CN113981457A - Method for removing failure coating of single crystal high-pressure turbine blade - Google Patents
Method for removing failure coating of single crystal high-pressure turbine blade Download PDFInfo
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- CN113981457A CN113981457A CN202111258457.9A CN202111258457A CN113981457A CN 113981457 A CN113981457 A CN 113981457A CN 202111258457 A CN202111258457 A CN 202111258457A CN 113981457 A CN113981457 A CN 113981457A
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- pressure turbine
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- 239000011248 coating agent Substances 0.000 title claims abstract description 69
- 238000000576 coating method Methods 0.000 title claims abstract description 69
- 238000000034 method Methods 0.000 title claims abstract description 27
- 239000013078 crystal Substances 0.000 title claims abstract description 19
- 238000005406 washing Methods 0.000 claims abstract description 30
- 239000002253 acid Substances 0.000 claims abstract description 24
- 239000004576 sand Substances 0.000 claims abstract description 20
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 19
- 238000007664 blowing Methods 0.000 claims abstract description 17
- 238000004140 cleaning Methods 0.000 claims abstract description 12
- 238000004040 coloring Methods 0.000 claims abstract description 6
- 238000010297 mechanical methods and process Methods 0.000 claims abstract description 4
- 238000005554 pickling Methods 0.000 claims description 29
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 12
- KRHYYFGTRYWZRS-UHFFFAOYSA-N Fluorane Chemical compound F KRHYYFGTRYWZRS-UHFFFAOYSA-N 0.000 claims description 12
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 12
- 238000000227 grinding Methods 0.000 claims description 9
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 claims description 6
- 238000009835 boiling Methods 0.000 claims description 6
- 238000001035 drying Methods 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 6
- 229910017604 nitric acid Inorganic materials 0.000 claims description 6
- 230000001681 protective effect Effects 0.000 claims description 4
- 238000004018 waxing Methods 0.000 claims description 4
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 238000005260 corrosion Methods 0.000 claims description 3
- 230000007797 corrosion Effects 0.000 claims description 3
- 238000007689 inspection Methods 0.000 claims description 3
- 238000002156 mixing Methods 0.000 claims description 3
- 238000006386 neutralization reaction Methods 0.000 claims description 3
- 238000002791 soaking Methods 0.000 claims description 3
- 239000002390 adhesive tape Substances 0.000 claims description 2
- 229910052593 corundum Inorganic materials 0.000 claims description 2
- 239000010431 corundum Substances 0.000 claims description 2
- 238000002360 preparation method Methods 0.000 claims description 2
- 230000003472 neutralizing effect Effects 0.000 abstract 1
- 239000000956 alloy Substances 0.000 description 5
- 229910045601 alloy Inorganic materials 0.000 description 5
- 238000012423 maintenance Methods 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 238000010517 secondary reaction Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
Images
Classifications
-
- 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
- C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
- C23G1/00—Cleaning or pickling metallic material with solutions or molten salts
- C23G1/02—Cleaning or pickling metallic material with solutions or molten salts with acid solutions
- C23G1/08—Iron or steel
- C23G1/086—Iron or steel solutions containing HF
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/04—Cleaning involving contact with liquid
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/04—Cleaning involving contact with liquid
- B08B3/10—Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity or by vibration
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B1/00—Processes of grinding or polishing; Use of auxiliary equipment in connection with such processes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
-
- 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
- C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
- C23G1/00—Cleaning or pickling metallic material with solutions or molten salts
- C23G1/14—Cleaning or pickling metallic material with solutions or molten salts with alkaline solutions
- C23G1/19—Iron or steel
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Cleaning And De-Greasing Of Metallic Materials By Chemical Methods (AREA)
Abstract
A method for removing the failure coating of single-crystal high-pressure turbine blade includes such steps as cleaning the adhesion layer, washing, protecting, preparing acid washing solution, removing coating by acid washing, water washing, neutralizing, removing protecting wax layer, removing residual wax, blowing sand, thermal colouring, and removing residual coating by mechanical method.
Description
Technical Field
The invention belongs to the technical field of maintenance of blades of aero-engines, and particularly relates to a method for removing a failure coating of a single-crystal high-pressure turbine blade.
Background
The high-pressure turbine single crystal blade of the third generation aviation turbofan engine is characterized in that the surface of the blade is coated with an AlCrY coating on an MCrAlY + air inlet edge by a PVD method. In the service process, due to the combined action of gas scouring and oxidation of the engine, the high-temperature oxidation resistant coating on the part of the gas inlet edge is damaged, so that the protective performance of the coating on the blade is lost, hidden danger is brought to safe use of the engine, when the engine is repaired, the blade with the damaged coating needs to be repaired again, the damaged coating needs to be removed, and the blade can be installed and used after being recoated. How to remove the coating to the maximum extent without corroding the base material of the blade has become one of the difficulties in the maintenance of the aeroengine blade.
Disclosure of Invention
In order to solve the technical problems, the invention provides a method for removing the failure coating of the single crystal high-pressure turbine blade, which provides a formula of a reported pickling solution for removing the coating of the locally failed single crystal turbine blade and a process technology, and provides technical support for realizing the maintenance and the utilization of the single crystal turbine blade of an aeroengine.
The invention is realized by the following technical scheme.
The invention provides a method for removing a failure coating of a single crystal high-pressure turbine blade, which is characterized by comprising the following steps of:
step 1, cleaning an adhesion layer: protecting the tenon and the exhaust edge of the blade, and then blowing sand to the blade body of the blade to remove the adhesion layer;
step 3, preparing an acid washing solution: mixing nitric acid, hydrofluoric acid and iron to prepare pickling solution, and heating the pickling solution in water bath to 38 ℃ after preparation;
and 4, step 4: acid washing to remove the coating: putting the whole blade into an acid washing solution, controlling the temperature of the acid washing solution at 38 +/-2 ℃, carrying out corrosion condition inspection on the blade every 10min when the blade is subjected to acid washing, and stopping the acid washing in advance when the removal amount of a coating is 25%;
step 5, water washing neutralization: subjecting the pickled leaves to Na treatment at room temperature2CO3Soaking in the solution for 5min, and then washing with water and drying;
and 6, removing the protective wax layer: after the leaves are washed and dried, the leaf bodies of the leaves are immersed in boiling water for dewaxing;
step 7, removing residual wax: after wax removal in boiling water, the leaves are soaked in acetone to remove residual wax;
step 8, sand blowing: protecting the tenon and the exhaust edge of the blade, and blowing sand to the blade body of the blade, wherein the air pressure is 0.15 MPa;
and step 9: checking thermal coloring: putting the whole blade into a muffle furnace for heating, then air-cooling to room temperature, and observing by naked eyes after the blade is cooled, wherein if a part presenting yellow brown is arranged on the blade, the blade is determined as a residual coating;
step 10: removing the residual coating by a mechanical method: and (4) grinding and removing the residual coating by using a grinding wheel grinding method, and repeating the steps 9-10 until no yellow brown part of the blade is generated, wherein the blade coating is completely removed.
Further, in the step 1, when sand blowing is performed, the sand blowing angle is 50-75 degrees, the interval is 80mm, the sand granularity is brown fused alumina F100, and the air pressure is 0.2 MPa.
Further, in the step 2, when the blade is waxed, the number of coating times is 3-4.
Further, in the step 3, the concentration of nitric acid in the prepared pickling solution is 350g/L, the concentration of hydrofluoric acid in the prepared pickling solution is 9g/L, and the concentration of iron in the prepared pickling solution is 2 g/L.
Further, in the step 3, the amount of the pickling solution to be prepared is determined so that 250ml of the solution is prepared for each leaf.
Further, in the step 4, the whole pickling time is not more than 50min, and the solution temperature is controlled at 38 +/-2 ℃.
Further, in the step 5, Na is used2CO3The concentration of the solution was 30 g/L.
Further, in the step 9, the leaves are put into a muffle furnace to be heated to 600 ℃ and kept warm for 1 h.
Further, in the step 1 and the step 8, when the tenon and the exhaust edge of the blade are protected, the blade is wrapped by using an adhesive tape and is removed after sand blowing is finished.
The invention has the beneficial effects that: according to the invention, by removing the formula configuration of the pickling solution, the pickling time, the control of the solution temperature and the judgment of engineering application, the coating can be effectively removed to the maximum extent, the base material of the blade is not corroded, the coating removal effect is convenient to inspect and judge, the using amount of the pickling solution is controlled according to the processing amount of the blade, and a solution with little economic benefit and little influence on the environment is provided for removing the coating with failure of the blade.
Drawings
FIG. 1 is a cross-sectional scanning electron microscope profile of a blade coating;
FIG. 2 is the surface appearance of the base alloy of the blade after 50min of acid cleaning;
FIG. 3 is a partial profile of a completely removed area of a cross-sectional profile of a blade coating after 50min of acid washing;
FIG. 4 is a partial profile of a substantially removed area of a cross-sectional profile of a blade coating after 50min of pickling.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
The method for removing the failure coating of the single crystal high-pressure turbine blade mainly comprises the following steps:
step 1, cleaning an adhesion layer: protecting the tenon and the exhaust edge of the blade, and then blowing sand to the blade body of the blade to remove the attachment layer, wherein the sand blowing angle is 50-75 degrees, the interval is 80mm, the sand granularity is brown corundum F100, and the air pressure is 0.2 MPa;
step 3, preparing an acid washing solution: mixing nitric acid, hydrofluoric acid and iron to prepare an acid pickling solution, wherein the concentration of the nitric acid is 350g/L, the concentration of the hydrofluoric acid is 9g/L, and the concentration of the iron is 2g/L, preparing, performing water bath, and heating to 38 ℃;
and 4, step 4: acid washing to remove the coating: putting the whole blade into a pickling solution, controlling the temperature of the pickling solution within 38 +/-2 ℃, carrying out corrosion condition inspection on the blade every 10min from the beginning of pickling the blade, and stopping pickling in advance when the removal amount of a coating is 25%; after the blade is subjected to acid cleaning treatment for 50min, after the blade is subjected to 600 ℃ hot coloring for 1h, the light black area is usually removed completely in the acid cleaning process, and corresponds to the dark blue area after the hot coloring, and through the color change, the removal degree of the blade body coating in the acid cleaning process can be corresponded, and the removal amount is about 25%;
step 5, water washing neutralization: the acid-washed leaves were treated with Na at a concentration of 30g/L at room temperature2CO3Soaking in the solution for 5min, and then washing with water and drying;
and 6, removing the protective wax layer: after the leaves are washed and dried, the leaf bodies of the leaves are immersed in boiling water for dewaxing;
step 7, removing residual wax: after wax removal in boiling water, the leaves are soaked in acetone to remove residual wax, and can also be placed in an oil removal solution;
step 8, sand blowing: protecting the tenon and the exhaust edge of the blade, and blowing sand to the blade body of the blade, wherein the air pressure is 0.15 MPa;
and step 9: checking thermal coloring: putting the whole blade into a muffle furnace, heating to 600 ℃, preserving heat for 1h, then air-cooling to room temperature, and observing by naked eyes after the blade is cooled, wherein if a part appearing yellow brown is arranged on the blade, the blade is determined as a residual coating;
step 10: removing the residual coating by a mechanical method: and (4) grinding and removing the residual coating by using a grinding wheel grinding method, and repeating the steps 9-10 until no yellow brown part of the blade is generated, wherein the blade coating is completely removed.
As shown in fig. 1, a scanning electron microscope shows the cross-sectional morphology of the MCrAlY coating after the blade is used, and the cross-sectional morphology is divided into four regions in the figure. The area 1 is an oxidation film and scale produced in the use process of the blade, and is mainly a CMAS layer formed in the use process; zone 2 is the MCrAlY coating; region 3 is an interdiffusion zone formed during the vacuum diffusion of the as-deposited coating; the region 4 is a secondary reaction zone formed by interdiffusion of the coating and the substrate during use of the blade. The thickness of region 2 is about 42 μm and the total thickness of regions 3 and 4 is about 38 μm. Complete removal of the coating is not only meant to be removal of the coating in region 2, but should also include regions 3 and 4.
FIG. 2 shows the surface appearance of the base alloy of the blade after 50min of pickling, and the upper right area shows the appearance of the coating completely removed, and in comparison with FIG. 4 in FIG. 3, it can be seen that the base alloy of the blade is slightly over-pickled (the base alloy is pickled) and has no influence on the base alloy (shown by black arrows) in FIG. 3. FIG. 4 shows a substantially removed area, in which a portion of the coating in FIG. 4 has been substantially completely pickled, but a portion of the coating remains, with the remaining coating on the outer edge and the interdiffusion zone and secondary reaction zone inward. After 50 minutes of pickling, the depth of pickling of these partial areas reached just to the bottom of the secondary reaction zone of the coating, as shown by the black line in FIG. 4, with a coating removal of 25%. Therefore, the pickling time control method comprises the following steps: and when the area of the coating removed by the blade acid washing reaches 25%, stopping the blade acid washing. When the pickling time reaches the specified time, the pickling of the leaves is stopped; and the scrapping caused by over-pickling of the blade substrate is prevented.
Claims (9)
1. A method for removing a failed coating of a single crystal high pressure turbine blade, comprising the steps of:
step 1, cleaning an adhesion layer:
protecting the tenon and the exhaust edge of the blade, and then blowing sand to the blade body of the blade to remove the adhesion layer;
step 2, cleaning protection:
washing the blade with hot water, drying, and then waxing the part 8-10mm away from the air inlet edge, 4-5mm away from the air outlet edge and the tenon part, wherein during waxing, the rest parts are cleaned with alcohol or acetone after the temperature of the blade is ensured to be 30-40 ℃;
step 3, preparing an acid washing solution:
mixing nitric acid, hydrofluoric acid and iron to prepare pickling solution, and heating the pickling solution in water bath to 38 ℃ after preparation;
and 4, step 4: acid washing to remove the coating:
putting the whole blade into an acid washing solution, controlling the temperature of the acid washing solution at 38 +/-2 ℃, carrying out corrosion condition inspection on the blade every 10min when the blade is subjected to acid washing, and stopping the acid washing in advance when the removal amount of a coating is 25%;
step 5, water washing neutralization:
subjecting the pickled leaves to Na treatment at room temperature2CO3Soaking in the solution for 5min, and then washing with water and drying;
and 6, removing the protective wax layer:
after the leaves are washed and dried, the leaf bodies of the leaves are immersed in boiling water for dewaxing;
step 7, removing residual wax:
after wax removal in boiling water, the leaves are soaked in acetone to remove residual wax;
step 8, sand blowing:
protecting the tenon and the exhaust edge of the blade, and blowing sand to the blade body of the blade, wherein the air pressure is 0.15 MPa;
and step 9: checking thermal coloring:
putting the whole blade into a muffle furnace for heating, then air-cooling to room temperature, and observing by naked eyes after the blade is cooled, wherein if a part presenting yellow brown is arranged on the blade, the blade is determined as a residual coating;
step 10: removing the residual coating by a mechanical method:
and (4) grinding and removing the residual coating by using a grinding wheel grinding method, and repeating the steps 9-10 until no yellow brown part of the blade is generated, wherein the blade coating is completely removed.
2. The method of removing a single crystal high pressure turbine blade failure coating of claim 1, wherein: in the step 1, when sand blowing is carried out, the sand blowing angle is 50-75 degrees, the interval is 80mm, the granularity of the sand is brown corundum F100, and the air pressure is 0.2 MPa.
3. The method of removing a single crystal high pressure turbine blade failure coating of claim 1, wherein: in the step 2, when the blade is waxed, the number of coating times is 3-4.
4. The method of removing a single crystal high pressure turbine blade failure coating of claim 1, wherein: in the step 3, the prepared pickling solution has the concentration of 350g/L of nitric acid, 9g/L of hydrofluoric acid and 2g/L of iron.
5. The method of removing a single crystal high pressure turbine blade failure coating of claim 1, wherein: in the step 3, the amount of the prepared pickling solution is prepared according to the amount of 250ml of the solution corresponding to each leaf.
6. The method of removing a single crystal high pressure turbine blade failure coating of claim 1, wherein: in the step 4, the whole pickling time is not more than 50min, and the solution temperature is controlled at 38 +/-2 ℃.
7. The method of removing a single crystal high pressure turbine blade failure coating of claim 1, wherein: in the step 5, Na is used2CO3The concentration of the solution was 30 g/L.
8. The method of removing a single crystal high pressure turbine blade failure coating of claim 1, wherein: in the step 9, the leaves are placed into a muffle furnace to be heated to 600 ℃ and kept warm for 1 h.
9. The method of removing a single crystal high pressure turbine blade failure coating of claim 1, wherein: in the step 1 and the step 8, when the tenon and the exhaust edge of the blade are protected, the blade is wrapped by using an adhesive tape and is removed after sand blowing is finished.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111258457.9A CN113981457A (en) | 2021-10-27 | 2021-10-27 | Method for removing failure coating of single crystal high-pressure turbine blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111258457.9A CN113981457A (en) | 2021-10-27 | 2021-10-27 | Method for removing failure coating of single crystal high-pressure turbine blade |
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| Publication Number | Publication Date |
|---|---|
| CN113981457A true CN113981457A (en) | 2022-01-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111258457.9A Pending CN113981457A (en) | 2021-10-27 | 2021-10-27 | Method for removing failure coating of single crystal high-pressure turbine blade |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0713957A1 (en) * | 1994-11-25 | 1996-05-29 | FINMECCANICA S.p.A. AZIENDA ANSALDO | Method of repairing the coating of turbine blades |
| CN111036519A (en) * | 2019-11-20 | 2020-04-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for repairing high-pressure turbine working blade anti-oxidation coating in full life cycle |
| CN111254377A (en) * | 2020-01-22 | 2020-06-09 | 中国人民解放军第五七一九工厂 | Repair method for long-life thermal barrier coating of F-grade ground heavy gas turbine blade |
-
2021
- 2021-10-27 CN CN202111258457.9A patent/CN113981457A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0713957A1 (en) * | 1994-11-25 | 1996-05-29 | FINMECCANICA S.p.A. AZIENDA ANSALDO | Method of repairing the coating of turbine blades |
| CN111036519A (en) * | 2019-11-20 | 2020-04-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for repairing high-pressure turbine working blade anti-oxidation coating in full life cycle |
| CN111254377A (en) * | 2020-01-22 | 2020-06-09 | 中国人民解放军第五七一九工厂 | Repair method for long-life thermal barrier coating of F-grade ground heavy gas turbine blade |
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Application publication date: 20220128 |