CN106493505A - The advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired - Google Patents
The advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired Download PDFInfo
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- CN106493505A CN106493505A CN201611006722.3A CN201611006722A CN106493505A CN 106493505 A CN106493505 A CN 106493505A CN 201611006722 A CN201611006722 A CN 201611006722A CN 106493505 A CN106493505 A CN 106493505A
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- stator blade
- welding
- blade
- dimensional dimension
- reparation
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- 238000000034 method Methods 0.000 title claims abstract description 37
- 238000003466 welding Methods 0.000 title claims abstract description 31
- 229910000679 solder Inorganic materials 0.000 claims abstract description 29
- 238000005219 brazing Methods 0.000 claims abstract description 25
- 238000004140 cleaning Methods 0.000 claims abstract description 22
- 238000007689 inspection Methods 0.000 claims abstract description 13
- 238000010438 heat treatment Methods 0.000 claims abstract description 12
- 238000009413 insulation Methods 0.000 claims abstract description 12
- 239000012720 thermal barrier coating Substances 0.000 claims abstract description 12
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims abstract description 8
- 238000001514 detection method Methods 0.000 claims abstract description 8
- 238000012545 processing Methods 0.000 claims abstract description 6
- 229910052786 argon Inorganic materials 0.000 claims abstract description 4
- 238000005476 soldering Methods 0.000 claims description 12
- 238000012360 testing method Methods 0.000 claims description 10
- 230000000149 penetrating effect Effects 0.000 claims description 7
- 208000031481 Pathologic Constriction Diseases 0.000 claims description 5
- 239000012459 cleaning agent Substances 0.000 claims description 5
- 239000000356 contaminant Substances 0.000 claims description 5
- 238000002594 fluoroscopy Methods 0.000 claims description 5
- 238000000465 moulding Methods 0.000 claims description 5
- 238000005498 polishing Methods 0.000 claims description 5
- 239000000126 substance Substances 0.000 claims description 5
- 210000001215 vagina Anatomy 0.000 claims description 5
- 230000001680 brushing effect Effects 0.000 claims description 2
- 239000000463 material Substances 0.000 claims 1
- 208000037656 Respiratory Sounds Diseases 0.000 abstract description 3
- 206010011376 Crepitations Diseases 0.000 abstract description 2
- 241001076960 Argon Species 0.000 description 2
- 235000013876 argon Nutrition 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 208000025599 Heat Stress disease Diseases 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
-
- 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
- B23P6/04—Repairing fractures or cracked metal parts or products, e.g. castings
- B23P6/045—Repairing fractures or cracked metal parts or products, e.g. castings of turbine components, e.g. moving or stationary blades, rotors, etc.
-
- 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
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/008—Soldering within a furnace
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacture Of Motors, Generators (AREA)
Abstract
The present invention relates to the advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired, comprises the following steps：S1, removing thermal barrier coating；S2, flaw detection；S3, removal oxide；S4, cleaning；S5, spot welding；S6, insulation；S7, vacuum brazing：It is evacuated to<6.30*10‑2Pa, rises to 550～560 DEG C with the heating rate of 10～12 DEG C/min, is incubated 10～12min；Then 1170～1175 DEG C are risen to the heating rate of 15～16 DEG C/min again, is incubated 20～30min；It is cooled to 800～900 DEG C with stove, then fills 800～1200mbar argon and be cooled to 70 DEG C and come out of the stove；S8, the processing of type face；S9, postwelding inspection.Advantages of the present invention：Simple to operate, repairing quality is high, after reparation, solder hardly shrinks, the reparation of three-dimensional dimension can be met, can also meet reparation of the width more than 1mm crackles, the reparation of aero-engine stator blade three-dimensional dimension method for welding is can be widely applied to, solve to carry out the repair issues of device blade three-dimensional dimension with conventional brazing mode.
Description
Technical field
The present invention relates to aircraft engine maintenance field, particularly a kind of aero-engine stator blade three-dimensional dimension is repaiied
Multiple advanced method for welding.
Background technology
Aero-turbine stator blade is the maximum hot-end component of heat-shock in electromotor, and which uses temperature one
As be higher than 1000 DEG C, in high temperature, high pressure, the adverse circumstances of exhaust gas corrosion be on active service.Due to temperature field uneven, with electromotor
Transient temperature drastically changes, and produces very big thermal stress and thermal strain in guide vane, cause heat fatigue cracking to germinate, extend,
Blade bending and thermal barrier coating such as come off at the failure.
For crack width is more than failures such as 1mm, inadequate, the blade flexural deformations of blade dimensions, using traditional soldering side
Method cannot meet the repairing of stator blade.At present, there is no open report carry out stator blade three-dimensional dimension both at home and abroad to repair
Multiple welding method；Therefore, it is badly in need of a kind of welding method for carrying out stator blade three-dimensional dimension reparation, solves guider leaf
A reparation difficult problem for piece three-dimensional dimension.
Content of the invention
It is an object of the invention to overcoming the shortcoming of prior art, there is provided a kind of high aviation of simple to operate, repairing quality
The advanced method for welding that electromotor stator blade three-dimensional dimension is repaired, checks flawless, pore through fluorescent penetrating inspection, x-ray detection
Etc. failure, after the stator blade after reparation is through engine long examination examination, brazed portions flawless, nothing fall the phenomenons such as block, meet
Electromotor use requirement.
The purpose of the present invention is achieved through the following technical solutions：A kind of aero-engine stator blade three-dimensional dimension is repaiied
Multiple advanced method for welding, comprises the following steps：
S1, removing thermal barrier coating：According to stator blade thermal barrier coating pattern, thermal boundary is removed using chemical method or blast method and is applied
Layer；
S2, flaw detection：Trouble location is marked using fluorescent penetrating inspection, and is taken a picture；
S3, removal oxide：Using fluorion cleaning technique cleaning blade surface and inside crack oxide, until surface and splitting
Stricture of vagina subscale is removed completely；
S4, cleaning：Using aqueous cleaning agent cleaning blade surface and oil contaminant, foul；
S5, spot welding：Trouble location is welded in the solder point of presintering using spot welding mode, it is ensured that solder is fitted intact with blade；
S6, insulation：Stator blade is put into 30～50min of insulation in 100～150 DEG C of baking oven；
S7, vacuum brazing：It is evacuated to<6.30*10-2Pa, rises to 550～560 DEG C with the heating rate of 10～12 DEG C/min,
10～12min of insulation；Then 1170～1175 DEG C are risen to the heating rate of 15～16 DEG C/min again, is incubated 20～30min；With
Stove is cooled to 800～900 DEG C, then fills 800～1200mbar argon and is cooled to 70 DEG C and comes out of the stove；
S8, the processing of type face：Stator blade brazed portions after to soldering carry out polishing repairing type, make the molding surface size at reparation position
Return to the size of new blade；
S9, postwelding inspection：Stator blade after reparation carries out X-ray, fluoroscopy, if meet brazing quality touchstone repairing
Finish again, if not meeting brazing quality touchstone, repeat step S1～S8.
In step S5, the solder thickness ratio needs the high 0.5～1.5mm of repairing type apparent height.
In step S5, after spot welding solder, also include brushing the step of stop-off gent is around solder, and between stop-off gent and solder
Every 0.2～0.5mm.
After step S9, the stator blade for meeting brazing quality touchstone is also included repairing the examination examination of posterior lobe length of a film
Step：Stator blade after to reparation is randomly selected 3 and carries out endurance test test, after long examination, the equal nothing of soldering restoring area
Crackle, nothing fall block phenomenon, are examined by long examination.
The present invention has advantages below：
1st, cleaned using Aqueous cleaning machine, rust inhibition is good, energy consumption is low, environmental protection.
2nd, the special vacuum brazing of employing of the invention, after tested, solder brazing position shrinkage factor is only 5%, and reparation is led
The failures such as flawless, pore are checked to device vanes fluorescent penetrating inspection, x-ray detection, the stator blade after reparation is through engine long
After examination examination, brazed portions flawless, nothing fall the phenomenons such as block, meet electromotor use requirement.
3rd, after restorative procedure operating process of the invention is simple, do not need high professional qualification operator, soldering, solder does not almost have
There is a contraction, process is simple, quick, reliable, this kind of method for welding can meet the reparation of three-dimensional dimension, can also meet width exceedes
The reparation of 1mm crackles, can be widely applied to the reparation of aero-engine stator blade three-dimensional dimension method for welding, solves use
Conventional brazing mode cannot carry out the repair issues of device blade three-dimensional dimension.
Specific embodiment
With reference to embodiment, the present invention will be further described, but protection scope of the present invention is not limited to following institute
State.
【Embodiment 1】
The advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired, comprises the following steps：
S1, removing thermal barrier coating：According to stator blade thermal barrier coating pattern, thermal boundary is removed using chemical method or blast method and is applied
Layer；
S2, flaw detection：Trouble location is marked using fluorescent penetrating inspection, and is taken a picture；
S3, removal oxide：Using fluorion cleaning technique cleaning blade surface and inside crack oxide, until surface and splitting
Stricture of vagina subscale is removed completely；
S4, cleaning：Using aqueous cleaning agent cleaning blade surface and oil contaminant, foul；
S5, spot welding：Trouble location is welded in the solder point of presintering using spot welding mode, it is ensured that solder fit with blade intact,
The solder thickness ratio needs the high 1.5mm of repairing type apparent height, then brushes stop-off gent around solder, and between stop-off gent and solder
Every 0.5mm；
S6, insulation：Stator blade is put into insulation 30min in 150 DEG C of baking oven；
S7, vacuum brazing：It is evacuated to<6.30*10-2Pa, rises to 560 DEG C with the heating rate of 12 DEG C/min, is incubated 10min；
Then 1170 DEG C are risen to the heating rate of 15 DEG C/min again, is incubated 30min；It is cooled to 800 DEG C with stove, then fills 1200mbar argons
Air cooling is come out of the stove to 70 DEG C；
S8, the processing of type face：Stator blade brazed portions after to soldering carry out polishing repairing type, make the molding surface size at reparation position
Return to the size of new blade；
S9, postwelding inspection：Stator blade after reparation carries out X-ray, fluoroscopy, if meet brazing quality touchstone repairing
Finish again, if not meeting brazing quality touchstone, repeat step S1～S8.
The step of repairing the examination examination of posterior lobe length of a film is also included to the stator blade for meeting brazing quality touchstone：To repairing
Stator blade after multiple is randomly selected 3 and carries out endurance test test, and after long examination, the equal flawless of soldering restoring area, nothing are fallen
Block phenomenon, is examined by long examination.
【Embodiment 2】
The advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired, comprises the following steps：
S1, removing thermal barrier coating：According to stator blade thermal barrier coating pattern, thermal boundary is removed using chemical method or blast method and is applied
Layer；
S2, flaw detection：Trouble location is marked using fluorescent penetrating inspection, and is taken a picture；
S3, removal oxide：Using fluorion cleaning technique cleaning blade surface and inside crack oxide, until surface and splitting
Stricture of vagina subscale is removed completely；
S4, cleaning：Using aqueous cleaning agent cleaning blade surface and oil contaminant, foul；
S5, spot welding：Trouble location is welded in the solder point of presintering using spot welding mode, it is ensured that solder fit with blade intact,
The solder thickness ratio needs the high 0.1mm of repairing type apparent height, then brushes stop-off gent around solder, and between stop-off gent and solder
Every 0.3mm；
S6, insulation：Stator blade is put into insulation 40min in 130 DEG C of baking oven；
S7, vacuum brazing：It is evacuated to<6.30*10-2Pa, rises to 555 DEG C with the heating rate of 11 DEG C/min, is incubated 11min；
Then 1172 DEG C are risen to the heating rate of 15.5 DEG C/min again, is incubated 25min；It is cooled to 850 DEG C with stove, then fills 1000mbar
Argon is cooled to 70 DEG C and comes out of the stove；
S8, the processing of type face：Stator blade brazed portions after to soldering carry out polishing repairing type, make the molding surface size at reparation position
Return to the size of new blade；
S9, postwelding inspection：Stator blade after reparation carries out X-ray, fluoroscopy, if meet brazing quality touchstone repairing
Finish again, if not meeting brazing quality touchstone, repeat step S1～S8.
The step of repairing the examination examination of posterior lobe length of a film is also included to the stator blade for meeting brazing quality touchstone：To repairing
Stator blade after multiple is randomly selected 3 and carries out endurance test test, and after long examination, the equal flawless of soldering restoring area, nothing are fallen
Block phenomenon, is examined by long examination.
【Embodiment 3】
The advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired, comprises the following steps：
S1, removing thermal barrier coating：According to stator blade thermal barrier coating pattern, thermal boundary is removed using chemical method or blast method and is applied
Layer；
S2, flaw detection：Trouble location is marked using fluorescent penetrating inspection, and is taken a picture；
S3, removal oxide：Using fluorion cleaning technique cleaning blade surface and inside crack oxide, until surface and splitting
Stricture of vagina subscale is removed completely；
S4, cleaning：Using aqueous cleaning agent cleaning blade surface and oil contaminant, foul；
S5, spot welding：Trouble location is welded in the solder point of presintering using spot welding mode, it is ensured that solder fit with blade intact,
The solder thickness ratio needs the high 0.5mm of repairing type apparent height, then brushes stop-off gent around solder, and between stop-off gent and solder
Every 0.2mm；
S6, insulation：Stator blade is put into insulation 50min in 100 DEG C of baking oven；
S7, vacuum brazing：It is evacuated to<6.30*10-2Pa, rises to 550 DEG C with the heating rate of 10 DEG C/min, is incubated 12min；
Then 1175 DEG C are risen to the heating rate of 16 DEG C/min again, is incubated 20min；It is cooled to 900 DEG C with stove, then fills 800mbar argons
Air cooling is come out of the stove to 70 DEG C；
S8, the processing of type face：Stator blade brazed portions after to soldering carry out polishing repairing type, make the molding surface size at reparation position
Return to the size of new blade；
S9, postwelding inspection：Stator blade after reparation carries out X-ray, fluoroscopy, if meet brazing quality touchstone repairing
Finish again, if not meeting brazing quality touchstone, repeat step S1～S8.
The step of repairing the examination examination of posterior lobe length of a film is also included to the stator blade for meeting brazing quality touchstone：To repairing
Stator blade after multiple is randomly selected 3 and carries out endurance test test, and after long examination, the equal flawless of soldering restoring area, nothing are fallen
Block phenomenon, is examined by long examination.
Claims (4)
1. the advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired, it is characterised in that：Including following
Step：
S1, removing thermal barrier coating：According to stator blade thermal barrier coating pattern, thermal boundary is removed using chemical method or blast method and is applied
Layer；
S2, flaw detection：Trouble location is marked using fluorescent penetrating inspection, and is taken a picture；
S3, removal oxide：Using fluorion cleaning technique cleaning blade surface and inside crack oxide, until surface and splitting
Stricture of vagina subscale is removed completely；
S4, cleaning：Using aqueous cleaning agent cleaning blade surface and oil contaminant, foul；
S5, spot welding：Trouble location is welded in the solder point of presintering using spot welding mode, it is ensured that solder is fitted intact with blade；
S6, insulation：Stator blade is put into 30～50min of insulation in 100～150 DEG C of baking oven；
S7, vacuum brazing：It is evacuated to<6.30*10-2Pa, rises to 550～560 DEG C with the heating rate of 10～12 DEG C/min, protects
10～12min of temperature；Then 1170～1175 DEG C are risen to the heating rate of 15～16 DEG C/min again, is incubated 20～30min；With stove
It is cooled to 800～900 DEG C, then fills 800～1200mbar argon and be cooled to 70 DEG C and come out of the stove；
S8, the processing of type face：Stator blade brazed portions after to soldering carry out polishing repairing type, make the molding surface size at reparation position
Return to the size of new blade；
S9, postwelding inspection：Stator blade after reparation carries out X-ray, fluoroscopy, if meet brazing quality touchstone repairing
Finish again, if not meeting brazing quality touchstone, repeat step S1～S8.
2. the advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired according to claim 1, its
It is characterised by：In step S5, the solder thickness ratio needs the high 0.5～1.5mm of repairing type apparent height.
3. the advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension according to claim 1 or claim 2 is repaired,
It is characterized in that：In step S5, after spot welding solder, also include brushing the step of stop-off gent is around solder, and stop-off gent and pricker
0.2～0.5mm of material interval.
4. the advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired according to claim 1, its
It is characterised by：After step S9, the stator blade for meeting brazing quality touchstone is also included repairing the examination examination of posterior lobe length of a film
The step of：Stator blade after to reparation is randomly selected 3 and carries out endurance test test, and after long examination, soldering restoring area is equal
Flawless, nothing fall block phenomenon, are examined by long examination.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611006722.3A CN106493505A (en) | 2016-11-16 | 2016-11-16 | The advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611006722.3A CN106493505A (en) | 2016-11-16 | 2016-11-16 | The advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired |
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| CN106493505A true CN106493505A (en) | 2017-03-15 |
Family
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|---|---|---|---|
| CN201611006722.3A Pending CN106493505A (en) | 2016-11-16 | 2016-11-16 | The advanced method for welding that a kind of aero-engine stator blade three-dimensional dimension is repaired |
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Cited By (9)
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| CN108723621A (en) * | 2018-06-11 | 2018-11-02 | 浙江科技学院 | A kind of side welding method of the deformable metal foil structure of small initial angle |
| CN109048220A (en) * | 2018-08-31 | 2018-12-21 | 贵州凯阳航空发动机有限公司 | A method of replacement aircraft engine blade |
| CN109175881A (en) * | 2018-09-28 | 2019-01-11 | 中国人民解放军第五七九工厂 | A kind of vacuum brazing method of aero-turbine stator blade surgical repair |
| CN109434233A (en) * | 2018-11-02 | 2019-03-08 | 中国航发北京航空材料研究院 | A kind of preprosthetic removing surface method of single crystal turbine guide vane crackle soldering |
| CN112045363A (en) * | 2020-08-07 | 2020-12-08 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN114131285A (en) * | 2021-12-24 | 2022-03-04 | 上海科技大学 | A kind of repairing method of metal parts and use thereof |
| CN115365595A (en) * | 2022-09-30 | 2022-11-22 | 成都和鸿科技股份有限公司 | Brazing method for duplex guide vane |
| CN116100125A (en) * | 2022-09-07 | 2023-05-12 | 中国航发北京航空材料研究院 | Repairing process for defects of casting superalloy guide structural member |
| CN117464307A (en) * | 2023-11-10 | 2024-01-30 | 中国航发沈阳黎明航空发动机有限责任公司 | An in-situ brazing repair method for turbine guide blade cracks |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108723621B (en) * | 2018-06-11 | 2020-06-09 | 浙江科技学院 | Side welding method of deformable metal foil structure with small initial included angle |
| CN108723621A (en) * | 2018-06-11 | 2018-11-02 | 浙江科技学院 | A kind of side welding method of the deformable metal foil structure of small initial angle |
| CN109048220A (en) * | 2018-08-31 | 2018-12-21 | 贵州凯阳航空发动机有限公司 | A method of replacement aircraft engine blade |
| CN109175881A (en) * | 2018-09-28 | 2019-01-11 | 中国人民解放军第五七九工厂 | A kind of vacuum brazing method of aero-turbine stator blade surgical repair |
| CN109434233A (en) * | 2018-11-02 | 2019-03-08 | 中国航发北京航空材料研究院 | A kind of preprosthetic removing surface method of single crystal turbine guide vane crackle soldering |
| CN112045363B (en) * | 2020-08-07 | 2022-03-11 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN112045363A (en) * | 2020-08-07 | 2020-12-08 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN114131285A (en) * | 2021-12-24 | 2022-03-04 | 上海科技大学 | A kind of repairing method of metal parts and use thereof |
| CN114131285B (en) * | 2021-12-24 | 2023-08-22 | 上海科技大学 | A kind of repairing method and application of metal parts |
| CN116100125A (en) * | 2022-09-07 | 2023-05-12 | 中国航发北京航空材料研究院 | Repairing process for defects of casting superalloy guide structural member |
| CN116100125B (en) * | 2022-09-07 | 2024-09-13 | 中国航发北京航空材料研究院 | Repairing method for defects of casting superalloy guide structural member |
| CN115365595A (en) * | 2022-09-30 | 2022-11-22 | 成都和鸿科技股份有限公司 | Brazing method for duplex guide vane |
| CN117464307A (en) * | 2023-11-10 | 2024-01-30 | 中国航发沈阳黎明航空发动机有限责任公司 | An in-situ brazing repair method for turbine guide blade cracks |
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