CN101007366A - Repair method of high temperature alloy vane by electron beam welding - Google Patents
Repair method of high temperature alloy vane by electron beam welding Download PDFInfo
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- CN101007366A CN101007366A CN 200710071695 CN200710071695A CN101007366A CN 101007366 A CN101007366 A CN 101007366A CN 200710071695 CN200710071695 CN 200710071695 CN 200710071695 A CN200710071695 A CN 200710071695A CN 101007366 A CN101007366 A CN 101007366A
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- solder
- blades
- electron beam
- superalloy
- brazing
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 49
- 239000000956 alloy Substances 0.000 title claims abstract description 49
- 238000000034 method Methods 0.000 title claims abstract description 39
- 238000010894 electron beam technology Methods 0.000 title claims abstract description 29
- 230000008439 repair process Effects 0.000 title abstract description 16
- 238000003466 welding Methods 0.000 title description 2
- 229910000679 solder Inorganic materials 0.000 claims abstract description 41
- 239000000843 powder Substances 0.000 claims abstract description 24
- 230000006378 damage Effects 0.000 claims abstract description 21
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims abstract description 18
- 229910000601 superalloy Inorganic materials 0.000 claims abstract 24
- 238000005219 brazing Methods 0.000 claims abstract 22
- 239000000853 adhesive Substances 0.000 claims abstract 3
- 230000001070 adhesive effect Effects 0.000 claims abstract 3
- 238000009736 wetting Methods 0.000 claims description 8
- 239000002184 metal Substances 0.000 claims description 7
- 229910052751 metal Inorganic materials 0.000 claims description 7
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical group [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 6
- 239000000203 mixture Substances 0.000 claims description 3
- 229910052759 nickel Inorganic materials 0.000 claims description 3
- 239000010941 cobalt Substances 0.000 claims description 2
- 229910017052 cobalt Inorganic materials 0.000 claims description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 2
- 239000010953 base metal Substances 0.000 claims 2
- 229910000531 Co alloy Inorganic materials 0.000 claims 1
- 239000000945 filler Substances 0.000 claims 1
- 239000000463 material Substances 0.000 claims 1
- 238000010438 heat treatment Methods 0.000 abstract description 5
- 238000005476 soldering Methods 0.000 description 13
- 239000011230 binding agent Substances 0.000 description 4
- 238000009418 renovation Methods 0.000 description 4
- 208000027418 Wounds and injury Diseases 0.000 description 3
- 208000014674 injury Diseases 0.000 description 3
- 238000005498 polishing Methods 0.000 description 3
- 230000002950 deficient Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000002929 anti-fatigue Effects 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 235000006708 antioxidants Nutrition 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Landscapes
- Powder Metallurgy (AREA)
Abstract
电子束钎焊修复高温合金叶片的方法，本发明涉及一种钎焊修复高温合金叶片的方法，它为了解决原有修复高温合金叶片的方法存在修复工艺复杂、修复周期长、钎焊修复时需要整体加热、钎焊工作时在高温停留时间长的问题。该方法通过以下步骤实现：(一)磨去叶片损伤并将损伤处打磨成槽，将钎料或合金粉末与丙酮或市售通用钎焊粘结剂混合成膏状并放入槽中；(二)设定工艺参数并钎焊；(三)当钎料或合金粉末完全熔化时，冷却至室温取出高温合金叶片，高温合金叶片被修复。本发明中电子束钎焊修复高温合金叶片的方法修复工艺简单，修复周期短，一个周期仅需要5min～10min，仅需对损伤的部位加热，修复时叶片在高温停留时间降低到原有方法的0.1～10％。A method for repairing superalloy blades by electron beam brazing. The invention relates to a method for repairing superalloy blades by brazing. In order to solve the problems in the original method for repairing superalloy blades, the repair process is complicated, the repair period is long, and the brazing repair needs The problem of long residence time at high temperature during overall heating and brazing work. The method is realized through the following steps: (1) grinding off the blade damage and grinding the damaged part into a groove, mixing solder or alloy powder with acetone or a commercially available general brazing adhesive to form a paste and putting it into the groove; 2) Setting process parameters and brazing; (3) When the solder or alloy powder is completely melted, cool to room temperature and take out the superalloy blade, and the superalloy blade is repaired. The method for repairing superalloy blades by electron beam brazing in the present invention has simple repairing process, short repairing cycle, and only needs 5 minutes to 10 minutes for one cycle, only needs to heat the damaged part, and the time of blades staying at high temperature during repairing is reduced to that of the original method. 0.1-10%.
Description
Technical field
The present invention relates to a kind of soldering and repair the method for high-temperature alloy blades.
Background technology
Excellent performance but the very expensive high-temperature alloy blades of price can work long hours in 600 ℃～1100 ℃ hot environment and have good anti-oxidant and hot corrosion resistance, good anti-fatigue performance and higher excellent properties such as fracture toughness, but since blade work long hours be worn, effects such as impact, high-temperature fuel gas and cold and hot fatigue, can crack, corrode and defective such as wearing and tearing, cause a large amount of blades to be scrapped; Adopt the high-temperature alloy blades service technique, reblading surface and inner defective are recovered even are strengthened its original performance etc., and this all will prolong the life cycle of engine greatly, effectively improve its economy.But there is the renovation technique complexity in the method for original reparation high-temperature alloy blades, and repairing efficiency is long, and one-period needs 5h～20h, needs whole heating when soldering is repaired, and energy loss is big, and is long at high-temperature residence time during soldering work, needs the problem of 0.5h～10h.
Summary of the invention
The present invention be for the method that solves original reparation high-temperature alloy blades have that renovation technique complexity, repairing efficiency are long, when soldering is repaired when the whole heating of needs, soldering work in the long problem of high-temperature residence time, and the method for the electron beam to braze that proposes reparation high-temperature alloy blades.This method realizes by following steps: (one) with sander with 2500～3500 rev/mins speed grind off to repair damage on the high-temperature alloy blades 60～100% and with the injury region grooving of polishing, to be that 0～90 ° 80 orders～800 purpose solders or alloy powder and mass concentration are that 95～99.5% acetone or commercially available general soldering binding agent are mixed into paste with the angle of wetting of blade mother metal, and paste mixture be put into the groove that polish and groove is filled up; (2) leave standstill 1～5 minute, the high-temperature alloy blades that will repair is put into vacuum chamber, and vacuumizing the vacuum that makes in the vacuum chamber is 4.50～5.30 * 10
-2Pa, being 100～150mm, line input mode in electron gun and the operating distance that will repair damage location, to add scanning, scan frequency be that 500～1000Hz, accelerating potential are that 55～60kV, focus current be that 1500～2700mA, temperature gather way are that 5～100 ℃/s, scan amplitude are that VX=0～30, VY=0～30 and sweep trace of electron beam are under the condition of function waveform track the high-temperature alloy blades damage location to be carried out soldering in order time to defocus; (3) when solder or alloy powder melt fully, lower the temperature with the speed of 5～100 ℃/s, take out high-temperature alloy blades when temperature is reduced to room temperature, high-temperature alloy blades is repaired.The method of electron beam to braze reparation high-temperature alloy blades is as thermal source with accurately controlled electron beam among the present invention, adopt the method fusing solder or the metal powder of local heat, the present invention is by the welding parameter of control electron beam focus current and line, make the temperature field of blade more even, reduce the effect of thermograde and thermal stress, avoided generation of defects such as fire check and pore.The method renovation technique of electron beam to braze reparation high-temperature alloy blades is simple among the present invention, repairing efficiency is short, one-period only needs 5min～10min, only needs the position heating to damage, and blade is reduced to 0.1～10% of original method at high-temperature residence time during reparation.
The specific embodiment
The specific embodiment one: electron beam to braze is repaired the method for high-temperature alloy blades in the present embodiment, it is characterized in that this method realizes by following steps: (one) with sander with 2500～3500 rev/mins speed grind off to repair damage on the high-temperature alloy blades 60～100% and with the injury region grooving of polishing, to be that 0～90 ° 80 orders～800 purpose solders or alloy powder and mass concentration are that 95～99.5% acetone or commercially available general soldering binding agent are mixed into paste with the angle of wetting of blade mother metal, and paste mixture be put into the groove that polish and groove is filled up; (2) leave standstill 1～5 minute, the high-temperature alloy blades that will repair is put into vacuum chamber, and vacuumizing the vacuum that makes in the vacuum chamber is 4.50～5.30 * 10
-2Pa, being 100～150mm, line input mode in electron gun and the operating distance that will repair damage location, to add scanning, scan frequency be that 500～1000Hz, accelerating potential are that 55～60kV, focus current be that 1500～2700mA, temperature gather way are that 5～100 ℃/s, scan amplitude are that VX=0～30, VY=0～30 and sweep trace of electron beam are under the condition of function waveform track the high-temperature alloy blades damage location to be carried out soldering in order time to defocus; (3) when solder or alloy powder melt fully, lower the temperature with the speed of 5～100 ℃/s, take out high-temperature alloy blades when temperature is reduced to room temperature, high-temperature alloy blades is repaired.
Present embodiment is particularly useful for the reparation of aero-engine high temperature blade.
The method renovation technique of electron beam to braze reparation high-temperature alloy blades is simple in the present embodiment, repairing efficiency is short, one-period only needs 5min～10min, only needs the position heating to damage, and blade is reduced to 0.1～10% of original method at high-temperature residence time during reparation.
The specific embodiment two: the difference of the present embodiment and the specific embodiment one is that step () high-temperature alloy blades is blade of aviation engine, moving turbine blade or guide vane; Solder is the BCo-1 solder in a kind of or cobalt-based solder among BNi-1 solder, BNi-2 solder, BNi-3 solder, BNi-4 solder, BNi-5 solder, BNi-6 solder, BNi-7 solder, BNi-8 solder, B п p24, B п p27 or the B п p11 in the nickel-based solder, and alloy powder is nickel-base alloy powder ZX.Ni17 or cobalt-base alloys powder ZX.Co55.Other step is identical with the specific embodiment one.
The specific embodiment three: the difference of the present embodiment and the specific embodiment one be in the step () with sander with 2800～3200 rev/mins speed grind off to repair damage on the high-temperature alloy blades 70～90% and with the injury region grooving of polishing.Other step is identical with the specific embodiment one.
The specific embodiment four: the difference of the present embodiment and the specific embodiment one is in the step () will to be that 150 orders～700 purpose solders of 5～88 ° or alloy powder and mass concentration are that 95～99.5% acetone or commercially available general soldering binding agent are mixed into paste with the angle of wetting of blade mother metal.Other step is identical with the specific embodiment one.
The specific embodiment five: the difference of the present embodiment and the specific embodiment one is in the step () will to be that 100 orders～650 purpose solders of 35 ° or alloy powder and mass concentration are that 96～99% acetone or commercially available general soldering binding agent are mixed into paste with the angle of wetting of blade mother metal.Other step is identical with the specific embodiment one.
The specific embodiment six: the difference of the present embodiment and the specific embodiment one is in (one) will to be that 35 ° 600 purpose solders or alloy powder and mass concentration are that 99% acetone is mixed into paste with the angle of wetting of blade mother metal.Other step is identical with the specific embodiment one.
The specific embodiment seven: it is 5.25 * 10 that the difference of the present embodiment and the specific embodiment one is to vacuumize in the step (two) vacuum that makes in the vacuum chamber
-2Pa.Other step is identical with the specific embodiment one.
The specific embodiment eight: the difference of the present embodiment and the specific embodiment one is that the function waveform track is a triangular trajectory in the step (two).Other step is identical with the specific embodiment one.
The specific embodiment nine: the difference of the present embodiment and the specific embodiment one is that the function waveform track is a circular trace in the step (two).Other step is identical with the specific embodiment one.
The specific embodiment ten: present embodiment is that with the difference of the specific embodiment one the function waveform track is for mixing the shape track in the step (two).Other step is identical with the specific embodiment one.
The specific embodiment 11: the difference of the present embodiment and the specific embodiment one is that the function waveform track is square track in the step (two).Other step is identical with the specific embodiment one.
The specific embodiment 12: the difference of the present embodiment and the specific embodiment one is that step (two) electron gun and the operating distance that will repair damage location are 110～145mm.Other step is identical with the specific embodiment one.
The specific embodiment 13: the difference of the present embodiment and the specific embodiment one is that step (two) electron gun and the operating distance that will repair damage location are 135mm.Other step is identical with the specific embodiment one.
The specific embodiment 14: the difference of the present embodiment and the specific embodiment one is that scan frequency is 550～950Hz in the step (two).Other step is identical with the specific embodiment one.
The specific embodiment 15: the difference of the present embodiment and the specific embodiment one is that scan frequency is 800Hz in the step (two).Other step is identical with the specific embodiment one.
The specific embodiment 16: the difference of the present embodiment and the specific embodiment one is that operating current is 1900～2600mA in the step (two).Other step is identical with the specific embodiment one.
The specific embodiment 17: the difference of the present embodiment and the specific embodiment one is that operating current is 2400mA in the step (two).Other step is identical with the specific embodiment one.
The specific embodiment 18: the difference of the present embodiment and the specific embodiment one is that it is 10～95 ℃/s that the middle temperature of step (two) gathers way.Other step is identical with the specific embodiment one.
The specific embodiment 19: the difference of the present embodiment and the specific embodiment one is that it is 20 ℃/s that the middle temperature of step (two) gathers way.Other step is identical with the specific embodiment one.
The specific embodiment 20: the difference of the present embodiment and the specific embodiment one is that it is 40 ℃/s that the middle temperature of step (two) gathers way.Other step is identical with the specific embodiment one.
The specific embodiment 21: the difference of the present embodiment and the specific embodiment one is that it is 60 ℃/s that the middle temperature of step (two) gathers way.Other step is identical with the specific embodiment one.
The specific embodiment 22: the difference of the present embodiment and the specific embodiment one is that it is 80 ℃/s that the middle temperature of step (two) gathers way.Other step is identical with the specific embodiment one.
The specific embodiment 23: the difference of the present embodiment and the specific embodiment one be in the step (two) the line input mode under defocus add scanning, scan amplitude is VX=8～24, VY=8～24.Other step is identical with the specific embodiment one.
The specific embodiment 24: the difference of the present embodiment and the specific embodiment one be in the step (two) the line input mode under defocus add scanning, scan amplitude is VX=12, VY=12.Other step is identical with the specific embodiment one.
The specific embodiment 25: the difference of the present embodiment and the specific embodiment one is in the step (two) that be 120～140mm at electron gun with the operating distance that will repair damage location, the line input mode under defocus and add scanning, scan frequency is 600～900Hz, accelerating potential is 56～59kV, focus current is 2000～2500mA, it is 20～90 ℃/s that temperature gathers way, scan amplitude is VX=5～25, VY=5～25 and sweep trace of electron beam are under the condition of the circular trace in the function waveform track high-temperature alloy blades damage location to be carried out soldering.Other step is identical with the specific embodiment one.
The specific embodiment 26: the difference of the present embodiment and the specific embodiment one is in the step (two) that be 125mm at electron gun with the operating distance that will repair damage location, the line input mode under defocus and add scanning, scan frequency is 1000Hz, accelerating potential is 55kV, focus current is 1790mA, it is 80 ℃/s that temperature gathers way, scan amplitude is VX=10, VY=10 and sweep trace of electron beam are under the condition of the square track in the function waveform track high-temperature alloy blades damage location to be carried out soldering.Other step is identical with the specific embodiment one.
The specific embodiment 27: the difference of the present embodiment and the specific embodiment one is in the step (three) to lower the temperature with the speed of 20～80 ℃/s when solder or alloy powder melt fully.Other step is identical with the specific embodiment one.
The specific embodiment 28: the difference of the present embodiment and the specific embodiment one is in the step (three) to lower the temperature with the speed of 60 ℃/s when solder or alloy powder melt fully.Other step is identical with the specific embodiment one.
The specific embodiment 29: the difference of the present embodiment and the specific embodiment one is in the step (three) to lower the temperature with the speed of 40 ℃/s when solder or alloy powder melt fully.Other step is identical with the specific embodiment one.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CNB2007100716952A CN100546748C (en) | 2007-01-26 | 2007-01-26 | Electron beam brazing method for repairing superalloy blades |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100716952A CN100546748C (en) | 2007-01-26 | 2007-01-26 | Electron beam brazing method for repairing superalloy blades |
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| CN101007366A true CN101007366A (en) | 2007-08-01 |
| CN100546748C CN100546748C (en) | 2009-10-07 |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101811222A (en) * | 2010-05-20 | 2010-08-25 | 西安航天远征流体控制股份有限公司 | Method for welding titanium anode slot |
| CN101890549A (en) * | 2010-08-17 | 2010-11-24 | 中国航空工业集团公司北京航空制造工程研究所 | Method for brazing end cover of turbine blade of engine by using vacuum electron beam |
| US7932477B2 (en) | 2007-11-23 | 2011-04-26 | Tsinghua University | Electron beam heating system having carbon nanotubes |
| CN102029449A (en) * | 2009-09-30 | 2011-04-27 | 通用电气公司 | Method and system for focused energy brazing |
| CN102120292A (en) * | 2011-03-18 | 2011-07-13 | 中国航空工业集团公司北京航空制造工程研究所 | Vacuum brazing repairing method for cracks of high-temperature alloy thin-wall part |
| US7988515B2 (en) | 2007-11-02 | 2011-08-02 | Tsinghua University | Method for manufacturing field emission electron source having carbon nanotubes |
| US7997950B2 (en) | 2007-11-02 | 2011-08-16 | Hon Hai Precision Industry Co., Ltd. | Field emission electron source having carbon nanotubes and method for manufacturing the same |
| US8029328B2 (en) | 2007-11-02 | 2011-10-04 | Tsinghua University | Method for manufacturing field emission electron source having carbon nanotubes |
| CN101626862B (en) * | 2007-10-15 | 2012-11-28 | 三菱重工业株式会社 | Method of repair |
| CN103372713A (en) * | 2013-02-20 | 2013-10-30 | 天津工业大学 | Aero-engine blade damage repair method |
| CN107363356A (en) * | 2011-03-08 | 2017-11-21 | 通用电气公司 | Make the method and component of component |
| CN108326508A (en) * | 2018-01-24 | 2018-07-27 | 沈阳金研激光再制造技术开发有限公司 | A kind of cobalt base superalloy burner inner liner crackle, ablated region process method for welding and repairing |
| CN109175656A (en) * | 2018-10-30 | 2019-01-11 | 南昌航空大学 | A kind of method that electron beam frit repairs high-strength steel defect |
| CN110052681A (en) * | 2011-11-03 | 2019-07-26 | 西门子能源公司 | The nearly ternary eutectic alloy of NI-TI-CR for internal passages of gas turbine components reparation |
| CN112191967A (en) * | 2020-09-29 | 2021-01-08 | 中国航发动力股份有限公司 | Electron beam brazing repair method for local defects of vacuum brazing part |
| CN112543690A (en) * | 2018-08-09 | 2021-03-23 | 西门子能源美国公司 | Pre-sintered preform for repairing a gas turbine component in service |
| FR3121376A1 (en) * | 2021-04-06 | 2022-10-07 | Safran Helicopter Engines | ELECTRON BEAM BRAZING |
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2007
- 2007-01-26 CN CNB2007100716952A patent/CN100546748C/en not_active Expired - Fee Related
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| CN101626862B (en) * | 2007-10-15 | 2012-11-28 | 三菱重工业株式会社 | Method of repair |
| US7988515B2 (en) | 2007-11-02 | 2011-08-02 | Tsinghua University | Method for manufacturing field emission electron source having carbon nanotubes |
| US7997950B2 (en) | 2007-11-02 | 2011-08-16 | Hon Hai Precision Industry Co., Ltd. | Field emission electron source having carbon nanotubes and method for manufacturing the same |
| US8029328B2 (en) | 2007-11-02 | 2011-10-04 | Tsinghua University | Method for manufacturing field emission electron source having carbon nanotubes |
| US7932477B2 (en) | 2007-11-23 | 2011-04-26 | Tsinghua University | Electron beam heating system having carbon nanotubes |
| CN102029449A (en) * | 2009-09-30 | 2011-04-27 | 通用电气公司 | Method and system for focused energy brazing |
| CN102029449B (en) * | 2009-09-30 | 2016-05-11 | 通用电气公司 | For the method and system of focused energy brazing |
| CN101811222A (en) * | 2010-05-20 | 2010-08-25 | 西安航天远征流体控制股份有限公司 | Method for welding titanium anode slot |
| CN101890549B (en) * | 2010-08-17 | 2012-06-20 | 中国航空工业集团公司北京航空制造工程研究所 | Method for brazing end cover of turbine blade of engine by using vacuum electron beam |
| CN101890549A (en) * | 2010-08-17 | 2010-11-24 | 中国航空工业集团公司北京航空制造工程研究所 | Method for brazing end cover of turbine blade of engine by using vacuum electron beam |
| CN107363356A (en) * | 2011-03-08 | 2017-11-21 | 通用电气公司 | Make the method and component of component |
| CN102120292A (en) * | 2011-03-18 | 2011-07-13 | 中国航空工业集团公司北京航空制造工程研究所 | Vacuum brazing repairing method for cracks of high-temperature alloy thin-wall part |
| CN102120292B (en) * | 2011-03-18 | 2012-07-25 | 中国航空工业集团公司北京航空制造工程研究所 | Vacuum brazing repairing method for cracks of high-temperature alloy thin-wall part |
| CN110052681A (en) * | 2011-11-03 | 2019-07-26 | 西门子能源公司 | The nearly ternary eutectic alloy of NI-TI-CR for internal passages of gas turbine components reparation |
| CN103372713A (en) * | 2013-02-20 | 2013-10-30 | 天津工业大学 | Aero-engine blade damage repair method |
| CN103372713B (en) * | 2013-02-20 | 2015-10-14 | 天津工业大学 | A kind of restorative procedure of aero-engine blade damage |
| CN108326508A (en) * | 2018-01-24 | 2018-07-27 | 沈阳金研激光再制造技术开发有限公司 | A kind of cobalt base superalloy burner inner liner crackle, ablated region process method for welding and repairing |
| CN112543690A (en) * | 2018-08-09 | 2021-03-23 | 西门子能源美国公司 | Pre-sintered preform for repairing a gas turbine component in service |
| CN109175656A (en) * | 2018-10-30 | 2019-01-11 | 南昌航空大学 | A kind of method that electron beam frit repairs high-strength steel defect |
| CN112191967A (en) * | 2020-09-29 | 2021-01-08 | 中国航发动力股份有限公司 | Electron beam brazing repair method for local defects of vacuum brazing part |
| FR3121376A1 (en) * | 2021-04-06 | 2022-10-07 | Safran Helicopter Engines | ELECTRON BEAM BRAZING |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100546748C (en) | 2009-10-07 |
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