CN105108337A - Method for restoring crack of blade of hydraulic turbine - Google Patents
Method for restoring crack of blade of hydraulic turbine Download PDFInfo
- Publication number
- CN105108337A CN105108337A CN201510549734.XA CN201510549734A CN105108337A CN 105108337 A CN105108337 A CN 105108337A CN 201510549734 A CN201510549734 A CN 201510549734A CN 105108337 A CN105108337 A CN 105108337A
- Authority
- CN
- China
- Prior art keywords
- blade
- welding
- stage
- hole
- laser beam
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/21—Bonding by welding
- B23K26/24—Seam welding
Abstract
The invention discloses a method for restoring a crack of a blade of a hydraulic turbine. The method mainly comprises a preparation stage, a self-melting welding stage, a filling welding stage and an aftertreatment stage. At the preparation stage, the blade to be restored is cleaned and detected; at the self-melting welding stage, an inclined convergent laser beam with a negative defocusing amount is adopted for carrying out scanning in the extending direction of the crack, a V-shaped melting pool is formed, and molten metal liquid sinks to the bottom of the melting pool under the action of gravity, and is solidified to form a self-melting weld joint; at the filling welding stage, a material identical to a body of the blade is adopted as a welding wire for surface layer bead welding; at the aftertreatment stage, distressing tempering and blade surface finishing machining are carried out after welding is completed. In the restoring process, based on self-melting of the material of the body of the blade, the blade is filled with a few materials identical to the body of the blade, the material of the weld joint is identical to that of the blade, the material and the blade are combined well, a weld joint defect is not likely to be generated, and the combining strength of the weld joint is improved. In the self-welding welding and filling welding processes, molten metal in the melting pool is vibrated through ultrasonic waves generated by an ultrasonic generator on the back face of the blade to remove gas, and the defects of weld porosity and the like are reduced.
Description
Technical field
The present invention relates to metal parts recovery technique field, specifically the renovation technique of turbine blade.
Background technology
The blade of the equipment such as steam turbine or the hydraulic turbine is subject to fluid working medium at work and impacts, and longtime running can produce fatigue crack at blade surface, comprehends cause leaf destruction as carried out repair place not in time.Blade reparation often adopts built-up welding, melts modes such as covering.
If application number is the Chinese invention patent of 201310054557.9, a kind of restorative procedure of aero-engine blade damage is disclosed, the method carries out segment processing according to blade surface size shape feature to be repaired, set each section of hot input parameter of pulse plasma and pulsed wire feeding controling parameters, Plasma Welding reparation is carried out in segmentation.For another example application number is the Chinese invention patent of 201310170388.5, a kind of high-temperature alloy turbine blade repair materials and renovation technique thereof are disclosed, then describe the method adopting micro-arc spark deposition repairing turbine blade, according to the prefabricated welding material rod of technological requirement, adopting micro-arc spark depositing operation to carry out built-up welding to needing the region of repairing, after welding, carrying out vacuum heat.
Common repair methods (namely filling welding) due to packing material different from blade body material, solder bond interface material composition, tissue are complicated, and easily produce weld defect bottom weld seam, affect weld seam bond strength, reduce the service life after blade reparation.
Summary of the invention
The object of the invention is to the deficiency overcoming above-mentioned prior art, without the need to beating groove when providing a kind of pretreatment, improving the turbine blade method for repairing crack of weld seam bond strength.
To achieve these goals, the technical solution used in the present invention is: a kind of turbine blade method for repairing crack, is characterized in that: comprise the preparatory stage: cleaning detects blade to be repaired; From the fusion welding stage: adopt the convergent laser bundle of the negative defocusing amount tilted to scan along crack orientation, form V-arrangement molten bath, molten metal liquid sinks to bottom molten bath under gravity, solidifies rear formation and stitches from melting welding; Fill the welding stage: adopt the material identical with blade body as welding wire, carry out top layer built-up welding; Post-processing stages: carry out destressing tempering and blade surface finishing processing after having welded.
Further, be fixed with a supersonic generator at the back side of described blade, ultrasonic wave can be produced described startup in fusion welding stage and filling welding stage.
Further, in the described preparatory stage, by X-ray, blade cracks is detected, determine crack orientation and crackle depth capacity and position thereof; Then respectively at crackle two ends make a call to a diameter and be greater than crack width 1-2mm, what the degree of depth was greater than crack depth 3mm blocks hole; The exploration hole that a diameter is greater than crack width 1-2mm, the degree of depth is greater than crack depth 3mm is made a call at crack depth maximum.Described scanning crackle with laser beam in the fusion welding stage take exploration hole as starting point, be scanned up to the cut-off hole at two ends respectively, comprise the steps: 1) first preheating is carried out to exploration hole, adopt the vertical beam of light irradiation exploration hole of convergent angle 5-8 °, make detection hole wall and base material generation local melting; 2) laser beam being tilted backwards, is 5-7 ° of angle with the opposite direction blade surface of scanning direction, and along crack orientation scanning, molten metal liquid is lowered into bottom molten bath at ultrasonic wave and Action of Gravity Field, and after laser beam leaves, cooled and solidified forms weld seam; 3) when laser beam flying to crackle one end block hole after, slewed laser beam makes it vertical with blade surface, and carries out irradiation to blocking hole; 4) again by exploration hole, above-mentioned steps 1 is repeated)-3), carry out scanning welding to other end cut-off hole; The focused spot diameter of described laser beam is greater than exploration hole diameter 0.5mm, and laser power is (250-300) × 10
9w/m
2, pulse width is 10ms, is 5-8 pulse width to the exposure time in exploration hole and cut-off hole.
Further, in the described filling welding stage, following steps are performed: 1) adjusting laser beam convergent angle, is collimated light beam, and laser beam is perpendicular to described face of weld; 2) laser beam from one end block hole along crackle trend to the other end block hole scanning, add simultaneously and send the welding wire identical with the bulk material of blade, carry out fillings weld; 3) scanning repeated from crackle one end to the other end is welded, until weld seam upper surface is higher than blade upper surface, fills welding process and completes.The focal plane of described laser beam is positioned at 0.5mm place below weld seam upper surface, and laser spot diameter is about 1mm; Described filling welding stage etch 3) in, the scanning welding of repetition is until weld seam upper surface stops welding higher than during blade upper surface 0.5mm.
The invention has the beneficial effects as follows: adopt above-mentioned restorative procedure, without the need to beating groove during pretreatment, certainly melt based on blade body material during reparation, the material that a small amount of filling is identical with blade body, weld material is identical with blade, and the two combines good, and not easily produces weld defect, improve weld seam bond strength, extend the blade service life after repairing.
Concrete, in welding process, the first rear-inclined of laser beam makes crackle base material first melt, the incomplete penetration defect that the shutoff phenomenon easily produced when avoiding top first to melt causes, ultrasonic wave vibration is conducive to molten pool metal liquid and flows into bottom molten bath, and be conducive to the discharge of gas in molten pool metal liquid, eliminate the defects such as the pore easily occurred in weld seam; The convergent laser bundle of negative defocusing amount makes molten bath form the larger V-arrangement molten bath of upper opening, contributes to the discharge of metal vapors and plasma, avoids molten pool metal liquid by molten bath of blowing off, increase substantially weldquality.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Fig. 1 is FB(flow block) of the present invention.
Fig. 2 Leaf crack orientation of the present invention schematic diagram.
Exploration hole preheating schematic diagram in Fig. 3 the present invention.
From fusion welding schematic diagram in Fig. 4 the present invention.
In diagram: 1, blade; 2, hole is blocked; 3, crackle side; 4, convergent laser bundle; 5, exploration hole; 6, supersonic generator; 7, crackle.
Detailed description of the invention
As Figure 1-4, a kind of turbine blade method for repairing crack of the present invention, comprises the preparatory stage, from the fusion welding stage, fills welding stage, post-processing stages.
Wherein, the above-mentioned preparatory stage, perform following steps: 1) clean blade 1 to be repaired, remove greasy dirt, foreign material etc. in blade 1 surface and weld seam; 2) crack detection, by x-ray inspection, detects crackle 7 and moves towards and crackle 7 depth capacity and position thereof; 3) respectively at crackle 7 two ends make a call to a diameter and be greater than crack width 1-2mm, what the degree of depth was greater than crack depth about 3mm blocks hole 2; 4) make a call to a diameter at crack depth maximum and be greater than crack width 1-2mm, the degree of depth is greater than the exploration hole 5 of crack depth about 3mm; 5) on vacuum side of blade, fix a supersonic generator 6.
After the preparatory stage completes, carry out crackle from fusion welding, mainly comprise the following steps from fusion welding.
1) exploration hole 5 preheating: adopt convergent angle 5-8 °, focused spot diameter is greater than the vertical beam of light 4 irradiation exploration hole of exploration hole diameter 0.5mm, laser power (250-300) × 10
9w/m
2, about pulse width 10ms, exposure time is about 5-8 pulse width, makes detection hole wall and base material generation local melting.
2) from fusion welding: make laser beam 4 tilt backwards, be 5-7 ° of angle with the opposite direction blade surface of scanning direction; Laser beam 4 moves towards the velocity scanning with 0.8-1.3mm/s along crackle 7, starts the supersonic generator 6 being placed in vacuum side of blade simultaneously.Be lowered into bottom molten bath at gravity and ul-trasonic irradiation after crackle 7 both sides metal is melted, after laser beam 4 leaves, cooled and solidified forms weld seam.
3) when laser beam 4 scan crackle one end block hole 2 after slewed laser beam 4 make its with blade 1 surface vertical, and carry out an irradiation 5-8 pulse width to blocking hole 2.
4) from exploration hole 5, above-mentioned steps 1 is repeated)-3), carry out scanning welding to the other end.
In fusion welding process, the convergent angle of 5-8 ° of laser beam 4 makes molten bath form V-arrangement molten bath, is conducive to the discharge of metal vapors and plasma gas, avoids molten pool metal liquid by molten bath of blowing off.And laser beam 4 tilts backwards 5-7 °, crackle 7 bottom metal is first melted, avoid upper metal liquation to cool formation shutoff and cause occurring incomplete penetration defect in weld seam.And the ultrasonic wave that supersonic generator 6 produces is conducive to molten pool metal liquid to molten bath flows, and the gas accelerated in molten pool metal liquid is discharged, and avoids producing the defects such as pore in weld seam.
After fusion welding completes, enter after the fusing of crackle 7 two layers of material bottom molten bath and formed from melting welding seam, weld seam upper surface caves in, and lower than blade 1 surface, need carry out filling welding, supplementary metal material makes weld seam upper surface a little more than blade.
In the above-mentioned filling welding stage, mainly perform following steps.
1) adjusting laser beam 4 convergent angle, making it is as far as possible collimated light beam (convergent angle size depends on laser instrument self performance), laser beam 4 is perpendicular to face of weld, and the focal plane of laser beam 4 is positioned at about 0.5mm below weld seam upper surface, and laser spot diameter is about 1mm.
2) laser beam 4 from one end block hole along crackle 7 trend to the other end block hole scanning, add simultaneously and send diameter to be about the 0.3mm material welding wire identical with the bulk material of blade 1, carry out filling welding, supersonic generator 6 is in starting state in the process.
3) scanning repeated from crackle 1 one end to the other end is welded, until weld seam upper surface is higher than surperficial about the 0.5mm of blade 1, fills welding process and completes.
After above-mentioned filling welding terminates, carry out post-processing stages: first carry out destressing tempering to blade 1, concrete temperature and temperature retention time depend on the material of blade 1; After tempering, finishing processing is carried out to the surface of blade 1, make blade 1 reach design size.
Finally should be noted that; above content is only in order to illustrate technical scheme of the present invention; but not limiting the scope of the invention; the simple modification that those of ordinary skill in the art carries out technical scheme of the present invention or equivalently to replace, does not all depart from essence and the scope of technical solution of the present invention.
Claims (7)
1. a turbine blade method for repairing crack, is characterized in that: comprise the preparatory stage: cleaning detects blade to be repaired; From the fusion welding stage: adopt the convergent laser bundle of the negative defocusing amount tilted to scan along crack orientation, form V-arrangement molten bath, molten metal liquid sinks to bottom molten bath under gravity, solidifies rear formation and stitches from melting welding; Fill the welding stage: adopt the material identical with blade body as welding wire, carry out top layer built-up welding; Post-processing stages: carry out destressing tempering and blade surface finishing processing after having welded.
2. turbine blade method for repairing crack according to claim 1, is characterized in that: be fixed with a supersonic generator at the back side of described blade, can produce ultrasonic wave described startup in fusion welding stage and filling welding stage.
3. turbine blade method for repairing crack according to claim 2, be is characterized in that: in the described preparatory stage, detected blade cracks by X-ray, determines crack orientation and crackle depth capacity and position thereof; Then respectively at crackle two ends make a call to one and block hole; An exploration hole is made a call at crack depth maximum.
4. turbine blade method for repairing crack according to claim 3, it is characterized in that: described scanning crackle with laser beam in the fusion welding stage take exploration hole as starting point, be scanned up to the cut-off hole at two ends respectively, comprise the steps: 1) first preheating is carried out to exploration hole, adopt the vertical beam of light irradiation exploration hole of convergent angle 5-8 °, make detection hole wall and base material generation local melting; 2) laser beam being tilted backwards, is 5-7 ° of angle with the opposite direction blade surface of scanning direction, and along crack orientation scanning, molten metal liquid is lowered into bottom molten bath at ultrasonic wave and Action of Gravity Field, and after laser beam leaves, cooled and solidified forms weld seam; 3) when laser beam flying to crackle one end block hole after, slewed laser beam makes it vertical with blade surface, and carries out irradiation to blocking hole; 4) again by exploration hole, above-mentioned steps 1 is repeated)-3), carry out scanning welding to other end cut-off hole.
5. turbine blade method for repairing crack according to claim 4, is characterized in that: the focused spot diameter of described laser beam is greater than exploration hole diameter 0.5mm, and laser power is (250-300) × 10
9w/m
2, pulse width is 10ms, is 5-8 pulse width to the exposure time in exploration hole and cut-off hole.
6. turbine blade method for repairing crack according to claim 2, is characterized in that: the described filling welding stage, performs following steps: 1) adjusting laser beam convergent angle, is collimated light beam, and laser beam is perpendicular to described face of weld; 2) laser beam from one end block hole along crackle trend to the other end block hole scanning, add simultaneously and send the welding wire identical with the bulk material of blade, carry out fillings weld; 3) scanning repeated from crackle one end to the other end is welded, until weld seam upper surface is higher than blade upper surface, fills welding process and completes.
7. turbine blade method for repairing crack according to claim 6, is characterized in that: the focal plane of described laser beam is positioned at 0.5mm place below weld seam upper surface, and laser spot diameter is 1mm; Described filling welding stage etch 3) in, the scanning welding of repetition is until weld seam upper surface stops welding higher than during blade upper surface 0.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510549734.XA CN105108337B (en) | 2015-09-01 | 2015-09-01 | A kind of turbine blade method for repairing crack |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510549734.XA CN105108337B (en) | 2015-09-01 | 2015-09-01 | A kind of turbine blade method for repairing crack |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105108337A true CN105108337A (en) | 2015-12-02 |
| CN105108337B CN105108337B (en) | 2017-07-28 |
Family
ID=54656564
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510549734.XA Expired - Fee Related CN105108337B (en) | 2015-09-01 | 2015-09-01 | A kind of turbine blade method for repairing crack |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105108337B (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105312834A (en) * | 2015-10-30 | 2016-02-10 | 沈阳黎明航空发动机(集团)有限责任公司 | Repair method for main body cracks of high-temperature alloy thin-wall welding machine case |
| CN106695125A (en) * | 2017-02-20 | 2017-05-24 | 上海海事大学 | System and method for improving laser processing surface integrity of workpiece on line |
| CN106956079A (en) * | 2017-04-17 | 2017-07-18 | 江苏大学 | A kind of method that metal surface micro-crack is made in micro- consolidation of laser up |
| CN109062135A (en) * | 2018-06-26 | 2018-12-21 | 上海航天设备制造总厂有限公司 | A kind of incomplete penetration defect removing method based on the control of UG programming route |
| CN109048200A (en) * | 2018-07-10 | 2018-12-21 | 吉林大学 | The method of the reparation trolley coach brake disc fire check of the bionical locking pinning of laser |
| CN110181051A (en) * | 2019-06-18 | 2019-08-30 | 浙江工业大学 | A kind of narrow gap fill method of laser remanufacturing oriented under Lorentz force effect |
| CN111604639A (en) * | 2020-05-15 | 2020-09-01 | 浙江博星工贸有限公司 | Camshaft repair system |
| CN111621733A (en) * | 2020-05-15 | 2020-09-04 | 浙江博星工贸有限公司 | Working method of camshaft repairing system |
| CN113560580A (en) * | 2021-07-08 | 2021-10-29 | 中国科学院力学研究所 | Laser repairing method and device for metal parts |
| CN113681012A (en) * | 2021-08-24 | 2021-11-23 | 江苏拜欧尼克智能科技有限公司 | Method for repairing hole defects of cast cylinder block by laser |
| CN114101848A (en) * | 2021-12-30 | 2022-03-01 | 天津大学 | Welding method for repairing thin-wall cracks of metal component |
| CN114192983A (en) * | 2021-12-27 | 2022-03-18 | 武汉锐科光纤激光技术股份有限公司 | Laser self-fluxing welding method |
| CN115283869A (en) * | 2022-07-28 | 2022-11-04 | 上海宝冶集团有限公司 | Repair welding method for stainless steel composite plate defect |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000126889A (en) * | 1998-10-21 | 2000-05-09 | Fanuc Ltd | Laser beam machining method, and its machine, and auxiliary tool for piercing |
| CN1737197A (en) * | 2005-09-01 | 2006-02-22 | 上海交通大学 | Crack controlling means for laser deposition formed metal parts |
| CN1883872A (en) * | 2005-06-22 | 2006-12-27 | 中国科学院金属研究所 | Crack repair process for high-pressure turbine blade tip in gas turbine |
| CN101195183A (en) * | 2007-12-24 | 2008-06-11 | 哈尔滨工业大学 | Ultrasound wave auxiliary laser braze (fuse) welding method |
| CN102059453A (en) * | 2011-01-10 | 2011-05-18 | 哈尔滨工业大学 | Non-contact-type ultrasonic-assisted laser welding method |
| CN104607742A (en) * | 2008-02-14 | 2015-05-13 | 三菱日立电力系统株式会社 | Turbine rotor blade repair method |
-
2015
- 2015-09-01 CN CN201510549734.XA patent/CN105108337B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000126889A (en) * | 1998-10-21 | 2000-05-09 | Fanuc Ltd | Laser beam machining method, and its machine, and auxiliary tool for piercing |
| CN1883872A (en) * | 2005-06-22 | 2006-12-27 | 中国科学院金属研究所 | Crack repair process for high-pressure turbine blade tip in gas turbine |
| CN1737197A (en) * | 2005-09-01 | 2006-02-22 | 上海交通大学 | Crack controlling means for laser deposition formed metal parts |
| CN101195183A (en) * | 2007-12-24 | 2008-06-11 | 哈尔滨工业大学 | Ultrasound wave auxiliary laser braze (fuse) welding method |
| CN104607742A (en) * | 2008-02-14 | 2015-05-13 | 三菱日立电力系统株式会社 | Turbine rotor blade repair method |
| CN102059453A (en) * | 2011-01-10 | 2011-05-18 | 哈尔滨工业大学 | Non-contact-type ultrasonic-assisted laser welding method |
Non-Patent Citations (2)
| Title |
|---|
| 叶秀华等: "《焊接施工技术》", 31 October 1991 * |
| 范绍林等: "《焊工操作技巧集锦》", 31 January 2008 * |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105312834A (en) * | 2015-10-30 | 2016-02-10 | 沈阳黎明航空发动机(集团)有限责任公司 | Repair method for main body cracks of high-temperature alloy thin-wall welding machine case |
| CN105312834B (en) * | 2015-10-30 | 2018-01-16 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of high temperature alloy thin walled welds casing main body method for repairing crack |
| CN106695125A (en) * | 2017-02-20 | 2017-05-24 | 上海海事大学 | System and method for improving laser processing surface integrity of workpiece on line |
| CN106956079A (en) * | 2017-04-17 | 2017-07-18 | 江苏大学 | A kind of method that metal surface micro-crack is made in micro- consolidation of laser up |
| CN109062135A (en) * | 2018-06-26 | 2018-12-21 | 上海航天设备制造总厂有限公司 | A kind of incomplete penetration defect removing method based on the control of UG programming route |
| CN109048200A (en) * | 2018-07-10 | 2018-12-21 | 吉林大学 | The method of the reparation trolley coach brake disc fire check of the bionical locking pinning of laser |
| CN109048200B (en) * | 2018-07-10 | 2020-12-25 | 吉林大学 | Method for repairing thermal cracks of brake disc of railway passenger car by laser bionic locking pinning |
| CN110181051A (en) * | 2019-06-18 | 2019-08-30 | 浙江工业大学 | A kind of narrow gap fill method of laser remanufacturing oriented under Lorentz force effect |
| CN111621733A (en) * | 2020-05-15 | 2020-09-04 | 浙江博星工贸有限公司 | Working method of camshaft repairing system |
| CN111604639A (en) * | 2020-05-15 | 2020-09-01 | 浙江博星工贸有限公司 | Camshaft repair system |
| CN111604639B (en) * | 2020-05-15 | 2021-06-18 | 浙江博星工贸有限公司 | Camshaft repair system |
| CN113560580A (en) * | 2021-07-08 | 2021-10-29 | 中国科学院力学研究所 | Laser repairing method and device for metal parts |
| CN113681012A (en) * | 2021-08-24 | 2021-11-23 | 江苏拜欧尼克智能科技有限公司 | Method for repairing hole defects of cast cylinder block by laser |
| CN114192983A (en) * | 2021-12-27 | 2022-03-18 | 武汉锐科光纤激光技术股份有限公司 | Laser self-fluxing welding method |
| CN114101848A (en) * | 2021-12-30 | 2022-03-01 | 天津大学 | Welding method for repairing thin-wall cracks of metal component |
| CN114101848B (en) * | 2021-12-30 | 2023-02-28 | 天津大学 | Welding method for repairing thin-wall cracks of metal component |
| CN115283869A (en) * | 2022-07-28 | 2022-11-04 | 上海宝冶集团有限公司 | Repair welding method for stainless steel composite plate defect |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105108337B (en) | 2017-07-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105108337A (en) | Method for restoring crack of blade of hydraulic turbine | |
| JP5897248B2 (en) | Laser welding repair of combustion cap effusion plate | |
| CN105665933B (en) | A kind of Invar mould steel laser electrical arc complex welding method | |
| CN111545912A (en) | Narrow-gap laser circular oscillation motion wire-filling welding method for aluminum alloy thick-wall component | |
| CN107414292A (en) | A kind of titanium alloy parts defect laser accurate repairs soldering method | |
| JP5468471B2 (en) | Gas turbine blade repair method and gas turbine blade | |
| CN101704165B (en) | Laser welding repair method for machining liner of nickle-base wrought superalloy annular machine | |
| CN105643103A (en) | Galvanized steel sheet laser lapping welding method | |
| KR20150110799A (en) | Method of laser re-melt repair of superalloys using flux | |
| JP5645128B2 (en) | Laser narrow groove multilayer welding method and apparatus | |
| CN106077951A (en) | Control the method that nickel-base alloy multilamellar wire filling laser welding beat-affected zone crack is formed | |
| JP2016117083A (en) | Repair method of casting made of aluminum alloy | |
| JP6838832B2 (en) | Welding filler for superalloys | |
| CN112756788A (en) | Welding process suitable for deep groove between tube plate and heat exchange tube | |
| JP6487530B2 (en) | Method for building a gas turbine engine component | |
| JP7189516B2 (en) | Weld defect repair method | |
| CN110899974A (en) | Laser swing welding method for medium plate armored steel | |
| CN107252972A (en) | It is a kind of to reduce the laser filling wire welding technique of austenitic stainless steel weld joint solidification cracking | |
| CN105722635A (en) | Welding process and reduced restraint weld joint | |
| CN114012260A (en) | Laser welding repair method for crack damage of high-temperature component of gas turbine | |
| CN115386873A (en) | Defect repairing method for TA15 titanium alloy part formed by selective laser melting | |
| CN108406057A (en) | A kind of ultrasonic wave added cobalt-base alloys-nickel-base alloy argon tungsten-arc welding device and method | |
| CN107335920A (en) | Method for laser welding | |
| CN109664024A (en) | Repair the method for laser welding of base material surface or internal flaw | |
| CN105345222B (en) | The welding method of single face welding and double face shaping |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170728 Termination date: 20210901 |