CN110592520A - Remanufacturing and repairing method for blade boss of aero-engine compressor - Google Patents
Remanufacturing and repairing method for blade boss of aero-engine compressor Download PDFInfo
- Publication number
- CN110592520A CN110592520A CN201910848544.6A CN201910848544A CN110592520A CN 110592520 A CN110592520 A CN 110592520A CN 201910848544 A CN201910848544 A CN 201910848544A CN 110592520 A CN110592520 A CN 110592520A
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- China
- Prior art keywords
- blade
- boss
- spraying
- compressor
- compressor blade
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- 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.)
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Classifications
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C29/00—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides
- C22C29/02—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides
- C22C29/06—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds
- C22C29/067—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds comprising a particular metallic binder
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C29/00—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides
- C22C29/02—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides
- C22C29/06—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds
- C22C29/08—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides based on carbides or carbonitrides based on carbides, but not containing other metal compounds based on tungsten carbide
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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
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
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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
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
-
- 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
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/126—Detonation spraying
-
- 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
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/18—After-treatment
Abstract
The invention discloses a remanufacturing and repairing method for a lug boss of a compressor blade of an aircraft engine, which relates to the field of maintenance of the blade of the aircraft engine and comprises the following steps: s1, protection: protecting the non-spraying surface of the boss part of the compressor blade by using a high-temperature pressure-sensitive adhesive tape and a copper wire winding mode; s2, coarsening: carrying out sand blasting and coarsening treatment on the worn part of the lug boss of the compressor blade until the worn surface has no obvious metal luster; s3, ash removal and inspection: blowing out residual sand or floating ash on the sand blasting surface by using compressed air, checking whether protective measures are intact or not, and if the protective measures are damaged, carrying out re-protection; s4, spraying: the blade is clamped in a clamp which horizontally reciprocates, powder melted by an explosion spray gun is sprayed to a lug boss of the blade of the gas compressor through a window on the clamp, the thickness of the coating of the lug boss of the blade of the gas compressor is measured in real time in the spraying process, when the thickness of the coating meets the process requirement, the spraying is stopped, and the blade is dismounted.
Description
Technical Field
The invention relates to the field of maintenance of aero-engine blades, in particular to a remanufacturing and repairing method for a boss of an aero-engine compressor blade.
Background
The low-pressure compressor blade is a key part of an aeroengine, and a damping boss is generally designed on a rotor blade of the low-pressure compressor in order to reduce vibration caused by combined action of several forces such as centrifugal force, aerodynamic bending moment and the like when the low-pressure compressor blade rotates at high speed. After the aircraft engine is in service for a long time, the size of the damping lug boss of the blade is out of tolerance due to abrasion, and the size of the lug boss needs to be repaired in the subsequent overhaul process so as to meet the subsequent use requirement.
At present, when a shock absorption boss of a compressor blade is repaired, the size of the shock absorption boss is generally repaired by a method of brazing a hard wear-resistant layer. However, the brazing process of the boss wear-resistant layer is difficult to control due to the defects of large heat input amount, uncontrollable hard phase distribution of the wear-resistant layer and the like in the brazing process, and the mechanical property of the base body and the wear-resistant property of the boss are easily reduced due to overheating of the base body and uneven hard phase distribution. Therefore, the method for repairing the lug boss of the compressor blade in a green, efficient, small heat input and strong controllability mode is urgently needed.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a remanufacturing and repairing method for a blade boss of an aircraft engine compressor, which has the advantages of simple process flow, small heat input, strong controllability, high production efficiency and strong wear resistance of a repaired blade.
The purpose of the invention is realized by the following technical scheme: a remanufacturing and repairing method for a lug boss of a blade of an aircraft engine compressor comprises the following steps:
s1, protection: protecting the non-spraying surface of the boss part of the compressor blade by using a high-temperature pressure-sensitive adhesive tape and a copper wire winding mode;
s2, coarsening: carrying out sand blasting and coarsening treatment on the worn part of the lug boss of the compressor blade until the worn surface has no obvious metal luster;
s3, ash removal and inspection: blowing out residual sand or floating ash on the sand blasting surface by using compressed air, checking whether protective measures are intact or not, and if the protective measures are damaged, carrying out re-protection;
s4, spraying: the blade is clamped in a clamp which horizontally reciprocates, powder melted by an explosion spray gun is sprayed to a lug boss of the blade of the gas compressor through a window on the clamp, the thickness of the coating of the lug boss of the blade of the gas compressor is measured in real time in the spraying process, when the thickness of the coating meets the process requirement, the spraying is stopped, the blade is dismounted,
s5, post-processing: and removing the protective adhesive tape, cleaning the residual coating of the transition area, and polishing the lug boss of the compressor blade to the size required by assembly by using an abrasive belt polisher.
Further, the powder components include: WC: 70-78%, Co 20-25%, and the balance.
Further, the parameters of the spraying process are as follows: oxygen flow rate: 32.5-38.5 grids, liquefied petroleum gas flow: 22-25 grids, powder feeding flow: 3-8 grids, oxygen pressure: 0.11-0.13 MPa, liquefied petroleum gas pressure: 0.15 to 0.19 MPa.
Further, the frequent emission of the explosion spraying spray gun is as follows: 4 times/second
Further, before protection in step S1, cleaning and polishing are also included,
the cleaning comprises the following steps: cleaning a boss part of a compressor blade by using acetone to remove dirt on the surface of the boss;
the polishing comprises the following steps: and polishing the wear surface of the lug boss of the compressor blade by using a diamond grinding wheel to repair and level the wear surface and remove oxides on the repaired surface.
The invention has the following advantages: the mode of explosion spraying of hard wear-resistant alloy is adopted to remanufacture and repair the lug boss of the compressor blade, the process flow is simple, the heat input is small, the controllability is strong, the production efficiency is high, the repaired blade has strong wear resistance, and the method can be applied to the size repair of the damping lug boss of the blade of the compressor of most aero-engines.
Drawings
FIG. 1 is a schematic view of a clamp according to an embodiment of the present invention;
FIG. 2 is an enlarged view of a portion of the clip according to an embodiment of the present invention.
In the figure: the method comprises the following steps of 1-compressor blades, 2-baffle plates with spraying windows, 3-supports, 4-compressor blade body baffle plates, 5-reciprocating travelling mechanism mounting seats, 6-compressor blade bosses and 7-bosses to be sprayed.
Detailed Description
The invention will be further described with reference to the accompanying drawings, but the scope of the invention is not limited to the following.
The method for repairing the dimensions of the boss part of the secondary blade of the compressor comprises the following specific steps:
(1) dipping the white silk cloth in alcohol, and wiping the boss to remove oil stains on the boss.
(2) And a high-temperature pressure-sensitive adhesive tape is used for protecting the non-spraying area of the boss of the secondary blade of the compressor in a manner of being wound by a copper wire, and only the boss surface of the position to be sprayed is leaked.
(3) Coarsening a convex table surface to be sprayed by No. 46 white corundum, wherein the sand blasting pressure is 0.4MPa, and the sand blasting angle is 80。The sand blasting distance is 120mm, the spray gun is uniformly moved in the sand blasting process, and the parts are subjected to sand blasting treatment layer by layer in a covering mode until the surface to be sprayed has no obvious metal luster.
(4) The method comprises the steps of removing residual sand and floating ash on the surface to be sprayed of a part by using clean and dry compressed air, clamping a blade of an air compressor in a clamp shown in figure 1, fixing the clamp on a reciprocating horizontal travelling mechanism through a clamp 5, and setting the travelling speed of the travelling mechanism to be 15 mm/s. During spraying, explosive spraying powder is sprayed onto the boss 7 to be sprayed through the window 2, and the other boss of the compressor blade is supported through the window 3 to bear the impact force of the explosive spraying. The blade body baffle 4 protects the blade body of the compressor blade. The whole mechanism reciprocates to realize one-time spraying of a plurality of blades.
(5) Starting the explosion spraying equipment for spraying, wherein the spraying process parameters are as follows: the parameters of the spraying process are as follows: oxygen flow rate: 35 grids, liquefied petroleum gas flow: 24 grids, powder feeding air flow: 6 grids. Oxygen pressure: 0.12 MPa, liquefied petroleum gas pressure: 0.18 MPa, and 4 times/second of explosive spraying emission frequency.
(6) And after the coating is sprayed to the required size, the part is disassembled, the protection clamp is disassembled, the residual coating is cleaned, and then the coating is polished to the required size for assembly.
(7) And after the sprayed coating is inspected by fluorescence and visual inspection to have no peeling, cracks and chipping defects, the parts can be assembled.
Claims (5)
1. The remanufacturing and repairing method for the aeroengine compressor blade boss is characterized by comprising the following steps of S1: protecting the non-spraying surface of the boss part of the compressor blade by using a high-temperature pressure-sensitive adhesive tape and a copper wire winding mode;
s2, coarsening: the abrasion part of the lug boss of the compressor blade is subjected to sand blasting roughening treatment until the abrasion surface has no obvious metal luster,
s3, ash removal and inspection: blowing out residual sand or floating ash on the sand blasting surface by using compressed air, checking whether protective measures are intact or not, and if the protective measures are damaged, carrying out re-protection;
s4, spraying: the blade is clamped in a clamp which horizontally reciprocates, powder melted by an explosion spray gun is sprayed to a lug boss of the blade of the gas compressor through a window on the clamp, the thickness of the coating of the lug boss of the blade of the gas compressor is measured in real time in the spraying process, when the thickness of the coating meets the process requirement, the spraying is stopped, the blade is dismounted,
s5, post-processing: and removing the protective adhesive tape, cleaning the residual coating of the transition area, and polishing the lug boss of the compressor blade to the size required by assembly by using an abrasive belt polisher.
2. The method for remanufacturing and repairing a boss of a compressor blade of an aircraft engine according to claim 1, wherein the powder component comprises: WC: 70-78%, Co 20-25%, and the balance.
3. The remanufacturing and repairing method for the boss of the compressor blade of the aero-engine according to claim 1, wherein parameters of a spraying process are as follows: oxygen flow rate: 32.5-38.5 grids, liquefied petroleum gas flow: 22-25 grids, powder feeding flow: 3-8 grids, oxygen pressure: 0.11-0.13 MPa, liquefied petroleum gas pressure: 0.15 to 0.19 MPa.
4. The remanufacturing and repairing method for the aero-engine compressor blade boss according to claim 1, wherein the frequent emission of the explosion spraying spray gun is as follows: 4 times/sec.
5. The remanufacturing and repairing method of an aircraft engine compressor blade boss according to claim 1, wherein the step of cleaning and grinding is further included before the protection of the step S1,
the cleaning comprises the following steps: cleaning a boss part of a compressor blade by using acetone to remove dirt on the surface of the boss;
the polishing comprises the following steps: and polishing the wear surface of the lug boss of the compressor blade by using a diamond grinding wheel to repair and level the wear surface and remove oxides on the repaired surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910848544.6A CN110592520A (en) | 2019-09-09 | 2019-09-09 | Remanufacturing and repairing method for blade boss of aero-engine compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910848544.6A CN110592520A (en) | 2019-09-09 | 2019-09-09 | Remanufacturing and repairing method for blade boss of aero-engine compressor |
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| Publication Number | Publication Date |
|---|---|
| CN110592520A true CN110592520A (en) | 2019-12-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910848544.6A Pending CN110592520A (en) | 2019-09-09 | 2019-09-09 | Remanufacturing and repairing method for blade boss of aero-engine compressor |
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| CN (1) | CN110592520A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112410712A (en) * | 2020-10-30 | 2021-02-26 | 中国航发北京航空材料研究院 | Repair method for wear-resistant coating of titanium alloy blade shoulder |
| CN114134449A (en) * | 2021-11-13 | 2022-03-04 | 中国航发沈阳黎明航空发动机有限责任公司 | Protection method for supersonic flame spraying special-shaped part |
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2019
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112410712A (en) * | 2020-10-30 | 2021-02-26 | 中国航发北京航空材料研究院 | Repair method for wear-resistant coating of titanium alloy blade shoulder |
| CN114134449A (en) * | 2021-11-13 | 2022-03-04 | 中国航发沈阳黎明航空发动机有限责任公司 | Protection method for supersonic flame spraying special-shaped part |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191220 |
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| RJ01 | Rejection of invention patent application after publication |