CN113088962A - Laser cladding multi-azimuth repairing method for titanium alloy thin-wall blade damaged part - Google Patents
Laser cladding multi-azimuth repairing method for titanium alloy thin-wall blade damaged part Download PDFInfo
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- CN113088962A CN113088962A CN202110363935.6A CN202110363935A CN113088962A CN 113088962 A CN113088962 A CN 113088962A CN 202110363935 A CN202110363935 A CN 202110363935A CN 113088962 A CN113088962 A CN 113088962A
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- 238000004372 laser cladding Methods 0.000 title claims abstract description 54
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 48
- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000005253 cladding Methods 0.000 claims abstract description 71
- 230000008439 repair process Effects 0.000 claims abstract description 34
- 239000000843 powder Substances 0.000 claims abstract description 22
- 239000002356 single layer Substances 0.000 claims abstract description 11
- 230000008569 process Effects 0.000 claims abstract description 9
- 238000005520 cutting process Methods 0.000 claims abstract description 7
- 238000005498 polishing Methods 0.000 claims abstract description 6
- 238000003801 milling Methods 0.000 claims abstract description 5
- 238000000227 grinding Methods 0.000 claims abstract description 3
- 230000001174 ascending effect Effects 0.000 claims abstract 2
- 238000001816 cooling Methods 0.000 claims description 4
- 239000010410 layer Substances 0.000 description 7
- 238000003754 machining Methods 0.000 description 4
- 238000009825 accumulation Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009469 supplementation Effects 0.000 description 1
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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
- 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
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- 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
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- 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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Abstract
本申请提供一种钛合金薄壁叶片损伤件的激光熔覆多方位修复方法，其特征在于：所述方法包括如下步骤：S1：采用线切割在待修复薄壁叶片的损伤区域开一个槽；S2：确定激光熔覆的工艺参数；S3：利用同轴送粉激光熔覆对槽按槽口从左到右的方向熔覆若干列，所述列均采用从槽底向槽口的螺旋上升的方式熔覆，所述各列的深度均高于列所在位置对应的槽口至槽底的深度；S4：对槽的两侧面依次进行单层S型搭接第二次激光熔覆；S5：对钛合金叶片熔覆修复部位进行多轴数控铣削加工和打磨抛光，完成钛合金薄壁叶片的损伤修复。整个修复过程简单易操作、实用性强，适用范围广，具有防止薄壁叶片修复边缘塌陷不平整、避免激光烧蚀、减小热变形等优点。
The present application provides a laser cladding multi-directional repair method for damaged parts of a titanium alloy thin-walled blade, which is characterized in that: the method includes the following steps: S1: using wire cutting to open a groove in the damaged area of the thin-walled blade to be repaired; S2: Determine the process parameters of laser cladding; S3: Use coaxial powder feeding laser cladding to clad several rows of slots in the direction of the slot from left to right, and the rows are all spirally ascending from the bottom of the slot to the slot. The depth of each row is higher than the depth from the slot corresponding to the position of the row to the bottom of the slot; S4: The second laser cladding is performed on both sides of the slot in turn with a single-layer S-shaped lap; S5 : Multi-axis CNC milling and grinding and polishing are performed on the cladding repair parts of titanium alloy blades to complete the damage repair of titanium alloy thin-walled blades. The whole repair process is simple and easy to operate, has strong practicability, and has a wide range of applications.
Description
Technical Field
The invention relates to the technical field of laser cladding, in particular to a laser cladding multi-azimuth repairing method for a titanium alloy thin-wall blade damaged part.
Background
The titanium alloy has the advantages of high specific strength, good high and low temperature performance, corrosion resistance and the like, and is widely applied to parts such as aviation engine fans, gas compressors, casings and the like. Because the fan/compressor blade is positioned at the front end of the air inlet of the engine and the blade profile is thin, the damage such as abrasion, pits, tearing, gaps, chipping and the like is easily formed under the impact of foreign objects such as sand dust, gravel, hailstones, birds and the like in the service process, the overall performance and the safety and the reliability of the engine are reduced, and therefore, the damaged blade needs to be repaired in time in the maintenance process to recover the blade profile and the performance of the blade. The laser cladding technology has the advantages of high repair precision, small heat input and heat influence on a matrix, excellent structure performance of a deposited material, high automation degree and the like, and becomes one of key means for repairing the blade damage of the aero-engine.
The fan/compressor titanium alloy thin-wall blade is easy to deform and overburn in the laser cladding process due to small thickness, and the thin-wall gap piece repair area is small in area and small in bearing capacity, so that titanium alloy powder is not easy to accumulate in the repair area during cladding powder spraying, the problems of collapse of the edge of a bonding interface, weak bonding force and the like are easily caused, and the mechanical property of the titanium alloy thin-wall repair piece is seriously influenced. The existing repair of titanium alloy thin-wall parts mostly adopts a microminiature laser, but the application range is small, the working efficiency is low, and the problems of weak interface binding force and the like still exist.
Therefore, aiming at the problems, the existing laser cladding process needs to be changed so as to meet the relevant technical requirements of the blade profile and the performance of the repaired titanium alloy thin-wall blade.
Disclosure of Invention
In view of the above, the invention provides a laser cladding multi-azimuth repairing method for a titanium alloy thin-wall blade damaged part, which is characterized by comprising the following steps: the method comprises the following steps:
s1: a groove is formed in a damaged area of the thin-wall blade to be repaired by linear cutting, the bottom of the groove is arc-shaped, and the groove is mechanically polished;
wherein the groove completely covers the damaged area of the thin-wall blade to be repaired;
s2: determining technological parameters of laser cladding, wherein the technological parameters comprise laser spot diameter, laser power, scanning speed, powder feeding amount and single-layer cladding depth;
s3: setting parameters of the coaxial powder feeding laser cladding equipment according to the laser cladding parameters determined in the step S2, cladding a plurality of rows of the grooves in the width direction of the groove opening by using the coaxial powder feeding laser cladding, wherein the rows are clad in a mode of spirally rising from the groove bottom to the groove opening, and the depth of each row is higher than the depth from the groove opening corresponding to the position of the row to the groove bottom;
s4: carrying out single-layer S-shaped lap joint on two side surfaces of the groove in sequence for the second laser cladding, wherein the cladding thickness of the two side surfaces of the groove exceeds the thickness of the original blade corresponding to the position of the cladding area, and the cladding area of the second laser cladding completely covers the side surfaces of the groove;
s5: and obtaining the geometric characteristics of the damaged area of the blade through reverse engineering, and then carrying out multi-axis numerical control milling and polishing on the fusion-covering repair part of the titanium alloy blade to finish the damage repair of the titanium alloy thin-wall blade.
Further, the width of the notch of the groove is at least 3 times the width of the damage region, and the maximum depth from the notch of the groove to the groove bottom is at least 1.5 times the depth of the damage region.
Further, the diameter of the laser spot is smaller than the thickness of the thin-wall blade to be repaired, the laser power is 700-.
Further, after the single row of cladding is finished, the next row of cladding is performed after cooling for a preset time in step S3, where the preset time is the shortest time required for condensing and molding the cladding powder.
Further, the scanning path of the second laser cladding in step S4 is perpendicular to the scanning path in the depth direction from the notch to the groove bottom, and is S-shaped.
Further, the second laser cladding is square and covers the side face of the groove completely, and the cladding scanning path is a scanning path perpendicular to the depth direction from the groove opening to the groove bottom.
The invention has the beneficial technical effects that:
1. the laser has wide application range. Through the improvement of the cladding process, the repair of the titanium alloy thin-wall blade damaged part is not limited to a microminiature laser, and the high-power laser can also realize the cladding repair of the titanium alloy thin-wall blade damaged part through the method.
2. The titanium alloy thin-wall repair part has the advantages of less heat accumulation, small deformation, no crack and pore and good bonding interface.
3. The method has the advantages of simple operation, strong applicability and high working efficiency, effectively prolongs the service life of the titanium alloy thin-wall part, and improves the repair technology of the damaged part of the titanium alloy thin-wall blade.
Drawings
The invention is further described below with reference to the following figures and examples:
FIG. 1 is a schematic view of laser cladding of a titanium alloy thin-wall blade damage part in the depth direction.
FIG. 2 is a schematic view of laser cladding supplementation on the side surface of a titanium alloy thin-wall blade damage part.
In fig. 1 and 2, the part numbers indicate:
1-coaxial powder feeding cladding nozzle, 2-titanium alloy thin-wall blade damage area, 3-titanium alloy thin-wall blade damage area deep cladding path enlargement, 4-titanium alloy thin-wall blade damage area enlargement, 5-titanium alloy thin-wall blade damage area, 6-titanium alloy thin-wall damage blade, 7-titanium alloy thin-wall blade side surface repair area, 8-titanium alloy thin-wall blade side surface repair area cladding path enlargement, and 9-secondary cladding area bottom.
Detailed Description
The invention is further described with reference to the accompanying drawings in which:
the invention provides a laser cladding multi-azimuth repairing method of a titanium alloy thin-wall blade damaged part, which is characterized by comprising the following steps of: the method comprises the following steps:
s1: a groove is formed in a damaged area of the thin-wall blade to be repaired by linear cutting, the bottom of the groove is arc-shaped, and the groove is mechanically polished;
wherein the groove completely covers the damaged area; the width of the notch of the groove is at least 3 times of the width of the damage area, and the maximum depth from the notch of the groove to the groove bottom is at least 1.5 times of the depth of the damage area.
S2: determining technological parameters of laser cladding, wherein the technological parameters comprise laser spot diameter, laser power, scanning speed, powder feeding amount and single-layer cladding depth; the diameter of the laser spot is smaller than the thickness of the thin-wall blade to be repaired, the laser power is 700-.
S3: setting parameters of the coaxial powder feeding laser cladding equipment according to the laser cladding parameters determined in the step S2, cladding a plurality of rows of the grooves in the width direction of the groove opening by using the coaxial powder feeding laser cladding, wherein the rows are clad in a mode of spirally rising from the groove bottom to the groove opening, and the depth of each row is higher than the depth from the groove opening corresponding to the position of the row to the groove bottom; and in the step S3, after the single-row cladding is finished, cooling for a preset time, and then carrying out the next-row cladding, wherein the preset time is the shortest time required by condensing and molding cladding powder. And the rows are closely adjacent to each other, so that dense cladding structure and bubble-free metallurgical bonding of the rows are ensured, and the rows are closely arranged in a straight line along the width direction of the notch. In this embodiment, a person skilled in the art can sequentially clad a plurality of rows in a line from left to right or from right to left along the direction of the slot opening until all the rows of cladding along the depth direction of the slot are clad, and each row of cladding spirally rises to the slot opening from the slot bottom to the direction of the slot opening, and the depth of each row is higher than that of the slot opening. The terms "left" and "right" are left and right in fig. 1, which are only schematic in the direction of the present application and do not form a limitation to the present application. The depth of each row is gradually changed because the groove bottom is arc-shaped, but the depth of each row is required to be higher than the depth from the groove opening corresponding to the position of the row to the groove bottom in cladding, and the part higher than the groove opening is reserved for the machining allowance of subsequent machining.
In this embodiment, the depth of the groove is the depth in the direction perpendicular to the plane of the notch, i.e. the line from the notch to the groove bottom and perpendicular to the plane of the notch is the depth of the groove, and the groove bottom has an arc-shaped structure, so the depth of the groove is gradually changed. The notch of the groove is the opening at the two ends of the groove, wherein the width of the notch is the length of the connecting line of the openings at the two ends of the groove vertical to the thickness of the blade. The thickness of the groove is the thickness of the blade.
S4: carrying out single-layer S-shaped lap joint on two side surfaces of the groove in sequence for the second laser cladding, wherein the cladding thickness of the two side surfaces of the groove exceeds the thickness of the original blade corresponding to the position of the cladding area, and the cladding area of the second laser cladding completely covers the side surfaces of the groove; the two side surfaces of the groove are sequentially and completely covered. The scanning path of the second laser cladding is perpendicular to the scanning path from the notch to the groove bottom in the depth direction and is S-shaped, the starting point and the end point of the cladding are both at the bottom of the secondary cladding area, namely all the starting points and the end points of the cladding are at the square bottom, as shown in 9 in fig. 2, the bottom is square and clings to the blade in the thickness direction, namely the right-angle edge of the cladding blade is avoided, and the cladding collapse is prevented. The second laser cladding is square and covers the side of the groove completely, and the cladding scanning path is a scanning path perpendicular to the depth direction from the groove opening to the groove bottom. The size of the square is determined by the area of the side of the groove, in this embodiment the area of the square is larger than the area of the side of the groove and the square completely covers the side of the groove. The side of the groove is the side perpendicular to the depth of the groove as shown in fig. 2, and 7 is one of the two sides as shown in fig. 2. Cladding is sequentially carried out on two side surfaces of the groove, so that the filling of the groove in the thickness direction is higher than the original thickness of the blade, and a machining allowance is reserved for subsequent machining.
S5: and obtaining the geometric characteristics of the damaged area of the blade through reverse engineering, and then carrying out multi-axis numerical control milling and polishing on the fusion-covering repair part of the titanium alloy blade to finish the damage repair of the titanium alloy thin-wall blade.
The description is made with reference to fig. 1 and 2:
a laser cladding repair method for a titanium alloy thin-wall blade damaged part comprises the following steps:
s1, arc cutting is carried out on the damaged area 5 of the titanium alloy thin-wall blade by utilizing linear cutting, and the specific size of a notch after the cutting of the repair area 2 in the figure 1 is as follows: the depth is 4mm, the width is 16mm, the thickness is 2mm, and then an oxide layer in the repair area 2 is removed through mechanical polishing;
s2, through the research on the existing titanium alloy laser cladding, determining the laser cladding process parameters of the titanium alloy 2mm thin-wall blade shown in figure 1: TC4 spherical powder with the particle size of 45-150 nanometers is used for laser cladding repair, the laser power is 700W, the diameter of a light spot is 1.6mm, the scanning speed is 7mm/s, the powder feeding amount is 400g/min, the single-layer cladding depth is 0.6mm, 10 layers are clad together in a single pass, the cladding depth is 6mm, the depth exceeds the repair area 2 by 2mm, and certain follow-up processing allowance is reserved.
S3, a cladding path shown in fig. 1, 3, in which a coaxial powder feeding laser cladding is used to perform single-pass multilayer laser cladding in the depth direction on the arc-shaped gap 2, the coaxial powder feeding laser cladding nozzle 1 is moved to the upper side of the to-be-repaired area 2, the indicator red light is turned on to aim at the bottom of the gap 2 to be repaired, the distance between the cladding nozzle 1 and the bottom of the repaired area 2 is adjusted, and the cladding starting point is determined; the scanning path 3 moves upwards from the bottom of the repair area, the starting point and the end point of each layer of cladding are outwards parallel and offset by 0.5mm compared with the upper layer, the cladding head 1 is controlled to move in an S shape through numerical control programming, and the cladding nozzle 1 is lifted by 1mm after one layer of cladding is finished; and cooling for ten seconds after the single round-trip cladding is finished to carry out the next cladding, namely, the cladding time between the second layer and the third layer is kept for ten seconds, so that the deformation caused by the excessive accumulation of heat is prevented until the cladding depth is greater than the depth of the arc-shaped notch.
S4, placing the titanium alloy thin-wall blade damage piece 6 as shown in figure 2 for secondary supplementary cladding of the side surface; the secondary cladding area 7 is determined by the side area of the repair area 2, and the size of the secondary cladding area 7 in fig. 2 is 20mm × 5 mm; performing single-layer laser cladding on two side surfaces 7 of the blade respectively, wherein the thickness of a final cladding area 7 is about 3mm and exceeds the thickness of the original blade by 2mm, and the cladding area 7 completely covers the arc-shaped gap; the laser power of secondary cladding is 7001000W, the scanning speed is 710 mm/s, the diameter of a light spot is 1.52 mm, the powder feeding amount is 400500 g/min, the single-layer cladding depth is 0.60.8 mm, and the overlapping rate of the light spot is 4050%; the scanning path of the secondary cladding is shown as 8, the cladding starting point and the cladding ending point are both the bottom of the secondary cladding area, and as shown as 9 in fig. 2, the scanning path is scanned in an S-shaped path and is perpendicular to the scanning path in the depth direction.
S5, when the damaged titanium alloy blade 6 is repaired, the geometrical characteristics of the damaged part 5 of the blade are obtained through reverse engineering, then the titanium alloy blade fusion-covered repairing part 5 is subjected to multi-axis numerical control milling, and then corresponding grinding and polishing are carried out, so that the damage repairing of the titanium alloy thin-wall blade 6 is completed.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (6)
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113770643A (en) * | 2021-10-21 | 2021-12-10 | 华瑞（江苏）燃机服务有限公司 | Large-area repairing method for blade with cooling hole |
| CN114434086A (en) * | 2021-12-26 | 2022-05-06 | 国营四达机械制造公司 | Method for repairing surface cracks of titanium alloy thin-walled workpiece |
| CN115074725A (en) * | 2022-06-29 | 2022-09-20 | 中国航发动力股份有限公司 | Repair method for defect of blade edge block of titanium alloy thin blade |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1505168A2 (en) * | 2003-08-05 | 2005-02-09 | United Technologies Corporation | Turbine element repair |
| JP2011106431A (en) * | 2009-11-20 | 2011-06-02 | Toshiba Corp | Repairing method of gas turbine moving blade and gas turbine moving blade |
| JP2013113208A (en) * | 2011-11-29 | 2013-06-10 | Mitsubishi Heavy Ind Ltd | Turbine blade and turbine |
| CN103320786A (en) * | 2013-06-07 | 2013-09-25 | 昆明理工大学 | Cutter reparation and manufacturing method |
| CN103668188A (en) * | 2013-12-31 | 2014-03-26 | 无锡透平叶片有限公司 | Water-erosion preventing method for turbine blade by laser cladding |
| WO2016074314A1 (en) * | 2014-11-12 | 2016-05-19 | 江苏大学 | Laser thermal combination remanufacturing method for damaged metal part |
| CN110819982A (en) * | 2019-11-13 | 2020-02-21 | 中国航发动力股份有限公司 | Method for repairing abrasion and cracks of blade shroud and sealing teeth |
| CN110977322A (en) * | 2019-11-21 | 2020-04-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for repairing defect of typical part of tail nozzle mechanical adjusting system |
| CN111975282A (en) * | 2020-08-21 | 2020-11-24 | 中国人民解放军第五七一九工厂 | TC4 titanium alloy blisk structure blade air inlet edge damage repair method |
-
2021
- 2021-04-02 CN CN202110363935.6A patent/CN113088962B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1505168A2 (en) * | 2003-08-05 | 2005-02-09 | United Technologies Corporation | Turbine element repair |
| JP2011106431A (en) * | 2009-11-20 | 2011-06-02 | Toshiba Corp | Repairing method of gas turbine moving blade and gas turbine moving blade |
| JP2013113208A (en) * | 2011-11-29 | 2013-06-10 | Mitsubishi Heavy Ind Ltd | Turbine blade and turbine |
| CN103320786A (en) * | 2013-06-07 | 2013-09-25 | 昆明理工大学 | Cutter reparation and manufacturing method |
| CN103668188A (en) * | 2013-12-31 | 2014-03-26 | 无锡透平叶片有限公司 | Water-erosion preventing method for turbine blade by laser cladding |
| WO2016074314A1 (en) * | 2014-11-12 | 2016-05-19 | 江苏大学 | Laser thermal combination remanufacturing method for damaged metal part |
| CN110819982A (en) * | 2019-11-13 | 2020-02-21 | 中国航发动力股份有限公司 | Method for repairing abrasion and cracks of blade shroud and sealing teeth |
| CN110977322A (en) * | 2019-11-21 | 2020-04-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for repairing defect of typical part of tail nozzle mechanical adjusting system |
| CN111975282A (en) * | 2020-08-21 | 2020-11-24 | 中国人民解放军第五七一九工厂 | TC4 titanium alloy blisk structure blade air inlet edge damage repair method |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113770643A (en) * | 2021-10-21 | 2021-12-10 | 华瑞（江苏）燃机服务有限公司 | Large-area repairing method for blade with cooling hole |
| CN114434086A (en) * | 2021-12-26 | 2022-05-06 | 国营四达机械制造公司 | Method for repairing surface cracks of titanium alloy thin-walled workpiece |
| CN115074725A (en) * | 2022-06-29 | 2022-09-20 | 中国航发动力股份有限公司 | Repair method for defect of blade edge block of titanium alloy thin blade |
| CN115074725B (en) * | 2022-06-29 | 2024-01-30 | 中国航发动力股份有限公司 | Repairing method for defects of titanium alloy thin blade She Biankuai |
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