CN113976414A - Preparation method of silicate coating for aero-engine blade - Google Patents
Preparation method of silicate coating for aero-engine blade Download PDFInfo
- Publication number
- CN113976414A CN113976414A CN202111241829.7A CN202111241829A CN113976414A CN 113976414 A CN113976414 A CN 113976414A CN 202111241829 A CN202111241829 A CN 202111241829A CN 113976414 A CN113976414 A CN 113976414A
- Authority
- CN
- China
- Prior art keywords
- coating
- silicate
- blade
- silicate coating
- aircraft engine
- 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.)
- Granted
Links
Images
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 a silicate coating for an aircraft engine blade, wherein the density of the silicate coating is generally lower than 1.40g/cm when a silicate solution is prepared3The silicate solution is dip-coated by adopting a liquid level sedimentation method to prepare a silicate coating, the blade is dried after the silicate coating is coated once, and the blade is driedThen putting the blade into a furnace at a certain temperature, preserving heat for a period of time to remove bound water in the silicate coating, then taking the blade out of the furnace, naturally cooling, washing with water and polishing the surface layer of the silicate coating by using fine metallographic abrasive paper, then blowing the blade by using compressed air, then dip-coating the silicate solution again to prepare the silicate coating in an overlapping manner, repeating the steps until the silicate coating presents an obvious bright reflecting layer, and finally ensuring the thickness requirement of the silicate coating by using a weighing method.
Description
Technical Field
The invention relates to the technical field of coating processes of blades of aero-engines, in particular to a process preparation method of a silicate coating for the blades of the aero-engines.
Background
In order to make an aircraft engine blade used in sea have better salt spray corrosion resistance in the air above sea and improve the service life of the 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 preparation of the silicate coating is carried out by adopting a spraying and drying process, the silicate coating prepared by the method has poor compactness, and the coating can have a chalking phenomenon after being placed for a period of time, so that the salt mist corrosion resistance of the silicate coating is greatly reduced. The silicate coating is prepared by adopting a process method of dip coating and drying, but the prepared silicate coating has different adverse phenomena of layering, flowing, bubbling, pulverization and the like, and the salt mist corrosion resistance of the silicate coating is seriously influenced.
Disclosure of Invention
The invention aims to provide a process preparation method of a silicate coating for an aircraft engine blade, which can prepare a high-quality silicate coating with good compactness, high binding force, uniform coating thickness, high surface smoothness of the coating and no pulverization after being placed for a period of time, and ensures good salt spray corrosion resistance in the air of sea areas.
In order to realize the technical purpose, the invention adopts the following technical scheme:
a method for preparing a silicate coating for an aircraft engine blade comprises,
the method comprises the steps of dip-coating silicate solution on the surface of the blade of the aero-engine for multiple times by adopting a liquid level sedimentation method, drying, heat preservation and solidification, cooling, cleaning, polishing and drying after each time of dip-coating of the silicate solution, and then performing next dip-coating.
Further, before the first dip-coating of silicate solution is carried out on the surface of the blade of the aircraft engine, the surface of the blade of the aircraft engine is washed and polished, and then the surface of the blade is dried. The washing and polishing are carried out simultaneously while polishing, and the washing and polishing before the silicate coating is dip-coated at each time are also modes of polishing and washing simultaneously.
Furthermore, when the silicate solution is dip-coated by adopting a liquid level sedimentation method, the blade tip of the blade of the aircraft engine faces downwards.
Further, the silicate solution has a density of less than 1.40g/cm3Generally, the method is adjusted based on the premise that the silicate solution does not generate too much bubbles 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 thickness of the silicate coating is 2-6 μm.
Further, the cooling is natural cooling. The natural cooling refers to cooling under the regulation of normal temperature (about 20 ℃) and normal pressure (1 standard atmospheric pressure).
Further, the washing is washing, for preventing that aquatic mineral substance from bringing the influence to the silicate coating, can adopt the deionized water, it adopts metallographic abrasive paper to polish, the drying adopts compressed air to weather.
Further, the curing temperature of the heat preservation curing is 400 ℃, and the heat preservation time is 8-12 min.
Further, the falling rate of the silicate solution in the liquid level sedimentation method is 17-22 mm/min.
And further, judging whether the thickness of the silicate coating meets the design requirement or not by a weighing method.
The invention adopts a faster liquid level sedimentation method to dip-coat the silicate solution with thinner density, so that the thickness of the prepared single-layer silicate coating is uniform, and the silicate coating with certain thickness is finally satisfied by layer-by-layer superposition, and the integral uniformity of the coating is good; before each silicate coating is superposed and combined, the surface of each silicate coating is polished, the roughness of each silicate coating is increased to increase the bonding force between the coatings, and the overall bonding force of the coatings is good; each layer of silicate coating is subjected to heat preservation for a certain time at a certain temperature to remove bound water in the silicate coating, and the coating is not pulverized in the later-stage placing process and has better compactness; aiming at the requirement of the coating thickness of 2-6 mu m, multiple test results show that the surface layer of the coating is obviously reflective after the layers of thinner coatings are superposed to 8 layers, 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 MmSiO4.nH2The modulus m in O.
In the invention, the curing temperature and curing time of each dip coating play a key role, and the curing and heat-insulating parameters of the invention can thoroughly remove the bound water in the silicate coating, so that the coating does not layer; 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 weathering cannot occur after the silicate coating is placed for a period of time.
The method of the invention has the advantages that the silicate coating of the steel blade of the aircraft engine is prepared by batch production, the thickness of the produced silicate coating is uniform (the coating thickness requirement of 2-6 mu m can be basically achieved after 8 times of dip coating), the compactness is good, the bonding force is high, the smoothness is high (the roughness can reach 0.1 and is far lower than the roughness requirement of 0.8), the base metal of the blade body can be obviously seen through the bright silicate coating, and the high praise of sea-area users is obtained.
Drawings
FIG. 1 is a schematic view of a liquid level sedimentation device in the process for preparing a silicate coating on a blade body of a blade according to the invention;
FIG. 2 is a schematic diagram showing the evolution of the multiple film layer stacking process for preparing the silicate coating by the method of the present invention;
in the drawings, 1. a jig; 2. a blade; 3. a silicate solution; 4. a silicate tank; 5. a liquid level settlement switch.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made based on the common technical knowledge and conventional means in the art without departing from the technical idea of the present invention are included in the scope of the present invention.
The basic idea of the invention is that the invention suitably reduces the density of the silicate solution 3 compared to the conventional silicate coating preparation process (the density of the silicate solution 3 is typically higher than 1.40g/cm during the conventional silicate coating preparation process3While the invention selects less than 1.40g/cm3Taking the premise that the silicate solution 3 does not foam too much when circularly flowing into a silicate groove 4 in the recycling process and the solution does not flow on the blade body due to overhigh viscosity in the dip coating process, dip-coating the silicate solution 3 by adopting a liquid level sedimentation method to prepare a silicate coating, drying the blade 2 after coating the silicate coating once, putting the blade into a furnace at a certain temperature after drying, keeping the temperature for a period of time to remove bound water in the silicate coating, then washing and polishing the surface layer of the silicate coating by fine metallographic abrasive paper after the blade 2 is taken out of the furnace for natural cooling, then blowing dry the blade 2 by compressed air, dip-coating the silicate solution 3 again to prepare the silicate coating by superposition, repeating the steps until the silicate coating presents a relatively obvious bright layer, and finally ensuring the thickness requirement of the silicate coating by a weighing method (the coating thickness of the blades 2 with different surface areas corresponds to a certain weighing difference value, corresponding to a range of dip coating passes).
The method ensures that the thickness of the silicate coating prepared in one time is thinner by properly reducing the density of the silicate solution 3, can completely remove the bound water in the silicate coating under the conditions of drying and certain temperature preservation, and can not cause the coating to generate a layer; after the bound water in the silicate coating is removed, the generation mechanism of coating chalking is eliminated in advance, and the silicate coating can not be chalked due to weathering after being placed for a period of time; each layer of thinner silicate coating is washed and polished by fine metallographic abrasive paper before being superposed and combined, the binding force is greatly increased, and the foaming phenomenon can not be generated by the dense superposition of the layers of thinner silicate coatings, so that the compactness is good; the sedimentation speed of the silicate solution 3 is high in the coating preparation process, the silicate viscous liquid coated on each blade body section along the blade tip and blade span direction is uniform, and the coating prepared after drying is high in uniformity.
The invention provides a process for preparing a silicate coating for an aircraft engine blade, which is characterized in that the density (generally lower than 1.40 g/cm) of a silicate solution 3 is properly reduced when the silicate solution is prepared3The silicate solution 3 is dip-coated by a liquid level sedimentation method to prepare a silicate coating, the blade 2 is dried after the silicate coating is coated once, the blade 2 is put into a furnace at a certain temperature and is kept warm for a period of time to remove binding water in the silicate coating after being dried, then the blade 2 is taken out of the furnace for natural cooling, then the water washing and the fine metallographic abrasive paper are carried out to polish the surface layer of the silicate coating, then the silicate solution 3 is dip-coated again after the blade 2 is dried by compressed air to prepare the silicate coating by superposition, the steps are repeated until the silicate coating presents a more obvious bright reflecting layer, and finally the thickness requirement of the silicate coating (the coating thickness of the blades 2 with different surface areas corresponds to a certain weighing difference value by a weighing method, corresponding to a range of dip coating passes).
The following detailed description of the embodiments of the present invention with reference to fig. 1 and 2 is provided to enable those skilled in the art to more easily understand the advantages and features of the present invention, thereby clearly and clearly defining the protection scope of the present invention.
The working principle of the liquid level settlement device in the method for preparing the silicate coating by the blade body of the blade 2 is shown in figure 1, in the figure, a clamp 1 is used for clamping the blade 2 to be 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 a silicate solution 3, and a liquid level settlement switch 5 is arranged on the silicate tank 4.
Fig. 2 shows a multi-time film layer stacking evolution process, which is a state diagram of a silicate coating film layer obtained by curing and shrinking … … for the tenth time after curing and shrinking from top to bottom sequentially during just dip coating, after curing and shrinking for the second time, and after curing and shrinking for the third time.
The specific embodiment (the thickness of the silicate coating is required to be 2-6 μm) comprises the following steps:
firstly, preparing a solution. Preparing silicate solution 3 (sodium silicate or potassium silicate solution, density 1.10 g/cm) at certain density according to certain proportion3～1.20g/cm3) The density of the solution has a great influence on the film-forming compactness, while the modulus of the solution (MmSiO)4.nH2M in O is the modulus of the silicate solution 3, M is a metal element) has great influence on the density of the solution, and the two factors can be comprehensively considered;
and secondly, washing and polishing. The polishing has three functions: the washing of polishing before dip-coating for the first time is mainly that clearance blade 2 surface increases certain roughness in order to strengthen its cohesion, polishes with metallographical sand paper: 240# -600 #; secondly, removing attachments on the surface of the silicate coating to make the silicate coating smooth; thirdly, the wetting angle (wetting when the wetting angle is less than or equal to 90 degrees) of the silicate coating is reduced so as to improve the adhesion of the silicate coating which is dip-coated again;
and thirdly, drying. Blowing the surface of the blade 2 by using compressed air with the pressure of 0.1-0.6 Mpa, wherein the compressed air cannot contain water, oil stains and other pollutants;
and fourthly, dip-coating a silicate coating. Dip-coating adopts a liquid level settlement method, as shown in figure 1, a mounting plate of the blade 2 is clamped on a clamp 1 and hung upside down on a silicate tank 4 along with the clamp 1, silicate solution 3 is slowly added into the tank until the blade body to be coated is submerged, a liquid level settlement switch 5 is opened to enable the liquid level to gradually descend until the liquid level is completely separated from the blade 2, and the descending rate of the silicate solution 3 in the tank is (17-22) mm/min.
And fifthly, drying. After the silicate coating is coated for one time in a dip-coating mode, a sponge is used for absorbing residual silicate solution 3 of the blade tip to prevent the blade tip silicate coating from being too thick, then the blade 2 is hung on an electric furnace together with the clamp 1 to be dried, the blade 2 is unloaded from the clamp 1 after the drying is finished and is placed on an enamel plate, and the unloading process needs to be careful to prevent the solution in the groove of the clamp 1 from flowing to the blade body of the blade 2.
And sixthly, solidifying and cooling. The curing step is important, and is a key link of silicate film forming, namely, the blade 2 which is coated with a silicate coating and dried once is placed in a 400 ℃ box furnace for heat preservation (8-12) min, and after the curing is finished, the blade 2 is placed in the air for natural cooling (the blade can be washed by water only after at least ten minutes of air cooling and cannot be directly washed by water, because the silicate coating is directly changed into the normal temperature from the high temperature, the silicate coating is changed into an amorphous film, the amorphous film is hard and brittle, and the coating is cooled unevenly and shrinks unevenly due to sudden water cooling, so that the coating is easily cracked in the microcosmic part to cause the compactness of the coating to be poor, and the phenomenon on the macroscopic surface is pulverization).
Seventhly, repeating the operation from the step two of washing and grinding to the step six of solidifying and cooling for multiple times until the silicate coating meets the design thickness requirement (the thickness of the silicate coating is expressed by a certain weight value in production), and the thickness of the silicate coating with the thickness of 2-6 microns required in the embodiment can be met after the dip coating passes are more than or equal to 8 times. The finally obtained silicate coating stacking evolution process is shown in fig. 2 and evolves from top to bottom in sequence: the surface is flat immediately after the silicate coating, since the silicate contains water of complexation (MmSiO)4.nH2nH in O2And O), with the progress of the process of removing the bound water by curing the silicate, removing the volume of the water occupied in the coating to enable the surface of the coating to become uneven, and then dip-coating the silicate coating for multiple times, wherein the uneven surface of the silicate coating is overlapped layer by layer to finally become the silicate coating with good compactness and smooth and bright surface.
Claims (10)
1. A preparation method of a silicate coating for an aircraft engine blade is characterized by comprising the following steps: comprises the steps of (a) preparing a mixture of a plurality of raw materials,
the method comprises the steps of dip-coating silicate solution on the surface of the blade of the aero-engine for multiple times by adopting a liquid level sedimentation method, drying, heat preservation and solidification, cooling, cleaning, polishing and drying after each time of dip-coating of the silicate solution, and then performing next dip-coating.
2. The method for preparing a silicate coating for an aircraft engine blade according to claim 1, wherein: before the first silicate solution dip-coating is carried out on the surface of the blade of the aero-engine, the surface of the blade of the aero-engine is washed and polished, and then the surface of the blade is dried.
3. The method for preparing a silicate coating for an aircraft engine blade according to claim 1, wherein: when the silicate solution is dip-coated by adopting a liquid level sedimentation method, the blade tip of the blade of the aircraft engine faces downwards.
4. The method for preparing a silicate coating for an aircraft engine blade according to claim 1, wherein: the silicate solution has a density of less than 1.40g/cm3。
5. The method for preparing a silicate coating for an aircraft engine blade according to claim 1, wherein: the thickness of the silicate coating is 2-6 μm.
6. The method for preparing a silicate coating for an aircraft engine blade according to claim 1, wherein: the cooling is natural cooling.
7. The method for preparing a silicate coating for an aircraft engine blade according to claim 1, wherein: the cleaning is water washing, the polishing is performed by using metallographic abrasive paper, and the drying is performed by using compressed air for drying.
8. The method for preparing a silicate coating for an aircraft engine blade according to claim 1, wherein: the curing temperature of the heat preservation curing is 400 ℃, and the heat preservation time is 8-12 min.
9. The method for preparing a silicate coating for an aircraft engine blade according to claim 1, wherein: the falling rate of the silicate solution in the liquid level sedimentation method is 17-22 mm/min.
10. The method for preparing a silicate coating for an aircraft engine blade 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 true CN113976414A (en) | 2022-01-28 |
| CN113976414B 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 (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56152767A (en) * | 1980-04-30 | 1981-11-26 | Kawaguchiko Seimitsu Kk | Manufacture of dial or timepiece |
| 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 |
| US20100304158A1 (en) * | 2010-07-03 | 2010-12-02 | Shahid Bahonar University Of Kerman | Surface pre-treatment coating film and process for metallic substrates |
| 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 |
-
2021
- 2021-10-25 CN CN202111241829.7A patent/CN113976414B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56152767A (en) * | 1980-04-30 | 1981-11-26 | Kawaguchiko Seimitsu Kk | Manufacture of dial or timepiece |
| 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 |
| US20100304158A1 (en) * | 2010-07-03 | 2010-12-02 | Shahid Bahonar University Of Kerman | Surface pre-treatment coating film and process for metallic substrates |
| 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 |
|---|
| 王琪超;王帅星;杜楠;程法嵩;赵晴;李新义;: "HBN粒径对7075-T6铝合金PEO膜结构和性能的影响", 中国有色金属学报, no. 11, pages 15 - 26 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113976414B (en) | 2023-08-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP3304104B2 (en) | Gas turbine blade manufacturing method | |
| KR101362969B1 (en) | Protective coatings for metals | |
| CN104149361B (en) | A kind of carbon fibre composite screw preparation method of post forming | |
| RU2134313C1 (en) | Process of precipitation of coat on substrate ( versions ) | |
| CN111013987A (en) | Steel structure anticorrosion construction process | |
| CN109127333A (en) | A kind of coating process of ship | |
| CN113976414A (en) | Preparation method of silicate coating for aero-engine blade | |
| CN106975729B (en) | A kind of lost-wax casting method of drill bit | |
| CN105108054A (en) | Transition layer coating for manufacturing shell of precision casting and preparation method of transition layer coating | |
| CN105837027B (en) | A kind of surface is covered with the preparation process of the tempered glass of copper-based composite coating | |
| CN111558692A (en) | Composite investment casting shell making process | |
| CN111394685A (en) | Preparation method of spraying/chemical nickel plating long-acting corrosion-resistant composite coating | |
| CN111992469A (en) | Three-dimensional pattern coating, preparation method thereof, lamp fitting and lamp | |
| CN115138544B (en) | Pot treatment method and pot | |
| CN107130202A (en) | A kind of preparation method of the ceramic base composite coating of sea water resistance cavitation erosion | |
| US20110195272A1 (en) | Process for the protection of a metal substrate from corrosion and abrasion, and metal substrate obtained by this process | |
| KR100608509B1 (en) | Resin coating method of grater for chemical tank | |
| CN214462151U (en) | Anticorrosive terrace of vinyl | |
| CN101760714A (en) | Method for immersion-plating titanium alloy parts | |
| GB2084488A (en) | Biofouling of surfaces | |
| CN105108053A (en) | Primary layer coating for manufacturing shell of precision casting and preparation method of primary layer coating | |
| CN105667015A (en) | Stone pattern glass plate and production process thereof | |
| CN103192461A (en) | Manufacturing method for high-wear-resistant fretsaw | |
| CN111074274A (en) | Long-life gradient composite coating on surface of crystallizer copper plate and preparation method thereof | |
| CN112980290A (en) | Solvent type epoxy resin primer and preparation method and application 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 |