CN106001863A - Hot processing method for improving elongation of heat-treatable strengthened aluminum alloy fusion welding joint - Google Patents
Hot processing method for improving elongation of heat-treatable strengthened aluminum alloy fusion welding joint Download PDFInfo
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- CN106001863A CN106001863A CN201610465129.9A CN201610465129A CN106001863A CN 106001863 A CN106001863 A CN 106001863A CN 201610465129 A CN201610465129 A CN 201610465129A CN 106001863 A CN106001863 A CN 106001863A
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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
- B23K9/12—Automatic feeding or moving of electrodes or work for spot or seam welding or cutting
-
- 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
-
- 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
- B23K2103/00—Materials to be soldered, welded or cut
- B23K2103/08—Non-ferrous metals or alloys
- B23K2103/10—Aluminium or alloys thereof
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- Mechanical Engineering (AREA)
- Arc Welding In General (AREA)
Abstract
The invention belongs to the technical field of welding, and relates to a hot processing method for improving the elongation of a heat-treatable strengthened aluminum alloy fusion welding joint. The method includes the steps that at first, two heat-treatable strengthened aluminum alloy workpieces to be welded are fixed to a welding tool without cushion plate; and backing welding is conducted through direct-current helium-arc tungsten inert gas (TIG) welding, a first layer of cosmetic welding is conducted through variable-polarity pulse TIG welding, and finally a second layer of cosmetic welding is conducted through variable-polarity pulse TIG welding, so that welding of the two heat-treatable strengthened aluminum alloy workpieces to be welded is completed. According to the method, the second layer of cosmetic face is added, and by designing the technical parameters and dimension parameters, the tensile strength of the welding joint additionally provided with the second layer of cosmetic face is effectively improved, and the elongation is improved by 40%.
Description
Technical field:
The present invention relates to a kind of hot-working method, particularly relate to a kind of raising heat-treatable strengthened aluminum alloy melting welding
The hot-working method of joint elongation percentage, belongs to welding technology field.
Background technology:
China carrier rocket core level tank uses heat-treatable strengthened aluminum alloy, such as 2A14, the models such as 2219,
Weld seam uses single two sides two-layer automatization TIG weld, and its weld shape is as it is shown in figure 1, ground floor uses nothing
Backing plate DC TIG welding realizes backing weld seam, and the second layer uses variable polarity TIG welding to realize cap weld.
Advantage is mainly reflected in:
1) pore in backing welding termination process is prone to overflow with being mingled with, and decreases weld defect, improves welding
Quality；
2) backing welding speed of welding is up to more than 12m/h, significantly improves welding efficiency；
3) while keeping bigger speed of welding, significantly reduce welding current, reduce the heat input of weld seam,
Reduce the welding deformation of product；
4) linear energy density is high, and welding penetration is big, and moderately thick can through welding of square groove.
The technique of DC TIG welding without backing plate has above clear advantage, but also has certain process limitation,
The heat input of intensive heat input and concentration, causes heat-treatable strengthened aluminum alloy welding point elongation percentage the highest,
Being about 3%, weld seam is under stress effect, it may occur however that brittle failure.
Trace it to its cause, 2219 aluminum alloy TIG postweldings, weld seam (WZ) and partially melted zone (PMZ) due to
There is Cu element segregation in various degree, overaging district (OAZ), heat affected area (HAZ) tissue also can be sent out
Raw certain change, makes welding joint mechanical property reduce.Each area distribution such as Fig. 1.Strong for making up weld seam
The deficiency of degree, generally retains certain weld reinforcement.The existence of reinforcement makes joint become Geometrical discontinuity body,
During stand under load, welding toe there will be stress concentration.Toe of weld is usually located at the intersection of weld seam and partially melted zone, and
The microstructure and mechanical property height of partially melted zone is non-homogeneous, the poorest the closer to melt run, intensity and plasticity.
During zero defect band reinforcement joint cross directional stretch, crack initiation position is typically near toe of weld, and fracture path may be in weldering
Seam or partially melted zone.
Summary of the invention:
The technology of the present invention solves problem: overcome the deficiencies in the prior art, it is provided that a kind of raising can heat treatment
The hot-working method of reinforced aluminium alloy joint made by flame welding elongation percentage, is effectively increased heat-treatable strengthened aluminum alloy weldering
Joint elongation percentage and the intensity of weld seam.
The technical solution of the present invention is: improve the heat of heat-treatable strengthened aluminum alloy joint made by flame welding elongation percentage
Processing method, comprises the following steps:
(1) two heat-treatable strengthened aluminum alloy workpiece to be welded are fixed on without on the welding tooling of backing plate；
(2) backing welding is carried out with direct current heliarc TIG weldering；
(3) ground floor cosmetic welding is carried out with Variable Polarity pulse TIG welding；
(4) second layer cosmetic welding is carried out with Variable Polarity pulse TIG welding, to complete two heat-treatable strengthened aluminum
The welding of alloy workpiece.
Carrying out the technological parameter of backing welding with direct current heliarc TIG weldering in described step (2) is: speed of welding is
13 23m/h, welding current is 160 300A, and arc voltage parameter is 13 18V.
Carrying out the technological parameter of ground floor cosmetic welding with Variable Polarity pulse TIG welding in described step (3) is: weldering
Connecing speed is 6 14m/h, and dutycycle is 45 70%, and background current is 200 300A.
In described step (4), the protection gas during welding of second layer cosmetic welding is argon, and speed of welding is 5 10m/h,
Welding current is 80 150A, and gas flow is 8 16L/min.
The dimensional parameters of described second layer capping meets:
2δ+b‐3mm≤a≤2δ+b+3mm
1.5mm≤h≤2mm
Wherein a is the frontal width of second layer capping, and b is the back side width of backing welding, and δ is work to be welded
The thickness of part, h is the topside height of second layer capping.
Described carry out second layer cosmetic welding with Variable Polarity pulse TIG welding implementation method be:
(6.1) two heat-treatable strengthened aluminum alloy workpiece to be welded and ground floor cap weld are polished
Process clean；
(6.2) welding gun side's starting the arc in welded joints, welding gun moves along position while welding, in the way of swinging,
Cover original weld seam comprehensively, and ensure that the dimensional parameters of second layer capping meets
2 δ+b 3mm≤a≤2 δ+b+3mm, 1.5mm≤h≤2mm.
Described two heat-treatable strengthened aluminum alloy thickness of workpiece to be welded are more than 4mm.
Compared with prior art, there is advantages that
(1) present invention is on the basis of existing weld seam uses single two sides two-layer automatization TIG weld, adds
Second layer capping, by design technology and dimensional parameters, makes (the welding of the commissure after increase second layer capping
Joint) tensile strength obtained a certain degree of raising, elongation percentage improves 40%.
(2) present invention the second capping size meets 2 δ+b 3mm≤a≤2 δ+b+3mm, effectively disperses
Former welding toe stress, optimizes welding point fracture path, thus increases intensity and the elongation percentage of weld seam.
(3) present invention is realized the width dimensions of second layer capping met requirement by swinging of welding gun, gram
Take the defect that traditional welding gun welding method middle cover face width dimensions is narrower.
Accompanying drawing illustrates:
Fig. 1 is the signal of to be welded two heat-treatable strengthened aluminum alloy workpiece routine bottoming capping composite welding
Figure；
Fig. 2 is the bottoming capping composite welding schematic diagram of the present invention；
Fig. 3 is torch swinging schematic diagram during second layer cover welding.
Detailed description of the invention:
Elongation percentage that single two sides two-layer automatization TIG weld brings and the highest present situation of intensity is used for weld seam,
The present invention proposes a kind of hot-working method improving heat-treatable strengthened aluminum alloy joint made by flame welding elongation percentage, including
Following steps:
(1) two heat-treatable strengthened aluminum alloy workpiece to be welded are fixed on without on the welding tooling of backing plate,
Two heat-treatable strengthened aluminum alloy thickness of workpiece the most to be welded are more than 4mm.
(2) carrying out backing welding with direct current heliarc TIG weldering, technological parameter is: speed of welding is 13 23m/h,
Welding current is 160 300A, and arc voltage parameter is 13 18V.
(3) carrying out ground floor cosmetic welding with Variable Polarity pulse TIG welding, technological parameter is: speed of welding is
6 14m/h, dutycycle is 45 70%, and background current is 200 300A.
(4) second layer cosmetic welding is carried out with Variable Polarity pulse TIG welding, to complete two heat-treatable strengthened aluminum
The welding of alloy workpiece.Protection gas during welding is argon, and speed of welding is 5 10m/h, and welding current is
80 150A, gas flow is 8 16L/min.When sheet material is thicker, for ensureing the molding of weld seam front, can fit
Degree adds welding wire.
As in figure 2 it is shown, the dimensional parameters of second layer capping meets:
2δ+b‐3mm≤a≤2δ+b+3mm
1.5mm≤h≤2mm
Wherein a is the frontal width of second layer capping, and b is the back side width of backing welding, and δ is work to be welded
The thickness of part, h is the topside height of second layer capping, and unit is mm.
In order to reach as above welding effect, after clean for production joint grinding process, it is fixed on welding tooling；
Welding gun side's starting the arc in welded joints, it is provided that heat acts on weld seam front, and welding gun moves along position while welding, successively
Cover one time comprehensively.
At welding gun along position while welding motor process, in the way of swinging, cover original weld seam comprehensively, as
Shown in Fig. 3, and ensure that weld shape meets Fig. 2 requirement.Swinging by clamping welding gun mechanism of welding gun
Automatically move and realize, it is also possible to mobile realized by manual.
Using rational welding parameter, welding gun is when covering the original weld seam of remelting, it is ensured that the front of remelting weld seam
Reinforcement degree is 1.5mm 2mm.
Embodiment 1:
It is the product of 8mm for model thickness, enforcement parameter such as table 1:
Table 1 thickness is the Product jointing parameter of 8mm
Wherein the dimensional parameters of second layer capping meets a=2 δ+b+3mm, and h=1.5mm, a are second layer lid
The frontal width in face, b is the back side width of backing welding, and δ is the thickness of workpiece to be welded, and h is second layer lid
The topside height in face, unit is mm.
Elongation percentage after ground floor cosmetic welding is 3.5%, and intensity is 280 290MPa.After second layer cosmetic welding
Elongation percentage be 5.0%, intensity is 320MPa.
Embodiment 2:
It is the product of 10mm for model thickness, enforcement parameter such as table 2:
Table 2 thickness is the Product jointing parameter of 10mm
Wherein the dimensional parameters of second layer capping meets a=2 δ+b 3mm, and h=2mm, a are second layer capping
Frontal width, b is the back side width of backing welding, and δ is the thickness of workpiece to be welded, and h is second layer capping
Topside height, unit is mm.
Elongation percentage after ground floor cosmetic welding is 3.5%, and intensity is 280 295MPa.After second layer cosmetic welding
Elongation percentage be 5.5%, intensity is 310MPa.
Embodiment 3:
It is the product of 12mm for model thickness, enforcement parameter such as table 3:
Table 3 thickness is the Product jointing parameter of 12mm
Wherein the dimensional parameters of second layer capping meets a=2 δ+b+2mm, and h=1.8mm, a are second layer lid
The frontal width in face, b is the back side width of backing welding, and δ is the thickness of workpiece to be welded, and h is second layer lid
The topside height in face, unit is mm.
Elongation percentage after ground floor cosmetic welding is 3.0%, and intensity is 290 300MPa.After second layer cosmetic welding
Elongation percentage be 5.5%, intensity is 330MPa.
From above three embodiments it can be seen that according to the inventive method, the joint mechanical property of workpiece to be welded
Can significantly improve, tensile strength is improved to 310 330MPa by 280 300MPa, and elongation percentage is improved by 3.0%
To 5.5%.
The present invention is unspecified partly belongs to general knowledge as well known to those skilled in the art.
Claims (7)
1. improve the hot-working method of heat-treatable strengthened aluminum alloy joint made by flame welding elongation percentage, it is characterised in that bag
Include following steps:
(1) two heat-treatable strengthened aluminum alloy workpiece to be welded are fixed on without on the welding tooling of backing plate；
(2) backing welding is carried out with direct current heliarc TIG weldering；
(3) ground floor cosmetic welding is carried out with Variable Polarity pulse TIG welding；
(4) second layer cosmetic welding is carried out with Variable Polarity pulse TIG welding, to complete two heat-treatable strengthened aluminum
The welding of alloy workpiece.
Hot-working method the most according to claim 1, it is characterised in that: in described step (2) with
Direct current heliarc TIG weldering carries out the technological parameter of backing welding: speed of welding is 13 23m/h, and welding current is
160 300A, arc voltage parameter is 13 18V.
Hot-working method the most according to claim 1, it is characterised in that: in described step (3) with
Variable Polarity pulse TIG welding carries out the technological parameter of ground floor cosmetic welding: speed of welding is 6 14m/h, accounts for
Empty ratio is 45 70%, and background current is 200 300A.
Hot-working method the most according to claim 1, it is characterised in that: in described step (4)
Protection gas during two layers of cosmetic welding welding is argon, and speed of welding is 5 10m/h, and welding current is 80 150A,
Gas flow is 8 16L/min.
Hot-working method the most according to claim 1, it is characterised in that: the chi of described second layer capping
Very little parameter meets:
2δ+b‐3mm≤a≤2δ+b+3mm
1.5mm≤h≤2mm
Wherein a is the frontal width of second layer capping, and b is the back side width of backing welding, and δ is work to be welded
The thickness of part, h is the topside height of second layer capping.
Hot-working method the most according to claim 5, it is characterised in that: described with Variable Polarity pulse
TIG weldering carries out the implementation method of second layer cosmetic welding:
(6.1) two heat-treatable strengthened aluminum alloy workpiece to be welded and ground floor cap weld are polished
Process clean；
(6.2) welding gun side's starting the arc in welded joints, welding gun moves along position while welding, in the way of swinging,
Cover original weld seam comprehensively, and ensure that the dimensional parameters of second layer capping meets
2 δ+b 3mm≤a≤2 δ+b+3mm, 1.5mm≤h≤2mm.
Hot-working method the most according to claim 1, it is characterised in that: described to be welded two can
Heat treatment reinforcement Al alloy parts thickness is more than 4mm.
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| CN201610465129.9A CN106001863B (en) | 2016-06-23 | 2016-06-23 | Improve the hot-working method of heat-treatable strengthened aluminum alloy joint made by flame welding elongation percentage |
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| CN201610465129.9A CN106001863B (en) | 2016-06-23 | 2016-06-23 | Improve the hot-working method of heat-treatable strengthened aluminum alloy joint made by flame welding elongation percentage |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107470749A (en) * | 2017-10-09 | 2017-12-15 | 徐州世通重工机械制造有限责任公司 | A kind of welding method of direct current bottoming pulse stuff capping |
| CN108296610A (en) * | 2017-12-08 | 2018-07-20 | 四川航天长征装备制造有限公司 | A kind of TIG weld method of heat treatment reinforcement aluminium alloy |
| CN109570694A (en) * | 2018-12-28 | 2019-04-05 | 天津航天长征火箭制造有限公司 | A kind of welding method suitable for middle thickness forging state aluminium alloy |
| CN110405316A (en) * | 2019-07-19 | 2019-11-05 | 清华大学 | The method for improving ageing strengthening aluminum alloy melting plumb joint tensile property |
| CN112453655A (en) * | 2020-11-28 | 2021-03-09 | 四川航天长征装备制造有限公司 | Low-porosity defect welding process method for barrel-shaped aluminum alloy medium-thickness wall plate |
| CN112548277A (en) * | 2020-11-12 | 2021-03-26 | 中国大唐集团科学技术研究院有限公司火力发电技术研究院 | Weld joint interface structure optimization method for dissimilar steel welded joint of thermal power plant |
| CN112719536A (en) * | 2020-12-29 | 2021-04-30 | 天津航天长征火箭制造有限公司 | Argon tungsten-arc welding method for annular seam of bottom flange of aluminum-lithium alloy ellipsoid box |
| CN113172310A (en) * | 2021-04-16 | 2021-07-27 | 哈尔滨焊接研究院有限公司 | Welding process for inlet and outlet connecting pipe of low-temperature reactor pressure vessel and heat exchanger connecting pipe |
| CN113199118A (en) * | 2021-06-07 | 2021-08-03 | 四川航天长征装备制造有限公司 | Welding method for large-thickness aluminum alloy flange plate |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107470749A (en) * | 2017-10-09 | 2017-12-15 | 徐州世通重工机械制造有限责任公司 | A kind of welding method of direct current bottoming pulse stuff capping |
| CN108296610A (en) * | 2017-12-08 | 2018-07-20 | 四川航天长征装备制造有限公司 | A kind of TIG weld method of heat treatment reinforcement aluminium alloy |
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| CN109570694A (en) * | 2018-12-28 | 2019-04-05 | 天津航天长征火箭制造有限公司 | A kind of welding method suitable for middle thickness forging state aluminium alloy |
| CN110405316A (en) * | 2019-07-19 | 2019-11-05 | 清华大学 | The method for improving ageing strengthening aluminum alloy melting plumb joint tensile property |
| CN112548277A (en) * | 2020-11-12 | 2021-03-26 | 中国大唐集团科学技术研究院有限公司火力发电技术研究院 | Weld joint interface structure optimization method for dissimilar steel welded joint of thermal power plant |
| CN112453655A (en) * | 2020-11-28 | 2021-03-09 | 四川航天长征装备制造有限公司 | Low-porosity defect welding process method for barrel-shaped aluminum alloy medium-thickness wall plate |
| CN112719536A (en) * | 2020-12-29 | 2021-04-30 | 天津航天长征火箭制造有限公司 | Argon tungsten-arc welding method for annular seam of bottom flange of aluminum-lithium alloy ellipsoid box |
| CN113172310A (en) * | 2021-04-16 | 2021-07-27 | 哈尔滨焊接研究院有限公司 | Welding process for inlet and outlet connecting pipe of low-temperature reactor pressure vessel and heat exchanger connecting pipe |
| CN113199118A (en) * | 2021-06-07 | 2021-08-03 | 四川航天长征装备制造有限公司 | Welding method for large-thickness aluminum alloy flange plate |
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