CN116535243A - Abradable seal coating with low friction coefficient and high volumetric abrasion rate and preparation method thereof - Google Patents
Abradable seal coating with low friction coefficient and high volumetric abrasion rate and preparation method thereof Download PDFInfo
- Publication number
- CN116535243A CN116535243A CN202310360224.2A CN202310360224A CN116535243A CN 116535243 A CN116535243 A CN 116535243A CN 202310360224 A CN202310360224 A CN 202310360224A CN 116535243 A CN116535243 A CN 116535243A
- Authority
- CN
- China
- Prior art keywords
- zro
- stabilization
- coating
- powder
- layer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000576 coating method Methods 0.000 title claims abstract description 113
- 239000011248 coating agent Substances 0.000 title claims abstract description 111
- 238000005299 abrasion Methods 0.000 title claims abstract description 37
- 238000002360 preparation method Methods 0.000 title claims abstract description 25
- 239000010410 layer Substances 0.000 claims abstract description 100
- 239000002131 composite material Substances 0.000 claims abstract description 73
- 238000000034 method Methods 0.000 claims abstract description 56
- 229910052761 rare earth metal Inorganic materials 0.000 claims abstract description 37
- 150000002910 rare earth metals Chemical class 0.000 claims abstract description 37
- 230000006641 stabilisation Effects 0.000 claims abstract description 31
- 238000011105 stabilization Methods 0.000 claims abstract description 31
- 239000000919 ceramic Substances 0.000 claims abstract description 12
- 239000011229 interlayer Substances 0.000 claims abstract description 8
- 239000000843 powder Substances 0.000 claims description 64
- 239000002344 surface layer Substances 0.000 claims description 56
- 239000000463 material Substances 0.000 claims description 46
- 238000005507 spraying Methods 0.000 claims description 41
- 238000007750 plasma spraying Methods 0.000 claims description 36
- 230000001050 lubricating effect Effects 0.000 claims description 35
- 239000011153 ceramic matrix composite Substances 0.000 claims description 29
- 239000011159 matrix material Substances 0.000 claims description 24
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 18
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 9
- 229910052786 argon Inorganic materials 0.000 claims description 9
- 239000001257 hydrogen Substances 0.000 claims description 9
- 229910052739 hydrogen Inorganic materials 0.000 claims description 9
- 238000005488 sandblasting Methods 0.000 claims description 9
- 239000002994 raw material Substances 0.000 claims description 8
- 238000002156 mixing Methods 0.000 claims description 7
- 239000002245 particle Substances 0.000 claims description 7
- 239000012790 adhesive layer Substances 0.000 claims description 6
- 239000011863 silicon-based powder Substances 0.000 claims description 6
- 229910052582 BN Inorganic materials 0.000 claims description 4
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 4
- 239000000440 bentonite Substances 0.000 claims description 4
- 229910000278 bentonite Inorganic materials 0.000 claims description 4
- SVPXDRXYRYOSEX-UHFFFAOYSA-N bentoquatam Chemical compound O.O=[Si]=O.O=[Al]O[Al]=O SVPXDRXYRYOSEX-UHFFFAOYSA-N 0.000 claims description 4
- WUKWITHWXAAZEY-UHFFFAOYSA-L calcium difluoride Chemical compound [F-].[F-].[Ca+2] WUKWITHWXAAZEY-UHFFFAOYSA-L 0.000 claims description 4
- 239000010439 graphite Substances 0.000 claims description 4
- 229910002804 graphite Inorganic materials 0.000 claims description 4
- 239000004642 Polyimide Substances 0.000 claims description 3
- 229910001634 calcium fluoride Inorganic materials 0.000 claims description 3
- 150000002148 esters Chemical class 0.000 claims description 3
- 229920001721 polyimide Polymers 0.000 claims description 3
- 229920006389 polyphenyl polymer Polymers 0.000 claims description 3
- 239000011247 coating layer Substances 0.000 claims description 2
- 238000007789 sealing Methods 0.000 abstract description 7
- 239000012071 phase Substances 0.000 description 54
- 230000000052 comparative effect Effects 0.000 description 13
- 239000007921 spray Substances 0.000 description 10
- 238000012360 testing method Methods 0.000 description 9
- 239000007789 gas Substances 0.000 description 8
- 229910004261 CaF 2 Inorganic materials 0.000 description 7
- 239000000758 substrate Substances 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000003647 oxidation Effects 0.000 description 5
- 238000007254 oxidation reaction Methods 0.000 description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 229910045601 alloy Inorganic materials 0.000 description 4
- 239000000956 alloy Substances 0.000 description 4
- 238000004458 analytical method Methods 0.000 description 4
- 230000008021 deposition Effects 0.000 description 4
- 239000012159 carrier gas Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 150000002500 ions Chemical class 0.000 description 3
- 238000002844 melting Methods 0.000 description 3
- 230000008018 melting Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000011148 porous material Substances 0.000 description 3
- 238000006467 substitution reaction Methods 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- JNDMLEXHDPKVFC-UHFFFAOYSA-N aluminum;oxygen(2-);yttrium(3+) Chemical compound [O-2].[O-2].[O-2].[Al+3].[Y+3] JNDMLEXHDPKVFC-UHFFFAOYSA-N 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000001747 exhibiting effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000010285 flame spraying Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 238000011031 large-scale manufacturing process Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 229910019901 yttrium aluminum garnet Inorganic materials 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
- C04B41/81—Coating or impregnation
- C04B41/89—Coating or impregnation for obtaining at least two superposed coatings having different compositions
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
- C04B41/52—Multiple coating or impregnating multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
- C04B41/81—Coating or impregnation
- C04B41/85—Coating or impregnation with inorganic materials
- C04B41/87—Ceramics
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Materials Engineering (AREA)
- Structural Engineering (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The invention discloses an abradable seal coating with low friction coefficient and high volume abrasion rate and a preparation method thereof, wherein Y is as follows 2 O 3 Stabilization of ZrO 2 The base composite coating is used as a surface coating, the surface coating and an Si bonding layer on the surface of the ceramic base composite material are combined together by utilizing a rare earth pyrosilicate interlayer to form an abradable seal coating composite material structure, and the abradable seal coating structure comprises the Si bonding layer, the rare earth pyrosilicate interlayer and Y which are sequentially deposited on the surface of the ceramic base composite material 2 O 3 Stabilization of ZrO 2 A base composite facing. The coating designed by the invention has better abradable sealing performance, can obviously reduce the hardness and friction coefficient of the coating and improve the volume abrasion rate. Is expected to solve the mechanical damage caused by mutual friction in the service process of parts such as an aero-engine turbine and the like, and can realize the vortex of the aero-engineAnd the gas path sealing of parts such as wheels is aimed, so that the efficiency of the engine is improved, and the oil consumption of the engine is reduced.
Description
Technical Field
The invention relates to an abradable seal coating for the surface of a ceramic matrix composite material and a preparation method thereof.
Background
The manufacture of aeroengines is an important manifestation of the comprehensive strength of a country. Aeroengines act as the heart of an aircraft, directly affecting the performance, economy and reliability of the aircraft. The blades of an aeroengine deform under the combined action of centrifugal force, aerodynamic force, thermal expansion and other factors under long-term service. Thus, the actual distance between the blade tips and the turbine outer ring will vary with changing engine operating conditions. In order to prevent mechanical damage to the blade tips and the turbine outer ring due to mutual friction in various conditions, suitable clearances between the blade tips and the turbine outer ring are necessary during design, manufacturing and maintenance of the aircraft engine. However, the presence of the gap may again cause leakage such that the aeroengine operating efficiency is reduced. Abradable seal coatings are widely used as a sacrificial coating to control the clearance between the blade tips of an aircraft engine and the turbine outer ring. When an engine blade is in contact with the coating, the coating will preferentially wear away without the blade being damaged. This requires a moderate hardness of the coating to be shaved by the blade, i.e. good abradability.
High propulsion, high efficiency and low fuel consumption are the goals of aircraft engine design and manufacture. Higher gas turbine inlet temperatures (1300 ℃) are required to increase the thrust to weight ratio of an aircraft engine. Accordingly, the corresponding case temperatureWill rise (1200 c). Turbine components and corresponding metal-based abradable seal coatings fabricated from conventional nickel-based alloys are difficult to service for extended periods of time at such temperatures. Ceramic Matrix Composites (CMCs) comprising C f SiC and SiC f SiC, etc., has the characteristics of low density, good high-temperature mechanical property, etc., and can partially replace high-temperature alloy to be used for hot end parts of aeroengines. Coefficient of thermal expansion of CMCs (4.5-5.9X10) -6 K -1 ) Is significantly lower than nickel-base superalloy material (15-17×10 -6 K -1 )，Y 2 O 3 Stabilization of ZrO 2 Is commonly used as a ceramic-based abradable seal coating material, but Y 2 O 3 Stabilization of ZrO 2 High thermal expansion coefficient (10-11.8X10) -6 K -1 ) Making it difficult to match CMCs. Patent application number CN202210037677.7 discloses a preparation method of a plasma spraying YSZ ceramic-based seal coating capable of improving the deposition rate, compared with the traditional YSZ ceramic-based agglomerated powder, the plasma spraying deposition rate of the YSZ ceramic-based agglomerated powder containing yttrium aluminum garnet binder phase is improved by 181.49%, but the prepared friction coefficient and the volume abrasion rate are not disclosed. Patent application number CN201711423744.4 discloses a high-temperature abradable seal coating and a preparation method thereof. Spraying MCrAlY alloy powder to the surface of a substrate through supersonic flame spraying equipment to prepare a coating, spraying the surface of the substrate for multiple times, wherein the deposition thickness of single spraying is less than or equal to 0.01mm, and carrying out stress relief and diffusion treatment on the coated coating by adopting vacuum heat treatment every time of spraying of 0.5-1.0 mm; finally spraying to obtain the sealing coating with the thickness of more than or equal to 1.5 mm. The sealing coating prepared by the method has the characteristics of oxidation resistance, low hardness at high temperature, abradability, high temperature stability, thermal shock resistance and high bonding strength, the working temperature can reach 1100 ℃, the abrasion of turbine rotor blades can be obviously reduced, the abradability, the reliability and the service life of the coating are improved, the porosity of the coating tissue is lower than 1%, the oxygen content is lower than 5%, the bonding strength is higher than 60MPa, the high-temperature hardness HR45Y of the coating at 1000 ℃ is less than or equal to 70, but the friction coefficient and the volume abrasion rate of the prepared coating are not disclosed. Therefore, the prior art also focuses mainly on the preparation process of the abradable seal coating, but is not yet mainly concernedHow to break through necessary performance from the performance of the material, develop a composite coating which can be matched with CMCs and has abradable sealing performance and a preparation technology thereof, reduce the gap between the tip of a blade and the outer ring of a turbine, improve the efficiency of an engine, reduce the mechanical damage of an aeroengine blade in the service process, and avoid the oxidation and structural degradation of the CMCs to be the technical problem to be solved urgently.
Disclosure of Invention
In order to solve the problems of the prior art, the invention aims to overcome the defects of the prior art, and provides an abradable seal coating with low friction coefficient and high volume abrasion rate and a preparation method thereof.
In order to achieve the aim of the invention, the invention adopts the following technical scheme:
an abradable seal coating with low coefficient of friction and high bulk wear rate, Y 2 O 3 Stabilization of ZrO 2 The base composite coating is used as a surface coating, the surface coating and an Si bonding layer on the surface of the ceramic base composite material are combined together by utilizing a rare earth pyrosilicate interlayer to form an abradable seal coating composite material structure, and the abradable seal coating structure comprises the Si bonding layer, the rare earth pyrosilicate interlayer and Y which are sequentially deposited on the surface of the ceramic base composite material 2 O 3 Stabilization of ZrO 2 A base composite facing. The invention has an abradable seal coating structure with low friction coefficient and high volume abrasion rate, which sequentially comprises a ceramic matrix composite material matrix, a bonding layer positioned on the surface of the matrix, an intermediate layer positioned between the bonding layer and a surface layer, and a surface layer; the bonding layer is an Si bonding layer, the intermediate layer is a rare earth disilicate layer, and the surface layer is Y 2 O 3 Stabilization of ZrO 2 A base composite facing. Wherein Y is 2 O 3 Stabilization of ZrO 2 Abbreviated as YSZ. The YSZ-based composite surface layer has high melting point and low heat conductivity, can exert good heat insulation performance, is an ideal high-temperature thermal protection coating material, and is suitable for being used as an abradable seal coating material. The rare earth pyrosilicate intermediate layer has the characteristics of high melting point, good high-temperature phase stability, low thermal expansion coefficient, good high-temperature plasticity and the like, and can relieve stress concentration caused by the thermal expansion coefficient of the ceramic matrix composite material and the YSZ composite surface layer. In the material system, the chemical compatibility of the Si bonding layer is good, and the Si bonding layer is matched with the thermal expansion coefficient of the ceramic matrix composite material, so that the corrosion phenomena such as oxidation and the like of the ceramic matrix composite material in the service process can be effectively relieved.
Preferably, the invention has the abradable seal coating with low friction coefficient and high volume abrasion rate, the main phase of the YSZ-based composite surface layer is YSZ, and the invention also comprises a lubricating phase and a pore-forming phase; the intermediate layer of rare earth pyrosilicate adopts Lu 2 Si 2 O 7 、Er 2 Si 2 O 7 、Y 2 Si 2 O 7 、Yb 2 Si 2 O 7 At least one of them. Further preferably, the composite layer is formed from a main phase, a lubricating phase, and a pore-forming phase in the YSZ-based composite facing. Further preferably, the YSZ-based composite face layer further includes voids therein left by the pore-forming phase after ablation during the heat treatment.
Further preferably, the lubricating phase is calcium fluoride (CaF 2 ) The method comprises the steps of carrying out a first treatment on the surface of the The pore-forming phase is at least one of polyimide and polyphenyl ester (PHB).
Still further preferably, the YSZ-based composite face layer of the invention uses YSZ as a main phase, graphite, bentonite, diatomite, hexagonal boron nitride (h-BN) and CaF 2 PHB is a lubricating phase and PHB is a pore-forming phase. In the material system, YSZ has high melting point, low heat conductivity and high hardness, can resist erosion of air flow or particles, and provides certain strength for the coating. CaF (CaF) 2 And the like as a lubricating phase, has low shear strength, can provide a certain lubricating effect for the coating, and reduces the friction coefficient of the coating. PHB is used as pore-forming phase, and pores are formed in the coating by heat treatment, so that the hardness of the coating can be reduced, and the stress concentration in the coating can be relievedAnd improves the abradability of the coating.
Preferably, the invention has an abradable seal coating with low coefficient of friction and high bulk wear rate, the YSZ-based composite top layer has a thickness of 500 to 2000 μm, the rare earth pyrosilicate interlayer has a thickness of 50 to 500 μm, and the Si tie layer has a thickness of 50 to 400 μm.
Further preferably, the YSZ-based composite surface layer has a thickness of 500 to 1000 μm, the rare earth pyrosilicate interlayer has a thickness of 150 to 300 μm, and the Si bonding layer has a thickness of 50 to 100 μm.
Preferably, the abradable seal coating with low friction coefficient and high volume abrasion rate is calculated according to the mass percentage of the components, and the total amount of the components of the YSZ-based composite coating is 100 percent, in the YSZ-based composite surface layer, the content of YSZ is 60-94 percent, the content of lubricating phase is 5-30 percent, and the content of pore-forming phase is 1-10 percent.
Further preferably, the content of the lubricating phase is 10 to 20%, and the content of the pore-forming phase is 4 to 8%.
Preferably, the abradable seal coating of the present invention has a low coefficient of friction and a high bulk wear rate, with an average coefficient of friction of 0.103 to 0.373 and a bulk wear rate of 2.18×10 -2 ～5.47×10 -2 mm 3 The IDR value is 8.80-26.75%.
Preferably, the invention has an abradable seal coating with a low coefficient of friction and a high bulk wear rate, with a Rockwell hardness HR45Y of 59.98-90.43.
The invention relates to a preparation method of an abradable seal coating with low friction coefficient and high volume abrasion rate, which comprises the steps of firstly spraying an Si bonding layer on the surface of a ceramic matrix composite material by adopting a plasma spraying method; then, preparing a rare earth pyrosilicate intermediate layer on the surface of the Si bonding layer by adopting a plasma spraying method; and preparing a YSZ-based composite surface layer on the rare earth pyrosilicate intermediate layer by adopting a plasma spraying method to form an abradable seal coating composite material structure. The YSZ-based composite surface layer has compact structure and higher hardness, and the lubricating phase comprises graphite, bentonite, diatomite, hexagonal boron nitride (h-BN) and CaF 2 And the pore-forming phase PHB is used as an additive phase, so that the lubricating effect can be achieved, the porosity of the coating is improved, the friction coefficient of the coating is reduced, the volume abrasion rate of the coating is improved, and the abradability of the coating is improved.
Preferably, in preparing the Si adhesive layer, si powder having a particle diameter of 10 to 100 μm is used.
Preferably, the particle size of the rare earth pyrosilicate material powder used in the preparation of the rare earth pyrosilicate intermediate layer is 10-120 mu m.
Preferably, when preparing the YSZ-based composite surface layer, the main phase of the YSZ-based composite surface layer is YSZ, and the YSZ-based composite surface layer also comprises a lubricating phase and a pore-forming phase; the grain diameter of the powder adopting YSZ is 10-120 mu m, the grain diameter of the powder adopting the lubricating phase is 10-120 mu m, and the grain diameter of the powder adopting the pore-forming phase is 10-120 mu m.
Preferably, the method for preparing the abradable seal coating with low friction coefficient and high volumetric abrasion rate comprises the following steps: preparing a plasma spraying composite powder for the YSZ-based composite surface layer; coarsening the surface of the clean matrix to obtain a surface-pretreated matrix; preparing a Si bonding layer on the surface of the pretreated substrate; spraying a rare earth pyrosilicate intermediate layer on the surface of the bonding layer; and spraying and preparing a YSZ-based composite surface layer on the surface of the intermediate layer.
Further preferably, the method for preparing the abradable seal coating with low friction coefficient and high volumetric abrasion rate according to the invention is characterized by comprising the following steps:
(1) Preparing powder for the YSZ-based composite surface layer:
mixing YSZ powder with lubricating phase and pore-forming phase powder in a mechanical mixing mode to prepare a powder material used for the YSZ-based composite surface layer, wherein the main phase of the YSZ-based composite surface layer is YSZ, and the YSZ-based composite surface layer also comprises the lubricating phase and the pore-forming phase;
wherein the grain diameter of the YSZ powder is 10-120 mu m, the grain diameter of the lubricating phase powder is 10-120 mu m, and the grain diameter of the pore-forming phase powder is 10-120 mu m; the mass fraction of YSZ is 60-94%, the mass fraction of the lubricating phase is 10-20%, and the mass fraction of the pore-forming phase is 4-8%; the total mass fraction of the powder materials used by the YSZ-based composite surface layer is 100%;
(2) Pretreatment of a matrix:
pretreating the surface of a ceramic matrix composite material matrix, wherein the pretreatment is sand blasting coarsening, and the sand blasting pressure is 0.1-0.6 MPa;
(3) Preparation of the adhesive layer:
preparing an Si bonding layer on the surface of the ceramic matrix composite material, adopting a plasma spraying method, adopting Si powder as a raw material, and spraying the Si bonding layer with the thickness of 50-100 mu m;
the parameters of the plasma spraying process include:
current flow: 500-700A, argon flow: 40-50 slm, hydrogen flow: 5 to 20slm, spraying power: 30-55 kW, spraying distance: 100-200 mm, powder feeding rate: 10-35 r/min;
(4) Preparation of an intermediate layer:
preparing a rare earth pyrosilicate intermediate layer on the surface of the Si bonding layer, adopting a plasma spraying method, and adopting rare earth pyrosilicate material powder as a raw material, wherein the spraying thickness is 150-300 mu m;
the parameters of the plasma spraying process include:
current flow: 500-800A, argon flow: 30-55 slm, hydrogen flow: 5 to 20slm, spraying power: 30-60 kW, spraying distance: 100-200 mm, powder feeding rate: 10-30 r/min;
(5) Preparation of the surface layer:
spraying the powder material used for the YSZ-based composite surface layer prepared in the step (1) on the rare earth pyrosilicate interlayer prepared in the step (4) by adopting a plasma spraying method, wherein the spraying thickness is 500-1000 mu m;
the parameters of the plasma spraying process include:
current flow: 500-800A, argon flow: 30-50 slm, hydrogen flow: 5 to 15slm, spraying power: 30-60 kW, spraying distance: 100-250 mm, powder feeding rate: 10-35 r/min.
Compared with the prior art, the invention has the following obvious prominent substantive features and obvious advantages:
1. the YSZ-based composite surface layer material adopted by the invention has low hardness and friction coefficient, high volume abrasion rate, namely good abradability of the coating; on the basis of improving the heat protection and oxidation resistance of the coating, the friction coefficient of the abradable seal coating is further reduced, and the abrasion of the blade is reduced. Meanwhile, YSZ has low heat conductivity and good heat insulation performance;
2. the ceramic matrix composite material is easy to be corroded by high-temperature steam and oxygen in the service environment of the engine, and the rare earth pyrosilicate intermediate layer prepared by the method has good steam corrosion resistance and oxidation resistance and can play a good role in protecting a matrix;
3. the rare earth pyrosilicate is adopted as the intermediate layer, so that the ceramic matrix composite material has remarkable crack expansion resistance and excellent thermal shock resistance, and stress concentration between the ceramic matrix composite material matrix, the bonding layer and the YSZ matrix composite surface layer due to the difference of thermal expansion coefficients can be relieved;
4. the coating is prepared by adopting a plasma spraying method, and the method has the characteristics of simple process, high deposition efficiency, controllable coating thickness, suitability for large-scale production and the like.
Drawings
FIG. 1 is a schematic view of the structure of an abradable seal coating on the surface of a ceramic matrix composite substrate in accordance with a preferred embodiment of the invention.
Detailed Description
The present invention is further illustrated by the following embodiments, which are to be understood as merely illustrative of the invention and not limiting thereof.
The abradable seal coating structure includes: a Si bonding layer, a rare earth pyrosilicate intermediate layer and a YSZ-based composite surface layer. Wherein, the intermediate layer material of rare earth pyrosilicate adopts Lu 2 Si 2 O 7 、Er 2 Si 2 O 7 、Y 2 Si 2 O 7 、Yb 2 Si 2 O 7 At least one of the materials is characterized in that YSZ in the surface layer material is a ceramic-based main phase, and the lubricating phase is graphite, bentonite, diatomite, hexagonal boron nitride (h-BN) and calcium fluoride (CaF) 2 ) At least one of (a) and (b); the pore-forming phase is at least one of polyimide and polyphenyl ester (PHB)One of the two. The structural schematic diagram of the abradable seal coating on the surface of the ceramic matrix composite material matrix is shown in fig. 1, wherein the ceramic matrix composite material is taken as a matrix, the Si layer is taken as a bonding layer, and Yb is taken as a bonding layer 2 Si 2 O 7 The layer is composed of an intermediate layer and a YSZ-based composite coating layer as a surface layer. Wherein the bonding layer and the intermediate layer are compact in structure, and the layers of the coating system are tightly combined. The facing structure includes a lubricating phase uniformly distributed in the YSZ host phase and pores left after removal by the pore former.
And mixing the YSZ powder with the lubricating phase and pore-forming phase powder in a mechanical mixing mode to prepare the powder for the YSZ-based composite surface layer. Wherein the grain diameter of the YSZ powder is 10-120 mu m, the grain diameter of the lubricating phase powder is 10-120 mu m, and the grain diameter of the pore-forming phase powder is 10-120 mu m; the mass fraction of the YSZ is 60% -94%, the mass fraction of the lubricating phase is 10% -20%, and the mass fraction of the pore-forming phase is 4% -8%.
Pretreatment of a matrix:
i.e. sand blasting pretreatment. The matrix is ceramic matrix composite material and is pretreated by surface sand blasting and the like. The sand blasting pressure is 0.1-0.6 MPa.
Preparation of the adhesive layer:
preparing an Si-containing bonding layer on the surface of a matrix material, adopting a plasma spraying method, adopting Si powder as a raw material, and spraying the Si bonding layer, wherein the parameters of the plasma spraying process comprise: current flow: 500-700A, argon flow: 40-50 slm, hydrogen flow: 5 to 20slm, spraying power: 30-55 kW, spraying distance: 100-200 mm, powder feeding rate: 10-35 r/min. The thickness of the adhesive layer is 50 to 400. Mu.m, preferably 50 to 100. Mu.m.
Preparation of an intermediate layer:
preparing a rare earth pyrosilicate intermediate layer on the surface of the bonding layer, adopting a plasma spraying method, adopting rare earth pyrosilicate powder as a raw material, and spraying the rare earth pyrosilicate intermediate layer, wherein parameters of the plasma spraying process comprise: current flow: 500-800A, argon flow: 30-55 slm, hydrogen flow: 5 to 20slm, spraying power: 30-60 kW, spraying distance: 100-200 mm, powder feeding rate: 10-30 r/min. The thickness of the intermediate layer is 50 to 500. Mu.m, preferably 150 to 300. Mu.m.
Preparation of the surface layer:
and spraying the prepared YSZ-based composite surface layer powder on a substrate with a bonding layer and an intermediate layer by adopting a plasma spraying method. The parameters of the plasma spraying process include: current flow: 500-800A, argon flow: 30-50 slm, hydrogen flow: 5 to 15slm, spraying power: 30-60 kW, spraying distance: 100-250 mm, powder feeding rate: 10-35 r/min. The thickness of the top layer is 500 to 2000. Mu.m, preferably 500 to 1000. Mu.m.
The present invention will be further illustrated by the following examples.
It is also to be understood that the following examples are given solely for the purpose of illustration and are not to be construed as limitations upon the scope of the invention, since numerous insubstantial modifications and variations will now occur to those skilled in the art in light of the foregoing disclosure. The specific process parameters and the like described below are also merely examples of suitable ranges, i.e., one skilled in the art can make a suitable selection from the description herein and are not intended to be limited to the specific values described below.
The foregoing aspects are further described in conjunction with specific embodiments, and the following detailed description of preferred embodiments of the present invention is provided:
example 1
In this embodiment, an abradable seal coating structure with low coefficient of friction and high bulk wear rate has a YSZ-based composite facing layer utilizing Yb 2 Si 2 O 7 The layer combines the surface coating and the Si bonding layer on the surface of the ceramic matrix composite material together, so that the abradable seal coating structure forms the Si bonding layer and the Yb which are sequentially deposited on the surface of the ceramic matrix composite material 2 Si 2 O 7 A coating structure consisting of an intermediate layer and a YSZ-based composite surface layer.
In this embodiment, the method for preparing the abradable seal coating with low friction coefficient and high volumetric abrasion rate includes the following steps:
(1) Preparing powder for the YSZ-based composite surface layer:
mixing YSZ powder with the lubricating phase and pore-forming phase powder in a mechanical mixing mode to prepare a powder material for the YSZ-based composite surface layer; wherein the grain diameter of the YSZ powder is 10-120 mu m, the grain diameter of the lubricating phase powder is 10-120 mu m, and the grain diameter of the pore-forming phase powder is 10-120 mu m; the mass fraction of YSZ is 86%, the mass fraction of the lubricating phase is 10%, and the mass fraction of the pore-forming phase is 4%;
(2) Pretreatment of a matrix:
adopting a pretreatment process method, wherein a matrix adopts a ceramic matrix composite material, is subjected to surface sand blasting pretreatment, and adopts sand blasting pressure of 0.5MPa to complete the pretreatment process of the matrix;
(3) Preparation of the adhesive layer:
preparing an Si bonding layer on the surface of a matrix material, adopting a plasma spraying method, adopting Si powder as a raw material, and spraying an Si coating with the thickness of 100 mu m, wherein the parameters of the plasma spraying process are shown in Table 1.
TABLE 1 parameter Table of ion spray Process for preparing bonding layer
| Plasma gas Ar | 40slpm | Powder carrier gas Ar | 4slpm | Electric current | 550A |
| Plasma gas H 2 | 7slpm | Spray distance | 130mm | ||
| Spray power | 37kw | Powder feeding rate | 20rpm |
(4) Preparation of an intermediate layer:
preparation of Yb on Si bonding layer surface 2 Si 2 O 7 An intermediate layer is formed by adopting a plasma spraying method and adopting Yb 2 Si 2 O 7 The powder is used as raw material to spray Yb with 200 mu m thickness 2 Si 2 O 7 The parameters of the intermediate layer and the plasma spraying process are shown in Table 2.
TABLE 2 parameter Table of ion spray Process used to prepare intermediate layer
| Plasma gas Ar | 43slpm | Powder carrier gas Ar | 5slpm | Electric current | 600A |
| Plasma gas H 2 | 12slpm | Spray distance | 130mm | ||
| Spray power | 45kw | Powder feeding rate | 15rpm |
(5) Preparation of the surface layer:
spraying the powder material for the YSZ-based composite surface layer prepared in the step (1) on a substrate with a bonding layer and an intermediate layer by adopting a plasma spraying method to prepare 600 mu m-thickness YSZ-10wt.% CaF 2 -4wt.% PHB composite coating, the parameters of the plasma spraying process are given in table 3.
TABLE 3 parameter Table of ion spray Process for preparing surface layer
| Plasma gas Ar | 45slpm | Powder carrier gas Ar | 5slpm | Electric current | 500A |
| Plasma gas H 2 | 15slpm | Spray distance | 120mm | ||
| Spray power | 55kw | Powder feeding rate | 12rpm |
Test analysis:
example 1 the rockwell hardness of a surface YSZ-based composite coating was measured using a rockwell hardness tester. The abradability of the coating is checked by adopting a frictional abrasion experiment, and the conditions are as follows: the pin-disc contact mode is adopted, the counter-grinding material is GH4169 nickel-based alloy, the load is 15N, the linear speed is 0.5m/s, and the time is 5min. Automatically reading the friction coefficient of the coating through a wear device; the wear rate of the coating was measured and calculated using a profiler. Measuring the wear depth of the wear part by using a vernier caliper, and calculating the ratio (IDR) of the wear depth of the wear part to the wear depth of the coating to characterize the coatingAbradable properties. The Rockwell hardness of the prepared abradable seal surface layer is (87.73 +/-2.70) HR45Y. The average friction coefficient of the coating is 0.279+/-0.094, and the volume abrasion rate is (2.43+/-0.25) multiplied by 10 -2 mm 3 The IDR value was 26.75%. Compared with comparative example 1, the hardness was reduced by 3.91%, the friction coefficient was reduced by 38.95%, and the volumetric wear rate was increased by 14.19 times. Compared with comparative example 2, the hardness was reduced by 2.47%, the friction coefficient was reduced by 31.78%, and the volumetric wear rate was increased by 1.48 times.
Example 2
This embodiment is substantially the same as embodiment 1, except that:
in this example, the facing used was YSZ-10wt.% CaF 2 -8 wt% PHB composite facing. The procedure is as in example 1.
Test analysis:
this example shows that the Rockwell hardness of the abradable seal surface layer prepared is (67.09.+ -. 3.11) HR45Y. The abrasion performance of the coating was examined by using a frictional abrasion test, and the examination conditions were the same as in example 1. The average friction coefficient of the coating is 0.267+/-0.088, and the volume abrasion rate is (3.93+/-0.11) multiplied by 10 -2 mm 3 The IDR value was 17.28%. Compared with comparative example 1, the hardness was reduced by 26.52%, the friction coefficient was reduced by 41.58%, and the volumetric wear rate was increased by 23.56 times. Compared with comparative example 2, the hardness was reduced by 25.41%, the friction coefficient was reduced by 34.72%, and the volumetric wear rate was increased by 3.01 times.
Example 3
This embodiment is substantially the same as the above embodiment, and is characterized in that:
in this example, the facing used was YSZ-20wt.% CaF 2 -4 wt% PHB composite facing. The procedure is as in example 1.
Test analysis:
this example shows that the Rockwell hardness of the abradable seal surface layer prepared is (80.67 + -1.08) HR45Y. The abrasion performance of the coating was examined by using a frictional abrasion test, and the examination conditions were the same as in example 1. The average friction coefficient of the coating is 0.239+/-0.038, and the volume abrasion rate is (3.22+/-0.17) multiplied by 10 -2 mm 3 The IDR value was 21.46%. Compared with comparative example 1, the hardness was reduced by 11.64%, the friction coefficient was reduced by 47.70%, and the volumetric wear rate was increased by 19.13 times. Compared with comparative example 2, the hardness was reduced by 10.32%, the friction coefficient was reduced by 41.56%, and the volumetric wear rate was increased by 2.29 times. Exhibiting a lower coefficient of friction and a greater volumetric wear rate.
Example 4
This embodiment is substantially the same as the above embodiment, and is characterized in that:
in this example, the facing used was YSZ-20wt.% CaF 2 -8 wt% PHB composite facing. The procedure is as in example 1.
Test analysis:
this example shows that the Rockwell hardness of the abradable seal surface layer prepared is (62.91.+ -. 2.93) HR45Y. The abrasion performance of the coating was examined by using a frictional abrasion test, and the examination conditions were the same as in example 1. The average friction coefficient of the coating is 0.117+/-0.014, and the volume abrasion rate is (5.16+/-0.31) multiplied by 10 -2 mm 3 The IDR value was 8.80%. Compared with comparative example 1, the hardness was reduced by 31.30%, the friction coefficient was reduced by 74.40%, and the volumetric wear rate was increased by 31.25 times. Compared with comparative example 2, the hardness was reduced by 30.06%, the friction coefficient was reduced by 71.39%, and the volumetric wear rate was increased by 4.27 times. Exhibits excellent low friction coefficient and high bulk wear rate properties.
Comparative example 1:
in the comparative example, a ceramic matrix composite material is used as a matrix, and a plasma spraying method is adopted to prepare Si bonding layers and Yb 2 Si 2 O 7 The middle layer and YSZ top layer were sprayed with the same parameters as in example 1. The Rockwell hardness of the abradable seal surface layer prepared in this comparative example was (91.30.+ -. 1.25) HR45Y. The abrasion performance of the coating was examined by using a frictional abrasion test, and the examination conditions were the same as in example 1. The average friction coefficient of the coating is 0.457+ -0.046, and the volume abrasion rate is (0.16+ -0.04). Times.10 -2 mm 3 The IDR value was 222.72%.
Comparative example 2:
the comparative example uses ceramic matrix compositeThe material is used as a matrix, and a Si bonding layer and Yb are prepared by adopting a plasma spraying method 2 Si 2 O 7 Intermediate layer and YSZ-10wt.% CaF 2 The surface layer and the spraying parameters are the same as in example 1. The Rockwell hardness of the prepared abradable seal surface layer is (89.95+/-3.26) HR45Y. The abrasion performance of the coating was examined by using a frictional abrasion test, and the examination conditions were the same as in example 1. The average friction coefficient of the coating is 0.409+/-0.049, and the volume abrasion rate is (0.98+/-0.29) multiplied by 10 -2 mm 3 The IDR value was 29.50%.
In summary, the abradable seal coating structure with low coefficient of friction and high bulk wear rate of the above embodiments of the present invention includes a Si bond layer, a rare earth pyrosilicate intermediate layer, and a YSZ-based composite surface layer sequentially deposited on the surface of the ceramic-based composite material. The coating designed by the invention has better abradable sealing performance, can obviously reduce the hardness and friction coefficient of the coating and improve the volume abrasion rate. The method is expected to solve the mechanical damage caused by mutual friction of parts such as the turbine of the aero-engine in the service process, can realize the aim of sealing the gas path of the parts such as the turbine of the aero-engine, improves the efficiency of the engine and reduces the oil consumption of the engine.
The embodiments of the present invention have been described above with reference to the accompanying drawings, but the present invention is not limited to the embodiments described above, and various changes, modifications, substitutions, combinations or simplifications made under the spirit and principles of the technical solution of the present invention can be made according to the purpose of the present invention, and all the changes, modifications, substitutions, combinations or simplifications should be equivalent to the substitution, so long as the purpose of the present invention is met, and all the changes are within the scope of the present invention without departing from the technical principles and the inventive concept of the present invention.
Claims (10)
1. An abradable seal coating having a low coefficient of friction and a high bulk wear rate, characterized by: y is set to 2 O 3 Stabilization of ZrO 2 The base composite coating is used as a surface coating, the surface coating and an Si bonding layer on the surface of the ceramic base composite material are combined together by utilizing a rare earth pyrosilicate interlayer to form an abradable seal coating composite material structure, and the abradable seal coating structure comprisesSi bonding layer, rare earth pyrosilicate intermediate layer and Y sequentially deposited on surface of ceramic matrix composite 2 O 3 Stabilization of ZrO 2 A base composite facing.
2. The abradable seal coating having a low coefficient of friction and a high bulk wear rate of claim 1, wherein: y is Y 2 O 3 Stabilization of ZrO 2 The main phase of the base composite surface layer is Y 2 O 3 Stabilization of ZrO 2 The device also comprises a lubricating phase and a pore-forming phase; the intermediate layer of rare earth pyrosilicate adopts Lu 2 Si 2 O 7 、Er 2 Si 2 O 7 、Y 2 Si 2 O 7 、Yb 2 Si 2 O 7 At least one of them.
3. The abradable seal coating having a low coefficient of friction and a high bulk wear rate of claim 2, wherein: the lubricating phase is graphite, bentonite, diatomite, hexagonal boron nitride (h-BN), calcium fluoride (CaF) 2 ) At least one of (a) and (b); the pore-forming phase is at least one of polyimide and polyphenyl ester (PHB).
4. The abradable seal coating having a low coefficient of friction and a high bulk wear rate of claim 1, wherein: the Y is 2 O 3 Stabilization of ZrO 2 The thickness of the base composite surface layer is 500-2000 mu m, the thickness of the rare earth pyrosilicate intermediate layer is 50-500 mu m, and the thickness of the Si bonding layer is 50-400 mu m.
5. The abradable seal coating having a low coefficient of friction and high bulk wear rate of claim 4, wherein: the Y is 2 O 3 Stabilization of ZrO 2 The thickness of the base composite surface layer is 500-1000 mu m, the thickness of the rare earth pyrosilicate intermediate layer is 150-300 mu m, and the thickness of the Si bonding layer is 50-100 mu m.
6. According to claimThe abradable seal coating of claim 1 having a low coefficient of friction and a high bulk wear rate, wherein: calculated according to the mass percentage of the components and by Y 2 O 3 Stabilization of ZrO 2 The total amount of components of the base composite coating is 100%, at Y 2 O 3 Stabilization of ZrO 2 In the base composite coating layer, Y 2 O 3 Stabilization of ZrO 2 The content of the lubricating phase is 60-94%, the content of the lubricating phase is 5-30%, and the content of the pore-forming phase is 1-10%.
7. The abradable seal coating having a low coefficient of friction and a high bulk wear rate of claim 1, wherein: the average friction coefficient is 0.103-0.373, the volume abrasion rate is 2.18 multiplied by 10 -2 ～5.47×10 -2 mm 3 The IDR value is 8.80-26.75%.
8. A method of preparing an abradable seal coating having a low coefficient of friction and a high bulk wear rate as recited in claim 1, wherein: firstly, spraying an Si bonding layer on the surface of a ceramic matrix composite material matrix by adopting a plasma spraying method; then, preparing a rare earth pyrosilicate intermediate layer on the surface of the Si bonding layer by adopting a plasma spraying method; then adopting a plasma spraying method to prepare Y on the rare earth pyrosilicate intermediate layer 2 O 3 Stabilization of ZrO 2 And forming an abradable seal coating composite material structure based on the composite surface layer.
9. The method of preparing an abradable seal coating having a low coefficient of friction and a high bulk wear rate of claim 8, wherein: when preparing the Si bonding layer, adopting Si powder with the grain diameter of 10-100 μm;
when the rare earth pyrosilicate intermediate layer is prepared, the particle size of the adopted rare earth pyrosilicate material powder is 10-120 mu m;
in the preparation of Y 2 O 3 Stabilization of ZrO 2 When the surface layer is compounded, Y 2 O 3 Stabilization of ZrO 2 The main phase of the base composite surface layer is Y 2 O 3 Stabilization of ZrO 2 And also includesA lubricating phase and a pore-forming phase; by Y 2 O 3 Stabilization of ZrO 2 The grain diameter of the powder is 10-120 mu m, the grain diameter of the powder adopting the lubricating phase is 10-120 mu m, and the grain diameter of the powder adopting the pore-forming phase is 10-120 mu m.
10. The method of preparing an abradable seal coating having a low coefficient of friction and a high bulk wear rate of claim 9, comprising the steps of:
(1)Y 2 O 3 stabilization of ZrO 2 Preparing powder for the base composite surface layer:
y is mechanically mixed 2 O 3 Stabilization of ZrO 2 Mixing the powder with lubricating phase and pore-forming phase powder to prepare Y 2 O 3 Stabilization of ZrO 2 Powder material used for the basic composite surface layer; y is Y 2 O 3 Stabilization of ZrO 2 The main phase of the base composite surface layer is Y 2 O 3 Stabilization of ZrO 2 The device also comprises a lubricating phase and a pore-forming phase;
wherein Y is 2 O 3 Stabilization of ZrO 2 The particle size of the powder is 10-120 mu m, the particle size of the lubricating phase powder is 10-120 mu m, and the particle size of the pore-forming phase powder is 10-120 mu m; y is Y 2 O 3 Stabilization of ZrO 2 The mass fraction of the lubricating phase is 60-94%, the mass fraction of the lubricating phase is 10-20%, and the mass fraction of the pore-forming phase is 4-8%; y is Y 2 O 3 Stabilization of ZrO 2 The total mass fraction of the components of the powder material used for the base composite surface layer is 100%;
(2) Pretreatment of a matrix:
pretreating the surface of a ceramic matrix composite material matrix, wherein the pretreatment is sand blasting coarsening, and the sand blasting pressure is 0.1-0.6 MPa;
(3) Preparation of the adhesive layer:
preparing an Si bonding layer on the surface of the ceramic matrix composite material, adopting a plasma spraying method, adopting Si powder as a raw material, and spraying the Si bonding layer with the thickness of 50-100 mu m;
the parameters of the plasma spraying process include:
current flow: 500-700A, argon flow: 40-50 slm, hydrogen flow: 5 to 20slm, spraying power: 30-55 kW, spraying distance: 100-200 mm, powder feeding rate: 10-35 r/min;
(4) Preparation of an intermediate layer:
preparing a rare earth pyrosilicate intermediate layer on the surface of the Si bonding layer, adopting a plasma spraying method, and adopting rare earth pyrosilicate material powder as a raw material, wherein the spraying thickness is 150-300 mu m;
the parameters of the plasma spraying process include:
current flow: 500-800A, argon flow: 30-55 slm, hydrogen flow: 5 to 20slm, spraying power: 30-60 kW, spraying distance: 100-200 mm, powder feeding rate: 10-30 r/min;
(5) Preparation of the surface layer:
applying plasma spraying to the Y prepared in the step (1) 2 O 3 Stabilization of ZrO 2 Spraying a powder material used for the base composite surface layer on the rare earth pyrosilicate intermediate layer prepared in the step (4), wherein the spraying thickness is 500-1000 mu m;
the parameters of the plasma spraying process include:
current flow: 500-800A, argon flow: 30-50 slm, hydrogen flow: 5 to 15slm, spraying power: 30-60 kW, spraying distance: 100-250 mm, powder feeding rate: 10-35 r/min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310360224.2A CN116535243A (en) | 2023-04-06 | 2023-04-06 | Abradable seal coating with low friction coefficient and high volumetric abrasion rate and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310360224.2A CN116535243A (en) | 2023-04-06 | 2023-04-06 | Abradable seal coating with low friction coefficient and high volumetric abrasion rate and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116535243A true CN116535243A (en) | 2023-08-04 |
Family
ID=87449662
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310360224.2A Pending CN116535243A (en) | 2023-04-06 | 2023-04-06 | Abradable seal coating with low friction coefficient and high volumetric abrasion rate and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116535243A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102787290A (en) * | 2012-06-19 | 2012-11-21 | 中国航空工业集团公司北京航空材料研究院 | Preparation method of high-temperature abradable sealing coating |
| CN106045575A (en) * | 2014-12-22 | 2016-10-26 | 通用电气公司 | Environmental barrier coating with abradable coating for ceramic matrix composites |
| CN109371353A (en) * | 2018-11-27 | 2019-02-22 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of ceramic base answers material turbine outer ring high temperature seal coating and its preparation process |
| CN115340410A (en) * | 2022-06-20 | 2022-11-15 | 武汉理工大学 | Ceramic-based sealing coating for surface of silicon carbide fiber-reinforced silicon carbide composite material and preparation method and application thereof |
-
2023
- 2023-04-06 CN CN202310360224.2A patent/CN116535243A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102787290A (en) * | 2012-06-19 | 2012-11-21 | 中国航空工业集团公司北京航空材料研究院 | Preparation method of high-temperature abradable sealing coating |
| CN106045575A (en) * | 2014-12-22 | 2016-10-26 | 通用电气公司 | Environmental barrier coating with abradable coating for ceramic matrix composites |
| CN109371353A (en) * | 2018-11-27 | 2019-02-22 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of ceramic base answers material turbine outer ring high temperature seal coating and its preparation process |
| CN115340410A (en) * | 2022-06-20 | 2022-11-15 | 武汉理工大学 | Ceramic-based sealing coating for surface of silicon carbide fiber-reinforced silicon carbide composite material and preparation method and application thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP4651966B2 (en) | Field methods and compositions for repairing thermal barrier coatings | |
| CN111004990B (en) | MAX phase coating for thermal barrier coating anti-melting CMAS corrosion and thermal spraying preparation method | |
| JP5124468B2 (en) | Strontium titanium oxide and machinable coating made therefrom | |
| US7736760B2 (en) | Ceramic abradable material with alumina dopant | |
| CN111519125B (en) | Surface treatment method for outer ring of aircraft engine turbine and outer ring of aircraft engine turbine | |
| CN113249676A (en) | Abradable seal coating structure with low friction coefficient and high wear rate and preparation method thereof | |
| CN108950454B (en) | High-temperature ceramic-based abradable seal coating structure and preparation method thereof | |
| CN112176275B (en) | Thermal barrier coating and preparation method and application thereof | |
| US20240026837A1 (en) | Composite coating, piston, engine and vehicle | |
| CN104561881A (en) | Preparation method of high-temperature abradable seal coating | |
| CN112279682A (en) | Silicon-based composite coating, preparation method and application thereof, and aircraft engine | |
| CN110527940B (en) | High-bonding-strength high-temperature-oxidation-resistant porous MCrAlY abradable coating and preparation method thereof | |
| CN114315421A (en) | Abradable sealing composite coating material and preparation method thereof | |
| CN112250476B (en) | YSZ-RETaO with high-temperature ceramic coating4SiC-based composite material and preparation method thereof | |
| CN116535243A (en) | Abradable seal coating with low friction coefficient and high volumetric abrasion rate and preparation method thereof | |
| JP2010151267A (en) | Seal structure and gas turbine using the same | |
| CN114763598B (en) | Long-life environmental barrier coating and preparation method thereof | |
| CN115198271A (en) | High-heat-matching-property thermal barrier coating and preparation method and application thereof | |
| CN108707897B (en) | Ceramic coating of exhaust pipe and preparation method thereof | |
| US8974588B2 (en) | Coating composition, a process of applying a coating, and a process of forming a coating composition | |
| CN112646407B (en) | Coating for compressor interstage sealing device | |
| CN115386823B (en) | Environmental barrier coating capable of resisting high-temperature vapor corrosion and CMAS corrosion and preparation method thereof | |
| CN115354322B (en) | Preparation method of high-pore thermal barrier coating | |
| Liu et al. | Preparation and Property of Thermal Spraying Aluminum Bronze Polyester Abradable Sealing Coating | |
| CN117512491A (en) | Preparation method of high-temperature-resistant thermal barrier nickel-chromium-aluminum-yttrium coating |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |