |
| CN110643952A (en) * | 2019-10-14 | 2020-01-03 | 四川大学 | Oxidation-resistant aluminum oxide/titanium nitride silicon composite coating and preparation method thereof |
| CN110656313A (en) * | 2019-10-14 | 2020-01-07 | 四川大学 | Zirconium aluminum nitride/aluminum oxide composite coating firmly combined with hard alloy and preparation method thereof |
| CN110670020A (en) * | 2019-10-14 | 2020-01-10 | 四川大学 | Zirconium-aluminum-nitrogen-aluminum oxide multilayer composite coating firmly combined with metal ceramic and preparation method thereof |
| CN110670019A (en) * | 2019-10-14 | 2020-01-10 | 四川大学 | Anti-crater wear aluminum-titanium-zirconium-nitrogen and aluminum oxide multilayer composite coating and preparation method thereof |
| CN111057984A (en) * | 2019-12-27 | 2020-04-24 | 华瑞（江苏）燃机服务有限公司 | Hot spraying process for coating of turbine moving blade of gas turbine |
| CN113388830A (en) * | 2021-06-11 | 2021-09-14 | 季华实验室 | Preparation method of high-temperature-resistant anticorrosive ceramic coating |
| JP2022542655A (en) * | 2019-08-05 | 2022-10-06 | 沈陽富創精密設備股▲フン▼有限公司 | Manufacturing method of surface protective coating for main parts of IC device based on plasma spraying and low temperature spraying technology |
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Cited By (23)
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| CN106498335A (en) * | 2016-11-22 | 2017-03-15 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of preparation technology of hot-end component burner inner liner high temperature coating |
| CN107354418A (en) * | 2017-06-23 | 2017-11-17 | 广东技术师范学院 | A kind of Wear-resistant heat insulation coating and preparation method thereof |
| CN107354418B (en) * | 2017-06-23 | 2019-01-22 | 广东技术师范学院 | A kind of Wear-resistant heat insulation coating and preparation method thereof |
| CN108754495A (en) * | 2018-06-25 | 2018-11-06 | 广东省新材料研究所 | A kind of composite thermal barrier coating and the preparation method and application thereof |
| CN108754495B (en) * | 2018-06-25 | 2021-01-05 | 广东省科学院新材料研究所 | Composite thermal barrier coating and preparation method and application thereof |
| CN108950461A (en) * | 2018-06-30 | 2018-12-07 | 黑龙江科技大学 | A kind of preparation method suitable for iron base high-temperature alloy surface thermal barrier coating |
| CN109972133A (en) * | 2019-05-10 | 2019-07-05 | 兰州理工大学 | The method that induction fabricated in situ prepares NiCoCrAlY alloy coating at high temperature |
| JP7288548B2 (en) | 2019-08-05 | 2023-06-07 | 沈陽富創精密設備股▲フン▼有限公司 | Method for producing surface protective coatings for plasma etching chambers based on plasma spraying and low-temperature spraying technology |
| JP2022542655A (en) * | 2019-08-05 | 2022-10-06 | 沈陽富創精密設備股▲フン▼有限公司 | Manufacturing method of surface protective coating for main parts of IC device based on plasma spraying and low temperature spraying technology |
| CN110632048A (en) * | 2019-09-19 | 2019-12-31 | 西安交通大学 | Method for improving fluorescence transmittance of thermal barrier coating sprayed by plasma |
| CN110643935A (en) * | 2019-10-14 | 2020-01-03 | 四川大学 | Anti-crater wear titanium aluminum nitride/aluminum oxide composite coating and preparation method thereof |
| CN110643952A (en) * | 2019-10-14 | 2020-01-03 | 四川大学 | Oxidation-resistant aluminum oxide/titanium nitride silicon composite coating and preparation method thereof |
| CN110656313A (en) * | 2019-10-14 | 2020-01-07 | 四川大学 | Zirconium aluminum nitride/aluminum oxide composite coating firmly combined with hard alloy and preparation method thereof |
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| CN110670019A (en) * | 2019-10-14 | 2020-01-10 | 四川大学 | Anti-crater wear aluminum-titanium-zirconium-nitrogen and aluminum oxide multilayer composite coating and preparation method thereof |
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| CN110643951B (en) * | 2019-10-14 | 2021-04-30 | 四川大学 | High-temperature oxidation resistant aluminum-chromium-silicon-nitrogen-aluminum oxide multilayer composite coating and preparation method thereof |
| CN110643953B (en) * | 2019-10-14 | 2021-04-30 | 四川大学 | Aluminum oxide/titanium aluminum nitrogen composite coating suitable for milling and preparation method thereof |
| CN110643935B (en) * | 2019-10-14 | 2021-04-30 | 四川大学 | Anti-crater wear titanium aluminum nitride/aluminum oxide composite coating and preparation method thereof |
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| CN110643951A (en) * | 2019-10-14 | 2020-01-03 | 四川大学 | High-temperature oxidation resistant aluminum-chromium-silicon-nitrogen-aluminum oxide multilayer composite coating and preparation method thereof |
| CN111057984A (en) * | 2019-12-27 | 2020-04-24 | 华瑞（江苏）燃机服务有限公司 | Hot spraying process for coating of turbine moving blade of gas turbine |
| CN113388830A (en) * | 2021-06-11 | 2021-09-14 | 季华实验室 | Preparation method of high-temperature-resistant anticorrosive ceramic coating |
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