CN105112843A - Corrosion-resistant thermal barrier coating and preparation method thereof - Google Patents
Corrosion-resistant thermal barrier coating and preparation method thereof Download PDFInfo
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- CN105112843A CN105112843A CN201510495218.3A CN201510495218A CN105112843A CN 105112843 A CN105112843 A CN 105112843A CN 201510495218 A CN201510495218 A CN 201510495218A CN 105112843 A CN105112843 A CN 105112843A
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- thermal barrier
- barrier coating
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Abstract
The invention discloses a corrosion-resistant thermal barrier coating. The porosity of a ceramic phase can be increased after carbon powder is added and modified through high-temperature calcination, and parts of particles are slightly low in deformation degree when impacting a matrix because of not being sufficiently molten in plasma jet in the spraying process, so that an overlapped porous structure is easily formed, and furthermore the heat insulating property of the coating is remarkably improved; in addition, Zr<4+> is substituted with Y<3+> and Ce<4+> in a zirconium dioxide crystal lattice through a modification method, so that an oxygen vacancy and a local stress field are generated, the scatter of phonons in the crystal lattice is enhanced, and the heat conductivity is remarkably reduced; and the atomic weight of a solid-solution atom Ce is far larger than that of Y, so that the scattering intensity of the phonons in the corrosion-resistant thermal barrier coating disclosed by the invention can be remarkably improved, and furthermore the heat conductivity is reduced. The preparation process is simple; and the prepared coating is porous and excellent in high-temperature resistance and heat insulating property, has corrosion resistance, molten salt corrosion resistance and favorable thermal shock property and is widely applied to the fields of aviation, aerospace, traffic and energy.
Description
Technical field
The present invention relates to Machining of Ceramics technical field, be specifically related to a kind of corrosion resistant thermal barrier coating and preparation method thereof.
Background technology
Along with aero-gas turbine is to high flow capacity ratio, high thrust-weight ratio, high air inlet temperature future development, the working temperature in combustion chamber is considerably beyond the use temperature limit of Ni based high-temperature alloy.Prepare thermal barrier coating at superalloy matrix surface, holding warm ability to raising matrix has very directly effect, thus effectively improves the working temperature of part, increases the service life.
It is a kind ofly utilize the material that thermal conductivity is relatively low that thermal barrier coating leads to, and is coated on superalloy matrix surface thus plays the functional coating of heat-blocking action by suitable technology.Typical thermal barrier coating is made up of superalloy matrix, metal bonding coating and top heat insulating ceramic coat.Wherein, superalloy matrix mainly bears mechanical load; Tack coat mainly works to improve matrix and ceramic coating physical compatibility and antioxidant anticorrosive; Top ceramic layer Main Function is isolated heat and produces thermograde, and its heterogeneous microstructure plays a crucial role to the heat-proof quality of thermal barrier coating and work-ing life.But when thermal barrier coating is applied to the working temperature day by day increased, harsher Working environment will be faced, the obtained thermal barrier coating of prior art exist easily undergo phase transition, oxidation-resistance is low, intensity is little, poor high temperature stability, easily produce the defects such as high temperature corrosion, is difficult to meet the needs that turbine intake temperature improves further.Therefore, the focus that better heat-proof quality and good stability, elevated temperature corrosion resistant are excellent under the high temperature conditions novel heat barrier coat material become thermal barrier coating area research is in recent years found.
Summary of the invention
Object of the present invention is just to provide a kind of corrosion resistant thermal barrier coating and preparation method thereof, to overcome the deficiencies in the prior art.
The object of the present invention is achieved like this:
A kind of corrosion resistant thermal barrier coating, it is characterized in that, be made up of the raw material of following weight part: cerium oxide 20-23, zirconium dioxide 26-29, yttrium oxide 32-36, carbon dust 6-9, nanometer silicon carbide 0.7-0.9, NiCoCrAlYTa alloy powder 60-70, basalt fibre 4-6, coal gangue 18-22, vinyl-acetic ester 3-5, Union carbide A-162 2-4, potassium pyrophosphate 2-3.
The preparation method of described a kind of corrosion resistant thermal barrier coating, is characterized in that comprising the following steps:
(1) by nanometer silicon carbide, NiCoCrAlYTa alloy powder in 640-760 DEG C of pyroprocessing 30-50 minute, be cooled to room temperature rapidly, add potassium pyrophosphate ultrasonic grinding 20-40 minute, be heated to melting, stir 5-8h, under vacuum atmosphere, condensation is shaping, obtained modified metal tack coat of pulverizing;
(2) carbon dust, basalt fibre joined grinding in ball grinder 10-15 minute, spray into vaporific Union carbide A-162 and mix thoroughly, add vinyl-acetic ester, carry out ball milling under normal temperature, mix, break up obtained modification carbon dust;
(3) by modification carbon dust, cerium oxide, zirconium dioxide, yttrium oxide through 1550-1640 DEG C of high-temperature calcination 2-4 hour, cooling adds other remaining component and is ground to 200-300 order, obtained modified ceramic powder;
(4) by superalloy matrix after ultrasonic oil removing, sandblasting pre-treatment, by electron thermal explosion method by step (1) material even application on superalloy matrix;
(5) finally by air plasma spraying method, the spraying current of 500A is adopted to be deposited on metal bonding coating by obtained for step (3) modified ceramic powder.
The present invention has following beneficial effect: the thermal barrier coating that the present invention obtains is compared with traditional thermal barrier coating, add carbon dust through the modified porosity improving ceramic phase of high-temperature calcination, and some particles melts insufficient in plasma jet in spraying process, when clashing into matrix, deformation extent is slightly weak, the vesicular structure that easy formation overlaps, the heat-proof quality of coating is significantly improved, and secondly the present invention is by method of modifying, Y in zirconium dioxide lattice
3+, Ce
4+replace Zr
4+create the stress field of Lacking oxygen and local, add the phon scattering in lattice, thermal conductivity obviously reduces, and the nucleidic mass of solid solution atom Ce is far longer than the nucleidic mass of Y, the scattering strength of the phonon in product of the present invention can be significantly improved, thus reduce thermal conductivity, preparation technology of the present invention is simple, prepared coated porous high temperature insulation is excellent, there is corrosion-resistant, anti-fused salt corrosion and good thermal shock performance, have been widely used at Aeronautics and Astronautics, traffic, energy field tool.
Embodiment
The corrosion resistant thermal barrier coating of described one, it is characterized in that, be made up of the raw material of following weight part: cerium oxide 21, zirconium dioxide 26, yttrium oxide 35, carbon dust 9, nanometer silicon carbide 0.7, NiCoCrAlYTa alloy powder 60, basalt fibre 4, coal gangue 22, vinyl-acetic ester 5, Union carbide A-162 2, potassium pyrophosphate 3.
Making method comprises the following steps:
(1) by nanometer silicon carbide, NiCoCrAlYTa alloy powder in 640-760 DEG C of pyroprocessing 30-50 minute, be cooled to room temperature rapidly, add potassium pyrophosphate ultrasonic grinding 20-40 minute, be heated to melting, stir 5-8h, under vacuum atmosphere, condensation is shaping, obtained modified metal tack coat of pulverizing;
(2) carbon dust, basalt fibre joined grinding in ball grinder 10-15 minute, spray into vaporific Union carbide A-162 and mix thoroughly, add vinyl-acetic ester, carry out ball milling under normal temperature, mix, break up obtained modification carbon dust;
(3) by modification carbon dust, cerium oxide, zirconium dioxide, yttrium oxide through 1550-1640 DEG C of high-temperature calcination 2-4 hour, cooling adds other remaining component and is ground to 200-300 order, obtained modified ceramic powder;
(4) by superalloy matrix after ultrasonic oil removing, sandblasting pre-treatment, by electron thermal explosion method by step (1) material even application on superalloy matrix;
(5) finally by air plasma spraying method, the spraying current of 500A is adopted to be deposited on metal bonding coating by obtained for step (3) modified ceramic powder.
The technical parameter index of the thermal barrier coating using the present invention to produce is as follows:
(1) coating porosity: 18.9%;
(2) record coating cross sections through metaloscope and have more closed hole and vertical micro--crack;
(3) temperature head by measuring coatingsurface and the sample back side calculates the heat-proof quality of coating, and increase rate has been up to about 50.9%.
Claims (4)
1. a corrosion resistant thermal barrier coating, it is characterized in that, be made up of the raw material of following weight part: cerium oxide 20-23, zirconium dioxide 26-29, yttrium oxide 32-36, carbon dust 6-9, nanometer silicon carbide 0.7-0.9, NiCoCrAlYTa alloy powder 60-70, basalt fibre 4-6, coal gangue 18-22, vinyl-acetic ester 3-5, Union carbide A-162 2-4, potassium pyrophosphate 2-3.
2. the making method of a kind of corrosion resistant thermal barrier coating according to claim 1, is characterized in that comprising the following steps:
(1) by nanometer silicon carbide, NiCoCrAlYTa alloy powder in 640-760 DEG C of pyroprocessing 30-50 minute, be cooled to room temperature rapidly, add potassium pyrophosphate ultrasonic grinding 20-40 minute, be heated to melting, stir 5-8h, under vacuum atmosphere, condensation is shaping, obtained modified metal tack coat of pulverizing;
(2) carbon dust, basalt fibre joined grinding in ball grinder 10-15 minute, spray into vaporific Union carbide A-162 and mix thoroughly, add vinyl-acetic ester, carry out ball milling under normal temperature, mix, break up obtained modification carbon dust;
(3) by modification carbon dust, cerium oxide, zirconium dioxide, yttrium oxide through 1550-1640 DEG C of high-temperature calcination 2-4 hour, cooling adds other remaining component and is ground to 200-300 order, obtained modified ceramic powder;
(4) by superalloy matrix after ultrasonic oil removing, sandblasting pre-treatment, by electron thermal explosion method by step (1) material even application on superalloy matrix;
(5) finally by air plasma spraying method, the spraying current of 500A is adopted to be deposited on metal bonding coating by obtained for step (3) modified ceramic powder.
3. the making method of a kind of corrosion resistant thermal barrier coating according to claim 2, is characterized in that, described metal bonding coating coating thickness is 100 μm, and ceramic layer coats thickness is 300 μm.
4. the making method of a kind of corrosion resistant thermal barrier coating according to claim 2, is characterized in that, described superalloy matrix is K4169 superalloy.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109437892A (en) * | 2018-11-27 | 2019-03-08 | 陈涛 | A kind of zirconia ceramics coating and preparation method thereof |
| CN112126915A (en) * | 2020-09-27 | 2020-12-25 | 灵璧县飞松机械制造有限责任公司 | Centrifugal fan impeller blade surface treatment process |
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| CN1701951A (en) * | 2004-05-18 | 2005-11-30 | 通用电气公司 | Bi-layer hvof coating with controlled porosity for use in thermal barrier coatings |
| CN101660115A (en) * | 2009-09-18 | 2010-03-03 | 武汉理工大学 | Preparation method of nanometer zirconia heat barrier coating |
| CN102351545A (en) * | 2011-04-07 | 2012-02-15 | 世林（漯河）冶金设备有限公司 | High temperature heat barrier material, coating, molded product and application thereof |
| CN103668191A (en) * | 2013-12-09 | 2014-03-26 | 广州有色金属研究院 | Preparation method for thermal-barrier coating |
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2015
- 2015-08-13 CN CN201510495218.3A patent/CN105112843A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1701951A (en) * | 2004-05-18 | 2005-11-30 | 通用电气公司 | Bi-layer hvof coating with controlled porosity for use in thermal barrier coatings |
| CN101660115A (en) * | 2009-09-18 | 2010-03-03 | 武汉理工大学 | Preparation method of nanometer zirconia heat barrier coating |
| CN102351545A (en) * | 2011-04-07 | 2012-02-15 | 世林（漯河）冶金设备有限公司 | High temperature heat barrier material, coating, molded product and application thereof |
| CN103668191A (en) * | 2013-12-09 | 2014-03-26 | 广州有色金属研究院 | Preparation method for thermal-barrier coating |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109437892A (en) * | 2018-11-27 | 2019-03-08 | 陈涛 | A kind of zirconia ceramics coating and preparation method thereof |
| CN112126915A (en) * | 2020-09-27 | 2020-12-25 | 灵璧县飞松机械制造有限责任公司 | Centrifugal fan impeller blade surface treatment process |
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Application publication date: 20151202 |
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