CN115815077A - Anti-seepage process for coating of aero-engine blade - Google Patents
Anti-seepage process for coating of aero-engine blade Download PDFInfo
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- CN115815077A CN115815077A CN202310067550.4A CN202310067550A CN115815077A CN 115815077 A CN115815077 A CN 115815077A CN 202310067550 A CN202310067550 A CN 202310067550A CN 115815077 A CN115815077 A CN 115815077A
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- 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
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- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention relates to an anti-seepage process for an aircraft engine blade coating, which comprises the steps of respectively preparing a bottom layer adhesive and a surface layer anti-seepage agent after the blade is pretreated, then respectively carrying out multiple brush coating and drying on the bottom layer adhesive and the surface layer anti-seepage agent on the position of the blade to be protected, and finally carrying out sand blowing treatment to finish the anti-seepage protection of the tenon tooth part of the aircraft engine blade. The preparation method is simple, the steps are easy to operate, the preparation efficiency of the surface anticorrosive coating of the aero-engine blade can be improved by adopting a mode of combining the bottom layer adhesive and the surface layer anti-seepage agent, the penetration of the blade tenon tooth part is effectively prevented, and the blade tenon tooth part is protected.
Description
Technical Field
The invention belongs to the technical field of coating preparation, and particularly relates to an anti-seepage process for an aircraft engine blade coating.
Background
The gas turbine and the gantry engine are taken as core power plant systems, and are one of the most important guarantees for developing the aerospace and ocean technologies, energy and power and other national important requirements. Because gas turbines and aircraft engines require extremely elaborate and complex manufacturing processes, their level of manufacture has been a benchmark that measures the overall industry level of a country. The blade is used as a key core part of an engine, the working environment of the blade is very harsh, and the blade needs to be simultaneously subjected to the synergistic action of working conditions such as oxidation, corrosion, titanium fire, fatigue, abrasion and the like, so that the service life of the blade is greatly influenced. Therefore, the surface of the blade needs to be coated with metal so as to prolong the service life of the blade. However, when the coating is prepared by an embedding method, the tenon and tooth parts of the blade cannot leak, and shielding protection measures are required. The existing method for protecting the tenon tooth part of the blade is to use heat-insulating aluminum silicate cotton as an inner layer, use nickel foil as an outer layer to wrap the whole tenon tooth part of the blade, tighten the tenon tooth part by adopting high-temperature alloy wires, and coat a glass lubricant at a gap. However, the seepage-proofing effect of the protection method is poor, so that the defective rate of the blade is increased, and the loss cost is high.
Disclosure of Invention
The invention provides an anti-seepage process for an aircraft engine blade coating, aiming at solving the problems that the existing method for protecting the tenon tooth part of a blade is poor in anti-seepage effect and easily causes defective products of the blade.
The invention adopts the following technical scheme: an anti-seepage process for an aircraft engine blade coating comprises the following steps:
(1) Pretreatment: inspecting the integrity of the surface of the blade of the aero-engine, and drying the blade to be coated after ultrasonic cleaning;
(2) Preparation of a bottom layer adhesive: respectively mixing 15-18 parts of liquid sodium silicate, 20-25 parts of corundum sand, 45-50 parts of titanium dioxide and 10-15 parts of water according to parts by weight to prepare a bottom layer binder;
(3) Preparing a surface layer anti-seepage agent: mixing 25-30 parts of liquid sodium silicate, 20-25 parts of corundum sand, 18-20 parts of titanium dioxide, 18-20 parts of nichrome powder and 5-10 parts of water according to parts by weight to prepare a surface layer anti-seepage agent;
(4) Film hanging of the anti-seepage agent: masking the cleaned edge plate and the quarter blade body height position on the upper surface of the edge plate by masking paper adhesive tape, uniformly coating a bottom layer adhesive on the blade tenon, wherein the coating thickness is 0.3-0.5mm until the bottom layer adhesive completely covers the blade tenon, placing the coated blade in a drying oven, setting the temperature of the drying oven at 120 ℃, drying for 30min,
taking out and cooling after drying, coating the bottom layer adhesive again, and drying again when the coating thickness is 0.2-0.3 mm;
(5) Coating the surface layer anti-seepage agent to the position of the blade tenon, wherein the coating thickness is 0.2-0.4mm until the surface layer anti-seepage agent completely covers the blade tenon, and placing the blade in an oven for drying; after cooling, brushing the secondary surface layer anti-seepage agent, wherein the brushing thickness is 0.2-0.3mm, and drying in the oven again;
(6) Blowing sand: taking out the dried blade, cooling, removing the masking tape, and blowing sand with corundum sand of 0.2Mpa.
Further, the ultrasonic cleaning in the step (1) is carried out at the temperature of 55-65 ℃ for 25-35min, and the drying temperature is 115-125 ℃ for 0.5-1.5h.
Further, when the interlayer adhesive in the step (2) is prepared, the components are uniformly mixed and stirred for 10-15min until a milky white solution with no or few particles is formed, 0.04% by mass of absolute ethyl alcohol is added into the milky white solution, the absolute ethyl alcohol is stirred to be fully and uniformly mixed, 0.04% by mass of deionized water is added into the milky white solution, the milky white solution is fully stirred for 10-15min, the prepared solution is placed into a vacuum box, the vacuum of the vacuum box is 0.1Pa, the time is 5min, air is slowly released, the adhesive is taken out and then stands for 30min, and the separated solution is poured out to obtain a jelly.
Further, in the step (3), the weighed components are mixed and stirred until a gray black solution without particles or with few particles is formed, the prepared solution is placed in a vacuum box, the vacuum degree is set to be 0.1pa, the time is 5min, and the surface layer anti-seepage agent is obtained by slowly deflating.
Further, in the step (6), corundum sand with 180 meshes is used in sand blowing, and the sand blowing pressure is 0.2MPa.
The advantages of the invention are as follows: the preparation method is simple, the steps are easy to operate, a mode of combining the bottom layer adhesive and the surface layer anti-seepage agent is adopted, methyl methacrylate added into the bottom layer adhesive can play a role in gluing and film forming, the preparation efficiency of the surface anti-corrosion coating of the aero-engine blade can be improved by matching with the surface layer anti-seepage agent, the addition of the nichrome powder can enable the surface layer anti-seepage agent to form an anti-seepage layer in a blade protection area, so that the penetration of the blade tenon tooth part can be effectively prevented, the blade tenon tooth part is protected, and the qualification rate of engine blade products is improved.
Drawings
FIG. 1 is a product drawing of an engine blade employing the barrier process of the present invention, a conventional protection process, and for barrier protection.
Fig. 2 is a metallographic effect diagram of the anti-seepage process in the second embodiment of the invention.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
The first embodiment is as follows:
an anti-seepage process for an aircraft engine blade coating comprises the following steps:
(1) Pretreatment: inspecting the integrity of the surface of the blade of the aero-engine, and drying the blade to be coated after ultrasonic cleaning, wherein the temperature during ultrasonic cleaning is 55 ℃, the ultrasonic cleaning time is 35min, the drying temperature is 115 ℃, and the drying time is 0.5h;
(2) Preparing a bottom layer binder, mixing 17.5% of liquid sodium silicate, 23.5% of corundum, 47% of titanium dioxide and 12% of water in percentage by mass, stirring for 15min until a milky white solution without or with few particles is formed, adding 0.04% of absolute ethyl alcohol into the milky white solution, stirring to fully mix the absolute ethyl alcohol, then adding 0.04% of deionized water into the solution, fully stirring for 10min, placing the prepared solution into a vacuum box, keeping the vacuum in the vacuum box at 0.1Pa for 5min, slowly discharging air, taking out the binder, standing for 30min, and pouring out the separated solution to obtain a jelly;
(3) Preparing a surface layer anti-seepage agent, taking 30% of liquid sodium silicate, 22% of corundum, 20% of titanium dioxide, 20% of nickel-chromium alloy powder and 8% of water according to parts by mass, mixing and stirring the weighed components until a gray black solution without particles or few particles is formed, placing the prepared solution in a vacuum box, controlling the vacuum degree to be 0.1pa and the time to be 5min, and slowly deflating to prepare the anti-seepage agent;
(4) Film hanging of the anti-seepage agent: masking the cleaned edge plate of the blade and the position of the quarter of the blade body height on the upper surface of the edge plate by using masking paper adhesive tapes, uniformly brushing a bottom layer adhesive on the blade tenon until the adhesive completely covers the blade tenon, wherein the brushing thickness is 0.3 mm;
putting the brushed workpiece into a drying box, setting the temperature of the drying box at 120 ℃, drying for 30min,
taking out, cooling, brushing the binder again, and drying again when the brushing thickness is 0.2 mm;
(5) Brushing the anti-seepage agent on the blade tenon again until the anti-seepage agent completely covers the blade tenon, wherein the brushing thickness is 0.2-0.4 mm; placing the leaves in an oven for drying;
taking out the dried blade, cooling, performing secondary anti-seepage agent brush coating with the thickness of 0.2-0.3mm, and drying in a drying oven;
(6) Blowing sand: taking out the dried blades, cooling, removing the masking tape, and blowing sand with 180-200 mesh corundum sand of 0.2Mpa.
Example two:
an anti-seepage process for an aircraft engine blade coating comprises the following steps:
(1) Pretreatment: inspecting the integrity of the surface of the blade of the aero-engine, and drying the blade to be coated after ultrasonic cleaning, wherein the ultrasonic cleaning temperature is 60 ℃, the ultrasonic cleaning time is 30min, the drying temperature is 120 ℃, and the drying time is 1h;
(2) Preparing a bottom layer binder, mixing 17.5% of liquid sodium silicate, 23.5% of corundum sand, 47% of titanium dioxide and 12% of water according to mass percentage, stirring for 15min until a milky white solution without or with few particulate matters is formed, adding 0.04% of absolute ethyl alcohol into the milky white solution, stirring to fully mix the absolute ethyl alcohol, then adding 0.04% of deionized water into the solution, fully stirring for 12min, placing the prepared solution in a vacuum box, keeping the vacuum in the vacuum box at 0.1Pa for 5min, slowly discharging air, taking out the binder, standing for 30min, pouring out the precipitated solution, and obtaining a jelly;
(3) Preparing a surface layer anti-seepage agent, taking 30% of liquid sodium silicate, 22% of corundum sand, 20% of titanium dioxide, 20% of nichrome powder and 8% of water according to parts by mass, mixing and stirring the weighed components until a gray black solution without particles or with few particles is formed, placing the prepared mixture in a vacuum box, keeping the vacuum degree at 0.1pa and the time at 5min, and slowly deflating to prepare the anti-seepage agent;
(4) Film hanging of the anti-seepage agent: masking the edge plate of the cleaned blade and the position of one fourth of the blade body height on the upper surface of the edge plate by using masking tape, uniformly coating the bottom layer adhesive on the blade tenon, wherein the coating thickness is 0.4mm until the adhesive completely covers the blade tenon;
putting the brushed workpiece into a drying box, setting the temperature of the drying box at 120 ℃, drying for 30min,
taking out, cooling, brushing the binder again, and drying again when the brushing thickness is 0.4 mm;
(5) Brushing the anti-seepage agent on the blade tenon again until the anti-seepage agent completely covers the blade tenon, and drying the blade in a drying oven;
taking out the dried blade, cooling, performing secondary anti-seepage agent brush coating with the thickness of 0.3mm, and drying in a drying oven;
(6) Blowing sand: taking out the dried blades, cooling, removing the masking tape, and blowing sand with 200-mesh corundum sand of 0.2Mpa.
Example three:
an anti-seepage process for an aircraft engine blade coating comprises the following steps:
(1) Pretreatment: inspecting the integrity of the surface of the blade of the aero-engine, and drying the blade to be coated after ultrasonic cleaning, wherein the temperature during ultrasonic cleaning is 65 ℃, the ultrasonic cleaning time is 25min, the drying temperature is 125 ℃, and the drying time is 0.5h;
(2) Preparing a bottom layer binder, mixing 17.5% of liquid sodium silicate, 23.5% of corundum, 47% of titanium dioxide and 12% of water in percentage by mass, stirring for 15min until a milky white solution without or with few particles is formed, adding 0.04% of absolute ethyl alcohol into the milky white solution, stirring to fully mix the absolute ethyl alcohol, then adding 0.04% of deionized water into the solution, fully stirring for 15min, placing the prepared solution into a vacuum box, keeping the vacuum in the vacuum box at 0.1Pa for 5min, slowly discharging air, taking out the binder, standing for 30min, and pouring out the separated solution to obtain a jelly;
(3) Preparing a surface layer anti-seepage agent, taking 30% of liquid sodium silicate, 22% of corundum, 20% of titanium dioxide, 20% of nickel-chromium alloy powder and 8% of water according to parts by mass, mixing and stirring the weighed components until a gray black solution without particles or few particles is formed, placing the prepared solution in a vacuum box, controlling the vacuum degree to be 0.1pa and the time to be 5min, and slowly deflating to prepare the anti-seepage agent;
(4) Film hanging of the anti-seepage agent: masking the cleaned edge plate of the blade and the position of the quarter of the blade body height on the upper surface of the edge plate by using masking paper adhesive tapes, uniformly brushing a bottom layer adhesive on the blade tenon until the adhesive completely covers the blade tenon, wherein the brushing thickness is 0.5 mm;
putting the brushed workpiece into a drying box, setting the temperature of the drying box at 120 ℃, drying for 30min,
taking out, cooling, brushing the binder again, and drying again when the brushing thickness is 0.3 mm;
(5) Brushing the anti-seepage agent on the blade tenon again until the anti-seepage agent completely covers the blade tenon, wherein the brushing thickness is 0.4 mm; placing the leaves in an oven for drying;
taking out the dried blade, cooling, performing secondary anti-seepage agent brush coating with the thickness of 0.3mm, and drying in a drying oven;
(6) Blowing sand: taking out the dried blades, cooling, removing the masking tape, and blowing sand with 180-200 mesh corundum sand of 0.2Mpa.
As shown in fig. 1, the number 1 indicates an engine blade treated by an anti-seepage process in embodiment 2 of the present invention, in fig. 1, the number 2 indicates an anti-seepage process performed by a conventional tape process, and the number 3 indicates an engine blade not treated by an anti-seepage process. As can be seen from fig. 1, the surface of the tenon tooth part of the engine blade of the number 1 is smooth and flat, no coating powder is adhered, the tenon tooth parts of the engine blades of the numbers 2 and 3 are adhered with coating powder in different degrees, and the cleanliness is poor, which indicates that the anti-seepage process effect is better by adopting the invention, and in addition, compared with the traditional tape protection process of the number 2, the tenon tooth protection area of the engine blade of the number 1 is more sealed, the possibility that the penetrant enters the tenon tooth protection area of the blade is reduced, and the application range of the protection area is wider.
As can be seen from FIG. 2, after the anti-seepage process of the second embodiment of the present invention is adopted for treatment, no seepage leakage occurs in the uncoated region, and the anti-seepage process of the present invention greatly improves the qualification rate of the product.
Claims (5)
1. An anti-seepage process for an aircraft engine blade coating is characterized in that: the method comprises the following steps:
(1) Pretreatment: checking whether the surface of the blade of the aero-engine is complete, and drying the blade to be coated after ultrasonic cleaning;
(2) Preparation of a bottom layer adhesive: respectively and uniformly mixing 15-18 parts of liquid sodium silicate, 20-25 parts of corundum sand, 5-10 parts of methyl methacrylate, 45-50 parts of titanium dioxide and 10-15 parts of water according to parts by weight to prepare a bottom layer binder;
(3) Preparing a surface layer anti-seepage agent: mixing 25-30 parts of liquid sodium silicate, 20-25 parts of corundum sand, 18-20 parts of titanium dioxide, 18-20 parts of nichrome powder and 5-10 parts of water according to parts by weight to prepare a surface layer anti-seepage agent;
(4) Film hanging of the anti-seepage agent: masking the edge plate of the cleaned blade and the quarter blade body height position on the upper surface of the edge plate by using masking paper adhesive tape, uniformly brushing the bottom layer adhesive on the blade tenon until the bottom layer adhesive completely covers the blade tenon, drying the brushed blade, brushing the bottom layer adhesive again, and drying again when the brushing thickness is 0.2-0.3 mm;
(5) Brushing the surface layer anti-seepage agent to the position of the blade tenon, wherein the brushing thickness is 0.2-0.4mm until the surface layer anti-seepage agent completely covers the blade tenon, and drying the blade; after cooling, brushing the secondary surface layer anti-seepage agent, wherein the brushing thickness is 0.2-0.3mm, and drying;
(6) Blowing sand: taking out the dried blade, cooling, removing the masking tape, and blowing sand with corundum sand of 0.2Mpa.
2. An anti-seepage process for coating an aircraft engine blade according to claim 1, characterised in that: the ultrasonic cleaning in the step (1) is carried out at the temperature of 55-65 ℃ for 25-35min, and the drying temperature is 115-125 ℃ for 0.5-1.5h.
3. An anti-seepage process for coating an aircraft engine blade according to claim 1, characterised in that: when the interlayer adhesive in the step (2) is prepared, the components are uniformly mixed and stirred for 10-15min until a milky white solution with no or few particles is formed, 0.04% of absolute ethyl alcohol is added into the milky white solution, the absolute ethyl alcohol is fully and uniformly mixed by stirring, 0.04% of deionized water is added into the milky white solution, the completely stirred solution is stirred for 10-15min, the prepared solution is placed in a vacuum box, the vacuum in the vacuum box is 0.1Pa, the time is 5min, air is slowly released, the adhesive is taken out and then stands for 30min, and the separated solution is poured out to obtain a jelly.
4. An anti-seepage process for coating an aircraft engine blade according to claim 1, characterised in that: and (3) mixing and stirring the weighed components until a gray black solution without particles or with few particles is formed, placing the prepared solution in a vacuum box, setting the vacuum degree to be 0.1pa and the time to be 5min, and slowly deflating to obtain the surface layer anti-seepage agent.
5. An anti-seepage process for coating an aircraft engine blade according to claim 1, characterised in that: and (3) using 180-mesh corundum sand in sand blowing in the step (6), wherein the sand blowing pressure is 0.2MPa.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310067550.4A CN115815077A (en) | 2023-02-06 | 2023-02-06 | Anti-seepage process for coating of aero-engine blade |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310067550.4A CN115815077A (en) | 2023-02-06 | 2023-02-06 | Anti-seepage process for coating of aero-engine blade |
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| CN115815077A true CN115815077A (en) | 2023-03-21 |
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| CN202310067550.4A Pending CN115815077A (en) | 2023-02-06 | 2023-02-06 | Anti-seepage process for coating of aero-engine blade |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114149703A (en) * | 2021-11-22 | 2022-03-08 | 武汉材料保护研究所有限公司 | Water-based anti-aluminizing coating and partial aluminizing modification method based on chemical vapor deposition |
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- 2023-02-06 CN CN202310067550.4A patent/CN115815077A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114149703A (en) * | 2021-11-22 | 2022-03-08 | 武汉材料保护研究所有限公司 | Water-based anti-aluminizing coating and partial aluminizing modification method based on chemical vapor deposition |
Non-Patent Citations (1)
| Title |
|---|
| 陈伯华等: ""CPS-1型复合防渗铝涂层的研制"", 腐蚀与防护, no. 02, pages 8 - 10 * |
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