CN115652252A - Aluminized protective coating repairing method for multi-connected blade assembly of aero-engine - Google Patents
Aluminized protective coating repairing method for multi-connected blade assembly of aero-engine Download PDFInfo
- Publication number
- CN115652252A CN115652252A CN202211424335.7A CN202211424335A CN115652252A CN 115652252 A CN115652252 A CN 115652252A CN 202211424335 A CN202211424335 A CN 202211424335A CN 115652252 A CN115652252 A CN 115652252A
- Authority
- CN
- China
- Prior art keywords
- blade
- aluminized
- repaired
- aero
- engine
- 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
Abstract
The invention relates to the field of repair processes of aero-engines, in particular to a method for repairing an aluminized protective coating of a multi-blade assembly of an aero-engine, which is low in cost and simple to operate, and comprises the following steps: a. cleaning oil stains on the surface of a part, and determining and marking an area on an aero-engine blade, which needs to be subjected to aluminizing layer repair; b. protecting the surface of the blade without repairing by using a protective adhesive tape; c. removing the surface aluminized layer of the area to be repaired by using a corundum polishing head; d. cleaning the surface of the area to be repaired by water sand blowing; e. preparing aluminized slurry consisting of diethyl n-amyl acetate oxalate, nitrocellulose and aluminum powder, and spraying the aluminized slurry to an area to be repaired by using compressed air; f. after the protective adhesive tape on the blade is removed, the surface of the blade which does not need to be repaired in the step b is checked, and the condition that no aluminizing slurry exists on the surface of the blade which does not need to be repaired is ensured; g. putting the blades into a vacuum furnace for heat treatment; h. and (3) blowing sand by water to clean the hanging ash on the surface of the blade.
Description
Technical Field
The invention relates to the field of aeroengine repair processes, in particular to a method for repairing an aluminized protective coating of a multi-connected blade assembly of an aeroengine.
Background
The multi-connected blade assembly of the aero-engine is oxidized and corroded by high-temperature gas in the using process, and the locally punctiform damage or corrosion phenomenon occurs in the service process, so that the service life is seriously influenced, and therefore, the aluminized layer needs to be restored again in the repair process to achieve the purposes of protecting the blade matrix and prolonging the service life of the blade. The multi-connected blade assembly of the aero-engine is complex in structure and high in assembly precision requirement. In the new product manufacturing process, firstly, single blade rough machining is adopted, then the whole is aluminized, then welding is carried out to form a multi-connected assembly, then, part of size is finely machined, and non-aluminized parts are machined and removed. In the service process, the multi-connected blade has the phenomena of punctiform corrosion damage and punctiform corrosion damage of protective coatings such as aluminizing in local areas, and the like, if the repair cost of a new product is higher, the whole removal and aluminizing repair process again has the following difficulties: 1. in the whole removing and re-aluminizing process, the installation size of the non-aluminized layer part is difficult to ensure, and the phenomenon of size damage and scrap is easily caused because no machining allowance exists; 2. the bulk removal and re-aluminizing process has a greater impact on the substrate. 3. The overall removal and re-aluminizing repair process is complicated, the repair cycle is long, and the cost is relatively high. 4. The protection of the non-aluminized part by the overall removing and aluminizing process is difficult to realize.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for repairing an aluminized protective coating of a multi-blade assembly of an aero-engine, which is low in cost and simple to operate.
The technical scheme adopted by the invention for solving the technical problems is as follows: the aluminized protective coating repairing method for the multi-connected blade assembly of the aero-engine comprises the following steps: a. cleaning oil stains on the surface of a part, and determining and marking an area on an aero-engine blade needing aluminizing layer repair; b. protecting the blade surface which does not need to be repaired by using a protective adhesive tape; c. removing the surface aluminized layer of the area to be repaired by using a corundum polishing head; d. cleaning the surface of the area to be repaired by water sand blowing; e. preparing aluminized slurry consisting of diethyl n-amyl acetate oxalate, nitrocellulose and aluminum powder, and spraying the aluminized slurry to an area to be repaired by using compressed air; f. after the protective adhesive tape on the blade is removed, the blade surface which does not need to be repaired in the step b is checked, and the fact that no aluminizing slurry exists on the blade surface which does not need to be repaired is guaranteed; g. putting the blades into a vacuum furnace for heat treatment; h. and (4) blowing sand by water to clean hanging ash on the surface of the blade.
Furthermore, in the step c, after the removal operation is finished, the existence of corrosion pits and black corrosion products is not allowed.
Furthermore, in the step d, in the sand blowing process, sand blowing is not allowed to be carried out on the part which does not need to be repaired.
Further, in step f, if the aluminized slurry is found to exist on the blade surface which does not need to be repaired after the inspection, the blade surface is wiped by adopting a silk cloth, and the surface is wiped by using acetone.
The beneficial effects of the invention are: 1. the method well solves the problem that the repair of the multi-connected guide blade assembly with a complex structure after service is difficult, adopts the method of locally removing the damaged aluminized coating and preparing the aluminized coating, has little influence on the size of the installation part, and realizes the repair of the coating of the multi-connected guide blade assembly. 2. Compared with the existing method for integrally removing the aluminized layer and re-preparing, the method has the advantages that the damage of the integrally removed aluminized layer to the base body is reduced, the influence on the installation size of the non-aluminized part is small, the repair process and period are shortened, and the service life of the blade of the aero-engine is prolonged. 3. The method does not need complex and expensive equipment, and has the advantages of low cost, simple operation and the like compared with the prior art. 4. The method is used for repairing the aluminized layer of the blade of the aircraft engine, and the aluminized layer has compact tissue, uniform thickness and higher controllability. The design idea of the invention can be effectively popularized to repair of various blades of single-connection or multi-connection blade assemblies of aero-engines, gas turbines and the like, and repair of local seeping layers of other types of complex parts.
Detailed Description
The aluminized protective coating repairing method of the multi-connected blade assembly of the aero-engine comprises the following steps: a. cleaning oil stains on the surface of a part, and determining and marking an area on an aero-engine blade needing aluminizing layer repair; b. protecting the surface of the blade without repairing by using a protective adhesive tape; c. removing the surface aluminized layer of the area to be repaired by using a corundum polishing head; d. cleaning the surface of the area to be repaired by water sand blowing; e. preparing aluminized slurry consisting of diethyl n-amyl acetate oxalate, nitrocellulose and aluminum powder, and spraying the aluminized slurry to an area to be repaired by using compressed air; f. after the protective adhesive tape on the blade is removed, the surface of the blade which does not need to be repaired in the step b is checked, the surface of the blade which does not need to be repaired is ensured not to have aluminized slurry, and the non-aluminized part is not sprayed with the aluminized slurry, so that the phenomenon of aluminizing leakage is avoided, particularly, the size of the installation edge is well maintained, and the assembly size is not influenced; g. putting the blades into a vacuum furnace for heat treatment; h. and (3) cleaning the surface of the blade from the hanging ash by water-blown sand, wherein the pressure time of the water-blown sand is controlled, and the principle that the thickness of the coating is not influenced and the hanging ash is not generated is taken as a principle. .
Because the whole aluminized layer removing cost of the multi-blade assembly of the aero-engine is high and the aluminized layer removing difficulty is high, the method for repairing the aluminized protective coating can solve the problem of repairing the local aluminized layer of the multi-blade assembly of the aero-engine, and the prepared aluminized layer has the advantages of compact structure, uniform thickness, low cost, low operation difficulty and the like. Meanwhile, the oxidation resistance and corrosion resistance of the multi-blade assembly of the aero-engine in the using process are improved, the blade matrix is protected, and the high-temperature service life of the multi-blade assembly of the aero-engine can be effectively prolonged.
In the step c, in order to ensure that the polishing operation of the polishing head is in place, after the polishing operation is finished, corrosion pits and black corrosion products are not allowed to exist, so that the influence of the corrosion pits and the black corrosion products on subsequent spraying repair is prevented. In addition, in the step d, the sand blowing process is required not to be allowed to carry out sand blowing on the parts which do not need to be repaired, so that the surfaces of the parts which do not need to be repaired are prevented from being damaged. And f, after inspection, if aluminized slurry exists on the blade surface which does not need to be repaired, wiping the blade surface by adopting silk cloth, and wiping the surface by using acetone.
Examples
The aluminized protective coating of a multi-blade assembly of an aero-engine is repaired according to the method, and the related steps are as follows: (1) Firstly, fault detection is carried out according to standard requirements, the other technical requirements of the part meet the requirements, and the local damage part of the aluminized layer is determined and marked. The spot corrosion of the aluminized layer on the surface of the leaf basin of the part exceeds the standard, aluminizing needs to be supplemented, and the rest parts of the base material meet the standard requirements. The parts such as the mounting edge of the part are not aluminized, and the requirement of assembly fit size exists.
(2) Protecting the surface of the non-repaired part of the blade by using an adhesive tape; mainly protects the blade back, the mounting edge and the non-runner surface.
(3) Polishing the aluminized layer on the surface of the part to be repaired by using a corundum polishing head; the presence of a small thickness of the original aluminized layer is allowed, but corrosion pits and black corrosion products are not allowed, which affect the new coating adhesion.
(4) And (4) blowing sand by water to clean the surface to be repaired. The sand blowing process does not allow for sand blowing of non-repaired sites.
(5) Preparing n-amyl acetate diethyl oxalate, nitrocellulose and aluminum powder according to a proportion to prepare slurry. And spraying the aluminizing agent to the part to be repaired by using compressed air. The spraying times and the thickness are controlled according to the thickness requirement of the product.
(6) And removing the blade protective adhesive tape, checking the rest aluminized parts which do not need to be repaired and do not allow aluminized slurry, if leaked spraying exists, wiping the aluminized parts by adopting silk cloth and the like, and wiping the surfaces by using acetone.
(7) And putting the blade into a vacuum furnace for heat treatment. The non-aluminized part is not sprayed with aluminized slurry, so that the aluminized leakage phenomenon cannot occur, and particularly, the size of the mounting edge is kept well without influencing the assembly size;
(8) And (3) blowing sand by water to clean loose hanging ash on the surface of the blade. The pressure time of water sand blowing is controlled, and the principles of not influencing the thickness of a coating and not hanging ash are taken as the principles.
By the repair method, the aluminized layer with uniform thickness and tissue can be prepared, the oxidation resistance and corrosion resistance of the multi-blade assembly of the aero-engine in the use process are improved, and the blade matrix is protected. Meanwhile, the repair cost and difficulty are reduced, and the high-temperature service life of the multi-blade assembly of the aero-engine is effectively prolonged.
Claims (4)
1. The method for repairing the aluminized protective coating of the multi-connected blade assembly of the aero-engine is characterized by comprising the following steps:
a. cleaning oil stains on the surface of a part, and determining and marking an area on an aero-engine blade needing aluminizing layer repair;
b. protecting the surface of the blade without repairing by using a protective adhesive tape;
c. removing the surface aluminized layer of the area to be repaired by using a corundum polishing head;
d. cleaning the surface of the area to be repaired by water sand blowing;
e. preparing aluminized slurry consisting of diethyl n-amyl acetate oxalate, nitrocellulose and aluminum powder, and spraying the aluminized slurry to an area to be repaired by using compressed air;
f. after the protective adhesive tape on the blade is removed, the surface of the blade which does not need to be repaired in the step b is checked, and the condition that no aluminizing slurry exists on the surface of the blade which does not need to be repaired is ensured;
g. putting the blades into a vacuum furnace for heat treatment;
h. and (3) blowing sand by water to clean the hanging ash on the surface of the blade.
2. The method for repairing the aluminized protective coating of the multi-blade assembly of the aero-engine as claimed in claim 1, wherein: in step c, after the removal operation is finished, corrosion pits and black corrosion products are not allowed to exist.
3. The method for repairing the aluminized protective coating of the multi-connected blade assembly of the aero-engine as claimed in claim 1 or 2, wherein: and d, in the sand blowing process, the part which does not need to be repaired is not allowed to be blown with sand.
4. The method for repairing the aluminized protective coating of the multi-connected blade assembly of the aero-engine as claimed in claim 1 or 2, wherein: and f, after inspection, if aluminized slurry exists on the surface of the blade which does not need to be repaired, wiping the blade by adopting silk cloth, and wiping the surface by using acetone.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211424335.7A CN115652252A (en) | 2022-11-15 | 2022-11-15 | Aluminized protective coating repairing method for multi-connected blade assembly of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211424335.7A CN115652252A (en) | 2022-11-15 | 2022-11-15 | Aluminized protective coating repairing method for multi-connected blade assembly of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115652252A true CN115652252A (en) | 2023-01-31 |
Family
ID=85021231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211424335.7A Pending CN115652252A (en) | 2022-11-15 | 2022-11-15 | Aluminized protective coating repairing method for multi-connected blade assembly of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115652252A (en) |
-
2022
- 2022-11-15 CN CN202211424335.7A patent/CN115652252A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110480254B (en) | Method for repairing casting defects of aluminum-silicon alloy shell of aircraft fuel system | |
| US5972424A (en) | Repair of gas turbine engine component coated with a thermal barrier coating | |
| JP3346988B2 (en) | Method for removing excess overlay coat from inside cooling holes of aluminide-coated gas turbine engine parts and gas turbine engine parts treated by the method | |
| CA2330218C (en) | Method of removing a thermal barrier coating | |
| JP4667714B2 (en) | Removal method of ceramic film | |
| US7008553B2 (en) | Method for removing aluminide coating from metal substrate and turbine engine part so treated | |
| EP1694463B1 (en) | Process for removing thermal barrier coatings | |
| US20080028605A1 (en) | Weld repair of metallic components | |
| US20100257733A1 (en) | High pressure single crystal turbine blade tip repair with laser cladding | |
| US6544346B1 (en) | Method for repairing a thermal barrier coating | |
| CN111020449A (en) | Size repairing method for abrasion of high-temperature alloy disc shaft of aero-engine | |
| CN109338271A (en) | A kind of aero-engine titanium alloy component seam allowance repairing sizes method | |
| CN106521487A (en) | Remanufacturing method for blade of titanium alloy gas compressor in middle service period | |
| CN111250368A (en) | Preparation process of polyphenyl ester sealing coating for aero-engine case parts | |
| CN111394680A (en) | Processing method of thermal spraying coating for repairing part size | |
| EP3406759A1 (en) | Green repair of oxidation and corrosion resistant coatings | |
| CN115652252A (en) | Aluminized protective coating repairing method for multi-connected blade assembly of aero-engine | |
| JP2008240563A (en) | Gas turbine high-temperature component repairing method, and gas turbine high-temperature component | |
| CN110592520A (en) | Remanufacturing and repairing method for blade boss of aero-engine compressor | |
| CN110905607A (en) | Control method for tip clearance of titanium alloy compressor | |
| EP2935834B1 (en) | Coating process for gas turbine engine component with cooling holes | |
| JP2012527537A (en) | Method for improving the corrosion and oxidation resistance of the lower platform region of a gas turbine blade | |
| EP3748125A1 (en) | Methods for repairing a multi-layer coated component | |
| US20170369981A1 (en) | Treated gas turbine components and processes of treating gas turbine systems and gas turbine components | |
| CN114196948A (en) | Processing method of high-temperature protective coating on high-temperature alloy of aircraft engine |
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 |