CN107755882A - A kind of large titanium alloy component laser gain material connection method - Google Patents
A kind of large titanium alloy component laser gain material connection method Download PDFInfo
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- CN107755882A CN107755882A CN201710962936.6A CN201710962936A CN107755882A CN 107755882 A CN107755882 A CN 107755882A CN 201710962936 A CN201710962936 A CN 201710962936A CN 107755882 A CN107755882 A CN 107755882A
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- welding wire
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Abstract
A kind of large titanium alloy component laser gain material connection method, contain the first connector and the second connector, first connector and the second connector are fixed into a part to be welded with frock clamp, there is a V-shaped gap between the joint face of the joint face of first connector and the second connector, the Breadth Maximum in the gap is less than 12mm；Part to be welded is placed in an inert gas environment, successively advanced with synchronous swung in V-shaped gap of laser beam and welding wire, the weld seam mutually merged by the heat melts welding wire of laser beam and the mother metal formation multilayer of both sides connector.
Description
Technical field
It is further the welding of titanium alloy member the invention belongs to aircraft manufacturing technology, specifically a kind of large titanium alloy
Component laser gain material connection method.
Background technology
With continuing to increase for aircraft size, physical burden and motor power, the thickness of load-carrying construction part, contour dimension
Reach unprecedented degree, cause solid forging and vacuum electron beam welding technology can not meet design requirement.In order to
Meet the connection of big specification, big thickness titanium alloy structure part, it is desirable to using Novel connecting method, ensureing the intensity and knot of joint
While stiffness of structural member, reach the purpose of structural member loss of weight.Furthermore, it desired to which technology has practicality, possesses large-scale production
High efficiency, ensure aircraft production and technical research it is ageing.
The large-scale component being related in large aircraft project is concentrated mainly on bearing beam, Loading End frame, intermediate-frame and rear portion
The positions such as bearing beam, material are high strength titanium alloy, and cross sectional shape is complicated, bears static load, dynamic load and alternate load mostly, even
By high temperature impact.The minimum contour dimension of component is 4.4m × 2.4m, and maximum contour dimension is 14m × 5m, is with reference to thickness
100~150mm, most junctions are not uniform thickness gradual change section.Forged because the projected area of component has exceeded largest domestic
Equipment 6m2The limit, also far beyond the electron beam weldering length and width of vacuum chamber, wide full-size, with reference to thickness more beyond
Laser Welding and the upper limit of electron beam weldering, cause three kinds of techniques can not meet to require.
Because the contour dimension and thickness of component are too big, far beyond the production energy of current domestic electron-beam welding equipment
Power；Then production efficiency is too low for increases material manufacturing technology, maintains the demand in scientific research stage reluctantly, can not meet to produce in batches；Swash at present
Flush weld connection technology can not manufacture the component that thickness exceedes 10mm；And mechanically connect substantially increase aircraft weight, not as
Optional program.
Depth-to-width ratio refers to combine the ratio between depth and width in gap at cross section, high-aspect-ratio refer generally to depth and width it
Than more than 10, such as the mother metal that thickness is 120mm, gap width requirement is less than 12mm.There was only vacuum electron beam and Laser Welding at present
Technique can reach high-aspect-ratio, and the depth-to-width ratio of conventional arc welding interconnection technique is difficult more than 4.
The content of the invention
It is an object of the present invention to for the practical problem in aircraft manufacturing, in order to meet big specification, big thickness titanium alloy
The connection of structural member, while the intensity and structural member rigidity of joint is ensured, reach the purpose of structural member loss of weight, be provided simultaneously with
The high efficiency of large-scale production, ensure aircraft production and technical research it is ageing, propose that a kind of large titanium alloy component swashs
Light increases material connection method.
A kind of large titanium alloy component laser gain material connection method, contains the first connector and the second connector, its feature
It is, 1) the first connector and the second connector are fixed into a part to be welded, the joint face of the first connector with frock clamp
There is a V-shaped gap between the joint face of the second connector, the Breadth Maximum in the gap is less than 12mm；2) part to be welded is placed in
In one inert gas environment, successively advanced with synchronous swung in V-shaped gap of laser beam and welding wire, pass through the heat of laser beam
The mother metal of filler wire and both sides connector forms the weld seam that multilayer mutually merges.
The beneficial effects of the present invention are：By the method for laser gain material, the mother metal of suitable solder and connector is melted
In narrow gap, the purpose of strong ties such as reach, ensure the smooth manufacture of big-thickness structure part.Laser gain material interconnection technique has
The features such as heat is concentrated, heating is fast, cooling is fast, heat affected area is small, deformation is small, production efficiency is high, using the technology of the present invention, not only
It the purpose of strong ties such as can reach, and production efficiency can be improved.2) present invention further advantage is that：For big thick
Degree, large-sized titanium alloy member devise effectively reliable etc. strong ties mode, make this large-scale component be no longer limited to weld
Connect the power and size of equipment.No matter the design is from follow-up operability, or connection procedure, which controls, can reach good
Effect.3) present invention efficiently solves the difficulty that big thickness, large-scale titanium alloy component electron-beam welding equipment can not be realized
Topic, the limit of forging equipment is overcome, improve the thickness range of laser welding, accelerate the production effect of increases material manufacturing technology
Rate, it is the embodiment of three aspect comprehensive advantages, meets the manufacture to big thickness, large-scale titanium alloy load-carrying construction part interconnection technique
Demand.
Accompanying drawing is described in further detail to the application with reference to embodiments：
Brief description of the drawings
Fig. 1 is large titanium alloy component laser gain material connection method schematic diagram.
Fig. 2 is large titanium alloy component joint face schematic diagram.
Fig. 3 is that large titanium alloy component laser gain material successively welds unfinished weld seam schematic diagram.
Fig. 4 is the weld seam schematic diagram that large titanium alloy component laser gain material successively welds formation.
Fig. 5 is welding wire and wire-feeding pipe relation schematic diagram.
Fig. 6 is wire-feeding pipe structural representation.
Explanation is numbered in figure：1 first component, 2 second components, 3 laser equipments, 4 laser beams, 5 welding wires, 6 weld seams, 7 backing plates,
8V shapes gap, 9 wire-feeding pipes, 10 grooves, 11 through holes
Embodiment
Referring to accompanying drawing, the present invention provides the narrow gap laser gain material connection skill of a kind of big thickness, large-scale titanium alloy component
Art, by the method for laser gain material, suitable solder is added in narrow gap, the purpose of strong ties such as reaches, ensure big thickness
The smooth manufacture of structural member.There is laser gain material interconnection technique heat to concentrate, heating is fast, cooling is fast, heat affected area is small, deformation
It small, the features such as production efficiency is high, using the technology of the present invention, the purpose of strong ties such as can not only reach, and life can be improved
Produce efficiency.
A kind of large titanium alloy component laser gain material connection method, by the first connector 1 and the recruitment clamping of the second connector 2
Tool is fixed into a part to be welded, has a V-shaped gap between the joint face of the first connector 1 and the joint face of the second connector 2
8, the Breadth Maximum in the gap is less than 12mm；Part to be welded is placed in an inert gas environment, successively with laser beam 4 and welding wire
5 synchronous swung in V-shaped gap are advanced, and multilayer is formed by the heat melts welding wire 5 of laser beam 4 and the mother metal of both sides connector
The weld seam 6 mutually merged, form a kind of large titanium alloy component laser gain material connector.
Technical process in implementation is：
Machine adds the connection faying face of connector first, make joint face be in no more than 4 ° of bevel angle, cleaning weldment and
Backing plate, remove all exotics such as surface and oil contaminant, oxide skin.By being assembled by fixture for the first connector 1 and the second connector 2
It is fixed, and argon arc welding positioning welding is used to backing plate 7, part to be welded is formed, and ensure the joint face and second of the first connector
The joint face of connector forms V-shaped gap, its bottom gap connector unfitness of butt joint of 2mm~3mm, top clearance 8mm~12mm, two
No more than 0.05mm.
Part to be welded is placed in argon gas pond, and uniformly and slowly argon gas, the height of argon gas upper surface are filled with from bottom
15mm~25mm above part to be welded should be exceeded, ensure that part to be welded is completely immersed in argon gas.The side to be changed colour using titanium alloy high-temperature
Method, detection argon gas height, and keep argon gas pond surrounding relatively placidity.
During welding, laser beam 4 caused by laser equipment 3 is radiated at the bottom of V-shaped gap, and welding wire, which is worn, is connected on a wire-feeding pipe
Interior, gap of the inert protective gas between wire-feeding pipe and welding wire enters in the V-shaped gap of part to be welded.Welding wire 5 is tight through wire-feeding pipe 9
Successively swing and advance in V-shaped gap with laser beam 4, the connector mother metal of the welding wire 5 that constantly fusing is sent into of laser beam 4 and both sides
Weld layer is formed, on the basis of first layer weld layer, then carries out the welding of the second layer, same welding wire follows laser beam closely in first layer
Swing and move ahead on weld seam, the weld seam of the connector mother metal and lower floor of the filler wire 5 of laser beam 4 and both sides forms higher level
New layer, until finally filling up whole V-shaped gap forms weld seam 6, play a part of connecting the first connector and the second connector.
Because welding wire is straight line and has fabulous handling, a non-powder-type material, collimation is relatively good during feeding, this hair
The bright welding wire for employing paraxonic feeding is as filling metal.Welding wire enters the appropriate position in gap by wire-feeding pipe, with laser
Beam is intersecting and melts.Coordinated between wire-feeding pipe and welding wire using gap, on the one hand ensure the smooth disengaging of welding wire, on the other hand pass through
Protectiveness inert gas is sent into gap between wire-feeding pipe and welding wire, forms localised protection atmosphere, and protectiveness inert gas is from wire feed
The rear end of pipe enters, and is discharged from front end.Protectiveness inert gas can not only prevent layer from aoxidizing, and can also exclude welding process
Caused flue dust, layer heat accelerated solidification can also be taken away.
In implementation, the leading section of above-mentioned wire-feeding pipe opens up four mutual expansion slots 10 in 90 °, ensures welding wire end-heating
When, welding process with anti-clamping welding wire, can be interrupted, expansion slot rear portion drills a diameter of 0.5mm multiple through holes with free wxpansion
11, it is distributed along the even circumferential of wire-feeding pipe 9, inertia excludes from through hole 10, forms highly certain layer of inert, supplements because of wire feed
The protective gas that mechanism enters and confuses or be lost in, while the laminar flow of flowing is formed, exclude flue dust.
Claims (4)
1. a kind of large titanium alloy component laser gain material connection method, containing the first connector and the second connector, its feature exists
In 1) the first connector and the second connector be fixed into a part to be welded with frock clamp, the joint face of the first connector with
There is a V-shaped gap between the joint face of second connector, the Breadth Maximum in the gap is less than 12mm；2) part to be welded is placed in one
In individual inert gas environment, successively advanced with synchronous swung in V-shaped gap of laser beam and welding wire, melted by the heat of laser beam
The mother metal for changing welding wire and both sides connector forms the weld seam that multilayer mutually merges.
2. large titanium alloy component laser gain material connection method as claimed in claim 1, it is characterised in that described welding wire
Wear and be connected in a wire-feeding pipe, inert protective gas enters in the V-shaped gap of part to be welded out of wire-feeding pipe.
3. the large titanium alloy component laser gain material connection method as described in claims 1 or 2, it is characterised in that described to send
The front end of fiber tube is provided with expansion slot, and through hole is additionally provided with the body of the front end of wire-feeding pipe.
4. a kind of large titanium alloy component laser gain material connector, contains the first connector and the second connector, it is characterised in that
There is a V-shaped gap between the joint face of first connector and the second connector, the Breadth Maximum in the gap is less than 12mm；Successively
Advanced with synchronous swung in V-shaped gap of laser beam and welding wire, pass through the heat melts welding wire of laser beam and both sides connector
Mother metal forms the weld seam that multilayer mutually merges.
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| CN201710962936.6A CN107755882A (en) | 2017-10-17 | 2017-10-17 | A kind of large titanium alloy component laser gain material connection method |
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| CN201710962936.6A CN107755882A (en) | 2017-10-17 | 2017-10-17 | A kind of large titanium alloy component laser gain material connection method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108526690A (en) * | 2018-03-13 | 2018-09-14 | 中国科学院合肥物质科学研究院 | The pre- filler narrow gap welding new method of myriawatt grade laser |
| CN110385493A (en) * | 2019-09-02 | 2019-10-29 | 湖南大学 | A kind of laser scanning filler welder and method |
| TWI677398B (en) * | 2018-10-24 | 2019-11-21 | 葉均蔚 | Welding method using alloy powder as welding filler material |
| CN113275596A (en) * | 2021-07-25 | 2021-08-20 | 北京煜鼎增材制造研究院有限公司 | Composite manufacturing titanium alloy part |
| CN113290254A (en) * | 2021-07-25 | 2021-08-24 | 北京煜鼎增材制造研究院有限公司 | Composite manufacturing method of metal part |
| CN113369728A (en) * | 2021-05-20 | 2021-09-10 | 北京航空航天大学 | Method for manufacturing titanium alloy large-scale complex structure component |
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| CN2683305Y (en) * | 2004-03-22 | 2005-03-09 | 中国航空工业第一集团公司北京航空制造工程研究所 | Laser wire filling welding gas protection integrated device |
| CN1657223A (en) * | 2005-04-11 | 2005-08-24 | 北京工业大学 | Welding wire filling method for laser welding to narrow gap of Al-alloy |
| CN103252578A (en) * | 2012-02-17 | 2013-08-21 | 沈阳新松机器人自动化股份有限公司 | Method for narrow-gap laser welding with filler wires for superconducting coil box |
| US20150251275A1 (en) * | 2014-03-07 | 2015-09-10 | Lincoln Global, Inc. | Method and system to start and use combination filler wire feed and high intensity energy source for root pass welding of the inner diameter of clad pipe |
| CN106001921A (en) * | 2016-06-21 | 2016-10-12 | 中国船舶重工集团公司第七二五研究所 | Follow-up gas protection device for thick plate ultra-narrow-gap laser welding with filler wire |
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| CN2683305Y (en) * | 2004-03-22 | 2005-03-09 | 中国航空工业第一集团公司北京航空制造工程研究所 | Laser wire filling welding gas protection integrated device |
| CN1657223A (en) * | 2005-04-11 | 2005-08-24 | 北京工业大学 | Welding wire filling method for laser welding to narrow gap of Al-alloy |
| CN103252578A (en) * | 2012-02-17 | 2013-08-21 | 沈阳新松机器人自动化股份有限公司 | Method for narrow-gap laser welding with filler wires for superconducting coil box |
| US20150251275A1 (en) * | 2014-03-07 | 2015-09-10 | Lincoln Global, Inc. | Method and system to start and use combination filler wire feed and high intensity energy source for root pass welding of the inner diameter of clad pipe |
| CN106001921A (en) * | 2016-06-21 | 2016-10-12 | 中国船舶重工集团公司第七二五研究所 | Follow-up gas protection device for thick plate ultra-narrow-gap laser welding with filler wire |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108526690A (en) * | 2018-03-13 | 2018-09-14 | 中国科学院合肥物质科学研究院 | The pre- filler narrow gap welding new method of myriawatt grade laser |
| TWI677398B (en) * | 2018-10-24 | 2019-11-21 | 葉均蔚 | Welding method using alloy powder as welding filler material |
| CN110385493A (en) * | 2019-09-02 | 2019-10-29 | 湖南大学 | A kind of laser scanning filler welder and method |
| CN113369728A (en) * | 2021-05-20 | 2021-09-10 | 北京航空航天大学 | Method for manufacturing titanium alloy large-scale complex structure component |
| CN113275596A (en) * | 2021-07-25 | 2021-08-20 | 北京煜鼎增材制造研究院有限公司 | Composite manufacturing titanium alloy part |
| CN113290254A (en) * | 2021-07-25 | 2021-08-24 | 北京煜鼎增材制造研究院有限公司 | Composite manufacturing method of metal part |
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Application publication date: 20180306 |