CN109234674A - A kind of turbo blade MCrAlY coating physics restorative procedure - Google Patents
A kind of turbo blade MCrAlY coating physics restorative procedure Download PDFInfo
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- CN109234674A CN109234674A CN201811355709.8A CN201811355709A CN109234674A CN 109234674 A CN109234674 A CN 109234674A CN 201811355709 A CN201811355709 A CN 201811355709A CN 109234674 A CN109234674 A CN 109234674A
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
- C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/02—Pretreatment of the material to be coated
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/02—Pretreatment of the material to be coated
- C23C14/021—Cleaning or etching treatments
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/02—Pretreatment of the material to be coated
- C23C14/021—Cleaning or etching treatments
- C23C14/022—Cleaning or etching treatments by means of bombardment with energetic particles or radiation
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/24—Vacuum evaporation
- C23C14/32—Vacuum evaporation by explosion; by evaporation and subsequent ionisation of the vapours, e.g. ion-plating
- C23C14/325—Electric arc evaporation
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/58—After-treatment
- C23C14/5806—Thermal treatment
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- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
The invention discloses a kind of restorative procedures of turbo blade MCrAlY coating; when occurring equipment fault in coating procedure, blade is discussed into whirlpool and is all taken out, checks that whether there is or not oxidative phenomenas for coating surface; to the turbo blade of non-oxidation, blade is wrapped up into protection to prevent exotic pollution after taking-up.After equipment repair is good, the direct shove charge of blade to package protection, after vacuumizing and reaching code requirement value; carry out aura, bombardment cleaning 5~10 minutes; coat coating is re-started, applies the time are as follows: technological procedure has applied time, then plus 30~40 minutes before wanting seeking time to subtract equipment fault.The blade for having generated oxidation clears up coating surface using wet blast method, coating treatment is re-started by technological procedure after cleaning, but coating time period should be adjusted, adjustment are as follows: technological procedure has applied time, then plus 60~80 points before wanting seeking time to subtract equipment fault.The method of the present invention improves coating production process efficiency energetically, and the waste product for avoiding blade occurs.
Description
Technical field
The invention belongs to engine turbine blade physical vapour deposition (PVD) preparation technical fields, and in particular to a kind of turbo blade
MCrAlY coating physics restorative procedure.
Background technique
In order to improve the anti-oxidant and corrosion resistance of turbo blade, turbine blade surface is applied anti-oxidant and corrosion-resistant
The MCrAlY coating of property, but in coating procedure, it sometimes appear that the reasons such as equipment fault, cause blade coatings thickness to be not achieved
Design requirement.Turbo blade with this catastrophic failure of pre-treatment is all to remove coat coating, then press original process again
It is applied.Because turbo blade type face is curved surface, it sometimes appear that blade profile local reduction, finally makes in removal process
It is scrapped at turbo blade；In addition, removal coating process is complicated, blade coatings manufacturing cost is caused to increase.
It is found during patent retrieval, a kind of high-pressure turbine working blade antioxidant anticorrosive coating repairing method, patent
Number CN 102817000B, inventor: Cheng Yuxian.It is described that blade is handled using wet blast processing method, it then will removal
Former cated blade carries out ultrasonic cleaning and acetone embathes, then is dried and visual examination, weighing；Then vacuum is used
Electric arc electroplating method carries out AlSiY coating coating to the blade after pre-treatment, carries out vacuum heat treatment to the blade after coating, finally
After carrying out the wet blast processing of coating to the blade after vacuum heat treatment, final products are obtained, there are following two points disadvantages for this method:
One, blast, which remove in original coating procedure, easily causes blade profile overproof, eventually leads to blade rejection；Secondly, at wet blast
Visual examination and weighing are only carried out after reason, can not determine blade whether dimension overproof.
Summary of the invention
The purpose of the present invention is to provide a kind of turbo blade MCrAlY coating physics restorative procedures, to solve the prior art
The problem of, the method for the present invention improves coating production process efficiency energetically, and the waste product for avoiding blade occurs, and the present invention can also
It is repaired for the coating after blade use.
In order to achieve the above objectives, the present invention adopts the following technical scheme:
A kind of turbo blade MCrAlY coating physics restorative procedure, comprising the following steps:
When occurring equipment fault in coating procedure, turbo blade is taken out from the device for step 1, checks coating surface
Whether there is or not oxidative phenomenas, when non-oxidation phenomenon, by turbo blade package protection to prevent exotic from polluting, subsequently into step 4；
When there is oxidative phenomena, 2 are entered step；
Step 2 protects turbo blade tenon, and it is clear to carry out blast to turbine blade coating surface using wet blast method
Reason, then dries up the turbo blade after wet blast with pure argon；
Step 3: the turbo blade after step 2 drying being subjected to ultrasonic cleaning, then by the turbine after ultrasonic cleaning
Blade is dried up with pure argon；
Step 4: after equipment repair is good, by turbo blade shove charge, adjusting vacuum degree and temperature to setting value；
Step 5: using aura, bombardment cleaning turbine blade surface；
Step 6: carrying out benefit coating treatment, when turbo blade non-oxidation phenomenon in step 1, mend the coating treatment time are as follows:
Technological procedure has been coated with time, then plus 30~40min before wanting seeking time to subtract equipment fault；When turbo blade is aerobic in step 1
When changing phenomenon, mend the coating treatment time are as follows: technological procedure has been coated with the time before wanting seeking time to subtract equipment fault, then plus 60~
80min；
Step 7: diffusion in vacuum processing is carried out to coating.
Further, in step 2 wet blast method 1.5~2Mpa of blast wind pressure.
Further, the blast time 10~20 seconds of wet blast method in step 2.
Further, ultrasonic cleaning is carried out as cleaning agent using acetone in step 3.
Further, the ultrasonic cleaning time is 20~25min in step 3.
Further, it is evacuated in step 4 higher than 5 × 10-2Heating room temperature is set as 100~140 DEG C, protected by Pa
1~1.5h of temperature；Then will heating room temperature be transferred to 280~350 DEG C, to heating room applying argon gas, make pressure up to (1.0~1.1) ×
10-1Pa。
Further, aura, bombardment clearance time are 5~10min in step 5.
Further, step 7 floating coat diffusion in vacuum is handled specifically: it is built-in that turbo blade tenon is inserted into tooling downward
Furnace temperature is risen to 800 DEG C by furnace, and heat preservation to Turbine Blade Temperature Field stops up to 800 DEG C, and in 800 DEG C of partial pressures to 5~20Pa；By furnace temperature
900~930 DEG C are risen to, heat preservation to Turbine Blade Temperature Field stops up to 890~940 DEG C, in 890~940 DEG C of 3~4h of heat preservation, by turbine
Blade with furnace vacuum cooled to 500 DEG C hereinafter, applying argon gas opens fan to 0.5~1.0bar again, by blade be as cold as 80 DEG C with
Under, blade is come out of the stove air-cooled to room temperature.
Further, heating rate when furnace temperature being risen to 800 DEG C is 6~8 DEG C/min.
Further, heating rate when furnace temperature being risen to 900~930 DEG C is 5~6 DEG C/min.
Compared with prior art, the invention has the following beneficial technical effects:
The method of the present invention improves coating production process efficiency energetically, and the waste product for avoiding blade occurs, the present invention
Coating after can be used for blade use is repaired.This method avoid because of turbine blade coating reworked processing process caused by catastrophic failure
In go removing coating to cause blade profile overproof and scrap, this method passes through tight to the grasp of coat coating thickness and blast technique
The control of lattice is repaired with reaching the efficient coating of no waste product.
Detailed description of the invention
Fig. 1 is primary coating section metallograph；
Fig. 2 is to repair section metallograph by primary coating.
Specific embodiment
Present invention is further described in detail below:
A kind of restorative procedure of turbo blade MCrAlY coating, detailed process is: occurring equipment fault in coating procedure
When, blade is discussed into whirlpool and is all taken out, checks that whether there is or not oxidative phenomenas for coating surface, to the turbo blade of non-oxidation, with dry after taking-up
Blade is wrapped up protection to prevent exotic pollution by net blank sheet of paper.After equipment repair is good, to package protection the direct shove charge of blade,
After vacuumizing and reaching code requirement value, aura, bombardment cleaning 5~10 minutes is carried out, coat coating is re-started, applies the time
Are as follows: technological procedure has applied time, then plus 30~40 minutes before wanting seeking time to subtract equipment fault.To the blade for having generated oxidation
(general oxidation is superficial layer oxidation tint), using wet blast method, clears up coating surface, technological procedure is pressed after cleaning
Re-start coating treatment, but coating time period should be adjusted, adjust are as follows: technological procedure want seeking time to subtract equipment fault before
Apply time, then plus 60~80min.Metallograph is repaired by primary coating as shown in Fig. 2, it can be seen from the figure that former apply
It is tightly combined between layer and coating layer.In order to check the combination situation of coating and matrix, using relevant criterion, the test piece of coating exists
On the pole of Φ 3mm bending be not less than 90 °, coating bending after, perpendicular to coating extend machine direction on have no coating cracking,
Aliquation complies fully with standard requirements.Pull test detects coating binding force, and data are as shown in table 1, and 1-1~1-3 is primary in table
Coating, 2-1~2-3 are to repair by primary coating, and as can be seen from the table, primary coating is repaired by primary coating
Entirely at glue surface, coating binding force is met the requirements of the standard fracture position.Using for blade overweight after coating, removing coating is removed
After allow with the presence of residual coating (5% area), then using technological procedure requirement technique re-start coating treatment, submission is tested
It receives.
Pulling force data between 1 coating of table and matrix
Operating process of the embodiment of the present invention is described in detail below:
Embodiment 1
Step 1 takes out turbo blade from the device, and blade is wrapped up protection to prevent exotic dirt with clean blank sheet of paper
Dye；
Step 2, wet blast: blade tenon is protected, and wet blast method is taken to carry out blast to turbine blade coating surface
Cleaning, blast wind pressure 1.5Mpa the time 20 seconds, remove oxidation tint, leaf appearance inspection, drying and circular flow after wet blast
In, do not allow directly to contact blade blade and supramarginal plate.Blade, waste leaf piece and test piece after wet blast is dried up with pure argon
(only to the blade for having oxidation).
Step 3, ultrasonic cleaning: acetone carries out ultrasonic cleaning, scavenging period as cleaning agent, by the blade after drying
It is 25 points.Blade pure argon after ultrasonic cleaning is dried up into (only to the blade for having oxidation).
Step 4, depositing coating: blade shove charge is vacuumized higher than 5 × 10-2Heating room temperature is set as 100 DEG C by Pa,
Keep the temperature 1.5h；Heating room temperature is transferred to 350 DEG C；To heating room applying argon gas, make pressure up to 1.1 × 10-1Pa；
Step 5, aura, bombardment cleaning blade surface；
Step 6 calculates and mends coating time period, starts to carry out benefit coating treatment.
Step 7, Coatings in Vacuum DIFFUSION TREATMENT wear clean white glove for blade tenon and are downwardly into shove charge in tooling, blade
Blade and edge version coating surface do not allow to contact with other, furnace temperature are risen to 800 DEG C with 6 DEG C/minute, heat preservation to Part temperature reaches
800 DEG C only, and in 800 DEG C of partial pressures to 5Pa；Furnace temperature is risen to 900 DEG C with 5 DEG C/min, heat preservation to Part temperature is up to 900 ± 10
DEG C only, in 900 ± 10 DEG C of heat preservation 3h, by blade with furnace vacuum cooled to 500 DEG C or less；Applying argon gas opens wind to 0.5bar again
Fan, is as cold as 80 DEG C or less for blade；Blade is come out of the stove air-cooled to room temperature.
Embodiment 2
Step 1 takes out turbo blade from the device, and blade is wrapped up protection to prevent exotic dirt with clean blank sheet of paper
Dye；
Step 2, wet blast: blade tenon is protected, and wet blast method is taken to carry out blast to turbine blade coating surface
Cleaning, blast wind pressure 2Mpa the time 10 seconds, remove oxidation tint, leaf appearance inspection, drying and circular flow after wet blast
In, do not allow directly to contact blade blade and supramarginal plate.Blade, waste leaf piece and test piece after wet blast is dried up with pure argon
(only to the blade for having oxidation).
Step 3, ultrasonic cleaning: acetone carries out ultrasonic cleaning, scavenging period as cleaning agent, by the blade after drying
It is 20 points.Blade pure argon after ultrasonic cleaning is dried up into (only to the blade for having oxidation).
Step 4, depositing coating: blade shove charge is vacuumized higher than 5 × 10-2Heating room temperature is set as 140 DEG C by Pa,
Keep the temperature 1h；Heating room temperature is transferred to 280 DEG C；To heating room applying argon gas, make pressure up to 1.0 × 10-1Pa；
Step 5, aura, bombardment cleaning blade surface；
Step 6 calculates and mends coating time period, starts to carry out benefit coating treatment.
Step 7, Coatings in Vacuum DIFFUSION TREATMENT wear clean white glove for blade tenon and are downwardly into shove charge in tooling, blade
Blade and edge version coating surface do not allow to contact with other, furnace temperature are risen to 800 DEG C with 8 DEG C/minute, heat preservation to Part temperature reaches
800 DEG C only, and in 800 DEG C of partial pressures to 20Pa；Furnace temperature is risen to 930 DEG C with 6 DEG C/min, heat preservation to Part temperature is up to 930 ± 10
DEG C only, in 930 ± 10 DEG C of heat preservation 4h, by blade with furnace vacuum cooled to 500 DEG C or less；Applying argon gas opens wind to 1.0bar again
Fan, is as cold as 80 DEG C or less for blade；Blade is come out of the stove air-cooled to room temperature.
Embodiment 3
Step 1 takes out turbo blade from the device, and blade is wrapped up protection to prevent exotic dirt with clean blank sheet of paper
Dye；
Step 2, wet blast: blade tenon is protected, and wet blast method is taken to carry out blast to turbine blade coating surface
Cleaning, blast wind pressure 1.6Mpa the time 15 seconds, remove oxidation tint, leaf appearance inspection, drying and circular flow after wet blast
In, do not allow directly to contact blade blade and supramarginal plate.Blade, waste leaf piece and test piece after wet blast is dried up with pure argon
(only to the blade for having oxidation).
Step 3, ultrasonic cleaning: acetone carries out ultrasonic cleaning, scavenging period as cleaning agent, by the blade after drying
It is 23 points.Blade pure argon after ultrasonic cleaning is dried up into (only to the blade for having oxidation).
Step 4, depositing coating: blade shove charge is vacuumized higher than 5 × 10-2Heating room temperature is set as 120 DEG C by Pa,
Keep the temperature 1.2h；Heating room temperature is transferred to 300 DEG C；To heating room applying argon gas, make pressure up to 1.1 × 10-1Pa；
Step 5, aura, bombardment cleaning blade surface；
Step 6 calculates and mends coating time period, starts to carry out benefit coating treatment.
Step 7, Coatings in Vacuum DIFFUSION TREATMENT wear clean white glove for blade tenon and are downwardly into shove charge in tooling, blade
Blade and edge version coating surface do not allow to contact with other, furnace temperature are risen to 800 DEG C with 7 DEG C/minute, heat preservation to Part temperature reaches
800 DEG C only, and in 800 DEG C of partial pressures to 10Pa；Furnace temperature is risen to 920 DEG C with 5.5 DEG C/min, heat preservation to Part temperature up to 920 ±
10 DEG C only, in 920 ± 10 DEG C of heat preservation 3.5h, by blade with furnace vacuum cooled to 500 DEG C or less；Applying argon gas is beaten to 0.9bar again
It opens fan, blade is as cold as 80 DEG C or less；Blade is come out of the stove air-cooled to room temperature.
Performance symbol and relevant criterion requirement, are shown in Table 2, table 3, table 4 after primary coating repairs turbo blade DIFFUSION TREATMENT.
2 room temperature tensile properties data of table
3 760 DEG C of high temperature endurance performance data of table
4 980 DEG C of high temperature endurance performance data of table
Claims (10)
1. a kind of turbo blade MCrAlY coating physics restorative procedure, which comprises the following steps:
When occurring equipment fault in coating procedure, turbo blade is taken out from the device for step 1, check coating surface whether there is or not
Oxidative phenomena, when non-oxidation phenomenon, by turbo blade package protection to prevent exotic from polluting, subsequently into step 4；When having
When oxidative phenomena, 2 are entered step；
Step 2 protects turbo blade tenon, carries out blast cleaning to turbine blade coating surface using wet blast method, so
The turbo blade after wet blast is dried up with pure argon afterwards；
Step 3: the turbo blade after step 2 drying being subjected to ultrasonic cleaning, then by the turbo blade after ultrasonic cleaning
It is dried up with pure argon；
Step 4: after equipment repair is good, by turbo blade shove charge, adjusting vacuum degree and temperature to setting value；
Step 5: using aura, bombardment cleaning turbine blade surface；
Step 6: carrying out benefit coating treatment, when turbo blade non-oxidation phenomenon in step 1, mend the coating treatment time are as follows: technique
The regulatory requirements time has been coated with time, then plus 30~40min before subtracting equipment fault；When turbo blade has oxidation existing in step 1
As when, mend the coating treatment time are as follows: technological procedure has been coated with time, then plus 60~80min before wanting seeking time to subtract equipment fault；
Step 7: diffusion in vacuum processing is carried out to coating.
2. a kind of turbo blade MCrAlY coating physics restorative procedure according to claim 1, which is characterized in that step 2
In wet blast method 1.5~2Mpa of blast wind pressure.
3. a kind of turbo blade MCrAlY coating physics restorative procedure according to claim 1, which is characterized in that step 2
In the blast time 10~20 seconds of wet blast method.
4. a kind of turbo blade MCrAlY coating physics restorative procedure according to claim 1, which is characterized in that step 3
It is middle that ultrasonic cleaning is carried out as cleaning agent using acetone.
5. a kind of turbo blade MCrAlY coating physics restorative procedure according to claim 1, which is characterized in that step 3
The middle ultrasonic cleaning time is 20~25min.
6. a kind of turbo blade MCrAlY coating physics restorative procedure according to claim 1, which is characterized in that step 4
In be evacuated to higher than 5 × 10-2Heating room temperature is set as 100~140 DEG C, keeps the temperature 1~1.5h by Pa；Then room will be heated
Temperature is transferred to 280~350 DEG C, to heating room applying argon gas, makes pressure up to (1.0~1.1) × 10-1Pa。
7. a kind of turbo blade MCrAlY coating physics restorative procedure according to claim 1, which is characterized in that step 5
Middle aura, bombardment clearance time are 5~10min.
8. a kind of turbo blade MCrAlY coating physics restorative procedure according to claim 1, which is characterized in that step 7
Floating coat diffusion in vacuum processing specifically: turbo blade tenon is inserted into shove charge in tooling downward, furnace temperature is risen to 800 DEG C, is protected
Temperature is stopped to Turbine Blade Temperature Field up to 800 DEG C, and in 800 DEG C of partial pressures to 5~20Pa；Furnace temperature is risen to 900~930 DEG C, heat preservation is extremely
Turbine Blade Temperature Field is stopped up to 890~940 DEG C, in 890~940 DEG C of 3~4h of heat preservation, by turbo blade with furnace vacuum cooled to 500
DEG C hereinafter, applying argon gas opens fan to 0.5~1.0bar again, by blade be as cold as 80 DEG C hereinafter, blade come out of the stove it is air-cooled to room temperature.
9. a kind of turbo blade MCrAlY coating physics restorative procedure according to claim 8, which is characterized in that by furnace temperature
Heating rate when rising to 800 DEG C is 6~8 DEG C/min.
10. a kind of turbo blade MCrAlY coating physics restorative procedure according to claim 8, which is characterized in that by furnace
Heating rate when temperature rise is to 900~930 DEG C is 5~6 DEG C/min.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113957378A (en) * | 2021-10-22 | 2022-01-21 | 中国航发贵州黎阳航空动力有限公司 | Coating repair method for turbine blade |
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| CN101724301A (en) * | 2008-10-15 | 2010-06-09 | 中国科学院金属研究所 | MCrAlY+AlSiY composite coating and preparation technique thereof |
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