CN115093252B - High-temperature composite material antioxidation low-emissivity coating, and preparation method and application thereof - Google Patents
High-temperature composite material antioxidation low-emissivity coating, and preparation method and application thereof Download PDFInfo
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Abstract
The invention relates to an antioxidation low-emissivity coating of a high-temperature composite material, a preparation method and application thereofThe coating is designed according to the principle of gradual change matching of thermal expansion coefficients, and sequentially comprises a transition layer, an oxygen barrier layer, a low emissivity functional layer and a surface protective film from inside to outside. The transition layer is a mullite-glass powder composite coating with oxidation resistance, the low-emissivity functional coating is a high-temperature-resistant metal Ir film with low emissivity, and the surface protection film is a high-temperature-resistant high-infrared transmittance-resistant SiO 2 A film. The high-temperature composite material antioxidation and low-emissivity coating prepared by the invention greatly improves the service performance and service life of the Ir film at high temperature, has excellent infrared stealth performance and strong antioxidation, and can be used at high temperature of 1200 ℃.
Description
Technical Field
The invention belongs to the field of special functional coating materials, and relates to an antioxidation low-emissivity coating of a high-temperature composite material, a preparation method and application thereof.
Background
With the rapid development of detection systems and accurate guidance technologies, fatal striking is caused to large aviation aircrafts or equipment systems, so that the infrared stealth performance requirements on high-temperature components are becoming more urgent. The C/C composite material is a preferable material for high-temperature structural components because of excellent high-temperature ablation resistance, thermal stability, bearing performance and the like, however, when the service temperature exceeds 500 ℃, the C/C composite material can react with oxygen in the air severely, so that the material is oxidized and loses efficacy, and the use of the material at high temperature is greatly limited. In addition, the high infrared emissivity of the C/C composite material poses a fatal threat to the safety of its service, and therefore, development of a low infrared emissivity coating that can be used at high temperatures is highly desired.
Inorganic infrared low-emissivity coatings, metal micropowder coatings and metal films are three general types of infrared low-emissivity coatings with medium-high temperature application potential. The inorganic low-emissivity coating has the advantages of simple manufacturing process, low cost and low infrared emissivity, but has poor temperature resistance and thermal shock resistance, and is difficult to meet the engineering application requirements. The infrared emissivity of the metal micro powder coating is lower, but the metal micro powder coating is limited by the tolerance temperature of dispersion media such as resin and the like, and cannot be used in a higher temperature environment. The metal film (such as Ir, au, pt, hf, cr, W, mo and the like) can simultaneously meet the characteristics of high temperature low emissivity, excellent oxidation resistance and the like. At present, a plurality of research results exist, and the results of depositing Au and Pt films on the surface of the Ni-based superalloy in the previous work show that the Au film has extremely low emissivity, but has the defects of element diffusion, easy oxidation and the like. The Pt film has the excellent characteristics of low infrared emissivity, strong thermal stability and the like, but has the phenomena of limited temperature resistance (less than or equal to 900 ℃), easy falling off, mutual diffusion of elements and the like in engineering application, and has certain influence on the long service life and stability. Aiming at the problems, it is important to develop a coating with high temperature resistance (more than or equal to 1200 ℃), low emissivity and strong oxidation resistance.
Disclosure of Invention
Technical problem to be solved
In order to avoid the defects of the prior art, the invention provides an antioxidation and low-emissivity coating of a high-temperature composite material, a preparation method and application thereof, and provides a high-temperature-resistant and antioxidation low-emissivity composite coating which can be continuously used for 1h under a high-temperature environment of 1200 ℃ and has excellent high-temperature stability.
Technical proposal
The high-temperature composite material antioxidation and low-emissivity coating is characterized by comprising a transition layer, an oxygen barrier layer, a low-emissivity functional layer and a surface protective film from inside to outside in sequence; the transition layer is SiC ceramic with the thermal expansion coefficient matched with that of the substrate, the oxygen barrier layer is mullite-glass powder composite coating with oxidation resistance, the low-emissivity functional coating is a high-temperature-resistant metal film with low emissivity, and the surface protective film is a high-temperature-resistant metal oxide film with high infrared transmittance; the layers are matched according to the gradual change of the thermal expansion coefficient.
The transition layer includes, but is not limited to: ir, au, pt, hf, cr, W and Mo high-melting-point, temperature-resistant, oxidation-resistant and low-emissivity metal.
The skin protective film includes, but is not limited to: high redSiO of external transmittance 2 、MgO、Al 2 O 3 A metal oxide film.
The emissivity of the high-temperature resistant metal film with low emissivity is 0.118 and 0.143 respectively under the wave bands of 3-5 um and 8-14 um.
The thickness of the transition layer is 80-200 um, the thickness of the oxygen barrier layer is 20-100 um, the thickness of the low-emissivity coating is 0.5-10 um, and the thickness of the surface protection layer is 0.5-3 um.
A method for preparing the high-temperature composite material antioxidation low-emissivity coating, which is characterized by comprising the following steps:
step 1, pretreatment of a base material: polishing the C/C substrate and ultrasonically treating the C/C substrate to remove surface impurities;
step 2, preparing a transition layer: preparing a SiC transition layer on the surface of the C/C substrate by using a chemical vapor deposition method;
step 3, preparing an oxygen barrier layer: preparing a mullite-glass powder oxygen barrier layer on the surface of the transition layer by adopting a sol-gel method, and annealing for 1-2 hours at a high temperature of 1100-1300 ℃ to improve the density of the oxygen barrier layer;
step 4, preparing a low-emissivity functional layer: preparing an Ir low-emissivity functional layer on the mullite-glass powder oxygen barrier layer by using a direct-current magnetron sputtering method;
step 5, preparing a surface protective film: siO is prepared on the surface of Ir functional layer by using radio frequency magnetron sputtering method 2 And a surface protective film.
The sol-gel method is used for preparing a mullite-glass powder oxygen barrier layer on the surface of the transition layer: the mass ratio is as follows: preparing mullite-glass powder precursor solution by silica sol, alumina sol, deionized water and D270 glass powder in a ratio of 5-10:10-50:20-60:5-20, preparing a transition layer C/C substrate, soaking the transition layer C/C substrate in the precursor solution, drying in air, and sintering under vacuum, wherein the soaking-drying-sintering process is repeated for 5-20 times.
The process parameters of the direct current magnetron sputtering method in the step 4 are as follows: the background vacuum is 7.0-9.0E-4 Pa, the target base distance is 60-70 mm, the sputtering power is 90-110W, and the substrate temperature is 200-280 ℃.
The technological parameters of the radio frequency magnetron sputtering method in the step 5 are as follows: the background vacuum is 7.0-9.0E-4 Pa, the target base distance is 70-80 mm, the sputtering power is 280-360W, and the substrate temperature is 220-280 ℃.
The outermost protective film improves the use performance and the service life of the Ir film at high temperature and is in service at 1200 ℃ while improving the Ir low-emissivity functional layer.
Advantageous effects
The invention provides an antioxidation and low emissivity coating of a high-temperature composite material, a preparation method and application thereof. The transition layer is a mullite-glass powder composite coating with oxidation resistance, the low-emissivity functional coating is a high-temperature-resistant metal Ir film with low emissivity, and the surface protection film is a high-temperature-resistant high-infrared transmittance-resistant SiO 2 A film. The method specifically comprises the following steps: 1. preparing a SiC transition layer by adopting a chemical vapor deposition method; 2. preparing a mullite-glass oxygen barrier coating by adopting a sol-gel method; 3. preparing a low-emissivity Ir film on the surface of the antioxidation coating by adopting a magnetron sputtering method; 4. preparation of SiO by magnetron sputtering 2 And a surface protective film. The high-temperature composite material antioxidation and low-emissivity coating prepared by the invention greatly improves the service performance and service life of the Ir film at high temperature, has excellent infrared stealth performance and strong antioxidation, and can be used at high temperature of 1200 ℃.
The antioxidation low emissivity coating is designed according to the principle of gradual change matching of thermal expansion coefficients, and sequentially comprises a transition layer, an oxygen barrier layer, a low emissivity functional layer and a surface protective film from inside to outside. The transition layer is SiC ceramic with the thermal expansion coefficient close to that of the substrate, so that the oxidation resistance requirement is met, and the cracking problem caused by unmatched thermal expansion coefficients is effectively avoided; the oxygen barrier layer is a mullite-glass powder composite coating with oxidation resistance, and glass powder in the mullite-glass coating flows in a melting way at high temperature to fill a defect area, so that a dense oxygen isolation film is formed, and the oxidation resistance of the material is optimized; the low-emissivity functional coating is a metal film and still has extremely strong oxygen and carbon resistance at a high temperature of 2100 ℃; the surface layer protection film is a high-temperature-resistant oxide film, and has extremely high transmittance to infrared rays in the wave bands of 3-5 um and 8-14 um. The method specifically comprises the following steps: 1. pretreating a base material; 2. preparing a transition layer; 3. preparing an oxygen barrier layer; 4. preparing a low emissivity functional layer; 5. and (5) preparing a surface protective film. The high-temperature composite material antioxidation and low-emissivity coating prepared by the method is expected to be applied to high-temperature parts such as high-speed aircrafts such as airplanes and missiles, and high-temperature parts such as projectile bodies and tail nozzles by virtue of the excellent performances such as 1200 ℃ high temperature resistance and low emissivity. And provides theoretical basis and technical support for the application of the high-temperature infrared low-emissivity coating on high-temperature parts such as an aeroengine and the like.
The high-temperature composite material antioxidation low-emissivity coating and the preparation method thereof have the beneficial effects that:
1. according to the principle of gradual change matching of the thermal expansion coefficient, siC which is similar to the thermal expansion coefficient of the base material is selected as a transition layer, and the SiC and the base material have good physical and chemical compatibility, so that the risk of cracking and invalidation of an interface caused by thermal stress is reduced, and the base material is effectively protected from oxidation.
2. The mullite-glass powder oxygen barrier layer is prepared by adopting a sol-gel method, and glass powder in the mullite-glass coating melts and flows at high temperature to fill the defect area, so that a dense oxygen isolation film is formed, and the oxidation resistance of the material is optimized.
3. The low-emissivity functional coating is prepared by adopting a direct-current magnetron sputtering method, and the metal film prepared by the method has high density, strong binding force and extremely strong oxygen and carbon resistance at a high temperature of 2100 ℃, so that infrared stealth is ensured, and meanwhile, the oxidation risk of a base material is protected.
4. The surface protection film with high temperature resistance and high infrared transmission property in specific wave bands (3-5 um and 8-14 um) is prepared by adopting a radio frequency magnetron sputtering method, and the film prepared by the method has high density and strong binding force. The dense structure and excellent infrared transmittance improve the service performance and service life of the bottom functional layer film at high temperature.
5. The special functional coating prepared by the invention can be used for 1h at the high temperature of 1200 ℃ and is expected to be applied to high-temperature parts such as high-speed aircrafts such as airplanes and missiles, projectile bodies, tail nozzles and the like. In addition, the invention provides theoretical basis and technical support for the application of the high-temperature infrared low-emissivity coating on high-temperature parts such as an aeroengine and the like.
Drawings
Fig. 1: the structural schematic of the high temperature composite oxidation resistant and low emissivity coating in example 1 of the present invention.
Fig. 2: the relation diagram of the emissivity of the low infrared emissivity composite coating in the wave bands of 3-5 um and 8-14 um at the high temperature of 1200 ℃ in the embodiment 1 of the invention and the annealing time.
Detailed Description
The invention will now be further described with reference to examples, figures:
example 1:
step 1, pre-treating a base treatment material: the C/C base material is coarsely ground by using 80-mesh, 400-mesh and 800-mesh 1200-mesh sand paper in sequence, then is polished by using a diamond polishing agent, and finally is put into absolute ethyl alcohol to be ultrasonically cleaned for 30min to remove impurities.
Step 2: preparing a transition layer: and preparing an SiC transition layer with the thickness of 80-200 mu m on the surface of the pretreated C/C composite material by using a chemical vapor deposition method.
Step 3: oxygen barrier layer preparation: preparing mullite-glass powder precursor by silica sol, alumina sol, deionized water and D270 glass powder according to the mass ratio of 5-10:10-50:20-60:5-20, then soaking the composite material obtained in the step 2 in the precursor solution for 10min, drying in air at 300 ℃ for 1-2 h, sintering at 1200 ℃ for 2h under vacuum, repeating the soaking-drying-sintering process for 5-20 times to obtain the mullite-glass powder oxygen barrier layer, and finally annealing in air at 1100-1300 ℃ for 1-2 h to improve the density of the oxygen barrier layer;
step 4: preparing a low emissivity functional layer: preparing a high-melting-point temperature-resistant oxidation-resistant low-emissivity Ir metal film on the composite material obtained in the step 3 by using a direct-current magnetron sputtering method, wherein the background vacuum is 7.0-9.0E-4 Pa, the target base distance is 60-70 mm, the sputtering air pressure is 0.2-1.8 Pa, the sputtering power is 80-160W, the substrate temperature is 160-280 ℃, and the emissivity of the Ir film under the wave bands of 3-5 um and 8-14 um are 0.118 and 0.143 respectively;
step 5: preparing a surface protective film: preparing SiO on the emissivity functional layer obtained in the step 4 by using a radio frequency magnetron sputtering method 2 The background vacuum of the metal film is 7.0-9.0E-4 Pa, the target base distance is 60-70 mm, the sputtering power is 50-110W, the substrate temperature is 200-280 ℃, and the relation between the emissivity of the low infrared emissivity composite coating at the high temperature of 1200 ℃ and the annealing time in the wave bands of 3-5 um and 8-14 um is shown in figure 2;
example 2:
step 1, pretreatment of a base material: sequentially using 80-mesh, 400-mesh and 800-mesh 1200-mesh sand paper to coarsely grind the C/C substrate, then using a diamond polishing agent to carry out polishing treatment, and finally putting the C/C substrate into absolute ethyl alcohol to carry out ultrasonic cleaning for 30min to remove impurities.
Step 2: preparing a transition layer: and preparing an SiC transition layer with the thickness of 80-200 mu m on the surface of the pretreated C/C composite material by using a chemical vapor deposition method.
Step 3: oxygen barrier layer preparation: preparing mullite-glass powder precursor by silica sol, alumina sol, deionized water and D270 glass powder according to the mass ratio of 5-10:10-50:20-60:5-20, then soaking the composite material obtained in the step 2 in the precursor solution for 10min, drying in air at 300 ℃ for 1-2 h, sintering at 1200 ℃ for 2h under vacuum, repeating the soaking-drying-sintering process for 5-20 times to obtain the mullite-glass powder oxygen barrier layer, and finally annealing in air at 1100-1300 ℃ for 1-2 h to improve the density of the oxygen barrier layer;
step 4: preparing a low emissivity functional layer: preparing a temperature-resistant oxidation-resistant low-emissivity Ir metal film on the composite material obtained in the step 3 by using a direct current magnetron sputtering method, wherein the background vacuum is 7.0-9.0E-4 Pa, the target base distance is 60-70 mm, the sputtering air pressure is 0.2-1.8 Pa, the sputtering power is 80-160W, and the substrate temperature is 160-280 ℃;
step 5: preparing a surface protective film: preparing an MgO metal film on the emissivity functional layer obtained in the step 4 by using a radio frequency magnetron sputtering method, wherein the background vacuum is 7.0-9.0E-4 Pa, the target base distance is 60-70 mm, the sputtering power is 50-110W, the sputtering air pressure is 2.8-3.2 Pa, and the substrate temperature is 200-280 ℃;
implementation 3:
step 1, pretreatment of a base material: sequentially using 80-mesh, 400-mesh and 800-mesh 1200-mesh sand paper to coarsely grind the C/C substrate, then using a diamond polishing agent to carry out polishing treatment, and finally putting the C/C substrate into absolute ethyl alcohol to carry out ultrasonic cleaning for 30min to remove impurities.
Step 2: preparing a transition layer: and preparing an SiC transition layer with the thickness of 80-200 mu m on the surface of the pretreated C/C composite material by using a chemical vapor deposition method.
Step 3: oxygen barrier layer preparation: preparing mullite-glass powder precursor by silica sol, alumina sol, deionized water and D270 glass powder according to the mass ratio of 5-10:10-50:20-60:5-20, then soaking the composite material obtained in the step 2 in the precursor solution for 10min, drying in air at 300 ℃ for 1-2 h, sintering at 1200 ℃ for 2h under vacuum, repeating the soaking-drying-sintering process for 5-20 times to obtain the mullite-glass powder oxygen barrier layer, and finally annealing in air at 1100-1300 ℃ for 1-2 h to improve the density of the oxygen barrier layer;
step 4: preparing a low emissivity functional layer: preparing a temperature-resistant oxidation-resistant low-emissivity Pt metal film on the composite material obtained in the step 3 by using a direct current magnetron sputtering method, wherein the background vacuum is 7.0-9.0E-4 Pa, the target base distance is 60-70 mm, the sputtering air pressure is 1.1-1.8 Pa, the sputtering power is 30-50W, and the substrate temperature is room temperature;
step 5: preparing a surface protective film: and (3) preparing the MgO metal film on the emissivity functional layer obtained in the step (4) by using a radio frequency magnetron sputtering method, wherein the background vacuum is 7.0-9.0E-4 Pa, the target base distance is 60-70 mm, the sputtering power is 50-110W, the sputtering air pressure is 2.8-3.2 Pa, and the substrate temperature is 200-280 ℃.
Claims (7)
1. A method for preparing an antioxidation low-emissivity coating of a high-temperature composite material is characterized by comprising the following steps:
step 1, pretreatment of a base material: polishing the C/C substrate and ultrasonically treating the C/C substrate to remove surface impurities;
step 2, preparing a transition layer: preparing a SiC transition layer on the surface of the C/C substrate by using a chemical vapor deposition method;
step 3, preparing an oxygen barrier layer: preparing a mullite-glass powder oxygen barrier layer on the surface of the transition layer by adopting a sol-gel method, and annealing for 1-2 hours at a high temperature of 1100-1300 ℃ to improve the density of the oxygen barrier layer;
step 4, preparing a low-emissivity functional layer: preparing an Ir low-emissivity functional layer on the mullite-glass powder oxygen barrier layer by using a direct-current magnetron sputtering method;
step 5, preparing a surface protective film: siO is prepared on the surface of Ir functional layer by using radio frequency magnetron sputtering method 2 A surface layer protective film;
the sol-gel method is used for preparing a mullite-glass powder oxygen barrier layer on the surface of the transition layer: the mass ratio is as follows: preparing mullite-glass powder precursor solution by silica sol, alumina sol, deionized water and D270 glass powder in a ratio of 5-10:10-50:20-60:5-20, preparing transition layer C/C base material to be immersed in the precursor solution, drying in air, and sintering under vacuum, wherein the immersing-drying-sintering process is repeated for 5-20 times;
the process parameters of the direct current magnetron sputtering method in the step 4 are as follows: background vacuum is 7.0-9.0E-4 Pa, target base distance is 60-70 mm, sputtering power is 90-110W, and substrate temperature is 200-280 ℃;
the technological parameters of the radio frequency magnetron sputtering method in the step 5 are as follows: the background vacuum is 7.0-9.0E-4 Pa, the target base distance is 70-80 mm, the sputtering power is 280-360W, and the substrate temperature is 220-280 ℃.
2. A high temperature composite oxidation resistant, low emissivity coating prepared by the method of claim 1, wherein: the transition layer, the oxygen barrier layer, the low emissivity functional layer and the surface protective film are sequentially arranged from inside to outside; the transition layer is SiC ceramic with the thermal expansion coefficient matched with that of the substrate, the oxygen barrier layer is mullite-glass powder composite coating with oxidation resistance, the low-emissivity functional layer is a high-temperature-resistant metal film with low emissivity, and the surface protective film is a high-temperature-resistant metal oxide film with high infrared transmittance; the layers are matched according to the gradual change of the thermal expansion coefficient.
3. The high temperature composite oxidation resistant, low emissivity coating of claim 2, wherein: the low emissivity functional layer includes: ir, au, pt, hf, cr, W and Mo high-melting-point, temperature-resistant, oxidation-resistant and low-emissivity metal.
4. The high temperature composite oxidation resistant, low emissivity coating of claim 2, wherein: the surface layer protective film includes: siO with high infrared transmittance 2 、MgO、Al 2 O 3 A metal oxide film.
5. The high temperature composite oxidation resistant, low emissivity coating of claim 2, wherein: the emissivity of the high-temperature resistant metal film with low emissivity is 0.118 and 0.143 respectively under the wave bands of 3-5 um and 8-14 um.
6. The high temperature composite oxidation resistant, low emissivity coating of claim 2, wherein: the thickness of the transition layer is 80-200 um, the thickness of the oxygen barrier layer is 20-100 um, the thickness of the low-emissivity functional layer is 0.5-10 um, and the thickness of the surface protection layer is 0.5-3 um.
7. An application of the high-temperature composite material oxidation-resistant and low-emissivity coating as claimed in any one of claims 2 to 6, which is characterized in that: the outermost protective film improves the use performance and the service life of the Ir film at high temperature and is in service at 1200 ℃ while improving the Ir low-emissivity functional layer.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103360124A (en) * | 2013-07-10 | 2013-10-23 | 航天材料及工艺研究所 | Composite coating and application thereof in carbon/carbon composite material |
| CN103924205A (en) * | 2014-04-28 | 2014-07-16 | 中国人民解放军国防科学技术大学 | High temperature-resistant low-infrared emittance composite coating and preparation method thereof |
| CN104149410A (en) * | 2014-07-08 | 2014-11-19 | 中国人民解放军国防科学技术大学 | Inorganic high-temperature-resistant low-infrared-emissivity composite coating and preparation method thereof |
| CN106679202A (en) * | 2016-12-20 | 2017-05-17 | 北京天瑞星光热技术有限公司 | Tower-type heat collector light-thermal conversion coating and preparation method thereof |
Family Cites Families (2)
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| ES2661324T3 (en) * | 2002-04-25 | 2018-03-28 | Vitro, S.A.B. De C.V. | Method for the manufacture of coated articles having an oxygen barrier coating and coated articles manufactured in this way |
| CN107922280B (en) * | 2015-08-18 | 2022-03-04 | 通用电气公司 | Dense environmental barrier coating composition |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103360124A (en) * | 2013-07-10 | 2013-10-23 | 航天材料及工艺研究所 | Composite coating and application thereof in carbon/carbon composite material |
| CN103924205A (en) * | 2014-04-28 | 2014-07-16 | 中国人民解放军国防科学技术大学 | High temperature-resistant low-infrared emittance composite coating and preparation method thereof |
| CN104149410A (en) * | 2014-07-08 | 2014-11-19 | 中国人民解放军国防科学技术大学 | Inorganic high-temperature-resistant low-infrared-emissivity composite coating and preparation method thereof |
| CN106679202A (en) * | 2016-12-20 | 2017-05-17 | 北京天瑞星光热技术有限公司 | Tower-type heat collector light-thermal conversion coating and preparation method thereof |
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