CN111702376B - Control method for ensuring multi-interface size after welding of aviation radiator - Google Patents

Control method for ensuring multi-interface size after welding of aviation radiator Download PDF

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Publication number
CN111702376B
CN111702376B CN202010559118.3A CN202010559118A CN111702376B CN 111702376 B CN111702376 B CN 111702376B CN 202010559118 A CN202010559118 A CN 202010559118A CN 111702376 B CN111702376 B CN 111702376B
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China
Prior art keywords
welding
liquid collecting
assembly
radiator
collecting tank
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CN202010559118.3A
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CN111702376A (en
Inventor
郭文平
孙德明
龙本滔
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Guizhou Yonghong Aviation Machinery Co Ltd
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Guizhou Yonghong Aviation Machinery Co Ltd
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23KSOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K37/00Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23KSOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K31/00Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups
    • B23K31/02Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups relating to soldering or welding
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23KSOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00Articles made by soldering, welding or cutting
    • B23K2101/04Tubular or hollow articles
    • B23K2101/14Heat exchangers

Abstract

The invention discloses a control method for ensuring the size of multiple interfaces after welding an aviation radiator. And finally, designing a simulation core with a standard (replacing a core subassembly with a tool) on the welding tool, repairing each subassembly on the tool, removing the repair allowance to ensure that the welding gap is uniform, and reserving the welding shrinkage for final welding. According to the invention, a plurality of welding seams with complicated and irregular shapes on an assembly product are split on the components, so that welding shrinkage and deformation are completed on each component, then, a repair allowance is reserved on each component, the number of the welding seams on the assembly is reduced, the welding seams with regular and same welding shrinkage directions are left for welding, and finally, the dimensional accuracy of each interface of the product is ensured.

Description

Control method for ensuring multi-interface size after welding of aviation radiator
Technical Field
The invention belongs to the technical field of machining of aviation aluminum plate-fin radiators, and particularly relates to a control method for ensuring the size of multiple interfaces after welding of a radiator.
Background
As shown in fig. 1-2, the product of the aviation aluminum plate-fin radiator is provided with a plurality of interface nozzles and a plurality of mounting seats, and the position dimensional tolerance between each interface nozzle and the interface nozzle and between the interface nozzles and the mounting seats are strict, in the process of welding each part to form an assembly product, because of more welding lines, different welding line joint forms, different welding line shapes, welding shrinkage and difficult control of the size and direction of welding deformation, the position dimensional tolerance after the product is welded can not be guaranteed, the product installation requirement can not be met, the design requirement is deviated, and batch scrapping or batch repair is caused. The product has a technological bottleneck in the implementation process, the product delivery cannot be completed, and the scientific research and production progress is seriously influenced.
Disclosure of Invention
The invention aims to provide a control method for ensuring the size of multiple interfaces after welding of an aviation radiator, and solves the problems that the existing aviation radiator has more welding lines, different joint forms of a plurality of welding lines, different welding line shapes and difficulty in controlling the size and direction of welding shrinkage and welding deformation in the welding process.
The basic idea of the invention is as follows: the method comprises the steps of splitting and combining a plurality of welding seams with complex shapes and irregular lines on a radiator assembly product on small components, completing welding shrinkage and deformation on each small component, and reserving a repair allowance on each small component to correct welding deformation by using the repair allowance. Meanwhile, the number of welding seams is reduced on the assembly, the regular welding seams in the same welding shrinkage direction are left for welding, and finally, the reserved welding shrinkage on the assembly is controlled and adjusted through a movable mandrel and an eccentric shaft on a welding tool, so that the dimensional accuracy of each interface after the product is welded is ensured.
The invention is realized by the following technical scheme:
the control method for ensuring the size of multiple interfaces after the aviation radiator is welded is characterized in that the radiator is divided into a first part containing an interface nozzle and a mounting seat and a second part not containing the interface nozzle and the mounting seat; the first part is welded independently, a repair allowance is reserved on the first part to correct welding deformation of the first part, then the first part and the second part are welded, and welding deformation generated when the first part and the second part are welded is reserved through a welding tool during welding.
Preferably, the control method is applied to argon arc welding of the aluminum alloy plate-fin radiator.
Preferably, when the first part is welded separately, welding deformation is reserved by adopting a welding tool.
Preferably, when the radiator is disassembled, only one welding seam type is welded between the first part and the second part, and the welding deformation directions are consistent.
Preferably, the welding tool comprises a welding mandrel capable of moving along the welding deformation direction, and a rotatable eccentric shaft with the eccentric direction perpendicular to the welding deformation direction.
Preferably, the welding of the first and second parts is performed on the same set of welding tools, i.e. both the welding of the first part alone and the welding of the first part to the second part are performed on the same set of welding tools.
Preferably, the control method for ensuring the size of the multiple interfaces after the aviation radiator is welded comprises the following steps:
step one, splitting a radiator into a radiator core assembly without an interface nozzle and a mounting seat, and a first liquid collecting tank assembly, a second liquid collecting tank assembly, a third liquid collecting tank assembly and a fourth liquid collecting tank assembly which comprise the interface nozzle and the mounting seat;
step two, respectively and independently welding an interface nozzle and a mounting seat on a first liquid collecting tank assembly, a second liquid collecting tank assembly, a third liquid collecting tank assembly and a fourth liquid collecting tank assembly, and reserving trimming allowance on the connecting end faces of the first liquid collecting tank assembly, the second liquid collecting tank assembly, the third liquid collecting tank assembly, the fourth liquid collecting tank assembly and the radiator core assembly;
step three, the first liquid collecting tank assembly, the second liquid collecting tank assembly, the third liquid collecting tank assembly, the fourth liquid collecting tank assembly and the radiator core assembly which are welded and provided with repair allowance are assembled in a simulation mode and the connecting end faces are repaired, and the uniform gaps are guaranteed;
welding the radiator core assembly with the first liquid collecting tank assembly, the second liquid collecting tank assembly, the third liquid collecting tank assembly and the fourth liquid collecting tank assembly through a welding tool, and reserving welding deformation through the welding tool before welding.
Preferably, in the third step, a structural member with the structure, the appearance and the size consistent with those of the radiator core assembly is adopted to replace the radiator core assembly to be assembled with the first liquid collecting tank assembly, the second liquid collecting tank assembly, the third liquid collecting tank assembly and the fourth liquid collecting tank assembly in a simulation mode.
Compared with the prior art, the control method is suitable for the conditions that the welding seams on the radiator product are complicated and more in quantity, and the welding seam joint forms are more than 2. The invention splits the radiator assembly product into a plurality of small components, and the small components split from the radiator assembly are welded and then the welding deformation and the welding shrinkage are corrected by the reserved allowance. When the small assembly disassembled from the radiator assembly is welded back to the assembly, the welding seam joint form is only one. When each small assembly is welded on the radiator assembly, the welding shrinkage is adjusted through the welding tool while the positions to be welded are firstly repaired to ensure the welding seam to be uniform.
Compared with the prior art, the invention can be applied to the connection of the aviation aluminum plate-fin radiator in an argon arc welding mode, and ensures a plurality of high-precision installation and interface sizes after welding. By adopting the control means, the invention can ensure higher interchangeability of the radiator product during installation.
Drawings
FIGS. 1-2 are schematic views of product structures;
FIGS. 3-5 are schematic views of the product part dimensions;
FIG. 6 is a schematic view of a first sump assembly;
FIG. 7 is a schematic view of a second sump assembly;
FIG. 8 is a schematic view of a third sump assembly;
FIG. 9 is a schematic view of a fourth sump assembly;
FIG. 10 is a schematic view of assembly product welding;
FIG. 11 is a schematic view of an assembly product being welded on a welding tool;
FIG. 12 is a schematic view of a simulated core on a welding tool;
FIG. 1-Heat sink core Assembly; 2-a first sump assembly; 3-a second sump assembly; 4-a third sump assembly; 5-a fourth sump assembly.
Detailed Description
The invention is further described with reference to the accompanying drawings, but the scope of protection claimed is not limited thereto.
The structure diagram of the radiator product is detailed in figures 1-2, and the partial installation dimension is detailed in figures 3-5. Aiming at the problem that the position dimensional tolerance of an aviation radiator product after welding can not be guaranteed in the prior art, the solution adopted in the embodiment is as follows:
the first step is as follows: splitting a product assembly into 5 large components according to the structural characteristics of a radiator product, wherein the large components are a radiator core component 1, a first liquid collecting tank component 2, a second liquid collecting tank component 3, a third liquid collecting tank component 4 and a fourth liquid collecting tank component 5 respectively, and the large components are shown in figures 6-9;
the second step is that: the first 2, second 3, third 4, and fourth 5 sump assemblies with interface nozzles, mounting seats, respectively, are each welded into small assemblies, with sufficient repair allowance reserved at one sump end (the end that is ultimately welded to the heat sink core assembly), as shown in detail in fig. 6, 7, 8, and 9. During welding, all components need to be carried out on a welding tool. After the welding is finished, repairing and allocating the liquid collecting tank by taking the simulation core on the welding tool as a reference after the welding deformation is finished, ensuring that the gap between the liquid collecting tank and the simulation core is uniform, and showing a simulation core diagram of the tool in detail as shown in FIG. 12;
the third step: the four components of the first liquid collecting groove component 2, the second liquid collecting groove component 3, the third liquid collecting groove component 4 and the fourth liquid collecting groove component 5 are welded with the heat radiator core component 1, and detailed view is shown in figure 10. During welding, a welding shrinkage is reserved for welding by adjusting a rotatable eccentric shaft on the welding tool (the eccentric shaft is fixed by a mode of forming a groove on the eccentric shaft, and when the groove on the eccentric shaft is opposite to a locking screw, the eccentric shaft is fixed by screwing the locking screw) and a welding mandrel. The processing of the assembly product is completed, and the detail is shown in figure 11.
The use of the present invention in an aircraft aluminum plate-fin radiator product example is described in further detail below with reference to fig. 1-2, 3-5, and 11.
1. Taking the fourth liquid collecting tank assembly 5 in fig. 1-2 as an example, when the assembly is welded, all parts on the small assembly are assembled on the welding tool shown in fig. 11, the positions of the connecting nozzle and the mounting support (the connecting nozzle and the mounting support are both provided with holes so as to realize the matching of the shaft and the holes) on the assembly are fixed through mandrels (a welding mandrel and a rotatable eccentric shaft) on the tool, and then the positions of the mandrels on the welding tool are adjusted so as to reserve the trimming allowance and the welding shrinkage
2. When the fourth liquid collecting tank assembly 5 is welded, the welding seam is a butt welding seam, and the welding contraction direction is contracted towards the direction of the radiator core assembly 1, so that when the fourth liquid collecting tank assembly 5 and the welded end of the radiator core assembly 1 are repaired to ensure that the welding seam gap is uniform, and then the corresponding core of the fourth fixed liquid collecting tank assembly 5 moves towards the opposite direction of the welding contraction, which is detailed in fig. 11. The movement amount is controlled by the shrinkage amount counted during the process of processing the craft piece.
3. And welding the fourth liquid collecting tank assembly 5 and the radiator core assembly 1, wherein the size of the welded radiator core assembly meets the design requirement through welding shrinkage and auxiliary action of a welding tool.
4. The welding size control method of the other small assemblies is the same as the above method. When the welding shrinkage direction is coaxial with the welding mandrel, the welding shrinkage is compensated by moving the position of the welding mandrel, and when the welding shrinkage direction is vertical to the axial direction of the welding mandrel, the welding shrinkage is compensated by rotating the eccentric shaft. The welding dabber fixed part has two kinds of structures in this embodiment, and one kind is that the dabber is plain noodles cylinder shape, and the part is radial restraint on the dabber, realizes size control through axial displacement. The other one is for taking the screwed mouthpiece on the part, and the spindle increases an adapter, adapter one end for with part mouthpiece threaded connection, one end for with the frock dabber through clearance fit's axle with the hole be connected, fixed mode becomes epaxial radial constraint equally, realizes size control through axial displacement. The specific welding sequence of the first liquid collecting tank assembly 2, the second liquid collecting tank assembly 3, the third liquid collecting tank assembly 4 and the fourth liquid collecting tank assembly 5 is determined according to the actual action of a product, the liquid collecting tanks at two ends of the high-pressure cavity are usually welded, and then an airtight test is carried out to verify the tightness of the core body.
5. Referring to fig. 11 and 12, the movable welding mandrel and the rotatable eccentric shaft are both mounted in the shaft hole of the support base through a bearing or a shaft sleeve, wherein the welding mandrel is connected with the interface nozzles and the mounting base on the first liquid collecting tank assembly 2, the second liquid collecting tank assembly 3, the third liquid collecting tank assembly 4 and the fourth liquid collecting tank assembly 5 through nuts. The surface of the rotatable eccentric shaft is provided with a groove along the axial direction, a locking screw is arranged at the joint of the rotatable eccentric shaft and the supporting seat and used for locking the eccentric shaft, and the rotatable eccentric shaft is directly inserted into the hole of the mounting seat.

Claims (6)

1. The control method for ensuring the size of the multiple interfaces after the aviation radiator is welded is characterized in that: the radiator is split into a first part containing an interface nozzle and a mounting seat and a second part not containing the interface nozzle and the mounting seat, when the radiator is split, only one welding seam type is welded between the first part and the second part, and the welding deformation directions are consistent; the welding method comprises the following steps of welding a first part independently, reserving a repair allowance on the first part for correcting the welding deformation of the first part, welding the first part and a second part, reserving the welding deformation generated when the first part and the second part are welded through a welding tool during welding, and specifically comprises the following steps:
the method comprises the following steps that firstly, a radiator is disassembled into a radiator core assembly (1) which does not comprise an interface nozzle and a mounting seat, and a first liquid collecting tank assembly (2), a second liquid collecting tank assembly (3), a third liquid collecting tank assembly (4) and a fourth liquid collecting tank assembly (5) which comprise the interface nozzle and the mounting seat;
step two, respectively and independently welding an interface nozzle and a mounting seat on a first liquid collecting groove component (2), a second liquid collecting groove component (3), a third liquid collecting groove component (4) and a fourth liquid collecting groove component (5), and reserving trimming allowance on the connecting end surfaces of the first liquid collecting groove component (2), the second liquid collecting groove component (3), the third liquid collecting groove component (4), the fourth liquid collecting groove component (5) and the radiator core component (1);
step three, the first liquid collecting tank assembly (2), the second liquid collecting tank assembly (3), the third liquid collecting tank assembly (4), the fourth liquid collecting tank assembly (5) which are welded and provided with repair allowances and the radiator core assembly (1) are assembled in a simulation mode, and connection end faces are repaired, so that uniform gaps are guaranteed;
welding the radiator core assembly (1) with the first liquid collecting groove assembly (2), the second liquid collecting groove assembly (3), the third liquid collecting groove assembly (4) and the fourth liquid collecting groove assembly (5) through a welding tool, and reserving welding deformation through the welding tool before welding.
2. The control method for ensuring the size of multiple interfaces after the aviation radiator is welded according to claim 1, characterized in that: the control method is applied to argon arc welding of the aluminum alloy plate-fin radiator.
3. The control method for ensuring the size of multiple interfaces after the aviation radiator is welded according to claim 1, characterized in that: and when the first part is independently welded, welding deformation is reserved by adopting a welding tool.
4. The control method for ensuring the size of multiple interfaces after the aviation radiator is welded according to claim 1, characterized in that: the welding tool comprises a welding mandrel and a rotatable eccentric shaft, wherein the welding mandrel can move along the welding deformation direction, and the rotatable eccentric shaft is perpendicular to the welding deformation direction in the eccentric direction.
5. The control method for ensuring the size of multiple interfaces after the aviation radiator is welded according to claim 1, characterized in that: the welding of the first portion and the second portion is performed on the same set of welding tools.
6. The control method for ensuring the size of multiple interfaces after the aviation radiator is welded according to claim 1, characterized in that: and in the third step, a structural member with the structure, the appearance and the size consistent with those of the radiator core assembly (1) is adopted to replace the simulated assembly of the radiator core assembly (1) and the first liquid collecting tank assembly (2), the second liquid collecting tank assembly (3), the third liquid collecting tank assembly (4) and the fourth liquid collecting tank assembly (5).
CN202010559118.3A 2020-06-18 2020-06-18 Control method for ensuring multi-interface size after welding of aviation radiator Active CN111702376B (en)

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CN112453639B (en) * 2020-10-27 2022-05-10 成都飞机工业(集团)有限责任公司 Method for efficiently repairing airplane welding guide pipe on clamp by adopting special device
CN113600976A (en) * 2021-07-16 2021-11-05 渤海造船厂集团有限公司 DN650 metal flexible connecting pipe installation size control method

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KR20130101745A (en) * 2012-03-06 2013-09-16 (주)해송엔지니어링 Method for manufacturing the radiator
CN105345384A (en) * 2015-11-13 2016-02-24 沈阳黎明航空发动机(集团)有限责任公司 Positioning and welding clamp for header pipe and welding deformation control method
CN107414332A (en) * 2017-08-29 2017-12-01 贵州永红航空机械有限责任公司 Fire the fixed-position welding device of oil cooler mounting seat
CN110142704A (en) * 2019-04-24 2019-08-20 贵州永红航空机械有限责任公司 Aluminum plate fin type radiator Welding Testing fixture and method

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1554508A (en) * 2003-12-26 2004-12-15 东方汽轮机厂 Deformation control method for large structure piece welding
KR20090045531A (en) * 2007-11-02 2009-05-08 장정구 Apparatus for automatic welding of radiator board for transformer
CN101564577A (en) * 2009-06-05 2009-10-28 贵州航天风华精密设备有限公司 Method for decreasing medical accelerator support arm welding deformation
KR20130101745A (en) * 2012-03-06 2013-09-16 (주)해송엔지니어링 Method for manufacturing the radiator
CN105345384A (en) * 2015-11-13 2016-02-24 沈阳黎明航空发动机(集团)有限责任公司 Positioning and welding clamp for header pipe and welding deformation control method
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