CN111036519A - Method for repairing high-pressure turbine working blade anti-oxidation coating in full life cycle - Google Patents
Method for repairing high-pressure turbine working blade anti-oxidation coating in full life cycle Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
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- B05D5/005—Repairing damaged coatings
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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
- 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
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Abstract
A method for repairing the whole life cycle of an anti-oxidation coating of a high-pressure turbine working blade belongs to the blade repairing technology, and comprises the following specific operation steps: (1) inspecting the appearance of the surface layer of the blade, and then carrying out cleaning, drying, hole checking, through hole processing, wax injection and gluing; (2) removing the original coating of the blade by adopting an acid pickling treatment method; (3) then cleaning the blade, drying, removing wax, checking holes and through holes, measuring thickness, carrying out surface nondestructive testing, carrying out thermal coloring testing, and finally carrying out visual inspection and quality confirmation; (4) and coating the blade coating again and checking. Compared with the prior art, the method greatly saves the manufacturing cost, and can be popularized to the repair of the anti-oxidation coatings of other two-vortex two-guide-blade. The method does not cause any corrosion to the substrate under the condition of removing the coating, and can remove the coating for multiple times without influencing the mechanical property of the substrate.
Description
Technical Field
The invention belongs to a blade repairing technology, and particularly relates to a method for repairing an antioxidant coating of a high-pressure turbine working blade in a full life cycle.
Background
The turbine blade of the aeroengine and the gas turbine has a severe service environment, and the surface of the turbine blade needs to be coated with a protective coating to improve the service life and the reliability of parts. After long-term use, the problems of the falling of the surface coating of the front edge of the blade body, the thinning of the blade coating, the deposition of environmental attachments on the surface of the blade coating and the like occur, so that the oxidation corrosion resistance of the blade is reduced, and the blade fails prematurely.
With the continuous increase of mass delivery and demand of engines, the number of engines which are subjected to large repair in the first-turn period is rapidly increased year by year, the annual repair amount can reach more than hundreds of engines, and through analysis of the decomposition result of the engines in the first-turn period, the M (Ni, Co or Ni + Co) CrAlY (Si) oxidation and corrosion resistant coating used by the high-pressure turbine blade is obviously reduced in Al content and obviously reduced in oxidation and corrosion resistant capability after the first-turn period, the service life of the coating is obviously reduced, and the repair technology research of the blade coating is urgently needed.
The currently widely used repair method is to remove the original coating by dry blasting sand and then to apply a new coating. However, due to the non-uniform sand blowing force and the non-uniform thickness of the coating, a large amount of un-removed or past-removed phenomena exist in the original coating removing process, and the re-coating and reuse of the blade coating are seriously influenced.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides a method for chemically removing an anti-oxidation coating of a high-pressure turbine blade reaching the service life. Particularly, the corrosion to the substrate is avoided under the condition of completely removing the coating, various mechanical properties of the substrate are maintained, and a new coating is coated again to enable the substrate to be used continuously.
The technical scheme for realizing the purpose of the invention is carried out according to the following process steps:
step 1, pretreatment process: inspecting the appearance of the surface layer of the blade, confirming whether the surface layer has a flaw, inspecting the thickness of the coating of the blade through a metallographic phase, and then cleaning, drying, inspecting holes, passing through the holes, injecting wax and coating glue;
step 2, removing an original coating: removing the original coating of the blade by adopting an acid pickling treatment method, wherein the acid pickling solution is a mixture of nitric acid and hydrofluoric acid water solution added with iron powder, and the acid pickling solution comprises the following components in percentage by weight: 250-390 ml/L, hydrofluoric acid: 10-15 ml/L, iron powder: 2-4 g/L, and the balance of distilled water; the operation steps are as follows:
(1) when the prepared acid solution is poured into an acid washing tank, heating is carried out until the temperature of the tank solution reaches 60-65 ℃, the blades are placed in a mode that the leaf basin faces upwards, the tank solution is kept in a stirring state, and the content of each component in the solution is controlled in the process;
(2) taking out the blade after the blade is placed in the groove for a period of time, wiping off residues on the blade body in flowing warm water, and checking the removal condition of the coating;
(3) if the coating is not completely removed, the coating is continuously removed on the original basis until the coating is completely removed by eyes, but the total time does not exceed the specified total time; wherein, if the residual coating of the leaf basin is more, the leaf basin is placed downwards, and if the residual coating of the leaf back is more, the leaf back is placed downwards;
and step 3, post-treatment process: then cleaning the blade, drying, removing wax, checking holes and through holes, measuring thickness, carrying out surface nondestructive testing, carrying out thermal coloring testing, and finally carrying out visual inspection and quality confirmation; the thermal coloring detection method comprises the specific operation steps of firstly protecting the non-coating surface of the blade; then, carrying out dry sand blowing by using aluminum oxide until the surface of the blade is free from metallic luster through visual inspection; finally, the cleaned blade is placed in an air circulating furnace to be heated to 570-590 ℃ and insulated for 1h, and then air-cooled to room temperature;
step 4, coating the blade coating again:
(1) firstly, preprocessing a blade, specifically wet sand blowing, strong water flow washing, ultrasonic cleaning, acetone immersion cleaning, drying, appearance detection and ion cleaning;
(2) then coating, appearance and metallographic examination were performed.
The method for repairing the antioxidant coating of the high-pressure turbine working blade in the whole life cycle comprises the following steps:
in the step 1, in order to prevent the bath solution from entering the blade inner cavity through the blade surface air film cooling hole and the tenon to corrode the welding line, before the blade coating and pickling removing scheme, wax injection protection measures are adopted for the welding line and the cover plate on one side of the blade inner cavity, and the outer surface of the blade inner cavity is protected by gluing.
In the step 2, the density of the nitric acid is 1.4g/cm3Hydrofluoric acid is an activating agent, and the content of the hydrofluoric acid is 30%; nitric acid and hydrofluoric acid react with metal elements such as Al, Cr and the like in the M (Ni, Co or Ni + Co) CrAlY (Si) oxidation resistant layer to generate oxidation products, the oxidation products are continuously wiped by scouring pad, the reaction is continuously carried out, and the M (Ni, Co or Ni + Co) CrAlY (Si) oxidation resistant layer is gradually removed; the Fe powder plays a role in relieving corrosion of the high-temperature alloy blade substrate, and because the content of Al, Cr and other elements in the alloy substrate is much lower than that in the coating, and the corrosion inhibition effect of the Fe powder is added, the Fe powder can not cause any corrosion to the alloy substrate under the condition of completely removing the coating by a time control method.
In the step 2(1), the content of each component in the solution is controlled by using an automatic acid-base titration device.
In the step 3, the mesh number of the alumina is 80-180 meshes, and the sand blowing pressure is 0.2-0.3 MPa; and checking the appearance after air cooling, wherein the appearance is golden yellow to indicate that the original coating exists, the appearance is brown to indicate that a diffusion permeation layer is generated, the appearance is blue to indicate that only bottom metal exists, the appearance is yellow brown to indicate that both the original coating and the diffusion permeation layer exist, and the diffusion permeation layer is continuously removed by using a dry sand blowing method until no residual coating permeation layer exists on the surface.
In the step 4, white corundum sand with the granularity of 180-250 meshes is adopted for wet sand blowing, the content of the corundum sand is 20-35%, the air pressure is 0.2-04 MPa, and the sand blowing distance is 180-350 nm; the water pressure is more than 2kg/cm2(ii) a The ultrasonic cleaning adopts distilled water solution, the frequency is 20KHz, the output voltage is 220V/Hz or 380V/Hz, and the cleaning time is 8-10 min; the acetone immersion cleaning time is 15-30 min; the temperature of the leaf drying machine is 120-150 ℃, and the drying time is 30-50 min; the arc current of the vacuum arc plating ion cleaning process is 600-700A, the workpiece voltage is 250V, and the cleaning time is 2-4 min.
The technical scheme of the method for repairing the antioxidant coating of the high-pressure turbine working blade in the whole life cycle is as follows:
(1) investigation of chemical removal coating formulations
And (3) investigating the influence of the chemical formula solution on the removal effect of the used coating, and searching process parameters for completely removing the original coating and removing the corroded coating on the local surface through tests. The influence of the removal process on the metallographic phase, room-temperature stretching, high-temperature durability and rotary bending fatigue mechanical properties of the coating is developed.
(2) Research on part protection technology
The feasibility and the influence of the protection of air film holes and the protection of tip solder in the process of removing the original coating by a chemical method are mainly considered, the removal degree of the original coating by different chemical formulas is researched, and the tool for removing the coating (the coating and the permeable layer are integrated, and the coating and a matrix are mutually diffused to form the permeable layer in the using process) for pickling and cleaning the blade is designed and manufactured.
(3) Residual infiltrated layer removal and inspection techniques
The influence of a dry sand blowing method on the removal effect of the residual permeable layer of the blade is researched, the influence of different sand blowing pressures and sand grain sizes on the removal of the permeable layer and the wall thickness of the blade is mainly researched, and the judgment method and the basis of the removal degree of the coating are researched.
(4) Study of coating recoating Process
The surface condition of the original coating after removal may have an effect on the interfacial bonding force of the recoating process. By researching the influence of a surface pretreatment system, a residual coating and a heat treatment system on the bending property, the thermal shock property, the matrix mechanical property and the like of the coating, the coating recoating process flow and process parameters are determined, and the recoated blade is removed to pass a vibration fatigue test.
According to the process clues of the previous investigation, the following three formulas of the pickling bath solution are preliminarily formulated:
① nitric acid, hydrofluoric acid and chromic anhydride
② nitric acid + hydrofluoric acid + ultrasound
③ nitric acid + hydrochloric acid + phosphoric acid
The removal process development flow is shown in fig. 1.
The three pickling bath solution formulas can react with the coating, wherein the bath solution ① has obvious intercrystalline corrosion and pitting corrosion on the substrate, the bath solution ② does not react with the substrate and has obvious gas precipitation phenomenon during the reaction with the coating, the bath solution ③ has pitting corrosion on the substrate, in order to avoid the influence of the coating removal process on the substrate, the bath solution ② is selected to carry out the actual blade original coating removal test, the finally formulated blade pickling process flow is shown in fig. 2, fig. 3(a) to (e) are gold phase diagrams of all links of the high-pressure turbine blade original coating removal process through the bath solution ②, and the bath solution ② can effectively remove the M (Ni, Co or Ni + Co) CrAlY (Si) coating and has no over corrosion phenomenon on the directionally solidified high-temperature alloy through being observed from the graphs of fig. 3(a) to (e).
The high-pressure turbine working blade of the engine is a hollow cast blade with a blade body provided with a cooling air film hole, and a blade tip is welded with a cover plate by adopting a brazing process.
Residual infiltrated layer removal and inspection techniques
The influence of the dry sand blowing method on the removal effect of the residual permeable layer of the blade is researched, the influence of different sand blowing pressures and sand grain sizes on the removal of the permeable layer and the wall thickness of the blade is mainly researched, the judgment method and the basis of the removal degree of the coating are researched, and the final technological parameters of the dry sand blowing method are determined.
Study of coating recoating Process
The surface condition of the original coating after removal may have an effect on the interfacial bonding force of the recoating process. By researching the influence of a surface pretreatment system, a residual coating and a heat treatment system on the bending property, the thermal shock property, the matrix mechanical property and the like of the coating, the coating recoating process flow and process parameters are determined, and the recoated blade is removed to pass a vibration fatigue test. The finally formulated blade coating recoating process flow comprises wet sand blowing, strong water flow flushing, ultrasonic cleaning, acetone immersion cleaning, blade drying, inspection after cleaning, preparation work before coating, diffusion treatment and coating quality inspection.
Compared with the prior art, the invention has the advantages that:
(1) the invention greatly saves the manufacturing cost and can be popularized to the repair of the anti-oxidation coatings of other two-vortex two-guide-blade.
(2) The blade coated with the coating after being removed by the method of the invention participates in the engine long test examination, and the surface state of the coating is intact after the 1000h examination.
(3) When the method is adopted to remove the coating, no corrosion is caused to the matrix, and the coating can be removed for multiple times without influencing the mechanical property of the matrix.
(4) Each high-pressure turbine blade is about 1.5 ten thousand yuan, and each taixing engine can save 120 ten thousand yuan according to the calculation of a new replacement part.
Drawings
FIG. 1 is a development flow chart of the original coating removing process of the high-pressure turbine blade of the invention.
FIG. 2 is a flow chart of the pickling process of the high-pressure turbine blade in the invention.
FIG. 3 is a metallographic graph showing the original coating removal process of the high-pressure turbine blade according to the present invention; wherein, (a) is original leaf golden phase diagram; (b) the original coating of the blade is not completely removed with a metallographic picture; (c) completely removing a metallographic picture from an original coating of the blade; (d) a golden phase diagram of a protective part of the matrix; (e) the gold phase diagram of the unprotected part of the matrix is shown.
FIG. 4 is a metallographic structure diagram of the high-pressure turbine blade of example 1 after the coating is removed and then coated.
FIG. 5 is a graph of the high pressure turbine blade coating after removal and recoating of the coating in accordance with example 1 of the present invention.
Detailed Description
Example 1
A method for repairing the antioxidant coating of a high-pressure turbine working blade in a full life cycle comprises the following steps of: 250ml/L, hydrofluoric acid: 10ml/L, iron powder: 2g/L and the balance of distilled water.
The method for repairing the antioxidant coating of the high-pressure turbine working blade in the whole life cycle specifically comprises the following implementation steps:
step 1, pretreatment process: checking the appearance of the surface layer of the blade of the coming part, confirming whether the surface layer has a flaw or not, checking the thickness of the coating of the blade through metallographic phase, then cleaning, drying, checking holes, passing through holes, injecting wax and gluing (adopting wax injection protection measures for a welding line and a cover plate at one side of the inner cavity of the blade and gluing the outer surface of the welding line and the cover plate);
step 2, removing an original coating: the method for removing the original coating of the blade by adopting the acid pickling treatment method comprises the following specific operation modes:
(1) pouring the prepared acid solution into a pickling tank, heating to 60 ℃, starting pickling, placing blades in a mode that a leaf basin is upward, stirring the tank solution, and controlling the content of each component in the solution by using an automatic acid-base titration device in the process;
(2) taking out the blade after the blade is placed in the groove for 6min, wiping off residues on the blade body by using a scouring pad in flowing warm water, and checking the removal condition of the coating;
(3) the coating is not removed completely, wherein more residual coating is left on the leaf back, so that the leaf back is placed downwards, and then the coating is continuously removed for 14min, and the coating is removed by visual inspection;
and step 3, post-treatment process: then cleaning the blade, drying, removing wax, checking holes and through holes, measuring thickness, carrying out surface nondestructive testing, carrying out thermal coloring testing, and finally carrying out visual inspection and quality confirmation; the thermal coloring detection method comprises the specific operation steps of firstly protecting the surface of a non-coating M (Ni, Co or Ni + Co) CrAlY (Si) of the blade; then, using 80-mesh alumina, blowing sand at the sand blowing pressure of 0.2MPa for dry sand blowing until the surface of the blade is visually checked to have no metallic luster; finally, placing the glass fiber reinforced plastic composite material into an air circulating furnace, heating the glass fiber reinforced plastic composite material to 570 ℃, preserving heat for 1h, air-cooling the glass fiber reinforced plastic composite material to room temperature, and checking that the appearance is blue;
step 4, coating the blade coating again:
(1) firstly, preprocessing a blade, specifically, carrying out wet sand blasting treatment on white corundum sand with the granularity of 180 meshes, wherein the content of the corundum sand is 20%, the wind pressure is 0.2MPa, and the sand blasting distance is 180 nm; the water pressure was 3kg/cm2(ii) a Then ultrasonic cleaning treatment is carried out, distilled water solution is adopted, the frequency is 20KHz, the output voltage is 220V/Hz, and the cleaning time is 8 min; then, acetone immersion cleaning is carried out for 15 min; then carrying out leaf drying treatmentThe specific drying temperature is 120 ℃, and the drying time is 30 min; then carrying out vacuum arc plating ion cleaning treatment, wherein the specific arc current is 600A, the workpiece voltage is 250V, and the cleaning time is 2 min;
(2) then coating, appearance and metallographic examination were performed.
The gold phase diagram of the coating of example 1 after coating is shown in fig. 4, and the bending test results after coating removal and recoating are shown in fig. 5. As can be seen from FIGS. 4 and 5, the coating is uniform, continuous and dense, free of large particles, flat in surface and good in coating state.
The results of the room temperature tensile test of the DZ125 alloy and the DZ125 alloy coated with the coating layer in example 1 are shown in Table 1,
TABLE 1 comparison of tensile properties at room temperature before and after repair of DZ125 alloy coatings
As can be seen from the detection data in Table 1, the room-temperature tensile properties of the samples after the coatings are removed and the coatings are removed again are equivalent to those of the DZ125 matrix alloy matrix, and the samples meet the requirements of model standards.
The DZ125 alloy and the coating DZ125 alloy of example 1 were subjected to a high temperature durability test, and the results are shown in Table 2,
TABLE 2 comparison of high-temperature durability before and after repair of DZ125 alloy coatings
From the results in Table 2, it can be seen that the high temperature durability after removing the coating and then coating the coating meets the requirements of the model standards.
The results of the tests for mechanical properties of rotating bending fatigue of the DZ125 alloy and the DZ125 alloy coated with the coating layer in example 1 are shown in Table 3,
TABLE 3 DZ125 alloy coating repair before and after spin bending fatigue life test results
As can be seen from Table 3, the coating removal recoating process had no effect on the rotating bending fatigue mechanical properties of the DZ125 alloy substrate.
Example 2
A method for repairing the antioxidant coating of a high-pressure turbine working blade in a full life cycle comprises the following steps of: 390ml/L, hydrofluoric acid: 15ml/L, iron powder: 4g/L, and the balance of distilled water.
The method for repairing the antioxidant coating of the high-pressure turbine working blade in the whole life cycle specifically comprises the following implementation steps:
step 1, pretreatment process: checking the appearance of the surface layer of the blade of the coming part, confirming whether the surface layer has a flaw or not, checking the thickness of the coating of the blade through metallographic phase, then cleaning, drying, checking holes, passing through holes, injecting wax and gluing (adopting wax injection protection measures for a welding line and a cover plate at one side of the inner cavity of the blade and gluing the outer surface of the welding line and the cover plate);
step 2, removing an original coating: the method for removing the original coating of the blade by adopting the acid pickling treatment method comprises the following specific operation modes:
(1) pouring the prepared acid solution into an acid washing tank, heating to 65 ℃, starting acid washing, placing blades in a mode that a leaf basin is upward, stirring the tank solution, and controlling the content of each component in the solution by using an automatic acid-base titration device in the process;
(2) taking out the blade after the blade is placed in the groove for 12min, wiping off residues on the blade body by using a scouring pad in flowing warm water, and checking the removal condition of the coating;
(3) the coating is removed clearly by visual inspection;
and step 3, post-treatment process: then cleaning the blade, drying, removing wax, checking holes and through holes, measuring thickness, carrying out surface nondestructive testing, carrying out thermal coloring testing, and finally carrying out visual inspection and quality confirmation; the hot coloring method is used for detecting the removal effect, and comprises the specific operation steps of firstly protecting the surface of a non-coating M (Ni, Co or Ni + Co) CrAlY (Si) of the blade; then, using 180-mesh alumina, blowing sand at the sand blowing pressure of 0.3MPa for dry sand blowing until the surface of the blade is visually checked to have no metallic luster; finally, placing the glass fiber reinforced plastic composite material into an air circulating furnace, heating the glass fiber reinforced plastic composite material to 590 ℃, preserving the heat for 1h, air-cooling the glass fiber reinforced plastic composite material to room temperature, and checking that the appearance is blue;
step 4, coating the blade coating again:
(1) firstly, preprocessing a blade, specifically, carrying out wet sand blasting treatment on white corundum sand with the granularity of 250 meshes, wherein the content of the corundum sand is 35%, the wind pressure is 0.4MPa, and the sand blasting distance is 350 nm; the water pressure was 5kg/cm2(ii) a Then ultrasonic cleaning treatment is carried out, distilled water solution is adopted, the frequency is 20KHz, the output voltage is 380V/Hz, and the cleaning time is 10 min; then, acetone immersion cleaning is carried out for 30 min; then, drying the leaves, wherein the specific drying temperature is 150 ℃, and the drying time is 50 min; then carrying out vacuum arc plating ion cleaning treatment, wherein the specific arc current is 700A, the workpiece voltage is 250V, and the cleaning time is 4 min;
(2) coating application, appearance and metallographic examination were then performed.
Example 3
A method for repairing the antioxidant coating of a high-pressure turbine working blade in a full life cycle comprises the following steps of: 300ml/L, hydrofluoric acid: 12ml/L, iron powder: 3g/L, and the balance of distilled water.
The method for repairing the antioxidant coating of the high-pressure turbine working blade in the whole life cycle specifically comprises the following implementation steps:
step 1, pretreatment process: checking the appearance of the surface layer of the blade of the coming part, confirming whether the surface layer has a flaw or not, checking the thickness of the coating of the blade through metallographic phase, then cleaning, drying, checking holes, passing through holes, injecting wax and gluing (adopting wax injection protection measures for a welding line and a cover plate at one side of the inner cavity of the blade and gluing the outer surface of the welding line and the cover plate);
step 2, removing an original coating: the method for removing the original coating of the blade by adopting the acid pickling treatment method comprises the following specific operation modes:
(1) pouring the prepared acid solution into an acid washing tank, heating to 62 ℃, starting acid washing, placing blades in a mode that a leaf basin is upward, stirring the tank solution, and controlling the content of each component in the solution by using an automatic acid-base titration device in the process;
(2) taking out the blade after the blade is placed in the groove for 5min, wiping off residues on the blade body by using a scouring pad in flowing warm water, and checking the removal condition of the coating;
(3) the coating is not removed completely, wherein more residual coatings are left on the leaf basin, so that the leaf basin is placed downwards, and then is continuously removed for 15min, and is removed completely by visual observation;
and step 3, post-treatment process: then cleaning the blade, drying, removing wax, checking holes and through holes, measuring thickness, carrying out surface nondestructive testing, carrying out thermal coloring testing, and finally carrying out visual inspection and quality confirmation; the hot coloring method is used for detecting the removal effect, and comprises the specific operation steps of firstly protecting the surface of a non-coating M (Ni, Co or Ni + Co) CrAlY (Si) of the blade; then, using 100-mesh alumina, blowing sand at the sand blowing pressure of 0.25MPa for dry sand blowing until the surface of the blade is visually checked to have no metallic luster; finally, placing the glass fiber reinforced plastic composite material into an air circulating furnace, heating the glass fiber reinforced plastic composite material to 580 ℃ and preserving heat for 1h, air-cooling the glass fiber reinforced plastic composite material to room temperature, and checking that the appearance is blue;
step 4, coating the blade coating again:
(1) firstly, preprocessing a blade, specifically, carrying out wet sand blasting treatment on white corundum sand with the granularity of 200 meshes, wherein the content of the corundum sand is 30%, the wind pressure is 0.3MPa, and the sand blasting distance is 250 nm; the water pressure was 4kg/cm2(ii) a Then ultrasonic cleaning treatment is carried out, distilled water solution is adopted, the frequency is 20KHz, the output voltage is 380V/Hz, and the cleaning time is 10 min; then, acetone immersion cleaning is carried out for 20 min; then, drying the leaves, wherein the specific drying temperature is 130 ℃, and the drying time is 40 min; then carrying out vacuum arc plating ion cleaning treatment, wherein the specific arc current is 650A, the workpiece voltage is 250V, and the cleaning time is 3 min;
(2) coating application, appearance and metallographic examination were then performed.
Claims (6)
1. A method for repairing the whole life cycle of an anti-oxidation coating of a high-pressure turbine working blade is characterized by comprising the following steps:
step 1, pretreatment process: inspecting the appearance of the surface layer of the blade, confirming whether the surface layer has a flaw, inspecting the thickness of the coating of the blade through a metallographic phase, cleaning, drying, inspecting holes, passing through the holes, injecting wax and coating glue;
step 2, removing an original coating: removing the original coating of the blade by adopting an acid pickling treatment method, wherein the acid pickling solution is a mixture of nitric acid and hydrofluoric acid water solution added with iron powder, and the acid pickling solution comprises the following components in percentage by weight: 250-390 ml/L, hydrofluoric acid: 10-15 ml/L, iron powder: 2-4 g/L, and the balance of distilled water; the specific operation steps are as follows:
(1) when the prepared acid solution is poured into an acid washing tank, heating is carried out until the temperature of the tank solution reaches 60-65 ℃, the blades are placed in a mode that the leaf basin faces upwards, the tank solution is kept in a stirring state, and the content of each component in the solution is controlled in the process;
(2) taking out the blade after the blade is placed in the groove for a period of time, wiping off residues on the blade body in flowing warm water, and checking the removal condition of the coating;
(3) if the coating is not completely removed, the coating is continuously removed on the original basis until the coating is completely removed by eyes, but the total time does not exceed the specified total time; wherein, if the residual coating of the leaf basin is more, the leaf basin is placed downwards, and if the residual coating of the leaf back is more, the leaf back is placed downwards;
and step 3, post-treatment process: then cleaning the blade, drying, removing wax, checking holes and through holes, measuring thickness, carrying out surface nondestructive testing, carrying out thermal coloring testing, and finally carrying out visual inspection and quality confirmation; the thermal coloring detection method comprises the specific operation steps of firstly protecting the non-coating surface of the blade; then, carrying out dry sand blowing by using aluminum oxide until the surface of the blade is free from metallic luster through visual inspection; finally, the cleaned blade is placed in an air circulating furnace to be heated to 570-590 ℃ and insulated for 1h, and then air-cooled to room temperature;
step 4, coating the blade coating again:
(1) firstly, preprocessing a blade, specifically wet sand blowing, strong water flow washing, ultrasonic cleaning, acetone immersion cleaning, drying, appearance detection, clamping and ion cleaning;
(2) then coating, appearance and metallographic examination were performed.
2. The method for repairing the antioxidant coating of the high-pressure turbine working blade in the whole life cycle according to the claim 1, wherein in the step 1, wax is injected to the welding seam and the cover plate on one side of the inner cavity of the blade, and the outer surface of the welding seam and the cover plate is coated with glue.
3. The method for repairing the antioxidant coating of the high-pressure turbine working blade in the whole life cycle according to claim 1, wherein in the step 2, the nitric acid density is 1.4g/cm330 percent of hydrofluoric acid and Fe powder corrosion inhibitor.
4. The method for repairing the antioxidant coating of the high-pressure turbine blade in the whole life cycle according to claim 1, wherein in the step 2(1), the content of each component in the solution is controlled by using an automatic acid-base titration device.
5. The method for repairing the antioxidant coating of the high-pressure turbine working blade in the whole life cycle according to claim 1, wherein in the step 3, the mesh number of alumina is 80-180 meshes, and the sand blowing pressure is 0.2-0.3 MPa; and checking the appearance after air cooling, wherein the appearance is golden yellow to indicate that the original coating exists, the appearance is brown to indicate that a diffusion permeation layer is generated, the appearance is blue to indicate that only bottom metal exists, the appearance is yellow brown to indicate that both the original coating and the diffusion permeation layer exist, and the diffusion permeation layer is continuously removed by using a dry sand blowing method until no residual coating permeation layer exists on the surface.
6. The method for repairing the antioxidant coating of the high-pressure turbine working blade in the whole life cycle according to claim 1, wherein in the step 4, white corundum sand with the granularity of 180-250 meshes is adopted as the wet blasting sand, the content of the corundum sand is 20-35%, the air pressure is 0.2-04 MPa, and the water pressure is more than 2kg/cm2The sand blowing distance is 180-350 nm; the ultrasonic cleaning adopts distilled water solution, the frequency is 20KHz, the output voltage is 220V/Hz or 380V/Hz, and the cleaning time is 8-10 min; the acetone immersion cleaning time is 15-30 min; bladeThe drying temperature is 120-150 ℃, and the drying time is 30-50 min; the arc current of the vacuum arc plating ion cleaning process is 600-700A, the workpiece voltage is 250V, and the cleaning time is 2-4 min.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112588639A (en) * | 2020-12-21 | 2021-04-02 | 兰州科近泰基新技术有限责任公司 | Single-wing cleaning method for four-wing type radio frequency quadrupole field linear accelerator |
| 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 |
| CN113953165A (en) * | 2021-11-10 | 2022-01-21 | 中国航发南方工业有限公司 | Spraying process of inorganic aluminum anticorrosive coating of compressor blade disc repair part and compressor blade disc |
| CN113969405A (en) * | 2021-10-27 | 2022-01-25 | 中国航发贵州黎阳航空动力有限公司 | Method for removing NiCrAlY coating of aeroengine blade |
| CN113981457A (en) * | 2021-10-27 | 2022-01-28 | 中国航发贵州黎阳航空动力有限公司 | Method for removing failure coating of single crystal high-pressure turbine blade |
| CN114107993A (en) * | 2021-11-23 | 2022-03-01 | 华瑞（江苏）燃机服务有限公司 | Acid washing stripping process for metal bonding layer of turbine moving blade of gas turbine |
| CN114606507A (en) * | 2022-03-07 | 2022-06-10 | 陈育钦 | Steel bar machining device for construction site and machining method thereof |
| CN115595581A (en) * | 2022-11-10 | 2023-01-13 | 上海电气燃气轮机有限公司（Cn） | Method for removing adhesive layer of thermal part after service |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102817000A (en) * | 2012-07-31 | 2012-12-12 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for preparing anti-oxidation corrosion coating of high pressure turbine blade |
| CN104342713A (en) * | 2014-10-07 | 2015-02-11 | 中国人民解放军第五七一九工厂 | Method removing aluminum oxide-titanium oxide ceramic seal coating |
-
2019
- 2019-11-20 CN CN201911139705.0A patent/CN111036519A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102817000A (en) * | 2012-07-31 | 2012-12-12 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for preparing anti-oxidation corrosion coating of high pressure turbine blade |
| CN104342713A (en) * | 2014-10-07 | 2015-02-11 | 中国人民解放军第五七一九工厂 | Method removing aluminum oxide-titanium oxide ceramic seal coating |
Non-Patent Citations (1)
| Title |
|---|
| 张斌科等: "航空发动机高压涡轮叶片失效涂层的清除", 《电镀与涂饰》 * |
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| CN112588639A (en) * | 2020-12-21 | 2021-04-02 | 兰州科近泰基新技术有限责任公司 | Single-wing cleaning method for four-wing type radio frequency quadrupole field linear accelerator |
| 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 |
| CN113969405A (en) * | 2021-10-27 | 2022-01-25 | 中国航发贵州黎阳航空动力有限公司 | Method for removing NiCrAlY coating of aeroengine blade |
| CN113981457A (en) * | 2021-10-27 | 2022-01-28 | 中国航发贵州黎阳航空动力有限公司 | Method for removing failure coating of single crystal high-pressure turbine blade |
| CN113953165A (en) * | 2021-11-10 | 2022-01-21 | 中国航发南方工业有限公司 | Spraying process of inorganic aluminum anticorrosive coating of compressor blade disc repair part and compressor blade disc |
| CN114107993A (en) * | 2021-11-23 | 2022-03-01 | 华瑞（江苏）燃机服务有限公司 | Acid washing stripping process for metal bonding layer of turbine moving blade of gas turbine |
| CN114606507A (en) * | 2022-03-07 | 2022-06-10 | 陈育钦 | Steel bar machining device for construction site and machining method thereof |
| CN115595581A (en) * | 2022-11-10 | 2023-01-13 | 上海电气燃气轮机有限公司（Cn） | Method for removing adhesive layer of thermal part after service |
| CN115595581B (en) * | 2022-11-10 | 2024-04-26 | 上海电气燃气轮机有限公司 | Method for removing bonding layer of thermal component after service |
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Application publication date: 20200421 |