CN114107993A - Acid washing stripping process for metal bonding layer of turbine moving blade of gas turbine - Google Patents
Acid washing stripping process for metal bonding layer of turbine moving blade of gas turbine Download PDFInfo
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- 229910045601 alloy Inorganic materials 0.000 claims abstract description 18
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- 238000005520 cutting process Methods 0.000 claims abstract description 14
- 238000005488 sandblasting Methods 0.000 claims description 31
- 238000004140 cleaning Methods 0.000 claims description 16
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 14
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- 229910052593 corundum Inorganic materials 0.000 claims description 4
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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
-
- 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
- B24C1/08—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for polishing surfaces, e.g. smoothing a surface by making use of liquid-borne abrasives
-
- 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
- C23G5/00—Cleaning or de-greasing metallic material by other methods; Apparatus for cleaning or de-greasing metallic material with organic solvents
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- 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)
- Cleaning And De-Greasing Of Metallic Materials By Chemical Methods (AREA)
Abstract
The invention discloses an acid washing stripping process of a metal bonding layer of a turbine moving blade of a gas turbine, which is used for stripping the metal bonding layer of a thermal barrier coating by acid washing, and is suitable for MCrAlY alloy of the metal bonding layer; acid washing: the non-coating area is shielded, particularly a cold cutting hole of the blade is shielded well, so that the pickling is prevented from entering a cold cutting channel of the blade to corrode the inside of the blade, then the alloy coating is removed through the reaction of acid and MCrAlY alloy, and the acid liquor can also react with a base material, so that the coating cannot be soaked or peeled off, and the peeling condition of the coating needs to be observed in time; the repairability and the service life of the movable blade are improved, the cost of an enterprise is reduced, meanwhile, the labor time is greatly reduced, and the production efficiency is improved.
Description
Technical Field
The invention relates to the field of movable blade coating stripping, in particular to an acid washing stripping process for a metal bonding layer of a movable blade of a turbine of a gas turbine.
Background
To ensure the safe operation of the gas turbine at high temperature, related material technology research must be firstly carried out, and advanced material technology comprises directional solidification, single crystal alloy, super cooling blade, Thermal Barrier Coating (TBC), oxidation and thermal corrosion resistant coating and the like. At present, the combustion chamber and the turbine blade of the gas turbine are generally made of austenitic stainless steel and nickel/cobalt-based super alloy, and the maximum size of the super alloy allowance-free precision casting single crystal blade reaches the 300mm grade.
With the increase of the initial temperature of the gas, the thermal shock and the thermal stress born by the turbine blade of the gas turbine are aggravated, in order to ensure the reliable work of high-temperature components, the advanced gas turbine widely uses a Thermal Barrier Coating (TBC), and the temperature of the metal surface can be reduced by 100 ℃ by adopting the technology, and the thermal stress is reduced by 20 percent compared with the traditional coating.
Most of bonding layers in modern TBC are MCrAlY (M = Nior/andCo) alloy coating coatings, and the coating is characterized by large component controllability, strong oxidation resistance and good ductility and toughness, is arranged between a heat insulation surface layer and a substrate, can provide oxidation resistance protection and relieve the mismatching between the surface layer and the substrate, and can simultaneously inhibit the premature aging of the substrate alloy caused by component diffusion (the method is to adjust the bonding layer to make the components thereof similar to the substrate)
The thermal barrier coating is a metal-ceramic composite coating system composed of a ceramic surface layer and a metal bonding layer, and is deposited on the surface of heat-resistant metal or superalloy, the ceramic surface layer has the function of forming high-temperature gradient along the coating thickness direction, the heat transfer of high-temperature gas to a substrate is weakened, the abrasion resistance, high-temperature oxidation resistance and corrosion resistance of the substrate are improved, and the bonding layer has the function of enabling the ceramic layer and the alloy substrate to be compatible in physical properties. The high-temperature blade can effectively reduce the working temperature of a metal matrix, achieves the purposes of prolonging the service life of a gas turbine and improving the heat efficiency, and is widely applied to high-temperature blades of aeroengines and gas turbines.
Typical thermal barrier coatings have three forms in structure: the thermal barrier coating with the classical double-layer structure comprises a metal bonding layer and a ceramic surface layer, wherein the bonding layer is generally MCrAlY or Pt-Al alloy and has the thickness of about 100-150 mu m; the thickness of the ceramic surface layer is about 300 mu m; the multilayer structure is additionally provided with the blocking layer on the basis of a double-layer structure, so that the corrosion and oxidation rate of the bonding layer are effectively reduced, the heat conductivity coefficient can be greatly reduced, the high-temperature resistance of the blade is improved by 260 ℃, the design concept is advanced, but the preparation process is more complex, the repeatability is poor, and the multilayer structure is mostly in the research and development stage; the superalloy component and the surface ceramic component of the functionally graded coating (composite structure) exhibit a continuous gradient, and the coating material is typically a mixture of YSZ and MCrAlY.
There is a need to protect various gas turbine components of a gas turbine from the high temperature gases within the gas turbine. Therefore, various technologies are used for the gas turbine component. For example, in a component such as a blade or a vane exposed to high-temperature combustion gas, a Thermal Barrier Coating (TBC) is applied to the surface of a component body. In order to protect such a member from the high-temperature combustion gas, a cooling hole for blowing out cooling air is provided in the blade body of the turbine blade of the member.
The TBC is eroded by the high-temperature combustion gas with the passage of time, and therefore needs to be repaired. The repair is performed by peeling off the TBC where erosion or the like has occurred first, and then applying the TBC again.
An inner coating layer made of an alloy and an outer coating layer made of a thermal barrier material such as ceramic are formed as TBC on the surface of the blade body. In the case of peeling off the TBC, the outer coating is peeled off by sandblasting first, and then the inner coating made of the alloy is peeled off by pickling.
Disclosure of Invention
The invention aims to solve the defects of the prior art and provides a pickling stripping process of a metal bonding layer of a turbine moving blade of a gas turbine, wherein the metal bonding layer of a thermal barrier coating is stripped by using a pickling method, and the method is suitable for MCrAlY alloy of the metal bonding layer;
acid washing process: the non-coating area is shielded, particularly a cold cutting hole of the blade is shielded well, so that the pickling is prevented from entering a cold cutting channel of the blade to corrode the inside of the blade, then the alloy coating is removed through the reaction of acid and MCrAlY alloy, and the acid liquor can also react with a base material, so that the coating cannot be soaked or peeled off, and the peeling condition of the coating needs to be observed in time; the repairability and the service life of the movable blade are improved, and the production efficiency is improved.
The technical scheme is that the acid washing stripping process of the metal bonding layer of the turbine movable blade of the gas turbine comprises the following process steps:
a. thermal degreasing of the parts: putting the component into an electric furnace, heating to 300-;
b. stripping of the surface ceramic coating: removing the zirconia ceramic coating on the surface of the part by using a sand blasting mode, covering a cold cutting hole and a blade root of the part by using an adhesive tape before sand blasting, preventing the part from being damaged by over-blasting because the part cannot be opposite to a local part for a long time during sand blasting, and purging the part after sand blasting is finished;
c. blocking the cold cutting hole: tearing off the shielding adhesive tape, plugging cold cutting holes at two ends of the blade by using resin, and then curing by using an ultraviolet lamp for about 108-13 minutes;
d. covering the blade root and the blade top, namely coating the blade root and the blade top without coating by using a covering adhesive for 2-4 layers, and coating the next layer after the previous layer is dried completely;
e. preparing a pickling solution: 30% hydrochloric acid was used: water = 1: 3, preparing a pickling solution and adding a catalyst;
f. stripping of the coating: heating the pickling solution to 7065-75 ℃, putting the part into a pickling tank, wherein the part needs to be completely immersed in the pickling solution, the pickling tank has bubbling and circulating filtering functions, the peeled coating is prevented from being attached to the part to influence the peeling effect, the part needs to be taken out and observed every 1-2 hours in the peeling process, the peeling condition of the coating on the part is observed, the interval time in the initial period of peeling is long, the interval time in the later period needs to be short, and the part is prevented from being corroded by over-peeling;
g. cleaning of parts: placing the component into a clean water tank, soaking the component for about 8-1310 minutes under the bubbling function in the clean water tank, taking out the component, washing the component with clean water, and cleaning acid liquor on the surface of the component;
h. removing the shielding glue: heating the components to 680650-;
i. cleaning of the parts: cleaning the part in a sand blasting cleaning mode;
j. and (3) detection: and judging the condition of the residual coating on the component by using a residual coating judging method, and polishing the residual coating on the component by using an abrasive belt machine on the unqualified component to remove the residual coating on the component until the coating on the component is completely removed.
Furthermore, in the step b, an included angle of 30-45 degrees is formed between the sand blasting gun and the sand blasting area of the blade, 40-mesh white corundum needs to be used, and the sand blasting pressure is 0.7-0.8 MPa.
Furthermore, in the step c, the cooling hole is blocked by resin, after the blade root is blocked for one section, the ultraviolet lamp irradiates for 8-1310 minutes for curing, then the cooling hole of the blade tip is blocked, and then the curing is carried out;
further, in the step d, the blade root without the coating is shielded by using the shielding glue, the shielding glue needs to be uniformly shaken before being used, the blade root is uniformly brushed by using a brush, the next layer can be continuously covered after the previous layer is dried, the 2-4 layers are brushed to meet the requirement of completely covering the blade root, and the shielding glue is noticed to completely cover the dead angle of the blade root.
Furthermore, in the step e, 3/4 water is added into the pickling tank, 1/4% hydrochloric acid is slowly added, and finally, 1000ml of 500-1000ml of catalyst is added.
Further, the method for judging the residual coating in the step j and the step j judges through color judgment or the seebeck effect, and specifically comprises the following steps:
judging the color of the residual coating: putting the part cleaned by sand blasting into a clean electric furnace, heating to 680 ℃, preserving heat for 1 hour, taking out in time after heat preservation is finished, judging the stripping condition of the coating according to the color of the surface of the part, wherein the color of the base metal is dark blue oxidized at high temperature of metal, and the color of the residual coating is light yellow;
judging the residual coating of the Seebeck effect: residual coatings were identified by using a thermoelectric alloy sorter. The invention aims to solve the defects of the prior art and provides the acid washing stripping process for the metal bonding layer of the turbine movable blade of the gas turbine.
Detailed Description
The technical content of the invention is explained in detail with reference to the following specific examples:
a pickling stripping process for a metal bonding layer of a turbine movable blade of a gas turbine comprises the following process steps of for a 2 nd-stage movable blade of a turbine part of a GE MS9001 FA (+ e) type gas turbine, stripping an MCrAlY alloy coating on the blade in a pickling manner by using a pickling stripping coating method:
a. thermal degreasing of the parts: putting the component into an electric furnace, heating to 350 ℃, preserving heat for 1 hour, and removing stains such as oil, dust and the like attached to the component in the running and dismounting processes;
b. stripping of the surface ceramic coating: removing the zirconia ceramic coating on the surface of the part by using a sand blasting mode, wherein a cold cutting hole and a blade root of the part are covered by using an adhesive tape before sand blasting, and the part cannot be opposite to one part for a long time during sand blasting so as to prevent the part from being damaged by over-blasting; the sand material adopts 40-mesh white corundum, the sand blasting pressure is 0.7-0.8MPa, the included angle between the spray gun angle and the component during sand blasting is optimal, the retention time of the front edge and the rear edge of the blade cannot be too long during sand blasting, and the blade is prevented from being thinned;
c. blocking the cold cutting hole: the cold cutting holes at the two ends of the blade are plugged by resin, and then the blade is cured by an ultraviolet lamp for about 10 minutes, which comprises the following steps: firstly, plugging a section of a blade root, then irradiating by an ultraviolet lamp for 10 minutes for curing, then plugging a cooling hole of the blade tip, and then curing, wherein if the part is heated after once plugging, the internal pressure is too large to cause overflow from the cooling hole in the resin curing process; wherein, the resin adopts 718 of Dymax company, and the glue dispensing equipment adopts Performis X100 equipment of Nordson EFD Optimum Systems; the ultraviolet curing apparatus used was a 2000-EC surface light source belt apparatus from Dymax corporation;
d. covering the blade root and the blade top, namely coating the uncoated blade root with a covering glue, coating 2-4 layers, coating the next layer after the previous layer is dried completely, and using SOCOMASK T2242 covering glue of SOCO MORE company as the covering glue;
e. preparing a pickling solution: 30% hydrochloric acid was used: water = 1: 3, adding a small amount of catalyst, heating to 70 ℃, and using AAA catalyst of Actane company as the catalyst, wherein the acid washing solution comprises the following components: catalyst = 1000: 1; the specific operation is as follows: 3/4 water is added into the acid washing tank, 1/4 percent of hydrochloric acid is slowly added, and finally, 1000ml of catalyst is added;
f. stripping of the coating: heating the pickling solution to 70 ℃, putting the part into a pickling tank, wherein the part needs to be completely immersed in the pickling solution, the pickling tank has bubbling and circulating filtering functions, the peeled coating is prevented from being attached to the part to influence the peeling effect, the part needs to be taken out and observed every 1-2 hours in the peeling process, and obvious color layering conditions can be caused if the coating is peeled off or not; the time interval can be longer in the initial stage of stripping, and needs to be shortened in the later stage, so that the corrosion of the component due to over-stripping can be prevented; the coating stripping is generally only needed to strip about 7-8 layers of the coating on the surface of the component, so that the component is prevented from being scrapped due to corrosion of the component after stripping;
g. cleaning of parts: placing the part into a clean water tank, starting bubbling, soaking for about 10 minutes, taking out, washing with flowing clean water, and cleaning acid liquor on the surface of the part;
h. removing the shielding glue: the components are heated to 680 ℃ by using an incinerator with tail gas treatment, the components are insulated for 1 hour, and the components are taken out after being cooled, wherein the tail gas treatment mode can be that a combustion chamber is added, the tail gas can be heated to 820 ℃, the heat energy utilization is improved, and the energy consumption is reduced;
i. cleaning of the parts: cleaning the component in a sand blasting cleaning mode, wherein 220-mesh white corundum sand is used for sand blasting, the sand blasting pressure is 0.3-0.4MPa, and the included angle between a spray gun angle and the component during sand blasting is optimal to be 30-45 degrees;
j. and (3) detection: the condition of the residual coating on the component is judged by utilizing a residual coating judging method, the unqualified component is polished by using an abrasive belt machine, the residual coating on the component is removed, until the coating on the component is completely removed, wherein the polishing process needs to be careful, and the condition of excessive polishing cannot occur.
The method for judging the residual coating in the step j judges through color judgment or the seebeck effect, and specifically comprises the following steps:
judging the color of the residual coating: putting the part cleaned by sand blasting into a clean electric furnace, heating to 680 ℃, preserving heat for 1 hour, taking out in time after heat preservation is finished, judging the stripping condition of the coating according to the color of the surface of the part, wherein the color of the base metal is dark blue oxidized at high temperature of metal, and the color of the residual coating is light yellow;
judging the residual coating of the Seebeck effect: residual coatings were identified by using a thermoelectric alloy sorter.
A thermoelectric alloy classifier: the principle involving the direct conversion of temperature differences into electrical energy is also known as the seebeck effect; forming a thermocouple-type circuit when the heated metal probe is in contact with the test metal; thermal connection of the two junctions; one at high temperature combines with the other at room temperature to produce a very small voltage; the voltage varies with the type of test metal and may be continuously correlated; this thermal property is used to describe most metals. Industrial quality control instruments as a method of identifying metal alloys; this is called the thermoelectric alloy classification, a well-known and approved method (ASTM e 977) for metal classification and validation.
In conclusion, by adopting the acid washing stripping process for the metal bonding layer of the blade of the turbine movable blade of the gas turbine, the ceramic coating of the movable blade is stripped in a sand blasting mode, the component is soaked in the acid liquor containing the catalyst, and the metal coating is stripped through the chemical reaction of the acid liquor and the metal bonding layer, so that the repairability and the service life of the movable blade are improved, meanwhile, the labor time is greatly reduced, and the production efficiency is improved.
The above description is the preferred embodiment of the present invention, and the scope of the claims of the present invention should not be limited thereto. It should be noted that modifications and equivalents may be made to the technical solution of the present invention by those skilled in the art without departing from the scope of the present invention.
Claims (6)
1. An acid washing stripping process for a metal bonding layer of a turbine moving blade of a gas turbine is characterized by comprising the following process steps:
thermal degreasing of the parts: putting the component into an electric furnace, heating to 300-;
stripping of the surface ceramic coating: removing the zirconia ceramic coating on the surface of the part by using a sand blasting mode, covering a cold cutting hole and a blade root of the part by using an adhesive tape before sand blasting, preventing the part from being damaged by over-blasting because the part cannot be opposite to a local part for a long time during sand blasting, and purging the part after sand blasting is finished;
blocking the cold cutting hole: tearing off the shielding adhesive tape, plugging cold cutting holes at two ends of the blade by using resin, and then curing by using an ultraviolet lamp for 8-13 minutes;
covering the blade root and the blade top, namely coating the blade root and the blade top without coating by using a covering adhesive for 2-4 layers, and coating the next layer after the previous layer is dried completely;
preparing a pickling solution: 30% hydrochloric acid was used: water = 1: 3, preparing a pickling solution and adding a catalyst;
stripping of the coating: heating the pickling solution to 65-75 ℃, putting the part into a pickling tank, wherein the part needs to be completely immersed in the pickling solution, the pickling tank has bubbling and circulating filtering functions, the peeled coating is prevented from being attached to the part to influence the peeling effect, the part needs to be taken out and observed every 1-2 hours in the peeling process, the peeling condition of the coating on the part is observed, the interval time in the initial period of peeling is long, the interval time in the later period needs to be short, and the part is prevented from being corroded by over-peeling;
cleaning of parts: placing the part into a clean water tank, soaking for about 8-13 minutes under the bubbling function in the clean water tank, taking out, washing with clean water, and cleaning acid liquor on the surface of the part;
removing the shielding glue: heating the components to 650-700 ℃ by using an incinerator, preserving the heat for 1 hour, cooling and taking out;
cleaning of the parts: cleaning the part in a sand blasting cleaning mode;
and (3) detection: and judging the condition of the residual coating on the component by using a residual coating judging method, and polishing the residual coating on the component by using an abrasive belt machine on the unqualified component to remove the residual coating on the component until the coating on the component is completely removed.
2. The acid cleaning and stripping process for the metal bonding layer of the blade of the turbine movable blade of the gas turbine as claimed in claim 1, wherein in the step b, the included angle between the sand blasting gun and the sand blasting area of the blade is 30-45 degrees, 40-mesh white corundum is required, and the sand blasting pressure is 0.7-0.8 MPa.
3. The acid washing stripping process of the metal bonding layer of the turbine movable vane blade of the gas turbine as claimed in claim 1, wherein the step c of blocking the cutting hole uses a resin hole blocking method, wherein after a section of the blade root is blocked, the ultraviolet lamp irradiates for 8-13 minutes for curing, then the cooling hole of the blade tip is blocked, and then the curing is carried out.
4. The acid washing stripping process of the metal bonding layer of the turbine movable blade of the gas turbine as claimed in claim 1, wherein in the step d, the blade root without the coating is shielded by using the shielding glue, the shielding glue needs to be uniformly shaken before being used, the blade root is uniformly brushed by using a brush, the next layer can be continuously covered after the previous layer is dried, the 2-4 layers are brushed to meet the requirement of completely covering the blade root, and the shielding glue is noticed to cover the dead angle of the blade root.
5. The process for acid pickling and stripping of metal bonding layers of turbine moving blade blades of a gas turbine as claimed in claim 1, wherein in step e, 3/4% of water is added into an acid pickling tank, 1/4% of hydrochloric acid is slowly added, and finally, 1000ml of catalyst is added.
6. The acid washing stripping process of the metal bonding layer of the turbine movable blade of the gas turbine as claimed in claim 1, wherein the method for judging the residual coating in the step j is judged by color judgment or Seebeck effect, and specifically comprises the following steps:
judging the color of the residual coating: putting the part cleaned by sand blasting into a clean electric furnace, heating to 680 ℃, preserving heat for 1 hour, taking out in time after heat preservation is finished, judging the stripping condition of the coating according to the color of the surface of the part, wherein the color of the base metal is dark blue oxidized at high temperature of metal, and the color of the residual coating is light yellow;
judging the residual coating of the Seebeck effect: residual coatings were identified by using a thermoelectric alloy sorter.
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Cited By (1)
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| CN115537824A (en) * | 2022-10-09 | 2022-12-30 | 广东省科学院新材料研究所 | Solvent for removing coating, method for removing coating and application |
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