CN117325084A - Treatment method for leakage and seepage of surface coating of turbine blade - Google Patents
Treatment method for leakage and seepage of surface coating of turbine blade Download PDFInfo
- Publication number
- CN117325084A CN117325084A CN202311252523.0A CN202311252523A CN117325084A CN 117325084 A CN117325084 A CN 117325084A CN 202311252523 A CN202311252523 A CN 202311252523A CN 117325084 A CN117325084 A CN 117325084A
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- China
- Prior art keywords
- blade
- coating
- leakage
- turbine blade
- cleaned
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- Pending
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- 238000000576 coating method Methods 0.000 title claims abstract description 51
- 239000011248 coating agent Substances 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000004140 cleaning Methods 0.000 claims abstract description 15
- 238000005488 sandblasting Methods 0.000 claims abstract description 13
- 230000007797 corrosion Effects 0.000 claims abstract description 8
- 238000005260 corrosion Methods 0.000 claims abstract description 8
- 239000011259 mixed solution Substances 0.000 claims abstract description 8
- 239000004576 sand Substances 0.000 claims abstract description 7
- 238000001035 drying Methods 0.000 claims abstract description 4
- 238000007664 blowing Methods 0.000 claims abstract description 3
- 238000005238 degreasing Methods 0.000 claims abstract description 3
- VEXZGXHMUGYJMC-UHFFFAOYSA-N Hydrochloric acid Chemical compound Cl VEXZGXHMUGYJMC-UHFFFAOYSA-N 0.000 claims description 21
- 230000000694 effects Effects 0.000 claims description 9
- 239000011159 matrix material Substances 0.000 claims description 7
- 238000010790 dilution Methods 0.000 claims description 3
- 239000012895 dilution Substances 0.000 claims description 3
- 239000003112 inhibitor Substances 0.000 claims description 3
- 230000008901 benefit Effects 0.000 abstract description 8
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 abstract description 4
- 229910052759 nickel Inorganic materials 0.000 abstract description 2
- 229910000601 superalloy Inorganic materials 0.000 abstract description 2
- BAUYGSIQEAFULO-UHFFFAOYSA-L iron(2+) sulfate (anhydrous) Chemical compound [Fe+2].[O-]S([O-])(=O)=O BAUYGSIQEAFULO-UHFFFAOYSA-L 0.000 abstract 1
- 229910000359 iron(II) sulfate Inorganic materials 0.000 abstract 1
- 238000000151 deposition Methods 0.000 description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 6
- 239000002253 acid Substances 0.000 description 5
- 230000008021 deposition Effects 0.000 description 5
- 239000012720 thermal barrier coating Substances 0.000 description 5
- 239000000919 ceramic Substances 0.000 description 4
- 239000002245 particle Substances 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 238000005507 spraying Methods 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 229910002515 CoAl Inorganic materials 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 239000003245 coal Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 238000002386 leaching Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 229910000951 Aluminide Inorganic materials 0.000 description 1
- 229910000789 Aluminium-silicon alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 238000005229 chemical vapour deposition Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 150000004673 fluoride salts Chemical class 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000001902 propagating effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- 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
-
- 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
- B08B3/08—Cleaning involving contact with liquid the liquid having chemical or dissolving effect
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a treatment method for the leakage and permeation of a coating on the surface of a turbine blade, which comprises the following steps of S1, respectively removing the leakage and permeation coating on the surface of the turbine blade by adopting a mode of mixed solution of concentrated HCl and FeSO4+HCl+H2O; s2, carrying out surface degreasing treatment on the blade, drying, and carrying out 60# and 320# dry sand blowing treatment; s3, cleaning the blade subjected to sand blasting, wherein the technological parameters are 30 ℃/15min, detecting whether the cleaned blade is cleaned again, and if not, cleaning the cleaned blade with compressed air again, so that the blade is dried rapidly, and corrosion is prevented. The invention realizes the rapid removal of the coating at the leakage position of the outer surface of the nickel-based superalloy blade, and the coating is removed without secondary pollution. Meanwhile, the scrapping and the loss of parts are reduced, and the economic benefit is improved.
Description
Technical Field
The invention belongs to the field of blade surface coating treatment, and particularly relates to a treatment method for leakage and seepage of a turbine blade surface coating.
Background
With the development of technology, thermal barrier coatings are increasingly applied to the most severe high-temperature environments of aircraft and industrial engines, the durability of the engines can be improved by reducing the surface temperature of rear end parts of the engines, and the use of the thermal barrier coatings not only improves the temperature of cooling gas inside the high-temperature parts, but also isolates a part of service temperature of outer surfaces, so that an advanced gas turbine can operate in the high-temperature environments even in environments exceeding the self-melting point temperature, thereby obviously improving the efficiency and performance of the engines.
The thermal barrier coating must be able to withstand the harsh environments of high temperatures, large temperature gradients, complex stress conditions and corrosive environments, and since the 70 s of the 20 th century, the working center of gravity for the development of coatings has been on the coating and diffusion coatings, wherein the aluminide coating of diffusion coatings has been the most stable way to address the high temperature service environment of turbine blades, improving the durability of turbine blades, including three ways of embedding, deposition on coating and chemical vapor deposition.
Although thermal barrier coatings are the best method to increase the service life of engine rear end parts, excessive deposition at locations where turbine blades do not need to be deposited can have a counter effect because turbine blades are subject to not only ultra-high temperatures, high corrosion and complex alternating loads, but also creep toughness of the material in high temperature environments, where excessive deposition is not required can increase the strength of the deposited locations, while decreasing the toughness of the deposited locations, resulting in cracks at the coated locations propagating first to the substrate under alternating loads, causing the part to fail.
In order to avoid depositing the coating at the position where deposition is not needed, proper protection of the turbine blade is needed before deposition, but due to unreasonable test protection and improper treatment, an unnecessary thermal barrier coating is inevitably introduced, if the whole is scrapped, immeasurable economic loss is inevitably brought, if a proper method for repairing the coating can be adopted, huge economic loss can be recovered, and time and experience wasted in the earlier stage can be avoided, so that immeasurable economic benefit is achieved.
The conventional method for removing the surface coating of the turbine blade mainly comprises a sand blasting method and solid CO 2 The spraying method, the high-pressure kettle peeling method, the high-pressure water gun method and the laser cleaning method, wherein the sand blasting method is a mechanical removal method, and the violent removal method is adopted, so that the device has the main advantages of simple operation, easy removal, capability of generating a relatively clean surface, insufficient uniformity of the removed coating and easiness in thinning the thickness of the blade. Solid CO 2 The spraying method is to use a spray gun for spraying solid carbon dioxide to carry out sand blasting treatment on the ceramic layer, and the method has the advantages that compared with other violent removing methods, CO 2 The temperature of the particles is very low, the particles have a unique thermodynamic induction surface mechanism, and no pollution is introduced, but the defects are low removal rate and high cost. The chemical stripping method is to put the turbine blade into acid fluoride salt and remove the ceramic layer by water stripping, and has the advantages of being capable of completely removing the ceramic layer, and being less in cost and time, but being easy to damage other positions of the blade parts. The high pressure water removal method generally comprises two forms, one with sand and one without sand, and has the advantages of high removal speed with sand, good effect, easy pollution introduction, time-consuming cleaning, low removal speed without sand, clean surface and difficult pollution introduction. The laser cleaning method can selectively remove the coatings at different positions of the blade, but the ceramic layer is not removed well, and the high-pressure water removing method is combined to complete the removal and cleaning of the coatings.
Disclosure of Invention
The invention aims at a treatment method for leakage of a turbine blade coating, by which not only the redundant CoAl coating at the tenon root and tenon tooth of a turbine blade can be removed, but also excessive dimensional deviation and surface damage are not caused.
A treatment method for leakage of a coating on the surface of a turbine blade comprises the following steps:
s1, adopting concentrationHCl and FeSO 4 +HCl+H 2 Removing the leakage coating on the surface of the turbine blade in the mode of O mixed solution;
s2, carrying out surface degreasing treatment on the blade, drying, and carrying out 60# and 320# dry sand blowing treatment;
s3, cleaning the blade subjected to sand blasting, wherein the technological parameters are 30 ℃/15min, detecting whether the cleaned blade is cleaned again, and if not, cleaning the cleaned blade with compressed air again, so that the blade is dried rapidly, and corrosion is prevented.
Further, feSO in S1 4 +HCl+H 2 The mixed solution of O slightly corrodes the matrix, and the removal effect is better by adopting concentrated hydrochloric acid with a certain dilution ratio or concentrated hydrochloric acid added with a corrosion inhibitor.
The invention has the beneficial effects that: the method can effectively remove excessive CoAl coating or AlSi coating deposited on the tenon and tenon tooth positions on the surface of the turbine blade, and can not excessively damage the turbine blade matrix to influence the continuous use of the subsequent turbine blade. The method not only remedies the unqualified turbine blade of the coating, but also realizes the rapid removal of the coating at the leakage position of the outer surface of the nickel-based superalloy blade, namely, the coating is removed without introducing secondary pollution, thereby preventing the turbine blade from being scrapped, reducing economic loss, improving the yield and bringing certain economic benefit.
Drawings
FIG. 1 is a physical view of a leaky leaf according to the invention;
FIG. 2 is a graph of the thickness of the original coating of a leaky bucket according to the invention;
FIG. 3 is a graph of the thickness of a grit blasted coating of the present invention;
FIG. 4 is a graph of the thickness of a coating treated by the acid leaching method of the present invention;
FIG. 5 is a coating diagram of a laser cleaning process of the present invention.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
In combination with the detailed and clear description of the physical drawings, the thickness drawings and the specific implementation process in the examples 1-2 of the invention, the specific implementation is carried out according to the following steps, and in order to realize the removal of the leakage coating on the surface of the nickel-base alloy blade, a sand blasting method is adopted to remove part of the coating, but a large amount of burr tissues are formed on the surface of the coating due to uneven shot particles, the removal effect is poor, some positions are removed, and the coating still remains at some positions.
In order to remove the leakage coating on the surface of the base alloy blade, the leakage coating on the surface of the turbine blade is removed by adopting a laser cleaning mode, the effect of laser cleaning treatment is not ideal, the turbine blade is required to be cleaned by combining a water pressure method, and meanwhile, the laser cleaning can burn the coating on the surface of the turbine blade at a high temperature, and because the leakage coating is cleaned in a large area, the high-temperature oxidized surface is possibly introduced in advance due to insufficient uniformity of the coating, so that the service life is reduced.
The invention adopts concentrated HCl and FeSO 4 +HCl+H 2 O mixed solution mode is used for respectively removing leakage coating on the surface of turbine blade, and research shows that HCl is adopted to remove relatively better effect, and FeSO 4 +HCl+H 2 The mixed solution of O slightly corrodes the matrix, if the mixed solution can adopt concentrated hydrochloric acid with a certain dilution ratio or concentrated hydrochloric acid added with a corrosion inhibitor, the removal effect is better, the matrix is not damaged too much, and the phenomenon of corroding the matrix is not caused. In order to realize the mode of combining weak acid and sand blasting, the blade needs to be subjected to surface oil removal treatment firstly, 60# +320# dry sand blasting treatment is carried out after drying for about 1min, the blade after sand blasting treatment is subjected to water cleaning, the technological parameters are 30 ℃/15min, the cleaned blade is detected again to determine whether the blade is cleaned, and if the blade is not cleaned, the cleaned blade is purged by compressed air, so that the blade is dried rapidly, and corrosion is prevented.
In conclusion, the effect of removing the surface coating by adopting the mode of combining weak acid and sand blasting is better, the purpose of removing the surface seepage coating is achieved, the pollution of excessively eroding a matrix is not introduced, meanwhile, the sand blasting treatment can also smooth the surface roughness of the corroded blade, the scrapping and the loss of turbine blade parts are reduced, and the economic benefit is improved.
TABLE 1 leakage untreated coating Table (um)
Table 2 sand blasting coating table (um)
TABLE 3 acid leaching treatment coating table (um)
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. The treatment method for the leakage of the surface coating of the turbine blade is characterized by comprising the following steps of:
s1, adopting concentrated HCl and FeSO 4 +HCl+H 2 Removing the leakage coating on the surface of the turbine blade in the mode of O mixed solution;
s2, carrying out surface degreasing treatment on the blade, drying, and carrying out 60# and 320# dry sand blowing treatment;
s3, cleaning the blade subjected to sand blasting, wherein the technological parameters are 30 ℃/15min, detecting whether the cleaned blade is cleaned again, and if not, cleaning the cleaned blade with compressed air again, so that the blade is dried rapidly, and corrosion is prevented.
2. The method for treating leakage of a surface coating of a turbine blade according to claim 1, wherein the FeSO in S1 4 +HCl+H 2 The mixed solution of O slightly corrodes the matrix, and the removal effect is better by adopting concentrated hydrochloric acid with a certain dilution ratio or concentrated hydrochloric acid added with a corrosion inhibitor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311252523.0A CN117325084A (en) | 2023-09-26 | 2023-09-26 | Treatment method for leakage and seepage of surface coating of turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311252523.0A CN117325084A (en) | 2023-09-26 | 2023-09-26 | Treatment method for leakage and seepage of surface coating of turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117325084A true CN117325084A (en) | 2024-01-02 |
Family
ID=89276548
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311252523.0A Pending CN117325084A (en) | 2023-09-26 | 2023-09-26 | Treatment method for leakage and seepage of surface coating of turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117325084A (en) |
-
2023
- 2023-09-26 CN CN202311252523.0A patent/CN117325084A/en active Pending
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