CN106903396A - Antifriction alloy welding procedure - Google Patents
Antifriction alloy welding procedure Download PDFInfo
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- CN106903396A CN106903396A CN201710126679.2A CN201710126679A CN106903396A CN 106903396 A CN106903396 A CN 106903396A CN 201710126679 A CN201710126679 A CN 201710126679A CN 106903396 A CN106903396 A CN 106903396A
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- welding
- antifriction alloy
- alloys
- pressure turbine
- welding procedure
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Classifications
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- 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
- B23K9/00—Arc welding or cutting
- B23K9/16—Arc welding or cutting making use of shielding gas
- B23K9/167—Arc welding or cutting making use of shielding gas and of a non-consumable electrode
-
- 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
- B23K9/00—Arc welding or cutting
- B23K9/23—Arc welding or cutting taking account of the properties of the materials to be welded
-
- 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
- B23K9/00—Arc welding or cutting
- B23K9/235—Preliminary treatment
Abstract
The invention discloses a kind of antifriction alloy welding procedure, the technique is welded using pulse electric current welding procedure wide and K4208 alloys, and the technological parameter in welding process is：Welding electrode is tungsten electrode；Welding current is 100 140A；Welding distance is 3+0.5mm；Weld interval is 7 13s；Amount of current pulses is 2Hz；The 10L/min of argon flow amount 6.The present invention has uniform arborescent structure using pulse electric current welding K4208 wear-resistant blocks wide, and corresponding circle of sensation is less than 0.5mm, and hardness is conducive to removal and repairs again in more than HV600 using technique welding wearing layer.
Description
Technical field
The present invention relates to weld aspect technical field, a kind of antifriction alloy welding procedure is concretely related to.
Background technology
RD-93 engines are the relatively advanced 3rd generation aero-engines of Russia, are restricted when service technique is introduced,
The crucial special warfare such as particularly advanced welding, Surface Engineering and heat treatment is more strictly controlled, the introduction of these techniques
Limited by the Russian national defence export of techniques, low-pressure turbine blade integral shroud antifriction alloy welding procedure for limitation the export of techniques it
One.And the wear-resistant block on the original-pack low-pressure turbine blade of RD-93 engines tests hardness in more than HV600, wear-resistant block is through chemistry
Constituent analysis, its composition is identical with K4208 alloys.K4208 antifriction alloy application studies are rarely reported, national engine turbine leaf
Bead-welding technology being used piece integral shroud wearing layer, its high-abrasive material is CoCrMo/CoCrW materials more.China's type newly develops turbofan hair
Motivation machine low-pressure turbine blade integral shroud wearing layer welds K4208 alloys using heap, and its average hardness is HV550 or so.Therefore, state
Interior existing welding procedure can not meet the repairing of RD-93 engine low-pressure turbine blades, it is necessary to carry out the exploitation of welding procedure.
The problem that existing low-pressure turbine blade integral shroud wear-resistant block welding procedure is present, with aeronautical product requirement quality stability
Do not correspond.To ensure the h type engine h low-pressure turbine blade repairing quality, it is necessary to carry out Low Pressure Turbine Rotor blade antifriction alloy
Welding process is studied.
The content of the invention
It is high that the technical problem to be solved in the present invention is to provide a kind of welding hardness, meets the wear-resisting of low-pressure turbine blade welding
The antifriction alloy welding procedure of alloy welding requirements.
In order to solve the above-mentioned technical problem, the technical scheme is that：A kind of antifriction alloy welding procedure, the technique is adopted
Welded with pulse electric current welding procedure wide and K4208 alloys, the technological parameter in welding process is：Welding electrode is tungsten electricity
Pole；Welding current is 100-140A；Welding distance is 3+0.5mm；Weld interval is 7-13s；Amount of current pulses is 2Hz；Argon gas
Flow 6-10L/min.
Preferably, the technological parameter in welding process is：Welding electrode is tungsten electrode；Electric current is 120A；Welding distance is 3
+0.5mm；Weld interval is 10s；Amount of current pulses is 2Hz；Argon flow amount is 7.5L/min.
Preferably, the technique comprises the following steps：
(1) K4208 alloys are selected, it is cut and is cleaned；
(2) welding torch position is adjusted, makes it perpendicular to the working face of workbench；
(3) Low Pressure Turbine Rotor blade shroud is fixed on the semi-automatic wear-resisting block welding of Low Pressure Turbine Rotor blade shroud
On the fixture assembly of accessory system；Ensure that the tungsten electrode of welding is perpendicularly oriented to the center of low-pressure turbine blade integral shroud solder side；
(4) adjustment of welding gun and blade face of weld, regulation welding condition is welded.
Preferably, the cutting uses common wire cutting that K4208 alloys are cut into size for 5.2x4.5x1.5mm is welded
Connect block.
Preferably, the cleaning is to carry out 5-10min pickling in the mixed solution of HCl+FeCL3+HNO3.
Preferably, the volume ratio of HCl, FeCL3 and HNO3 is in the mixing solution of the HCl+FeCL3+HNO3：1:1:
1。
Compared with prior art, the beneficial effects of the invention are as follows：1st, had using pulse electric current welding K4208 wear-resistant blocks wide
Uniform arborescent structure, corresponding circle of sensation is less than 0.5mm, and hardness is conducive to removal in more than HV600 using technique welding wearing layer
Again repair；2nd, using pulse flow welding K4208 wearing layers performance and В Ж Л 2- В И antifriction alloy phases made in Russia wide
Closely, can be used to repair low-pressure turbine leaf with K4208 alloy replacing В Ж Л 2- В И antifriction alloys are welded using pulse flow wide
The repairing of piece integral shroud.
Brief description of the drawings
The wear-resisting block welding schematic diagram of the wear-resisting low-pressure turbine blade integral shrouds of Fig. 1；
The structural representation of Fig. 2 semi-automation Low Pressure Turbine Rotor wear-resisting block welding accessory systems of blade shroud；
The original coarse-grain local organization patterns of Fig. 3；
Typical organization after Fig. 4 K4208 welding；
Fig. 5 solder joint delivery positions do not merge pattern (electric current 80A)；
Fig. 6 delivery position matrixes crystal boundary part overstriking typical case's pattern (electric current 150A)；
The local slight typical pattern (electric current 160A) of cracking of Fig. 7 delivery positions.
Specific embodiment
Specific embodiment of the invention is described further below in conjunction with the accompanying drawings.Herein it should be noted that for
The explanation of these implementation methods is used to help understand the present invention, but does not constitute limitation of the invention.Additionally, disclosed below
As long as each implementation method of the invention in involved technical characteristic do not constitute conflict each other and can just be mutually combined.
K4208 alloys in the present embodiment are prior art, from Beijing iron and steel research institute Zong Yuan.
1st, test
1.1 testing equipments
Micro Vickers：Perseverance one EM-1000VP, hardness determination：Test load is 300g, pressure head load time 10S；
Microscope：Zeiss, Germany electron microscope；
1.2nd, the preparation of wear-resistant block
The antifriction alloy requirement welded according to RD-93 engines low-pressure turbine blade, common line is used by K4208 alloys
Cutting by into the size 5.2x4.5x1.5mm for meeting welding, in HCl+FeCL3+HNO3Solution carries out 5-10min pickling removals
Wire cutting galvano-cautery layer, be prepared into and meet engine overhaul welding requirements, preferably, in the mixing solution HCl, FeCL3 and
The volume ratio of HNO3 is：1:1:1, naturally it is also possible to prepared according to actual requirement.
1.3rd, welding procedure
Welded using pulse electric current wide, entered with the wear-resisting block welding accessory system of semi-automatic Low Pressure Turbine Rotor blade shroud
Row welding, as shown in figure 1, the semi-automatic wear-resisting block welding accessory system of Low Pressure Turbine Rotor blade shroud, including workbench
1st, microcomputer controller 2, support 3, servomotor 5, leading screw sub-assembly 6, fixture assembly 10, wherein microcomputer controller 2, watch
The non-prior art of motor 5, leading screw sub-assembly 6, fixture assembly 10 is taken, fixture assembly 10 is fixed on workbench 1, is used for
Fixed low-pressure turbine blade, workbench 1 is provided with support guide 13；The bottom of support 3 is fixed on support guide 13, such support
3 just can on support guide 13 slide anteroposterior；Perpendicular guide rail 4 is respectively equipped with the left and right sidesing pillar of support 3；The top of support 3 is provided with to be watched
Take motor 5；Servomotor 5 is connected by leading screw sub-assembly 6 with rear support plate 7；Rear support plate 7 is consolidated by screw with front pressuring plate 9
Fixed connection；Rear support plate 7 is fixedly connected with cross rail 8；Cross rail 8 is fixed on crossbeam 11；The two ends connection sliding block 12 of crossbeam 11；
Sliding block 12 is fixed on perpendicular guide rail 4, and can be slided up and down along perpendicular guide rail 4；Microcomputer controller 2 is electrically connected with servomotor 5, is
It is easy to operation microcomputer controller 2 to be fixed on workbench 1；The microcomputer controller 2 (is not drawn into welding equipment in figure
Come) it is electrically connected with.
Concrete operations are as follows：
(1), equipment adjustment：
1st, the fixation and adjustment of welding gun：Welding gun is fixed on crossbeam 11 by front pressuring plate 9, is adjusted perpendicular to workbench
1 working face；
2nd, the fixation and adjustment of low-pressure turbine blade：Low-pressure turbine blade is fixed by fixture assembly 10, is passed through
Fixing screws are adjusted and fix to leaf position on fixture, it is ensured that blade and blade crown is parallel with workbench 1；
3rd, the adjustment of the adjustment welding condition of welding gun and blade face of weld：After completing 1 and 2 work, support 3 is adjusted
With rear support plate 7, it is ensured that the tungsten electrode of welding is perpendicularly oriented to the center of low-pressure turbine blade integral shroud solder side, and to support 3 after
Support plate 7 is fixed, and then adjusts welding condition, and welding parameter is shown in Table 1,
The welding condition of table 1
2nd, result and analysis
2.1 welding distances
General to require welding distance in the case where welding is not influenceed, distance should try one's best reductions, welding apart from conference make
Into starting the arc hardly possible and current interruption.Low-pressure turbine blade welding manner is shown in Fig. 1, and as seen from the figure in welding process, wear-resistant block is to lie in leaf
Hat step, electrode is maintained static, and during welding, wear-resistant block, in heated center, is initially heated fusing, blade due to small volume
Volume is big, and due to metal heat conduction effect, matrix surface is upper with the wear-resistant block arrival melting temperature time variant, is initially heated
When the wear-resistant block of fusing is heated into liquid, can form spherical in the presence of surface tension, wear-resistant block scantling is
4.5x5.2x1.5mm, when fusing is formed it is spherical when, the change of solid-liquid density is not considered, the cubature formula V=4 π r3/3 according to ball
Calculate, now a diameter of 4.2mm of ball, is only 0.3mm with the distance of electrode, so the electrode bonding for being easy to and welding is short
Road, welding is interrupted.When welding distance is less than 3mm, antifriction alloy bonding electric pole short circuit is easily caused during welding, welding is interrupted,
Wear-resisting block welding is scrapped.So weld distance during the welding of reality should be in more than 3mm.So welding distance is defined as 3+0.5mm.
2.2 welding currents
2.2.1 influence of the welding current to hardness
Influence of the welding current to hardness is carried out using coarse grain material, hardness determination is carried out after welding, hardness is shown in Table 2, weldering
After connecing, the hardness of rub resistance is average in HV650 or so, hardness hardness reduction with the increase of electric current.A weldering is randomly selected
Point (electric current is 140A) from outward appearance to inner essence etc. has carried out microhardness inspection to step pitch (300um), and inspection result is shown in Table 3, whole weldering
The hardness for connecing wear-resistant coating is more uniform, and tissue to welding to matrix has substantially no effect on.Hardness test result is 500
Position (at pad surface 1800um), is just on the interface of solder joint and matrix material.
Influence of the welding current of table 2 to hardness
Step pitch hardness test result (HV0.3) such as from outward appearance to inner essence of table 3
2.2.2 influence of the electric current to organizing
By metallographic specimen directly etching used in hardness test, original K4208 alloy structures solder marginal position is with
Based on bar-shaped, chain and island, the carbide of delivery position has substantially the white morphology of carbides of portion position based on bulk
Casting open texture, is shown in Fig. 3；Two carbide of position are carried out with energy spectrum composition analysis, the carbon of edge and medium position is found
Compound Ti, Fe, Ni are higher than the carbide of delivery position, and W, Mo content are less than the carbide of delivery position.K4208 is resistance to after welding
Friction eliminates the loose of original structure substantially without internal flaw, and carbide is more tiny and is uniformly dispersed, and fine microstructures are uniform
Arborescent structure, typical case's K4208 alloy structures are shown in Fig. 4 after welding.The middle part of different electric current solder joints and edge are carried out power spectrum into
Analysis, the composition in each region is close, similar to matrix composition.
During current low-voltage 100A, solder side it is more sensitive to the pollution containing surface, easily produce wearing layer and matrix not
Fusion phenomenon, is shown in Fig. 5；Each parameter solder joint has different degrees of crystal boundary roughening and cracking phenomena, to current parameters 120A with
Under solder joint, extension of the crackle on solder joint be smaller.When electric current is more than 140A, matrix corrode depth is larger, and crystal boundary is roughened and opens
Split phenomenon more obvious, see Fig. 6, Fig. 7.Welding current is different, and the matrix corrosion depth of butt welding point is also slightly different, small in trend
Electric current, the parameter matrix corrosion depth of short conduction time are shallow, but molten drop mobility is relatively poor (solder joint is spherical in shape)；In identical weldering
The time is connect under 10s, welding current is shown in Table 4 to fusion depth.
Consider the welding anti-wear energy of K4208 alloys and the influence to matrix, welding current is advisable in 100-140A.
Influence of the welding current of table 4 to fusion depth
2.3 weld intervals
Weld interval is less than the 5s times, easily occurs merging imperfect during K4208 alloy wear-resisting block weldings, and weld interval exists
7-13S is advisable.Under identical technological parameter, when electric current is less than 100A, multiple welding influences on the hardness of K4208 antifriction alloys
Smaller, the lengthening of weld interval, fusion depth increases, and increases the influence to the roughening of matrix crystal boundary.When electric current is higher than 140A, weldering
Time lengthening is connect, the trend for reducing occurs in the hardness for welding K4208 antifriction alloys, when weld interval increases to 30s, after welding
Hardness averagely drops to HV50, while intercrystalline crack, easily occurs in the influence increase to the roughening of matrix crystal boundary.Therefore, weld interval
It is advisable in 7~13s.
2.4 welding procedures
It is comprehensive to weld K4208 wear-resistant blocks hardness, tissue morphology and to welding base material by pulse flow soldering test wide
Influence, its welding condition is to be shown in Table 5.Under the technological parameter recommended, contrast welding K4208 antifriction alloys and made in Russia
В Ж Л 2- В И antifriction alloys, its tissue morphology, hardness are close, and the influence to matrix is similar.It can be considered that formulate
Technological parameter can be used for K4208 antifriction alloys and substitute antifriction alloy В Ж Л 2- В И made in Russia and place under repair to be possibly realized.
The welding condition of table 5
3rd, conclusion
(1) there is uniform arborescent structure using pulse flow welding K4208 wear-resistant blocks wide, corresponding circle of sensation is less than 0.5mm, firmly
Degree is adopted as technique welding wearing layer and is conducive to removal and repairs again in more than HV600.
It is (2) close with В Ж Л 2- В И antifriction alloys made in Russia using pulse flow welding K4208 wearing layers performance wide,
Can be used to repair low-pressure turbine blade leaf with K4208 alloy replacing В Ж Л 2- В И antifriction alloys are welded using pulse flow wide
The repairing of hat.
Embodiments of the present invention are explained in detail above in association with accompanying drawing, but the invention is not restricted to described implementation
Mode.For a person skilled in the art, in the case where the principle of the invention and spirit is not departed from, to these implementation methods
Various changes, modification, replacement and modification are carried out, is still fallen within protection scope of the present invention.
Claims (8)
1. a kind of antifriction alloy welding procedure, the technique is welded using pulse electric current welding procedure wide and K4208 alloys, its
It is characterised by, the technological parameter in welding process is：Welding electrode is tungsten electrode；Welding current is 100-140A；Welding distance
It is 3+0.5mm；Weld interval is 7-13s；Amount of current pulses is 2Hz；Argon flow amount 6-10L/min.
2. antifriction alloy welding procedure according to claim 1, it is characterised in that the technological parameter in welding process is：Weldering
Receiving electrode is tungsten electrode；Electric current is 120A；Welding distance is 3+0.5mm；Weld interval is 10s；Amount of current pulses is 2Hz；Argon
Throughput is 7.5L/min.
3. antifriction alloy welding procedure according to claim 1, it is characterised in that the technique comprises the following steps：
(1) K4208 alloys are selected, it is cut and is cleaned；
(2) welding torch position is adjusted, makes it perpendicular to the working face of workbench；
(3) Low Pressure Turbine Rotor blade shroud is fixed on the wear-resisting block welding auxiliary of semi-automatic Low Pressure Turbine Rotor blade shroud
On the fixture assembly of system；Ensure that the tungsten electrode of welding is perpendicularly oriented to the center of low-pressure turbine blade integral shroud solder side；
(4) adjustment of welding gun and blade face of weld, regulation welding condition is welded.
4. antifriction alloy welding procedure according to claim 3, it is characterised in that the cutting will using common wire cutting
K4208 alloys cut into size for 5.2x4.5x1.5mm welding blocks.
5. antifriction alloy welding procedure according to claim 3, it is characterised in that the cleaning is in HCl+FeCL3+HNO3
Mixed solution carry out 5-10min pickling.
6. antifriction alloy welding procedure according to claim 1, it is characterised in that the HCl+FeCL3+HNO3Mixing it is molten
HCl, FeCL in solution3And HNO3Volume ratio be：1:1:1.
Application of the 7.K4208 alloys in terms of Low Pressure Turbine Rotor blade shroud antifriction alloy welding.
Application of the 8.K4208 alloys in terms of RD-93 engine low-pressure turbine blade integral shroud welding.
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| CN201710126679.2A CN106903396B (en) | 2017-03-03 | 2017-03-03 | Welding process for wear-resistant alloy |
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|---|---|---|---|
| CN201710126679.2A CN106903396B (en) | 2017-03-03 | 2017-03-03 | Welding process for wear-resistant alloy |
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| CN102935543A (en) * | 2012-10-31 | 2013-02-20 | 国家电网公司 | Butt welding method for T23 steel tubes |
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| CN106862789A (en) * | 2017-03-03 | 2017-06-20 | 贵州凯阳航空发动机有限公司 | The application that K4208 alloys are welded in Low Pressure Turbine Rotor blade shroud antifriction alloy |
-
2017
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| US6080960A (en) * | 1995-12-18 | 2000-06-27 | Framatome | Method for joining two parts by heterogeneous welding and use thereof |
| CN101412138A (en) * | 2007-10-17 | 2009-04-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Overlaying welding technique of carbide alloy on turbine blade serrated shroud |
| CN101508053A (en) * | 2009-03-25 | 2009-08-19 | 山东大学 | Welding method of high-nickel alloy and stainless steel dissimilar metal |
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