CN117344260A - Ultrahigh-temperature ceramic abradable seal coating material and preparation method thereof - Google Patents
Ultrahigh-temperature ceramic abradable seal coating material and preparation method thereof Download PDFInfo
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- CN117344260A CN117344260A CN202311640695.5A CN202311640695A CN117344260A CN 117344260 A CN117344260 A CN 117344260A CN 202311640695 A CN202311640695 A CN 202311640695A CN 117344260 A CN117344260 A CN 117344260A
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- 238000000576 coating method Methods 0.000 title claims abstract description 95
- 239000011248 coating agent Substances 0.000 title claims abstract description 91
- 239000000463 material Substances 0.000 title claims abstract description 79
- 239000011215 ultra-high-temperature ceramic Substances 0.000 title claims abstract description 47
- 238000002360 preparation method Methods 0.000 title abstract description 13
- CPLXHLVBOLITMK-UHFFFAOYSA-N Magnesium oxide Chemical compound [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 claims abstract description 43
- 238000000034 method Methods 0.000 claims abstract description 33
- 239000000395 magnesium oxide Substances 0.000 claims abstract description 31
- 238000005245 sintering Methods 0.000 claims abstract description 31
- 238000005469 granulation Methods 0.000 claims abstract description 30
- 230000003179 granulation Effects 0.000 claims abstract description 30
- 239000007921 spray Substances 0.000 claims abstract description 28
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims abstract description 23
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims abstract description 20
- 229910052596 spinel Inorganic materials 0.000 claims abstract description 20
- 239000011029 spinel Substances 0.000 claims abstract description 20
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 claims abstract description 19
- 238000000498 ball milling Methods 0.000 claims abstract description 16
- 239000011230 binding agent Substances 0.000 claims abstract description 15
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 14
- 238000012216 screening Methods 0.000 claims abstract description 6
- 238000002156 mixing Methods 0.000 claims abstract description 5
- 239000000126 substance Substances 0.000 claims abstract description 5
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 16
- 239000002245 particle Substances 0.000 claims description 6
- 229920002134 Carboxymethyl cellulose Polymers 0.000 claims description 3
- 239000004793 Polystyrene Substances 0.000 claims description 3
- 239000004372 Polyvinyl alcohol Substances 0.000 claims description 3
- 239000001768 carboxy methyl cellulose Substances 0.000 claims description 3
- 235000010948 carboxy methyl cellulose Nutrition 0.000 claims description 3
- 239000008112 carboxymethyl-cellulose Substances 0.000 claims description 3
- 229920002223 polystyrene Polymers 0.000 claims description 3
- 229920002451 polyvinyl alcohol Polymers 0.000 claims description 3
- 230000035939 shock Effects 0.000 abstract description 20
- 230000008569 process Effects 0.000 abstract description 13
- 230000007704 transition Effects 0.000 abstract description 4
- 239000000843 powder Substances 0.000 description 64
- 230000000052 comparative effect Effects 0.000 description 19
- 238000007789 sealing Methods 0.000 description 10
- 238000001816 cooling Methods 0.000 description 6
- -1 rare earth silicate Chemical class 0.000 description 6
- 238000005507 spraying Methods 0.000 description 6
- 230000008859 change Effects 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 239000002002 slurry Substances 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 3
- 238000005524 ceramic coating Methods 0.000 description 3
- 238000001033 granulometry Methods 0.000 description 3
- 229910052749 magnesium Inorganic materials 0.000 description 3
- 239000011777 magnesium Substances 0.000 description 3
- 238000007750 plasma spraying Methods 0.000 description 3
- 229910052761 rare earth metal Inorganic materials 0.000 description 3
- 238000003723 Smelting Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 239000012720 thermal barrier coating Substances 0.000 description 2
- 238000007751 thermal spraying Methods 0.000 description 2
- 229910001928 zirconium oxide Inorganic materials 0.000 description 2
- 238000002441 X-ray diffraction Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 239000003153 chemical reaction reagent Substances 0.000 description 1
- 239000000306 component Substances 0.000 description 1
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- 238000001704 evaporation Methods 0.000 description 1
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- 239000008187 granular material Substances 0.000 description 1
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- 230000001788 irregular Effects 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
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Classifications
-
- 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
Abstract
The application provides an ultrahigh-temperature ceramic abradable seal coating material and a preparation method thereof, and relates to the field of coating materials. The ultra-high temperature ceramic abradable seal coating material is non-stoichiometric magnesia alumina spinel with a chemical formula of MgO.nAL 2 O 3 Wherein n is 1.1-1.3. The preparation method of the ultrahigh-temperature ceramic abradable seal coating material comprises the following steps: mixing magnesium oxide, aluminum oxide, a binder and water, and then sequentially performing ball milling, spray granulation, sintering and screening to obtain the ultrahigh-temperature ceramic abradable seal coating material. The ultrahigh-temperature ceramic abradable seal coating material provided by the application has more excellent thermal shock resistance and high-temperature mechanical property, higher phase transition temperature and excellent high-temperature stability, and can ensure the safety of an aeroengine in the service process.
Description
Technical Field
The application relates to the field of coating materials, in particular to an ultrahigh-temperature ceramic abradable seal coating material and a preparation method thereof.
Background
With the continuous improvement of the comprehensive requirements of advanced aeroengines on the material performance and the maximization of the development of the material self-performance, the adoption of a coating technology has become one of core technical measures for improving the surface performance and service life of aeroengine materials and key components under the use condition. The sealing coating material and the sealing coating technology are beneficial to reducing the radial clearance between the rotor and the stator of the aero-engine, and have important influence on improving the efficiency and the reliability of the aero-engine. In order to improve the running efficiency, the service life and reduce the oil consumption of the engine, the research of sealing coatings of the core components of the aeroengine, in particular to high-temperature sealing coatings, has been paid great attention to at home and abroad.
With the rapid development of aeroengines, the use temperature requirement of the abradable seal coating is increased to be more than 1200 ℃, and new requirements are provided for the high-temperature protection, seal, wear resistance and other performances of the seal coating. As the service temperature increases, abradable seal coating materials have evolved from low melting point metal-based seal materials to high melting point ceramic-based seal materials. Under the use condition of higher than 1200 ℃, the common metal-based MCrAlY sealing coating material can not meet the use requirement, and the thermal expansion coefficient of the YSZ high-temperature ceramic coating material system with better compatibility with a high-temperature alloy matrix, which is developed at present, is 10-12.5X10-6K -1 Compared with other ceramic coating and metal bottom layer, the thermal expansion coefficient of the ceramic coating and the metal bottom layer is>14×10-6K -1 ) More closely, the thermal stress generated in the high-temperature service process is smaller, but the phase transition temperature is 1150 ℃, and the Y plays a role in stabilization in a long-term service state 2 O 3 Is easy to precipitate, resulting in ZrO 2 With consequent occurrence ofThe phase change and the volume change accompanied by the phase change can cause the coating to crack and peel off, seriously affecting the service performance, and the low thermal conductivity of the thicker coating leads to the rise of the surface temperature, so that the coating cannot be used above 1200 ℃.
Disclosure of Invention
The purpose of the application is to provide an ultrahigh-temperature ceramic abradable seal coating material and a preparation method thereof, so as to solve the problems.
In order to achieve the above purpose, the present application adopts the following technical scheme:
the ultra-high temperature ceramic abradable seal coating material is non-stoichiometric magnesia alumina spinel with a chemical formula of MgO.nAL 2 O 3 Wherein n is 1.1-1.3.
Preferably, the surface opening porosity of the ultra-high temperature ceramic abradable seal coating material is 5-10%.
Preferably, the laser granularity D50 of the ultra-high temperature ceramic abradable seal coating material is 30-60 mu m.
The application also provides a preparation method of the ultrahigh-temperature ceramic abradable seal coating material, which comprises the following steps:
mixing magnesium oxide, aluminum oxide, a binder and water, and then sequentially performing ball milling, spray granulation, sintering and screening to obtain the ultrahigh-temperature ceramic abradable seal coating material.
Preferably, the mass ratio of the magnesium oxide to the aluminum oxide is (24-26): (74-76).
Preferably, the mass ratio of the total mass of the magnesium oxide and the aluminum oxide to the mass of the water and the binder is 100 (200-250): 7-10.
Preferably, the ball milling is performed using zirconia balls, and the mass ratio of the total mass of the magnesia and the alumina to the zirconia balls is 1: (3-5), wherein the ball milling time is 6-15h.
Preferably, the binder comprises one or more of polyvinyl alcohol, carboxymethyl cellulose, polystyrene.
Preferably, the inlet temperature of the spray granulation is 250-300 ℃, the outlet temperature is 100-120 ℃ lower than the inlet temperature, and the power is 28-32kw;
the residence time of the material in the tank body of the spray granulation equipment is 1-1.5min.
Preferably, the sintering temperature is 1300-1400 ℃ and the sintering time is 6-8h.
Compared with the prior art, the beneficial effects of this application include:
the ultrahigh-temperature ceramic abradable seal coating material provided by the application is non-stoichiometric magnesia-alumina spinel with a chemical formula of MgO 2 O 3 Wherein n is 1.1-1.3; the stoichiometric ratio n has obvious influence on the performance of the material, the thermal shock resistance of the material increases with the increase of n, and the high-temperature mechanical property of the material firstly increases and then decreases with the increase of n; the phase transition temperature of the coating material is up to 1600 ℃, the phase transition can not occur at high temperature, the high-temperature stability is excellent, and the safety of the aeroengine in the service process can be ensured; compared with the existing rare earth silicate-based thermal barrier coating material system which can be stable in phase structure above 1200 ℃, the toughness is higher, the thermal shock resistance is more excellent when the rare earth silicate-based thermal barrier coating material system is applied to an abradable seal coating with the thickness above 1.5mm, the problem that the existing rare earth silicate-based coating material cannot solve the problem of insufficient thermal shock resistance even if a porous structure, a double ceramic layer, a gradient structure and the like are adopted is effectively solved, and the service life of the high-temperature seal coating can be prolonged; the prepared coating has good thermal expansion matching performance with a monocrystalline superalloy substrate, has good thermal shock resistance and erosion resistance at 1400 ℃, and can meet the operating condition temperature use requirement of 1200-1400 ℃. Non-stoichiometric magnesia-alumina spinel has more excellent thermal shock resistance and high temperature mechanical properties than stoichiometric powders.
The preparation method of the ultrahigh-temperature ceramic abradable seal coating material adopts a spray granulation and sintering means, and has higher sphericity than powder prepared by an electric smelting sintering method and crushing method commonly used for the existing magnesia-alumina spinel, easier control of powder granularity, more excellent fluidity and good spraying adaptability, and is beneficial to subsequent preparation of thermal spraying coatings.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate certain embodiments of the present application and therefore should not be considered as limiting the scope of the present application.
FIG. 1 is a microscopic morphology of the ultra-high temperature ceramic abradable seal coating material obtained in example 1;
FIG. 2 is an enlarged view of the microscopic morphology of the ultra-high temperature ceramic abradable seal coating material obtained in example 1;
FIG. 3 is an XRD diffraction peak spectrum of the ultra-high temperature ceramic abradable seal coating material obtained in example 1;
FIG. 4 is a microscopic morphology of the ultra-high temperature ceramic abradable seal coating material obtained in example 2;
FIG. 5 is a microscopic morphology of the ultra-high temperature ceramic abradable seal coating material obtained in example 3;
FIG. 6 is a microscopic morphology of the ultra-high temperature ceramic abradable seal coating material obtained in comparative example 1;
fig. 7 is a microscopic morphology of the ultra-high temperature ceramic abradable seal coating material obtained in comparative example 2.
Detailed Description
In order to better explain the technical scheme provided by the application, before the embodiment, the technical scheme is integrally stated, and the technical scheme is specifically as follows:
the ultra-high temperature ceramic abradable seal coating material is non-stoichiometric magnesia alumina spinel with a chemical formula of MgO.nAL 2 O 3 Wherein n is 1.1-1.3.
Alternatively, n may be any value between 1.1, 1.2, 1.3, or 1.1-1.3.
In an alternative embodiment, the ultra-high temperature ceramic abradable seal coating material has a surface open porosity of 5-10%.
Alternatively, the surface open porosity of the ultra-high temperature ceramic abradable seal coating material may be any value between 5%, 6%, 7%, 8%, 9%, 10%, or 5-10%.
The magnesia-alumina spinel powder material for the sealing coating not only needs to have better thermal shock resistance, but also can be prepared into a coating with higher porosity to obtain better abradability, and the powder needs to be nearly spherical in shape, not less than 95% in sphericity and provided with tiny holes on the surface in order to ensure the spraying adaptability of the powder and obtain a coating structure with dispersive tiny pores.
In an alternative embodiment, the ultra-high temperature ceramic abradable seal coating material has a laser particle size D50 of 30-60 μm.
Alternatively, the laser particle size D50 of the ultra-high temperature ceramic abradable seal coating material may be any value between 30 μm, 40 μm, 50 μm, 60 μm, or 30-60 μm.
The application also provides a preparation method of the ultrahigh-temperature ceramic abradable seal coating material, which comprises the following steps:
mixing magnesium oxide, aluminum oxide, a binder and water, and then sequentially performing ball milling, spray granulation, sintering and screening to obtain the ultrahigh-temperature ceramic abradable seal coating material.
The traditional stoichiometric ratio magnesia-alumina spinel material is prepared by an electric smelting sintering method and crushing, and the method has poor sphericity of powder, no fluidity and inapplicability to thermal spraying, so the magnesia-alumina spinel powder is prepared by adopting a spray granulation method with higher sphericity.
In an alternative embodiment, the mass ratio of the magnesium oxide to the aluminum oxide is (24-26): (74-76).
Alternatively, the mass ratio of the magnesium oxide to the aluminum oxide may be 24: 76. 25: 75. 26:74 or (24-26): (74-76).
In an alternative embodiment, the mass ratio of the total mass of the magnesium oxide and the aluminum oxide to the mass of the water and the binder is 100 (200-250): 7-10.
Alternatively, the mass ratio of the total mass of the magnesium oxide and the aluminum oxide to the mass of the water and the binder may be 100:200: 7. 100:220: 8. 100:250:10 or 100 (200-250) to any value between (7-10).
For spray granulation, the ratio of the common ceramic material to pure water is generally lower than 1:2, and for magnesia-alumina spinel materials, the slurry is easy to be too viscous, the slurry fluidity is poor, and the material cannot be rapidly formed in the spray granulation process, so that water with higher ratio is required to be added for preparing the same volume of material.
In an alternative embodiment, the ball milling is performed using zirconia balls, and the mass ratio of the total mass of the magnesia and the alumina to the zirconia balls is 1: (3-5), wherein the ball milling time is 6-15h.
Alternatively, the mass ratio of the total mass of the magnesium oxide and the aluminum oxide to the zirconia balls may be 1: 3. 1: 4. 1:5 or 1: (3-5), the ball milling time may be any value between 6h, 8h, 10h, 12h, 15h or 6-15h.
In an alternative embodiment, the binder comprises one or more of polyvinyl alcohol, carboxymethyl cellulose, polystyrene.
In an alternative embodiment, the spray granulation has an inlet temperature of 250-300 ℃, an outlet temperature of 100-120 ℃ below the inlet temperature, and a power of 28-32kw;
the residence time of the material in the tank body of the spray granulation equipment is 1-1.5min.
Alternatively, the inlet temperature of the spray granulation may be any value between 250 ℃, 260 ℃, 270 ℃, 280 ℃, 290 ℃, 300 ℃ or 250-300 ℃, the difference between the outlet temperature and the inlet temperature may be any value between 100 ℃, 110 ℃, 120 ℃ or 100-120 ℃, and the power may be any value between 28kw, 29kw, 30kw, 31kw, 32kw or 28-32kw; the residence time of the material in the tank of the spray granulation device can be any value between 1min, 1.1min, 1.2min, 1.3min, 1.4min, 1.5min or 1-1.5min.
In the spray granulation process, important factors influencing the phase and morphology of the powder are the residence time of the powder and the inlet and outlet temperature difference. The temperature difference between the inlet and the outlet is too small, the residence time of the powder is short, the powder is not enough to granulate into spheres, the fluidity of the powder is affected, the surface pores are more, the powder is too loose and porous, and then the powder is broken in the sintering process, so that the feasibility of the spraying process is affected; the temperature difference is too high or the residence time of the powder is too long, the surface of the powder is too compact, the porous coating is not easy to prepare, the binder is decomposed in advance, the powder is broken in advance in the sintering process, and the generation of magnesia-alumina spinel phase is not easy to realize.
In an alternative embodiment, the sintering is performed at a temperature of 1300-1400 ℃ for a period of 6-8 hours.
Alternatively, the sintering temperature may be 1300 ℃, 1350 ℃, 1400 ℃ or any value between 1300 and 1400 ℃ and the time may be 6 hours, 7 hours, 8 hours or any value between 6 and 8 hours.
Compared with the stoichiometric ratio magnesia-alumina spinel powder, the non-stoichiometric ratio magnesia-alumina spinel powder provided by the application has more severe sintering temperature requirement, and the excessive sintering temperature can lead to the phase change of an alumina phase, so that the powder performance can not meet the requirement, the sintering temperature is too low and the time is too short, more alumina phase exists in the powder, and the magnesia-alumina spinel phase with higher occupation can not be obtained; the existence of more aluminum oxide phase can lead to poorer high temperature thermal shock resistance and thermal stability of the prepared coating, and the working condition using requirement of the sealing coating is not met. And the sintering time is too long, so that the crystal grains are oversized, the surface holes become large, the anti-collapse strength of the powder is obviously reduced, and the powder is crushed, so that the subsequent coating use performance is not facilitated.
Embodiments of the present application will be described in detail below with reference to specific examples, but it will be understood by those skilled in the art that the following examples are only for illustration of the present application and should not be construed as limiting the scope of the present application. The specific conditions are not noted in the examples and are carried out according to conventional conditions or conditions recommended by the manufacturer. The reagents or apparatus used were conventional products commercially available without the manufacturer's attention.
Example 1
The embodiment provides an ultrahigh-temperature ceramic abradable seal coating material, and the preparation method thereof is as follows:
(1) Proportioning and ball milling: preparing magnesium oxide, aluminum oxide powder, a binder and water into slurry, putting the slurry and zirconium oxide balls into a ball milling barrel together for ball milling and mixing, wherein the weight ratio of the magnesium oxide to the aluminum oxide is 24:76, the weight ratio of the material to the pure water to the binder is 100:200:7, the weight ratio of the material to the zirconium oxide balls is 1:3, and the ball milling time is 10 hours;
(2) And (3) spray granulation: putting the mixed raw materials into a spray granulation system for spray granulation, wherein the inlet temperature is 300 ℃, the power is 30kw, the outlet temperature is 180 ℃, and the residence time of the materials in a spray granulation tank body is 1.5min;
(3) Sintering: placing the powder into a high-temperature furnace for sintering, wherein the sintering temperature is 1400 ℃, and the sintering time is 6 hours;
(4) And (3) screening: and sieving the sintered powder to obtain the powder with proper particle size.
The morphology of the powder prepared in example 1 is shown in fig. 1, the enlarged view is shown in fig. 2, the sphericity of the powder is calculated to be 98%, and the open porosity of the surface is 6%. The XRD pattern of the powder prepared in example 1 is shown in fig. 3, and the powder was subjected to laser granulometry with the stoichiometric ratio n=1.2 calculated for magnesium aluminate spinel, d50=52.1 μm. The sealing coating prepared by adopting plasma spraying has no falling off and blocking after air cooling and thermal shock at 1350 ℃ for 2000 times, and the coating has excellent thermal shock resistance.
Example 2
The present embodiment provides an ultra-high temperature ceramic abradable seal coating material, which is performed according to the method of embodiment 1, except that in step (1), the weight ratio of magnesium oxide to aluminum oxide is 26:74, and in the sintering process of step (3), the sintering temperature is 1300 ℃, and the sintering time is 10 hours.
The morphology of the powder prepared in example 2 is shown in fig. 4, and the sphericity of the powder is measured to be 96%, and the open porosity of the surface is measured to be 8%. The powder was subjected to laser granulometry with a stoichiometric ratio n=1.1 calculated for magnesium aluminate spinel, d50=48.6 μm. The sealing coating prepared by adopting plasma spraying has no falling off and blocking after air cooling and thermal shock at 1350 ℃ for 2000 times, and the coating has excellent thermal shock resistance.
Example 3
The present embodiment provides an ultra-high temperature ceramic abradable seal coating material, which is performed by referring to the method of embodiment 1, except that in the sintering process of step (3), the sintering temperature is 1200 ℃ and the sintering time is 12 hours.
The morphology of the powder prepared in example 3 is shown in fig. 5, and the sphericity of the powder is 97% and the surface open porosity is 7.5%. The powder was subjected to laser granulometry with a stoichiometric ratio n=1.16 for the magnesium aluminate spinel, d50=54.3 μm. The sealing coating prepared by adopting plasma spraying has no falling off and blocking after air cooling and thermal shock at 1350 ℃ for 2000 times, and the coating has excellent thermal shock resistance.
Comparative example 1
The preparation is carried out by adopting an electrofusion sintering method and crushing, the weight ratio of magnesium oxide to aluminum oxide is 25:75, and the sintering process is 1400 ℃ for 12h.
The morphology of the powder finally prepared in comparative example 1 is shown in fig. 6, and the powder particles have irregular shape and no fluidity, which is unfavorable for the subsequent spraying.
Comparative example 2
The powder prepared by sintering in comparative example 1 is processed by adopting the process of example 1, wherein the weight ratio of the material to the pure water to the binder is 100:100:7, the weight ratio of the material to the zirconia balls is 1:3, and the ball milling time is 10 hours; and (3) putting the mixed raw materials into a spray granulation system for spray granulation.
The morphology of the powder prepared in comparative example 2 is shown in fig. 7, although the powder is nearly spherical, the sphericity of the powder is 94%, the open porosity of the surface is 50%, the powder is too coarse to facilitate the subsequent spraying preparation of a coating, and the powder is subjected to laser particle size measurement, d50=25.4 μm, so that the powder does not meet the use requirement, and even if screening is performed, the powder yield is low and is not suitable for engineering application.
Comparative example 3
The procedure of example 1 was followed, except that during the spray granulation of step (2), the power was 34kw and the residence time of the powder in the spray granulation system was 0.8min.
The powder of comparative example 3 has too high power, too short residence time of the powder in a spray granulation system, lower sphericity, 93% of sphericity of the powder, 10% of open porosity of the surface, no fluidity, higher temperature difference of a granulation inlet and a granulation outlet, broken powder, too small granularity d50=32.1 μm, unsatisfied use requirement and unfavorable coating spraying.
Comparative example 4
The procedure of example 1 was followed, except that during the spray granulation of step (2), the inlet temperature was 350℃and the outlet temperature was 280℃and the residence time of the powder in the spray granulation system was 0.8min.
Comparative example 4 has the advantages that the temperature is too high, the water evaporation is too fast, the sphericity of the powder is 95%, the porosity of the surface opening is 15%, the holes on the surface of the powder are more, the roughness is high, the strength of the powder is too low, the mechanical property of the subsequent coating is poor, the prepared coating drops off and blocks after 84 times of air cooling and thermal shock at 1350 ℃, and the thermal shock resistance of the coating is poor and does not meet the use requirement.
Comparative example 5
The procedure of example 1 was followed, except that the weight ratio of magnesium oxide to aluminum oxide in step (1) was 16:84.
The powder prepared in comparative example 5 has high sphericity, the sphericity of the powder is measured to be 96%, the open porosity of the surface is 6%, the stoichiometric ratio n=2 of the magnesia-alumina spinel is calculated, the powder contains a large amount of alumina phase, the hardness of the prepared coating is too high, the blade is easy to abrade, the prepared coating is subjected to air cooling and thermal shock at 1350 ℃ for 354 times to fall off, the thermal shock resistance of the coating is poor, and the use requirement of the abradable coating is not met.
Comparative example 6
The procedure of example 1 was followed, except that the weight ratio of magnesium oxide to aluminum oxide in step (1) was 28:72.
The stoichiometric ratio n=1 of the magnesia-alumina spinel in the powder prepared in the comparative example 6, the sphericity of the powder is 97% and the porosity of the surface opening is 7% through calculation, the prepared coating is subjected to air cooling thermal shock at 1350 ℃ for 103 times to fall off and block, and the thermal shock resistance of the coating cannot meet the use requirement.
Comparative example 7
The procedure of example 1 was followed, except that the inlet/outlet temperature difference in step (2) was 200 ℃.
The sphericity of the powder prepared in comparative example 6 is 97%, the open porosity of the surface is 3%, the surface of the powder is too compact, the porous coating is not easy to prepare, the prepared coating has lower porosity and too high hardness, and the blade can be scraped in the process of scraping the blade by grinding, so that the use requirement is not met.
The abrasion performance of the coatings obtained in the examples and the comparative examples was tested, and the detailed test method was referred to the enterprise standard Q/BK908-2014, abrasion performance test and evaluation method for seal coating.
The IDRs of examples 1-3 were each less than 15% and the IDRs of comparative examples were each greater than 30%.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present application.
Claims (10)
1. The ultra-high temperature ceramic abradable seal coating material is characterized in that the ultra-high temperature ceramic abradable seal coating material is non-stoichiometric magnesia alumina spinel with a chemical formula of MgO 2 O 3 Wherein n is 1.1-1.3.
2. The ultra-high temperature ceramic abradable seal coating material of claim 1, wherein the ultra-high temperature ceramic abradable seal coating material has a surface open porosity of 5-10%.
3. The ultra-high temperature ceramic abradable seal coating material of claim 1 or 2, wherein the ultra-high temperature ceramic abradable seal coating material has a laser particle size D50 of 30-60 μιη.
4. A method of preparing the ultra-high temperature ceramic abradable seal coating material of any one of claims 1-3, comprising:
mixing magnesium oxide, aluminum oxide, a binder and water, and then sequentially performing ball milling, spray granulation, sintering and screening to obtain the ultrahigh-temperature ceramic abradable seal coating material.
5. The method for preparing an abradable seal coating material of ultra-high temperature ceramic according to claim 4, wherein the mass ratio of the magnesium oxide to the aluminum oxide is (24-26): (74-76).
6. The method for preparing an ultra-high temperature ceramic abradable seal coating material according to claim 4, wherein the mass ratio of the total mass of the magnesium oxide and the aluminum oxide to the mass of the water and the binder is 100 (200-250): 7-10.
7. The method for preparing an ultra-high temperature ceramic abradable seal coating material according to claim 4, wherein the ball milling is performed using zirconia balls, and the mass ratio of the total mass of the magnesia and the alumina to the zirconia balls is 1: (3-5), wherein the ball milling time is 6-15h.
8. The method for preparing an ultra-high temperature ceramic abradable seal coating material according to claim 4, wherein the binder comprises one or more of polyvinyl alcohol, carboxymethyl cellulose, and polystyrene.
9. The method for preparing an ultra-high temperature ceramic abradable seal coating material according to claim 4, wherein the inlet temperature of the spray granulation is 250-300 ℃, the outlet temperature is lower than the inlet temperature by 100-120 ℃, and the power is 28-32kw;
the residence time of the material in the tank body of the spray granulation equipment is 1-1.5min.
10. The method for preparing an ultra-high temperature ceramic abradable seal coating material according to any one of claims 4 to 9, wherein the sintering temperature is 1300 to 1400 ℃ for 6 to 8 hours.
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| CN117551365A (en) * | 2024-01-10 | 2024-02-13 | 北矿新材科技有限公司 | Powder for sealing coating, sealing coating and preparation method of sealing coating |
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