CN117070941A - Laser deposition repair method for TC4 titanium alloy rectifying blade - Google Patents
Laser deposition repair method for TC4 titanium alloy rectifying blade Download PDFInfo
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- CN117070941A CN117070941A CN202311341229.7A CN202311341229A CN117070941A CN 117070941 A CN117070941 A CN 117070941A CN 202311341229 A CN202311341229 A CN 202311341229A CN 117070941 A CN117070941 A CN 117070941A
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- laser deposition
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- titanium alloy
- rectifying
- repairing
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- 230000008439 repair process Effects 0.000 title claims abstract description 60
- 230000008021 deposition Effects 0.000 title claims abstract description 49
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 43
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000010438 heat treatment Methods 0.000 claims abstract description 23
- 230000007547 defect Effects 0.000 claims abstract description 12
- 239000000843 powder Substances 0.000 claims abstract description 8
- 238000004140 cleaning Methods 0.000 claims abstract description 4
- 238000007689 inspection Methods 0.000 claims description 7
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 6
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 6
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 6
- 239000001301 oxygen Substances 0.000 claims description 6
- 229910052760 oxygen Inorganic materials 0.000 claims description 6
- 238000005498 polishing Methods 0.000 claims description 6
- 238000005137 deposition process Methods 0.000 claims description 4
- 229920000742 Cotton Polymers 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 229910052786 argon Inorganic materials 0.000 claims description 3
- 239000011449 brick Substances 0.000 claims description 3
- 238000004040 coloring Methods 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000002844 melting Methods 0.000 abstract description 2
- 230000008018 melting Effects 0.000 abstract description 2
- 229910052751 metal Inorganic materials 0.000 abstract description 2
- 239000002184 metal Substances 0.000 abstract description 2
- 239000007769 metal material Substances 0.000 abstract description 2
- 239000002994 raw material Substances 0.000 abstract description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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
- 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
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
- C23C24/106—Coating with metal alloys or metal elements only
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
-
- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Laser Beam Processing (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to the technical field of repair of titanium alloy rectifying blades of aeroengines, in particular to a laser deposition repair method of a TC4 titanium alloy rectifying blade, which comprises the following steps of firstly, cleaning defects; step two, laser deposition repair; step three, checking the quality of laser deposition; step four, local heat treatment; and fifthly, repairing and grinding the laser deposition repair part. The invention adopts the rapid forming principle, takes metal powder as a raw material, realizes the repair technology of parts with three-dimensional shape defects by melting and stacking the metal material layer by laser, ensures the precise control forming of the surface crack defects of the titanium alloy rectifying blade, and ensures the integral use reliability of the titanium alloy rectifying blade repair piece. The invention solves the problems that the titanium alloy rectifying blade is scrapped as a whole due to the failure of the overhaul engine, and the high cost is caused by the replacement of the rectifying blade.
Description
Technical Field
The invention relates to the technical field of repairing titanium alloy rectifying blades, in particular to a laser deposition repairing method for TC4 titanium alloy rectifying blades.
Background
In the inspection, the surface of the titanium alloy rectifying blade has a macroscopic crack fault; the crack failure mode of the titanium alloy rectifying blade mainly comprises weld cracks, anti-icing Kong Liewen, bulge cracks and reinforcing rib cracks, and along with the increase of the service life and the large-state proportion of the engine, the crack failure mode of the titanium alloy rectifying blade is greatly increased year by year due to the influence of factors such as micro cracks of an anti-icing hole electric pulse processing remelting layer, local thinning and the like, and the rejection rate is in a continuous and rapid rising trend, so that the repair cost and the replacement rate of the engine are high.
At present, when repairing the surface cracks of the TC4 titanium alloy rectifying blade of the engine by laser deposition, the repairing part is constrained by the whole workpiece, the repairing stress is locally concentrated, and when repairing in the constrained state, higher tensile stress is more likely to occur in a larger range than in the free state. And local stress concentration is generated at the repair part, so that more dangerous internal stress is easy to generate. The titanium alloy rectifying blade belongs to a thin-wall part, is easy to deform, has the minimum thickness of a repair part of 1.1mm, belongs to the thin-wall part, and is easy to deform under the action of internal stress. The repairing engine service damaged piece has no machining allowance, the repairing titanium alloy rectifying blade surface crack service damaged repaired workpiece is a finished workpiece, only has a certain dimensional tolerance, has no machining allowance, does not allow the occurrence of the phenomenon of causing new deformation out of tolerance, and damages the structural integrity of the workpiece.
Disclosure of Invention
In order to solve the technical problems, the invention provides a laser deposition repairing method for a TC4 titanium alloy rectifying blade; the specific technical scheme is as follows:
a laser deposition repair method for TC4 titanium alloy rectifying vane comprises the following steps:
step one, defect cleaning
Adopting hard alloy rotary file to repair and grind crack areas of cracks of the TC4 titanium alloy rectifying blade until the cracks are completely removed, wherein the amount of removed cracks is small and the cracks are smoothly transited; the repaired area is cleaned by acetone;
step two, laser deposition repair
Repairing the crack area of the TC4 titanium alloy rectifying blade by adopting laser deposition repairing equipment, wherein the powder is TC4 titanium alloy powder, the granularity is 53-105 mu m, and when the oxygen content of a laser deposition manufacturing system is below 50ppm, a repairing test is carried out;
step three, laser deposition quality inspection
The laser deposition is inspected by appearance, X-ray and coloring, the surface of the repair part is well formed, and no laser deposition repair defect is found in the repair part;
step four, local heat treatment
Fixing a heating plate and a thermocouple in a rectifying vane repair area for heating, placing the rectifying vane repair area on a heat-insulating refractory brick, wrapping heat-insulating cotton outside the rectifying vane repair area, placing the rectifying vane repair area in a glove box, opening a circulating system in the glove box by filling argon to enable the oxygen content of the rectifying vane repair area to be less than 100ppm, starting heating, wherein a local heat treatment temperature system is used for heating for 1.5 hours, the heat treatment temperature is 600 ℃, preserving heat for 2 hours, and performing air cooling;
step five, repairing and grinding the laser deposition repair part
And (3) polishing the repaired part by adopting a polishing method to meet the inspection size requirement of the rectifying blade.
The method for repairing the TC4 titanium alloy rectifying vane by laser deposition has the preferable scheme that in the second step, the technological parameters of TC4 laser deposition are as follows: the laser power is 780W, the scanning speed is 380mm/min, the feeding speed is 0.2r/min, the lap joint rate is 40% -50%, the scanning interval is 1.5mm, and the aspect ratio is 4.
In the second step, the crack area of the rectifying blade is repaired by adopting a double-pass lap joint laser deposition process because the single-pass laser deposition width of the crack area of the rectifying blade is narrower.
A TC4 titanium alloy rectifying blade laser deposition repairing method adopts a rapid prototyping principle, takes metal powder as a raw material, realizes a repairing technology of a part with three-dimensional shape defects by melting and stacking the metal material layer by laser, ensures the precise control formation of the surface crack defects of the titanium alloy rectifying blade, and ensures the integral use reliability of the titanium alloy rectifying blade repairing piece.
Compared with the prior art, the invention has the following beneficial technical effects:
according to the practical characteristics of narrow slits after regular processing of weld cracks, anti-icing Kong Liewen, bulge cracks and reinforcing rib crack defects of the titanium alloy rectifying blade of the aeroengine, a single-pass laser deposition repair process and a single-pass double-pass laser deposition repair process scheme are formulated, the influence rule of each process parameter on the quality of a deposition layer and the quality of the deposition layer obtained under the comprehensive effect of the process parameters are analyzed, the process parameter combination range suitable for TC4 titanium alloy laser deposition repair is summarized, and the dimensional stability and the internal quality of a deposition repair piece are ensured through the control of the process parameters, so that the optimal repair process parameters are obtained and the laser deposition repair of a damaged workpiece is carried out by using the optimal repair process parameters. The TC4 titanium alloy rectifying blade of the aeroengine can be repaired, and the rectifying blade is repaired to reach the final size after being started up for overhaul, so that the use requirement of overhaul assembly is met, and local heat treatment is adopted for stress relief.
The invention adopts the laser deposition repair of the titanium alloy rectifying blade, effectively controls the deformation generated by the repair, realizes the repair of cracks of the titanium alloy rectifying blade after use, and restores the use function of the titanium alloy rectifying blade. The method has the advantages of high efficiency, high quality, reliability, wide repair application and the like, can solve the problem that the titanium alloy rectifying blade is scrapped as a whole due to the failure of the overhaul engine, greatly reduces the replacement rate of the rectifying blade of the overhaul engine, can be popularized and applied to the repair of the titanium alloy rectifying blade of other similar aeroengines, and has good economic benefit.
Drawings
FIG. 1 is a schematic view of crack locations in a titanium alloy fairing blade of an aircraft engine.
In the figure: 1-crack area.
Detailed Description
The present invention will be described in detail with reference to fig. 1, but the scope of the present invention is not limited by the accompanying drawings.
A laser deposition repair method for TC4 titanium alloy rectifying vane comprises the following steps:
step one, defect cleaning
Adopting a hard alloy rotary file to repair and grind a crack area 1 on cracks of the TC4 titanium alloy rectifying blade until the cracks are completely removed, wherein the amount of removed cracks is small and the cracks are smoothly transited; the repaired area is cleaned by acetone;
step two, laser deposition repair
Repairing the crack area of the TC4 titanium alloy rectifying blade by adopting laser deposition repairing equipment, wherein the powder is TC4 titanium alloy powder, and the technological parameters of TC4 laser deposition are as follows: the laser power is 780W, the scanning speed is 380mm/min, the feeding speed is 0.2r/min, the lap joint rate is 40% -50%, the scanning interval is 1.5mm, and the aspect ratio is 4; the granularity is 53-105 mu m, and when the oxygen content of the laser deposition manufacturing system reaches below 50ppm, a repair test is carried out; because the single-pass width of the laser deposition of the crack region 1 of the rectifying blade is narrower, repairing the crack region 1 of the rectifying blade by adopting a double-pass overlap laser deposition process;
step three, laser deposition quality inspection
The laser deposition is inspected by appearance, X-ray and coloring, the surface of the repair part is well formed, and no laser deposition repair defect is found in the repair part;
step four, local heat treatment
Fixing a heating plate and a thermocouple in a rectifying vane repair area for heating, placing the rectifying vane repair area on a heat-insulating refractory brick, wrapping heat-insulating cotton outside the rectifying vane repair area, placing the rectifying vane repair area in a glove box, opening a circulating system in the glove box by filling argon to enable the oxygen content of the rectifying vane repair area to be less than 100ppm, starting heating, wherein a local heat treatment temperature system is used for heating for 1.5 hours, the heat treatment temperature is 600 ℃, preserving heat for 2 hours, and performing air cooling;
step five, repairing and grinding the laser deposition repair part
And (3) polishing the repaired part by adopting a polishing method to meet the inspection size requirement of the rectifying blade.
Claims (3)
1. A TC4 titanium alloy rectification blade laser deposition repair method is characterized in that: the method comprises the following steps:
step one, defect cleaning
Adopting hard alloy rotary file to repair and grind crack areas of cracks of the TC4 titanium alloy rectifying blade until the cracks are completely removed, wherein the amount of removed cracks is small and the cracks are smoothly transited; the repaired area is cleaned by acetone;
step two, laser deposition repair
Repairing the crack area of the TC4 titanium alloy rectifying blade by adopting laser deposition repairing equipment, wherein the powder is TC4 titanium alloy powder, the granularity is 53-105 mu m, and when the oxygen content of a laser deposition manufacturing system is below 50ppm, a repairing test is carried out;
step three, laser deposition quality inspection
The laser deposition is inspected by appearance, X-ray and coloring, the surface of the repair part is well formed, and no laser deposition repair defect is found in the repair part;
step four, local heat treatment
Fixing a heating plate and a thermocouple in a rectifying vane repair area for heating, placing the rectifying vane repair area on a heat-insulating refractory brick, wrapping heat-insulating cotton outside the rectifying vane repair area, placing the rectifying vane repair area in a glove box, opening a circulating system in the glove box by filling argon to enable the oxygen content of the rectifying vane repair area to be less than 100ppm, starting heating, wherein a local heat treatment temperature system is used for heating for 1.5 hours, the heat treatment temperature is 600 ℃, preserving heat for 2 hours, and performing air cooling;
step five, repairing and grinding the laser deposition repair part
And (3) polishing the repaired part by adopting a polishing method to meet the inspection size requirement of the rectifying blade.
2. The method for repairing the TC4 titanium alloy rectifying vane by laser deposition according to claim 1, which is characterized in that: in the second step, TC4 laser deposition process parameters: the laser power is 780W, the scanning speed is 380mm/min, the feeding speed is 0.2r/min, the lap joint rate is 40% -50%, the scanning interval is 1.5mm, and the aspect ratio is 4.
3. The method for repairing the TC4 titanium alloy rectifying vane by laser deposition according to claim 1, which is characterized in that: and step two, repairing the crack area of the rectifying blade by adopting a double lap joint laser deposition process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311341229.7A CN117070941A (en) | 2023-10-17 | 2023-10-17 | Laser deposition repair method for TC4 titanium alloy rectifying blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311341229.7A CN117070941A (en) | 2023-10-17 | 2023-10-17 | Laser deposition repair method for TC4 titanium alloy rectifying blade |
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| CN117070941A true CN117070941A (en) | 2023-11-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311341229.7A Pending CN117070941A (en) | 2023-10-17 | 2023-10-17 | Laser deposition repair method for TC4 titanium alloy rectifying blade |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105290589A (en) * | 2015-11-10 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Microbeam plasma welding repairing method for titanium alloy inlet casing support plate cracks |
| CN106637187A (en) * | 2016-11-16 | 2017-05-10 | 中国人民解放军第五七九工厂 | Laser cladding restoration method for damage of stator blade of welding assembly of large fan casing of aeroengine |
| CN106735906A (en) * | 2017-01-05 | 2017-05-31 | 机械科学研究总院青岛分院 | A kind of method for laser welding of titanium alloy sheet |
-
2023
- 2023-10-17 CN CN202311341229.7A patent/CN117070941A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105290589A (en) * | 2015-11-10 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Microbeam plasma welding repairing method for titanium alloy inlet casing support plate cracks |
| CN106637187A (en) * | 2016-11-16 | 2017-05-10 | 中国人民解放军第五七九工厂 | Laser cladding restoration method for damage of stator blade of welding assembly of large fan casing of aeroengine |
| CN106735906A (en) * | 2017-01-05 | 2017-05-31 | 机械科学研究总院青岛分院 | A kind of method for laser welding of titanium alloy sheet |
Non-Patent Citations (1)
| Title |
|---|
| 卞宏友 等: ""激光沉积修复金属去应力退火局部热处理工艺"", 《材料热处理学报》, vol. 38, no. 7, pages 126 - 131 * |
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Application publication date: 20231117 |