CN106903396B - Welding process for wear-resistant alloy - Google Patents
Welding process for wear-resistant alloy Download PDFInfo
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- CN106903396B CN106903396B CN201710126679.2A CN201710126679A CN106903396B CN 106903396 B CN106903396 B CN 106903396B CN 201710126679 A CN201710126679 A CN 201710126679A CN 106903396 B CN106903396 B CN 106903396B
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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
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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
- B23K9/23—Arc welding or cutting taking account of the properties of the materials to be welded
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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
- B23K9/235—Preliminary treatment
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Abstract
The invention discloses a wear-resistant alloy welding process, which adopts a pulse wide current welding process and K4208 alloy for welding, wherein the process parameters in the welding process are as follows: the welding electrode is a tungsten electrode; the welding current is 100-140A; the welding distance is 3.5 mm; the welding time is 7-13 s; the current pulse number is 2 Hz; the argon flow is 6-10L/min. The pulse wide current welding K4208 wear-resistant block has a uniform dendritic crystal structure, a fusion area is smaller than 0.5mm, the hardness is higher than HV600, and the process for welding the wear-resistant layer is favorable for removing and repairing.
Description
Technical Field
The invention relates to the technical field of welding, in particular to a wear-resistant alloy welding process.
Background
The RD-93 engine is a more advanced 3 RD generation aviation engine in Russia, is limited when a repair technology is introduced, particularly the key special processes such as advanced welding, surface engineering, heat treatment and the like are more strictly controlled, the introduction of the processes is limited by the Russia defense technology export, and the welding process of the low-pressure turbine rotor blade shroud wear-resistant alloy is one of the limited technology exports. And the test hardness of the wear-resistant block on the original low-pressure turbine blade of the RD-93 engine is more than HV600, and the composition of the wear-resistant block is the same as that of the K4208 alloy through chemical composition analysis. K4208 wear-resistant alloy application research is reported, the surfacing process is mostly adopted for the wear-resistant layer of the blade shroud of the turbine blade of the domestic engine, and the wear-resistant material is a CoCrMo/CoCrW material. The wear-resistant layer of the blade shroud of the low-pressure turbine rotor blade of a newly developed turbofan engine in China is formed by welding K4208 alloy in a surfacing mode, and the average hardness of the wear-resistant layer is about HV 550. Therefore, the domestic existing welding process cannot meet the repair of the low-pressure turbine blade of the RD-93 engine, and the development of the welding process is necessary.
The existing welding process of the wear-resistant block of the blade shroud of the low-pressure turbine rotor blade does not conform to the quality stability required by aviation products. In order to ensure the repair quality of the low-pressure turbine blade of the engine, the research on the fusion welding process of the wear-resistant alloy of the low-pressure turbine rotor blade must be carried out.
Disclosure of Invention
The invention aims to solve the technical problem of providing a wear-resistant alloy welding process which has high welding hardness and meets the welding requirements of wear-resistant alloy for welding low-pressure turbine blades.
In order to solve the technical problems, the technical scheme of the invention is as follows: a wear-resistant alloy welding process adopts a pulse wide current welding process to build up a K4208 alloy wear-resistant block on a blade crown of a low-pressure turbine rotor blade to serve as a wear-resistant layer, the wear-resistant block is horizontally placed on a step of the blade crown of the low-pressure turbine rotor blade in the welding process, and the technological parameters in the welding process are as follows: the welding electrode is a tungsten electrode; the welding current is 100-140A; the welding distance is 3.5 mm; the welding time is 7-13 s; the current pulse is 2 Hz; the argon flow is 6-10L/min.
Preferably, the process parameters in the welding process are as follows: the welding electrode is a tungsten electrode; the current is 120A; the welding distance is 3.5 mm; the welding time is 10 s; the current pulse is 2 Hz; the flow rate of argon was 7.5L/min.
Preferably, the wear-resistant alloy welding process comprises the following steps:
(1) selecting a K4208 alloy, cutting and cleaning the alloy; the cutting adopts common linear cutting to cut the K4208 alloy into wear-resistant blocks with the size of 5.2 multiplied by 4.5 multiplied by 1.5 mm;
(2) adjusting the position of the welding gun to be vertical to the working surface of the workbench;
(3) fixing the low-pressure turbine rotor blade shroud on a fixture assembly of a semi-automatic low-pressure turbine rotor blade shroud wear-resistant block welding auxiliary system; ensuring that the welded tungsten electrode vertically points to the center of the welding surface of the blade shroud of the low-pressure turbine rotor blade;
(4) and adjusting the welding surface of the welding gun and the blade shroud of the low-pressure turbine rotor blade, and adjusting the parameters of the welding process to weld.
Preferably, the washing is in HCl + FeCl3+HNO3The mixed solution is pickled for 5-10 min.
Preferably, the HCl + FeCl3+HNO3HCl and FeCl in the mixed solution3And HNO3The volume ratio of (A) to (B) is as follows: 1:1: 1.
Compared with the prior art, the method has the beneficial effects that 1, the pulse wide current welding K4208 wear-resistant block has a uniform dendritic structure, the fusion area is smaller than 0.5mm, the hardness is more than HV600, the wear-resistant layer is welded by the process and is beneficial to removal and repair, 2, the performance of the pulse wide current welding K4208 wear-resistant layer is similar to that of a Russian V Ж L2-V wear-resistant alloy, and the pulse wide current welding K4208 alloy can be used for repairing the blade crown of the low-pressure turbine rotor instead of the V Ж L2-V wear-resistant alloy.
Drawings
FIG. 1 is a schematic view of a weld of wear resistant pieces of a shroud of a wear resistant low pressure turbine rotor blade;
FIG. 2 is a schematic structural view of a semi-automated low pressure turbine rotor blade shroud wear block welding assistance system;
FIG. 3 shows the original coarse-grained local texture;
FIG. 4K 4208 exemplary structure after welding;
FIG. 5 shows unfused topography (current 80A) at the solder joint interface;
FIG. 6 shows a typical local coarsening of the grain boundary of the matrix at the interface (current 150A);
the typical topography (current 160A) is slightly cracked locally at the interface location of fig. 7.
Detailed Description
The following further describes embodiments of the present invention with reference to the drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The K4208 alloy in this example is prior art and is available from the Beijing institute of iron and Steel.
1. Test of
1.1 test apparatus
Microscopic vickers hardness tester: constant EM-1000VP, hardness detection: the test load is 300g, and the pressure head loading time is 10S; microscope: germany zeiss electron microscope;
1.2 preparation of abrasion-resistant blocks
According to the requirements of the abrasion-resistant alloy for welding the low-pressure turbine blade of the RD-93 engine, the K4208 alloy is cut into the size of 5.2 multiplied by 4.5 multiplied by 1.5mm meeting the welding requirement by adopting a common wire and is added with HCl + FeCl3+HNO3Pickling the solution for 5-10min to remove the linear cutting electroerosion layer, and preparing to meet the requirement of repairing and welding the engine, preferably, HCl and FeCl in the mixed solution3And HNO3The volume ratio of (A) to (B) is as follows: 1:1:1, and can be prepared according to actual requirements.
1.3 welding process
The welding method comprises the following steps of adopting pulse width current welding, and using a semi-automatic low-pressure turbine rotor blade shroud wear-resistant block welding auxiliary system to weld, as shown in figure 1, wherein the semi-automatic low-pressure turbine rotor blade shroud wear-resistant block welding auxiliary system comprises a workbench 1, a microcomputer controller 2, a support 3, a servo motor 5, a lead screw assembly 6 and a clamp assembly 10, wherein the microcomputer controller 2, the servo motor 5, the lead screw assembly 6 and the clamp assembly 10 are all in the prior art, the clamp assembly 10 is fixed on the workbench 1 and used for fixing low-pressure turbine blades, and a support guide rail 13 is arranged on the workbench 1; the bottom of the bracket 3 is fixed on the bracket guide rail 13, so that the bracket 3 can slide back and forth on the bracket guide rail 13; vertical guide rails 4 are respectively arranged on the left and right pillars of the bracket 3; a servo motor 5 is arranged at the top of the bracket 3; the servo motor 5 is connected with a rear supporting plate 7 through a lead screw assembly 6; the rear supporting plate 7 is fixedly connected with the front pressing plate 9 through screws; the rear supporting plate 7 is fixedly connected with the transverse guide rail 8; the transverse guide rail 8 is fixed on the cross beam 11; two ends of the beam 11 are connected with the sliding blocks 12; the slide block 12 is fixed on the vertical guide rail 4 and can slide up and down along the vertical guide rail 4; the microcomputer controller 2 is electrically connected with the servo motor 5, and the microcomputer controller 2 is fixed on the workbench 1 for convenient operation; the microcomputer controller 2 is electrically connected to a welding apparatus (not shown).
The specific operation is as follows:
(I) equipment adjustment:
1. fixing and adjusting a welding gun: the welding gun is fixed on the cross beam 11 through the front pressure plate 9 and is adjusted to be vertical to the working surface of the workbench 1;
2. fixing and adjusting the low-pressure turbine rotor blade shroud: the blade crown of the low-pressure turbine rotor blade is fixed through a clamp assembly 10, and the position of the blade is adjusted and fixed through a fixing screw on a clamp, so that the blade crown surface of the blade is parallel to the workbench 1;
3. adjusting welding technological parameters of a welding gun and the welding surface of a blade shroud of a low-pressure turbine rotor: after the work 1 and the work 2 are finished, the support 3 and the rear support plate 7 are adjusted to ensure that the welded tungsten electrode vertically points to the center of the welding surface of the blade shroud of the low-pressure turbine rotor blade, the rear support plate 7 of the support 3 is fixed, then the welding process parameters are adjusted, the welding parameters are shown in a table 1,
TABLE 1 welding Process parameters
2. Results and analysis
2.1 welding distance
Generally, the welding distance is required to be reduced as much as possible under the condition that the welding distance is not influenced, and arc striking is difficult and arc breakage is caused by overlarge welding distance. The welding mode of the low-pressure turbine blade is shown in figure 1, it can be seen from the figure that in the welding process, the wear-resistant block is horizontally placed on the step of the blade crown, the electrode is fixed, when welding, the wear-resistant block is positioned at the heating center due to small volume, and is firstly heated and melted, the blade is large in volume, and due to the metal heat conduction action, the time difference between the temperature of the base body surface and the temperature of the wear-resistant block reaching the melting point is obtained, when the wear-resistant block which is firstly heated and melted is heated into liquid, the wear-resistant block can form a sphere under the action of surface tension, the material size of the wear-resistant block is 4.5 multiplied by 5.2 multiplied by 1.5mm, when the wear-resistant block is melted into the sphere, the change of solid-liquid density is not considered, the calculation is carried out according to the volume formula V of the sphere being 4 pi r3/3, the diameter. When the welding distance is less than 3mm, the short circuit of the wear-resistant alloy bonding electrode is easily caused during welding, the welding is interrupted, and the welding of the wear-resistant block is scrapped. Therefore, the actual welding distance should be more than 3 mm. The welding distance is defined as 3+0.5 mm.
2.2 welding Current
2.2.1 influence of welding Current on hardness
The hardness was measured after welding by measuring the hardness after welding using a macrocrystalline material, and the average of the hardness after welding was HV650, which means that the hardness decreased with an increase in current, as shown in table 2. A welding point (the current is 140A) is randomly selected and subjected to microhardness inspection at equal steps (300um) from the outside to the inside, the inspection result is shown in table 3, the hardness of the whole welding wear-resistant coating is uniform, and the welding does not influence the structure of a matrix basically. The hardness test result is 500 (1800 um away from the surface of the welding spot) which is just at the interface of the welding spot and the base material.
TABLE 2 influence of welding current on hardness
TABLE 3 hardness test results from outside to inside at equal steps (HV0.3)
2.2.2 Effect of Current on tissue
Directly corroding a metallographic specimen used in the hardness inspection, wherein the white carbides at the edge position and the middle position of the original K4208 alloy structure solder are mainly rod-shaped, chain-shaped and island-shaped in morphology, the carbides at the joint position are mainly massive in shape, and obvious casting loose structures are formed, as shown in figure 3; the energy spectrum component analysis of the carbides at the two positions shows that the carbides of Ti, Fe and Ni at the edge and the middle position are higher than those at the joint position, and the content of W, Mo is lower than that of the carbides at the joint position. The K4208 after welding has the advantages that the friction resistance is basically free of internal defects, the looseness of an original structure is eliminated, carbides are finer and uniformly dispersed, a fine and uniform dendritic structure is formed, and a typical K4208 alloy structure after welding is shown in figure 4. And (4) performing energy spectrum component analysis on the middle part and the edge of the welding spot with different currents, wherein the components of all the areas are similar and are similar to the components of the matrix tissue.
When the current is low, the welding surface is sensitive to the pollution of the surface, and the phenomenon that the wear-resistant layer and the matrix are not fused is easily caused, as shown in figure 5; the welding points of all parameters have the phenomena of coarsening and cracking of grain boundaries in different degrees, and for the welding points with the current parameter below 120A, the extension of cracks on the welding points is small. When the current exceeds 140A, the matrix has larger ablation depth, and the phenomena of coarsening and cracking of the grain boundary are more obvious, as shown in fig. 6 and 7. The welding current is different, the corrosion depth of the basal body of the welding spot is slightly different, the corrosion depth of the basal body is shallow due to the parameters of small current and short electrifying time on the trend, but the fluidity of the molten drop is relatively poor (the welding spot is spherical); at the same welding time of 10s, the welding current vs. fusion depth is shown in table 4.
The welding current is preferably 100-140A by comprehensively considering the wear resistance and the influence on the matrix of the welding K4208 alloy.
TABLE 4 Effect of welding Current on fusion depth
2.3 weld time
The welding time is less than 5S, incomplete fusion is easy to occur when the K4208 alloy wear-resistant block is welded, and the welding time is preferably 7-13S. Under the same process parameters, when the current is less than 100A, the influence of multiple welding on the hardness of the K4208 wear-resistant alloy is small, the welding time is prolonged, the fusion depth is increased, and the influence on coarsening of a matrix grain boundary is increased. When the current is higher than 140A, the welding time is prolonged, the hardness of the welded K4208 wear-resistant alloy tends to be reduced, and when the welding time is increased to 30s, the hardness after welding is averagely reduced to HV50, and meanwhile, the influence on coarsening of matrix grain boundaries is increased, and intergranular cracks are easy to occur. Therefore, the welding time is preferably 7 to 13 seconds.
2.4 welding Process
Through a pulse wide-flow welding test, the hardness, the structure form and the influence on a welding substrate of a welding K4208 wear-resistant block are comprehensively integrated, the welding process parameters are shown in a table 5, under the recommended process parameters, compared with the structure form and the hardness of a welding K4208 wear-resistant alloy and a Russian V Ж V2-V wear-resistant alloy, the influence on a matrix is similar, therefore, the established process parameters can be considered to be possible to be used for replacing the Russian wear-resistant alloy V Ж V2-V for repairing the K4208 wear-resistant alloy.
TABLE 5 welding Process parameters
3. Conclusion
(1) The pulse wide-flow welding K4208 wear-resistant block has a uniform dendritic structure, a fusion area is smaller than 0.5mm, the hardness is higher than HV600, and the wear-resistant layer is welded by adopting the process, so that the wear-resistant layer is beneficial to removal and reparation.
(2) The performance of the pulse wide-flow welding K4208 wear-resistant layer is similar to that of a Russian V Ж L2-V wear-resistant alloy, and the pulse wide-flow welding K4208 alloy can be used for replacing a V Ж L2-V wear-resistant alloy for repairing the blade crown of the low-pressure turbine blade.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, and the scope of protection is still within the scope of the invention.
Claims (5)
1. A wear-resistant alloy welding process is characterized in that a pulse wide current welding process is adopted in the process, K4208 alloy wear-resistant blocks are overlaid on a blade crown of a low-pressure turbine rotor blade to serve as a wear-resistant layer, the wear-resistant blocks are flatly placed on steps of the blade crown of the low-pressure turbine rotor blade in the welding process, and technological parameters in the welding process are as follows: the welding electrode is a tungsten electrode; the welding current is 100-140A; the welding distance is 3.5 mm; the welding time is 7-13 s; the current pulse is 2 Hz; argon flow is 6-10L/min; the welding process of the wear-resistant alloy comprises the following steps:
(1) selecting a K4208 alloy, cutting and cleaning the alloy; the cutting adopts common linear cutting to cut the K4208 alloy into wear-resistant blocks with the size of 5.2 multiplied by 4.5 multiplied by 1.5 mm;
(2) adjusting the position of the welding gun to be vertical to the working surface of the workbench;
(3) fixing the low-pressure turbine rotor blade shroud on a fixture assembly of a semi-automatic low-pressure turbine rotor blade shroud wear-resistant block welding auxiliary system; ensuring that the welded tungsten electrode vertically points to the center of the welding surface of the blade shroud of the low-pressure turbine rotor blade;
(4) and adjusting the welding surface of the welding gun and the blade shroud of the low-pressure turbine rotor blade, and adjusting the parameters of the welding process to weld.
2. The welding process of the wear-resistant alloy according to claim 1, wherein the process parameters in the welding process are as follows: the welding electrode is a tungsten electrode; the current is 120A; the welding distance is 3.5 mm; the welding time is 10 s; the current pulse is 2 Hz; the flow rate of argon was 7.5L/min.
3. The process of claim 1, wherein the cleaning is performed in HCl + FeCl3+HNO3The mixed solution is pickled for 5-10 min.
4. The wear resistant alloy welding process of claim 3, wherein the HCl + FeCl3+HNO3HCl and FeCl in the mixed solution3And HNO3The volume ratio of (A) to (B) is as follows: 1:1:1.
The application of the K4208 alloy in welding of a blade crown of a low-pressure turbine blade of an RD-93 engine is characterized in that: a welding process using the wear resistant alloy of claim 1.
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| FR2742369B1 (en) * | 1995-12-18 | 1998-03-06 | Framatome Sa | METHOD FOR CONNECTION BY HETEROGENEOUS WELDING OF TWO PARTS 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 |
| CN101508053B (en) * | 2009-03-25 | 2010-12-29 | 山东大学 | Welding method of high-nickel alloy and stainless steel dissimilar metal |
| CN102935543B (en) * | 2012-10-31 | 2015-06-24 | 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 |
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