CN115652314A - Chemical removal method for NiCrAlYSi coating on nickel-based superalloy turbine blade - Google Patents
Chemical removal method for NiCrAlYSi coating on nickel-based superalloy turbine blade Download PDFInfo
- Publication number
- CN115652314A CN115652314A CN202211361684.9A CN202211361684A CN115652314A CN 115652314 A CN115652314 A CN 115652314A CN 202211361684 A CN202211361684 A CN 202211361684A CN 115652314 A CN115652314 A CN 115652314A
- Authority
- CN
- China
- Prior art keywords
- coating
- nicralysi
- nickel
- turbine blade
- based superalloy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- ing And Chemical Polishing (AREA)
Abstract
The invention belongs to the technical field of chemical removal of coatings, and particularly relates to a chemical removal method of a NiCrAlYSi coating on a nickel-based superalloy turbine blade. The technical scheme of the invention is as follows: the chemical NiCrAlYSi coating removing method on the nickel-based high-temperature alloy turbine blade comprises the steps of soaking the nickel-based high-temperature alloy turbine blade with the NiCrAlYSi coating in an acid solution for 10-30 min at the working temperature of room temperature-70 ℃; the formula of the acid solution is as follows: nitric acid with the concentration of 100-300 mL/L and sulfamic acid with the concentration of 80-200 g/L. The chemical removal method of the NiCrAlYSi coating on the nickel-based superalloy turbine blade provided by the invention can effectively remove the coating, and cannot corrode a base body and cause the base body to be thinned.
Description
Technical Field
The invention belongs to the technical field of chemical removal of coatings, and particularly relates to a chemical removal method of a NiCrAlYSi coating on a nickel-based superalloy turbine blade.
Background
The turbine blade is subjected to impact and erosion of high-temperature gas for a long time, and the service environment is very severe. The NiCrAlYSi coating is widely applied to hot end parts of aeroengines to improve the high-temperature oxidation resistance and corrosion resistance of the aeroengines. However, if the equipment state of the NiCrAlYSi coating is unstable in the plating process, the appearance or performance of the coating exceeds the standard, the coating inevitably falls into blocks or peels locally in the test run and use processes, and the coating is damaged due to accidental collision of parts in the turnover, assembly and other processes, and the coating which does not meet the requirements needs to be removed and re-plated.
At present, the NiCrAlYSi coating is usually removed by adopting a sand blowing or manual polishing and repairing method, and the mechanical method is easy to cause the wall thickness of the blade to be thinned and the size of the blade to be not in accordance with the requirement; if the NiCrAlYSi coating is removed by a chemical method, particularly the NiCrAlYSi coating on the nickel-based superalloy substrate is removed, the NiCrAlYSi coating is removed and the blade substrate is corroded at the same time because the components of the nickel-based superalloy and the NiCrAlYSi are similar.
Disclosure of Invention
The invention provides a chemical removal method of a NiCrAlYSi coating on a nickel-based superalloy turbine blade, which can effectively remove the coating and can not corrode a base body and cause the base body to be thinned.
The technical scheme of the invention is as follows: the chemical NiCrAlYSi coating removing method on the nickel-based high-temperature alloy turbine blade comprises the steps of soaking the nickel-based high-temperature alloy turbine blade with the NiCrAlYSi coating in an acid solution for 10-30 min at the working temperature of room temperature-70 ℃; the formula of the acid solution is as follows: nitric acid with the concentration of 100-300 mL/L and sulfamic acid with the concentration of 80-200 g/L.
The invention has the beneficial effects that: according to the invention, by controlling the technological parameters such as soaking time, working temperature and the like, the removal rate of the coating can be effectively controlled, and the base body cannot be corroded to cause the thinning of the base body, so that the ultra-poor thinning of the wall thickness of the blade caused by coating removal by the existing mechanical method and the scrapping of the blade are avoided; the method has low requirement on required equipment, is simple to operate and only needs water bath heating.
Drawings
FIG. 1 is a turbine blade cross-sectional micro-topography prior to coating removal;
FIG. 2 is a turbine blade cross-sectional micro-topography after removal of the coating.
Detailed Description
The chemical removal method of the NiCrAlYSi coating on the nickel-based superalloy turbine blade is characterized in that a turbine blade base material DZ125 specifically comprises the following steps:
the method comprises the following steps: wax injection protection is carried out on the inner cavity of the blade;
step two: preparing an acidic solution, wherein: 150mL/L nitric acid and 80g/L sulfamic acid;
step three: soaking the leaves in an acid solution at 23 ℃;
step four: taking out the blades every 5min to observe the surface state according to the reaction condition in the soaking process;
step five: and after the blade coating is removed, removing wax.
Claims (1)
1. The chemical removal method of the NiCrAlYSi coating on the nickel-based superalloy turbine blade is characterized in that an acid solution is used for soaking the nickel-based superalloy turbine blade with the NiCrAlYSi coating, the soaking time in the acid solution is 10-30 min, and the working temperature is room temperature-70 ℃; the formula of the acid solution is as follows: nitric acid with the concentration of 100-300 mL/L and sulfamic acid with the concentration of 80-200 g/L.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211361684.9A CN115652314A (en) | 2022-11-02 | 2022-11-02 | Chemical removal method for NiCrAlYSi coating on nickel-based superalloy turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211361684.9A CN115652314A (en) | 2022-11-02 | 2022-11-02 | Chemical removal method for NiCrAlYSi coating on nickel-based superalloy turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115652314A true CN115652314A (en) | 2023-01-31 |
Family
ID=84995645
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211361684.9A Pending CN115652314A (en) | 2022-11-02 | 2022-11-02 | Chemical removal method for NiCrAlYSi coating on nickel-based superalloy turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115652314A (en) |
-
2022
- 2022-11-02 CN CN202211361684.9A patent/CN115652314A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5643474A (en) | Thermal barrier coating removal on flat and contoured surfaces | |
| EP1010776B1 (en) | Caustic process for replacing thermal barrier coatings | |
| US7270764B2 (en) | Method for removing aluminide coating from metal substrate and turbine engine part so treated | |
| JP4870254B2 (en) | Method for removing an aluminide coating from a substrate | |
| US6210488B1 (en) | Method of removing a thermal barrier coating | |
| EP1803838B1 (en) | Method of selectively stripping a metallic coating | |
| US4317685A (en) | Method for removing a scale from a superalloy surface | |
| JP2002053985A (en) | Method for removing film from substrate and composition used therefor | |
| EP1930477A1 (en) | Method for selectively removing coatings from metal substrates | |
| CA2921814C (en) | Methods for removing barrier coatings, bondcoat and oxide layers from ceramic matrix composites | |
| CN101692382B (en) | Hydrogen removing method for radiator for transformer | |
| CN110735145A (en) | method for removing NiCrAlYSi/YSZ thermal barrier coating of high-pressure turbine blade | |
| US20060231123A1 (en) | Method for removing a layer area of a component | |
| US5248381A (en) | Etch solution and associated process for removal of protective metal layers and reaction deposits on turbine blades | |
| US6953533B2 (en) | Process for removing chromide coatings from metal substrates, and related compositions | |
| CN115652314A (en) | Chemical removal method for NiCrAlYSi coating on nickel-based superalloy turbine blade | |
| CN105420744A (en) | Method for removing ceramic surface layer of thermal barrier coating of turbine blade | |
| CN114392980A (en) | Molten salt preparation process and cleaning process for removing TBC ceramic coating | |
| CN114107993A (en) | Acid washing stripping process for metal bonding layer of turbine moving blade of gas turbine | |
| CN109321902B (en) | Method for electroplating chromium on powder metallurgy high-temperature alloy | |
| WO2004031448A1 (en) | Aqueous composition for the chemical removal of metallic surfacing present on turbine blades, and its use | |
| EP2128307A1 (en) | Method for removing a protective coating from a turbine blade airfoil in a repair process | |
| CN117448836A (en) | Method for removing NiCrAlYSi coating on surface of turbine blade | |
| CN114075690B (en) | Method for electrochemically removing MCrAlY coating | |
| JPS6160731B2 (en) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |