CN113976414B - Preparation method of silicate coating for aero-engine blade - Google Patents
Preparation method of silicate coating for aero-engine blade Download PDFInfo
- Publication number
- CN113976414B CN113976414B CN202111241829.7A CN202111241829A CN113976414B CN 113976414 B CN113976414 B CN 113976414B CN 202111241829 A CN202111241829 A CN 202111241829A CN 113976414 B CN113976414 B CN 113976414B
- Authority
- CN
- China
- Prior art keywords
- silicate
- coating
- blade
- silicate coating
- solution
- 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.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
- B05D7/14—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials to metal, e.g. car bodies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D1/00—Processes for applying liquids or other fluent materials
- B05D1/18—Processes for applying liquids or other fluent materials performed by dipping
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D1/00—Processes for applying liquids or other fluent materials
- B05D1/36—Successively applying liquids or other fluent materials, e.g. without intermediate treatment
- B05D1/38—Successively applying liquids or other fluent materials, e.g. without intermediate treatment with intermediate treatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/007—After-treatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D5/00—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
- B05D5/06—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures to obtain multicolour or other optical effects
- B05D5/061—Special surface effect
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
- B05D7/50—Multilayers
- B05D7/56—Three layers or more
Landscapes
- Life Sciences & Earth Sciences (AREA)
- Engineering & Computer Science (AREA)
- Wood Science & Technology (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
The invention discloses a preparation method of silicate coating for aero-engine blade, which is characterized in that the density is generally lower than 1.40g/cm when silicate solution is prepared 3 The method is characterized in that when silicate solution circularly flows into a silicate tank for recycling, excessive bubbles are not generated, the solution does not flow on the blade body due to overhigh viscosity in the dip coating process, a liquid level sedimentation method is adopted to dip coat the silicate solution to prepare a silicate coating, the blade is dried after the silicate coating is coated for a single time, the blade is put into a furnace at a certain temperature and kept warm for a period of time to remove bound water in the silicate coating after the silicate coating is dried, then the blade is taken out of the furnace and naturally cooled, water washing and fine metallographic abrasive paper polishing are carried out on the surface layer of the silicate coating, then compressed air is used for drying the blade, the silicate solution is dip coated again to prepare the silicate coating in a superposition mode, the steps are repeated until the silicate coating presents a more obvious bright reflecting layer, and finally the thickness requirement of the silicate coating is ensured by a weighing method.
Description
Technical Field
The invention relates to the technical field of coating processes of aero-engine blades, in particular to a process preparation method of a silicate coating for an aero-engine blade.
Background
In order to make the aeroengine blade used in the sea have better salt spray corrosion resistance above the sea surface, thereby improving the service life of the aeroengine blade, a silicate coating with a certain thickness (generally 2-6 μm) is often required to be prepared on the surface of the blade. The traditional silicate coating is prepared by adopting a spray coating and drying process, the compactness of the silicate coating prepared by the method is poor, and the coating can be chalked after being placed for a period of time, so that the salt spray corrosion resistance of the silicate coating is greatly reduced. The silicate coating is prepared by adopting a dip-coating and drying process, but the prepared silicate coating has different adverse phenomena such as layering, flowing, foaming, pulverization and the like, and the salt spray corrosion resistance of the silicate coating is seriously affected.
Disclosure of Invention
The invention aims to provide a process preparation method of a silicate coating for an aeroengine blade, which can prepare a high-quality silicate coating which has good compactness, high binding force, uniform coating thickness and high surface smoothness of the coating, and can not be atomized after being placed for a period of time, so that good salt spray corrosion resistance of the silicate coating above sea areas is ensured.
In order to achieve the technical purpose, the invention adopts the following technical scheme:
a preparation method of silicate coating for aero-engine blade comprises,
the method comprises the steps of adopting a liquid level sedimentation method and dip-coating silicate solution on the surface of an aero-engine blade for a plurality of times, sequentially drying, preserving heat, solidifying, cooling, cleaning, polishing and drying after each dip-coating of the silicate solution, and then carrying out dip-coating for the next time, wherein when the silicate coating on the surface of the aero-engine blade presents an obvious bright reflecting layer and the thickness of the silicate coating meets the design requirement, the preparation of the silicate coating is completed.
Further, before the first silicate solution dip-coating is carried out on the surface of the aero-engine blade, the surface of the aero-engine blade is washed and polished, and then the surface of the blade is dried. The water washing and polishing are performed simultaneously while polishing, and the subsequent cleaning and polishing before dip-coating the silicate coating each time can also be performed by polishing while water washing.
Further, when the silicate solution is dip-coated by adopting a liquid level sedimentation method, the blade tip of the aero-engine blade faces downwards.
Further, the silicate solution has a density of less than 1.40g/cm 3 The silicate solution is generally regulated based on that the silicate solution does not bubble too much when circularly flowing into a silicate tank for recycling, and the solution does not flow on the blade body due to overhigh viscosity in the dip coating process.
Further, the silicate coating has a thickness of 2 μm to 6 μm.
Further, the cooling is natural cooling. Natural cooling refers to cooling under normal temperature (about 20 ℃) and normal pressure (1 standard atmosphere).
Further, the cleaning is water cleaning, deionized water can be adopted for preventing mineral substances in water from influencing the silicate coating, metallographic sand paper is adopted for polishing, and compressed air is adopted for drying.
Further, the curing temperature of the heat preservation and curing is 400 ℃, and the heat preservation time is 8-12 min.
Further, the reduction rate of the silicate solution in the liquid level sedimentation method is 17-22 mm/min.
Further, whether the thickness of the silicate coating meets the design requirement is judged by a weighing method.
According to the invention, a silicate solution with thinner density is dip-coated by adopting a quicker liquid level sedimentation method, so that the prepared single-layer silicate coating has uniform thickness, and the silicate coating with a certain thickness is finally met by layer-by-layer superposition, so that the overall uniformity of the coating is good; before each silicate coating layer is overlapped and combined, polishing treatment is carried out on the surface of each silicate coating layer, the combining force between the coating layers is increased by increasing the roughness of each silicate coating layer, and the overall combining force of the coating layers is good; each silicate coating layer is insulated for a certain time at a certain temperature to remove the bound water in the silicate coating layer, the pulverization phenomenon can not occur in the later-stage placing process of the coating layer, and the compactness is better; aiming at the thickness requirement of a coating with the thickness of 2-6 mu m, the test results show that after the layer-by-layer thinner coating is added to 8 layers, the surface layer of the coating presents obvious reflection and the smoothness is good.
In the invention, the problems of solution foaming, solution flowing in the blade body in the dip-coating process and the like are solved by properly reducing the density of the silicate solution, and the density of the silicate solution can be changed by changing MmSiO 4 .nH 2 The modulus m in O.
In the invention, the curing temperature and the curing time of each dip-coating play a key role, and the bonding water in the silicate coating can be thoroughly removed through the curing heat preservation parameters of the invention, so that the coating cannot be layered; and after the bound water in the silicate coating is removed, the generation mechanism of coating pulverization is eliminated in advance, and the pulverization phenomenon caused by the weathering can not occur when the silicate coating is placed for a period of time in the later stage.
The method of the invention has realized the batch production of silicate coating of steel blade of aeroengine, the thickness of silicate coating produced is even (coating thickness requirement of 2 μm-6 μm can be basically reached after 8 times of dip-coating), compactness is good, binding force is high, smoothness is high (roughness can reach 0.1, roughness requirement is far lower than 0.8), the base metal of blade body can be obviously seen through bright silicate coating, and high praise of sea users is obtained.
Drawings
FIG. 1 is a schematic view of a liquid level sedimentation device in a process for preparing silicate coating from a blade body according to the present invention;
FIG. 2 is a schematic diagram showing the evolution of a multi-layer film stack lamination process for preparing silicate coatings by the method of the present invention;
in the figure, 1. A clamp; 2. a blade; 3. silicate solution; 4. a silicate bath; 5. a liquid level sedimentation switch.
Detailed Description
The present invention will be further described with reference to the drawings and the specific embodiments, but it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made according to the ordinary skill and familiar means of the art to which this invention pertains are included within the scope of the present invention without departing from the above technical idea of the invention.
The basic idea of the invention is that the density of the silicate solution 3 is suitably reduced compared to the conventional silicate coating preparation method (the density of the silicate solution 3 is generally higher than 1.40g/cm in the conventional silicate coating preparation process) 3 While the present invention selects less than 1.40g/cm 3 The method is characterized in that when silicate solution 3 circularly flows into a silicate tank 4 for recycling, excessive bubbles are not generated, solution does not flow in a blade body due to overhigh viscosity in the dip coating process, a liquid level sedimentation method is adopted to dip coat the silicate solution 3 to prepare a silicate coating, after the silicate coating is coated in a single time, the blade 2 is dried, the blade 2 is put into a furnace at a certain temperature and kept for a period of time to remove bound water in the silicate coating, then the blade 2 is taken out of the furnace and naturally cooled, then water washing and fine metallographic abrasive polishing are carried out on the surface layer of the silicate coating, then compressed air is used for drying the blade 2, the silicate solution 3 is dip-coated again to prepare the silicate coating in a superposition manner, the steps are repeated until the silicate coating presents a more obvious bright reflecting layer, and finally the thickness requirement of the silicate coating is ensured by a weighing method (the thickness of the blade 2 with different surface areas corresponds to a certain weighing difference and also corresponds to a certain dip coating number range).
The method ensures that the thickness of the silicate coating prepared in a single pass is thinner by properly reducing the density of the silicate solution 3, and can thoroughly remove the bound water in the silicate coating without layering when the silicate coating is dried and kept at a certain temperature; after the bound water in the silicate coating is removed, the generation mechanism of coating pulverization is eliminated in advance, and the pulverization phenomenon caused by the weathering can not occur when the silicate coating is placed for a period of time in the later period; each layer of thinner silicate coating is washed and polished by fine metallographic sand paper before being overlapped and combined, the bonding force is greatly increased, and foaming phenomenon can not be generated through dense overlapping of the silicate coatings with thinner layers, so that the compactness is good; the settlement speed of the silicate solution 3 is higher in the coating preparation process, the silicate viscous liquid coated on the section of each blade body along the blade tip stretching direction is more uniform, and the uniformity of the coating prepared after drying is high.
The invention provides silicon for an aeroengine bladeProcess for preparing acid salt coating, the density of silicate solution 3 is suitably reduced (generally less than 1.40 g/cm) 3 The method is characterized in that when silicate solution 3 circularly flows into a silicate tank 4 for recycling, excessive bubbles are not generated, the solution is not regulated in the dip coating process because of too high viscosity and flows in the blade body, a liquid level sedimentation method is adopted to dip coat the silicate solution 3 to prepare a silicate coating, after the silicate coating is coated in a single time, the blade 2 is dried, the blade 2 is put into a furnace at a certain temperature and kept for a period of time to remove bound water in the silicate coating, then the blade 2 is taken out of the furnace and naturally cooled, then water washing and fine metallographic abrasive paper polishing are carried out on the surface layer of the silicate coating, then compressed air is used for drying the blade 2, the silicate solution 3 is dip coated again for preparing the silicate coating in a superposition mode, the steps are repeated until the silicate coating presents a more obvious bright reflecting layer, and finally the thickness requirement of the silicate coating is ensured by a weighing method (the thickness of the blade 2 with different surface areas corresponds to a certain weighing difference and also corresponds to a certain dip coating range).
Specific embodiments of the invention will be described in detail below with reference to fig. 1 and 2 so that advantages and features of the invention will be more readily understood by those skilled in the art, thereby making a clearer and more definite definition of the scope of the invention.
In fig. 1, the working principle of a liquid level sedimentation device in a method for preparing silicate coating by a blade body of a blade 2 is shown, in the figure, a clamp 1 is used for clamping the blade 2 and is placed at the upper end of a silicate tank 4, the blade tip of the blade 2 faces downwards, the whole blade 2 is immersed in silicate solution 3, and a liquid level sedimentation switch 5 is arranged on the silicate tank 4.
In fig. 2, the evolution process of multi-layer film lamination is shown, and the silicate film layer is shown after the second curing shrinkage, the third curing shrinkage and the tenth curing shrinkage after … …, which are just dip-coated from top to bottom.
Specific examples (silicate coating thickness requirement: 2 μm to 6 μm) were performed as follows:
1. a solution is prepared. Preparing silicate solution 3 (sodium silicate or potassium silicate solution) with certain density according to a certain proportionDegree of freedom 1.10g/cm 3 ～1.20g/cm 3 ) The density of the solution has a great influence on the film forming compactness, while the modulus (MmSiO 4 .nH 2 M in O is the modulus of silicate solution 3, M is metal element) has great influence on the density of the solution, and two factors can be comprehensively considered;
2. and (5) washing and polishing. Polishing has three functions: the polishing water washing before the first dip coating mainly cleans the surface of the blade 2 and increases certain roughness to strengthen the binding force of the blade 2, and the metallographic sand paper for polishing is used for: 240# to 600#; secondly, removing attachments on the surface of the silicate coating to make the silicate coating flat and smooth; thirdly, reducing the wetting angle (wetting angle is less than or equal to 90 degrees) when the silicate coating is dip-coated again to improve the adhesion of the silicate coating;
3. and (5) blow-drying. Drying the surface of the blade 2 by compressed air with the pressure of 0.1-0.6 Mpa, wherein the compressed air cannot contain pollutants such as water, greasy dirt and the like;
4. a silicate coating is dip coated. The dip-coating adopts a liquid level sedimentation method, as shown in fig. 1, a blade 2 mounting plate is clamped on a clamp 1, a silicate solution 3 is slowly added into a silicate tank 4 along with the clamp 1 to gradually reach the condition that the effective blade body of a coating is not needed, a liquid level sedimentation switch 5 is opened to gradually lower the liquid level until the liquid level is completely separated from the blade 2, and the dropping rate of the silicate solution 3 in the tank is (17-22) mm/min.
5. And (5) drying. After the primary silicate coating is coated, absorbing residual silicate solution 3 of the blade tip by using sponge to prevent the blade tip silicate coating from being too thick, then hanging the blade 2 on an electric furnace in a reverse mode together with the clamp 1 for drying, unloading the blade 2 from the clamp 1 after drying, and placing the blade on a enamel plate, wherein the unloading process needs to be careful to prevent the solution in a groove of the clamp 1 from flowing to the blade body of the blade 2.
6. Solidifying and cooling. The curing step is important, and is a key link of silicate film forming, namely, the blade 2 after the silicate coating is dipped and dried once is placed in a box furnace at 400 ℃ for heat preservation (8-12) min, after the curing is finished, the blade 2 is placed in air for natural cooling (at least air cooling for more than ten minutes before water washing, but not direct water washing, because the silicate coating is directly changed into normal temperature from high temperature, the silicate coating becomes an amorphous film, the amorphous film is hard and brittle, and the coating is cooled unevenly and shrunk unevenly due to sudden water cooling, so that the coating is extremely easy to generate brittle fracture in the microcosmic interior to cause the coating compactness to be poor, and the phenomenon on the macroscopic surface of the silicate film is chalking).
7. The process from the second step of 'washing and polishing' to the sixth step of 'solidifying and cooling' is repeated for a plurality of times until the silicate coating meets the design thickness requirement (the thickness of the silicate coating is expressed by a certain weight gain value in production), and the thickness of the silicate coating of 2-6 mu m required in the embodiment can be met after the dip coating times are more than or equal to 8 times. The superposition evolution process of the finally obtained silicate coating is shown in fig. 2, and the superposition evolution process sequentially evolves from top to bottom: the surface was flat just after the silicate coating, and the silicate contained water of complexation (MmSiO 4 .nH 2 nH in O 2 O) along with the progress of the process of removing the bound water by silicate solidification, the volume of water occupied by the coating is removed to enable the surface of the coating to become uneven, then the uneven surface of the coating is subjected to repeated dip-coating of the silicate coating, and finally the silicate coating with good compactness and smooth and shiny surface is formed through layer-by-layer superposition.
Claims (8)
1. A preparation method of silicate coating for aero-engine blade is characterized in that: comprising the steps of (a) a step of,
the method comprises the steps of dip-coating silicate solution on the surface of an aeroengine blade by adopting a liquid level sedimentation method for a plurality of times, sequentially drying, preserving heat, solidifying, cooling, cleaning, polishing and drying after each dip-coating of the silicate solution, and then dip-coating for the next time, wherein when the silicate coating on the surface of the aeroengine blade presents an obvious bright reflecting layer and the thickness of the silicate coating meets the design requirement, the preparation of the silicate coating is completed;
the silicate solution has a density of less than 1.40g/cm 3 The silicate solution is regulated based on the condition that the solution does not flow in the blade body due to too high viscosity when the silicate solution circularly flows into the silicate tank for repeated use;
the curing temperature of the heat preservation curing is 400 ℃, and the heat preservation time is 8-12 min.
2. A method of preparing a silicate coating for aircraft engine blades according to claim 1, wherein: before the first silicate solution dip-coating is carried out on the surface of the aero-engine blade, the surface of the aero-engine blade is washed and polished, and then the surface of the blade is dried.
3. A method of preparing a silicate coating for aircraft engine blades according to claim 1, wherein: when the silicate solution is dip-coated by adopting a liquid level sedimentation method, the blade tip of the aero-engine blade faces downwards.
4. A method of preparing a silicate coating for aircraft engine blades according to claim 1, wherein: the thickness of the silicate coating is 2-6 mu m.
5. A method of preparing a silicate coating for aircraft engine blades according to claim 1, wherein: the cooling is natural cooling.
6. A method of preparing a silicate coating for aircraft engine blades according to claim 1, wherein: the cleaning is water washing, the polishing adopts metallographic sand paper for polishing, and the drying adopts compressed air for drying.
7. A method of preparing a silicate coating for aircraft engine blades according to claim 1, wherein: the dropping rate of silicate solution in the liquid level sedimentation method is 17-22 mm/min.
8. A method of preparing a silicate coating for aircraft engine blades according to claim 1, wherein: and judging whether the thickness of the silicate coating meets the design requirement or not by a weighing method.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111241829.7A CN113976414B (en) | 2021-10-25 | 2021-10-25 | Preparation method of silicate coating for aero-engine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111241829.7A CN113976414B (en) | 2021-10-25 | 2021-10-25 | Preparation method of silicate coating for aero-engine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113976414A CN113976414A (en) | 2022-01-28 |
| CN113976414B true CN113976414B (en) | 2023-08-04 |
Family
ID=79741034
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111241829.7A Active CN113976414B (en) | 2021-10-25 | 2021-10-25 | Preparation method of silicate coating for aero-engine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113976414B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1242805A (en) * | 1997-01-09 | 2000-01-26 | 辛辛那提大学 | Method of preventing corrosion of metals using silanes |
| CN101029395A (en) * | 2006-03-01 | 2007-09-05 | 联合工艺公司 | Dense protective coatings, methods for their preparation and coated articles |
| CN102036814A (en) * | 2008-03-18 | 2011-04-27 | 金属涂层技术有限责任公司 | Protective coatings for metals |
| CN105907294A (en) * | 2016-04-14 | 2016-08-31 | 顺德职业技术学院 | Preparation method of water-borne inorganic paint and method for preparation of inorganic coating from water-borne inorganic paint |
| JP2017155323A (en) * | 2016-03-01 | 2017-09-07 | 株式会社アート１ | Processing method of surface of magnesium metal material |
| DE102020000848A1 (en) * | 2020-02-05 | 2021-08-05 | OT Oberflächentechnik GmbH & Co. KG | Process for coating the blades of compressors, turbines and propellers |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56152767A (en) * | 1980-04-30 | 1981-11-26 | Kawaguchiko Seimitsu Kk | Manufacture of dial or timepiece |
| US8273411B2 (en) * | 2010-07-03 | 2012-09-25 | Sayed Morteza Madani | Surface pre-treatment coating film and process for metallic substrates |
-
2021
- 2021-10-25 CN CN202111241829.7A patent/CN113976414B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1242805A (en) * | 1997-01-09 | 2000-01-26 | 辛辛那提大学 | Method of preventing corrosion of metals using silanes |
| CN101029395A (en) * | 2006-03-01 | 2007-09-05 | 联合工艺公司 | Dense protective coatings, methods for their preparation and coated articles |
| CN102036814A (en) * | 2008-03-18 | 2011-04-27 | 金属涂层技术有限责任公司 | Protective coatings for metals |
| JP2017155323A (en) * | 2016-03-01 | 2017-09-07 | 株式会社アート１ | Processing method of surface of magnesium metal material |
| CN105907294A (en) * | 2016-04-14 | 2016-08-31 | 顺德职业技术学院 | Preparation method of water-borne inorganic paint and method for preparation of inorganic coating from water-borne inorganic paint |
| DE102020000848A1 (en) * | 2020-02-05 | 2021-08-05 | OT Oberflächentechnik GmbH & Co. KG | Process for coating the blades of compressors, turbines and propellers |
Non-Patent Citations (1)
| Title |
|---|
| HBN粒径对7075-T6铝合金PEO膜结构和性能的影响;王琪超;王帅星;杜楠;程法嵩;赵晴;李新义;;中国有色金属学报(第11期);15-26 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113976414A (en) | 2022-01-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR101362969B1 (en) | Protective coatings for metals | |
| CN101498021B (en) | Surface treating method for tap | |
| CN104032342B (en) | A kind of method improving Sintered NdFeB magnet and electrodeposited coating adhesion | |
| US20100187119A1 (en) | Cold spray and anodization repair process for restoring worn aluminum parts | |
| EP2971261A1 (en) | Electrodeposited compositions and nanolaminated alloys for articles prepared by additive manufacturing processes | |
| CN103882492B (en) | Metallic matrix chemical plating pre-treating method | |
| CN115403993B (en) | Water-based paint composition | |
| CN102389871B (en) | Method for forming aluminum coating on surface of neodymium iron boron magnet | |
| CN113976414B (en) | Preparation method of silicate coating for aero-engine blade | |
| CN102489798A (en) | Manufacturing process for insulating side walls of electrodes on line | |
| CN106975729B (en) | A kind of lost-wax casting method of drill bit | |
| CN109207985A (en) | A kind of preparation method of Mg alloy surface high-entropy alloy film layer | |
| CN1320991C (en) | Manufacturing method of composite material mold for resin transfer molding process | |
| CN113477941A (en) | Electro-deposition process for self-lubricating coating of additive manufactured aluminum alloy part | |
| CN111394685A (en) | Preparation method of spraying/chemical nickel plating long-acting corrosion-resistant composite coating | |
| CN115138544B (en) | Pot treatment method and pot | |
| JPH09205013A (en) | Bond magnet having rust-resistant coat layer and its rust-resistant coating method | |
| KR20090075362A (en) | Method for metal material coating and parts coated by same method | |
| JP5082113B2 (en) | Carrier for holding object to be polished and method for manufacturing the same | |
| US20110195272A1 (en) | Process for the protection of a metal substrate from corrosion and abrasion, and metal substrate obtained by this process | |
| CN112359393B (en) | Wear-resistant anti-seismic coating and preparation method thereof | |
| CN106984772B (en) | A kind of casting method of high-precision drill bit | |
| CN109294413A (en) | A kind of door and window aluminium section bar surface powder electrostatic coating method | |
| CN112538309B (en) | Wear-resistant anti-seismic coating and preparation method thereof | |
| CN111074274A (en) | Long-life gradient composite coating on surface of crystallizer copper plate and preparation method thereof |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |