CN107855395A - A kind of titanium alloy box-shaped part Hot drawing device - Google Patents
A kind of titanium alloy box-shaped part Hot drawing device Download PDFInfo
- Publication number
- CN107855395A CN107855395A CN201711284283.7A CN201711284283A CN107855395A CN 107855395 A CN107855395 A CN 107855395A CN 201711284283 A CN201711284283 A CN 201711284283A CN 107855395 A CN107855395 A CN 107855395A
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- Prior art keywords
- face
- mold
- mould
- lower mould
- punch
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
- B21D22/20—Deep-drawing
- B21D22/22—Deep-drawing with devices for holding the edge of the blanks
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/10—Die sets; Pillar guides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/16—Heating or cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Forging (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
Abstract
The present invention relates to a kind of titanium alloy box-shaped part Hot drawing device, it is related to titanium alloy hot forming techniques field.The present invention can realize that the difficult-to-deformation materials such as titanium alloy are special-shaped curved and carry the sagging part Hot drawing pressing formation of box-like, solve the problem that such part forming precision is not high, and easily generation wrinkles and ftractureed in formation.By novel, rational mould structure design, using twice passage drawing scheme formation of parts different shaped face during once-forming.Invention tool structure is simple, easy for operation, reduces batch production cost, improves production efficiency.Solves complex profile titanium alloy component Accurate Shaping problem.
Description
Technical field
The present invention relates to titanium alloy hot forming techniques field, and in particular to a kind of titanium alloy box-shaped part Hot drawing device.
Background technology
Titanium alloy component obtains increasing extensive use in aerospace field, is typically carried out using heat forming technology
Shaping, forming technology flow are：Plate blank is cut according to part, mould loads heating furnace, is heated to after design temperature plate
Material is placed on mould, waits plate to be pressurizeed after reaching predetermined temperature, and upper/lower die matched moulds and pastes mould at sheet metal deformation, pressurize one
Part blank is taken out after fixing time, removes part surplus.But heat forming technology shapes single surface parts or hyperboloid more now
Etc. the relatively simple part in type face.The part that the non-multiple type faces of deep camber transition are formed is easy to produce using common hot forming
Fold and crackle, apply pressure at process complementary surface without parting in type face transition position using hot deep drawing technical components
Bian Li, control material flowing, material is preferably bonded mould, can realize monolithic molding, and precision is higher.Hot deep drawing technique
The sheet metal deformation free degree is less, effective to control material flowing, and sheet material produces bigger deflection, can ensure External Shape chi
Very little and quality, the complex profile titanium alloy component for being difficult to shape to some common hot pressing are especially suitable.
Largely a kind of alloy complex type face is used in body structure and carries the part of box-like lower limit, in forming process
It is not in place to be easy to fillet shaping, or because deflection is excessive, cracking is produced at box-like wall and/or fillet.
The content of the invention
(1) technical problems to be solved
The technical problem to be solved in the present invention is：How alloy complex type face is solved with the sagging part Hot drawing of box-like
The problem of shaping, existing Hot drawing process is eliminated wrinkle, the cracking the defects of, reaches the difficult deformation plate material parts such as titanium alloy
Accurate Shaping.
(2) technical scheme
In order to solve the above-mentioned technical problem, the invention provides a kind of titanium alloy box-shaped part Hot drawing device, described zero
Part has doubly curved face, and doubly curved face is sunk with box-like, including mold 1, middle mould 2 and lower mould 3；On described
Mould 1 has punch-pin face and punch-pin face, and middle mould 2 has punch-pin face, and lower mould 3 has punch-pin face；The mold 1, middle mould
Tool 2 and lower mould 3 by positioning to eurymeric face, mold 1 and lower mould 3 be separately mounted to double acting hot forming forcing press it is upper,
On lower platform；The middle mould 2 is arranged on push rod 4, and the push rod 4 is connected with being taken blame for others under double acting hot forming forcing press, institute
Push rod 4 is stated to be applied on middle mould 2 through the power that lower mould 3 is taken blame for others by under；
The mold punch-pin face 7 can coordinate with middle female die of die face 5, and mold negative mold face 8 can be with lower mould
Punch-pin face 6 coordinates, the different shaped face during once-forming on two passage formation of parts；The middle mould 2 is in the first passage
Used in forming process as cavity plate, middle female die of die face 5 coordinates formation of parts with mold punch-pin face 7 under the effect of push rod 4
Curved surface, be used to realize blank holder function in the second passage forming process, pressure-pad-force can by change it is described under the ton taken blame for others
Realize adjustment in position；
The box-like that the mold matrix face 8 and lower mould convex face 6 are used to shape the part sink, the mold
Matrix face 8 has gap after being coupled with lower mould convex face 6；The mold 1 and lower mould 3 are from touching in closing course
Pressure-pad-force needs to adjust, and mold 1 is operation downwards of slowing down always；The middle mould matrix face 5 and mold convex face 7
There is gap after coupling.
Preferably, gap width after the mold matrix face 8 couples with lower mould convex face 6 is (1.5-2) times zero
Part maximum position wall thickness.
Preferably, the gap after middle mould matrix face 5 and mold convex face 7 coupling is part maximum position wall
It is thick.
Preferably, the part is aircraft nacelle.
Preferably, the part is TA15 materials.
(3) beneficial effect
The present invention can realize that the difficult-to-deformation materials such as titanium alloy are special-shaped curved and be sunk part Hot drawing pressing formation with box-like,
Solves the problem that such part forming precision is not high, and easily generation wrinkles and ftractureed in formation.Pass through novel, rational mould
Lamps structure designs, using twice passage drawing scheme formation of parts different shaped face during once-forming.Invention tool structure
Simply, it is easy for operation, batch production cost is reduced, improves production efficiency.Solves complex profile titanium alloy component Accurate Shaping
Problem.
Brief description of the drawings
Fig. 1 is with the sagging part schematic diagram of box-like using the alloy complex type face that the present invention applies；
Fig. 2 by it is provided by the invention be to realize that alloy complex type face band sink the structure of Hot drawing method using device
Schematic diagram；
Fig. 3 is lower die structure schematic diagram；
Fig. 4 is upper die structure structure schematic diagram.
Embodiment
To make the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to the present invention's
Embodiment is described in further detail.
As shown in figure 1, being TA15 titanium alloy components formed thereby, External Shape is that hyperboloid is bonded aircraft nacelle, it is desirable to
Precision is higher, is sunk more deeply with large area in doubly curved face.Part forming difficulty is big, mold design is unreasonable or technique not
Wrinkled when easily being formed on surface, box part wall and fillet easily ftracture.
As shown in Figures 2 to 4, one kind provided by the invention realize above-mentioned alloy complex type face titanium alloy component TA15 into
Device used in shape includes mold 1, middle mould 2 and lower mould 3, and mold 1, middle mould 2 and lower mould 3 pass through positioning pair
Eurymeric face, mold 1 and lower mould 3 are separately mounted on upper and lower platform.Middle mould 2 is arranged on push rod 4, push rod 4 and lower top
Cylinder is connected, and push rod 4 is applied on middle mould 2 through the power that lower mould 3 is taken blame for others by under.Mold punch-pin face 7 and middle female die of die
Tool face 5 coordinates, and mold negative mold face 8 coordinates with lower die punch face 6, during once-forming on two passage formation of parts
Different shaped face.
Middle mould 2 is used in the first passage forming process as cavity plate, and recessed die face 5 and mold are acted in push rod 4
Punch-pin face 7 coordinates formation of parts curved surface.Blank holder function is realized in the second passage forming process, can be by being taken blame for others under change
Tonnage controls pressure-pad-force.Material flowing is controlled during experiment, prevents part wrinkle and cracking.
Box-like on the mold matrix face 8 and the lower formation of parts of mould convex face 6 sink, it is necessary to which to design mold recessed
Type face 8 coupled with lower mould convex face 6 after fit clearance, gap width is (1.5-2) times part maximum position wall thickness.
The mold 1 and lower mould 3 need to adjust pressure-pad-force from touching in closing course, and mold 1 uses
Slow down always compared with low velocity the downward speed of service.
The gap obtained by scaling calculation after middle mould matrix face 5 and mold convex face 7 coupling is part
Maximum position wall thickness.
The alloy complex type face box-shaped part Hot drawing method realized using device provided by the invention, including following 6
Individual step：
(1) one set of die is arranged on double acting hot forming forcing press, mold 1, lower mould 3 are separately mounted to upper and lower
On platform.Middle mould 2 is arranged on push rod 4, and push rod 4 is taken blame for others with and is connected.
(2) required according to titanium alloy forming parameters, reach the titanium alloy of setting in the heating of double acting hot forming forcing press
Plate, which is put into, after 730 DEG C of part forming temperature starts formation of parts.
(3) moved down in the upper mounting plate of double acting hot forming forcing press, i.e., with larger speed of service 10mm/s to middle mould 2
Motion, push rod 4 apply tonnage in the presence of being taken blame for others under to middle mould 2, and mold 1 closes with middle mould 2, in middle female die of die
The the first passage shaping of part type face is completed under the coupling in face 5 and mold punch-pin face 7, formation of parts entirety double-curved profile, is protected
Press 5min.
(4) upper mounting plate continues to move down, and middle mould 2 uses as blank holder in the presence of lower push rod 4 and follows mould
Tool 1 continues to move downward, and to slow down the speed of service be 2mm/s when contact with lower mould 3, with part box-like chamber continuation formation of parts
The more and more violent mold speed of service of deformation finally slows down as 0.5mm/s.
(5) shaping stroke reaches mold 1 and the lower mould closure state of mould 3, mold negative mold face 8 and lower die punch
Face 6 couples, and completes the shaping that the box-like on part type face sink.Taken blame for others kiss gating-feeder material stream under being adjusted in forming process
It is dynamic.
(6) pressurize 30min after mold 1, middle mould 2 and the lower matched moulds of mould 3, part forming are completed, and mold 1 moves up,
Part is taken out in die sinking, is cooled to room temperature, cuts, processes part, then carry out next part forming.
As can be seen that the present invention realizes different shaped using one set of die according to part profile characteristics in once-forming middle substep
Face hot deep drawing.It can be good at a series of problems for solving the shaping of complex profile titanium alloy component.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, some improvement and deformation can also be made, these are improved and deformation
Also it should be regarded as protection scope of the present invention.
Claims (5)
1. a kind of titanium alloy box-shaped part Hot drawing device, it is characterised in that the part has doubly curved face, and hyperboloid
Type face is sunk with box-like, including mold (1), middle mould (2) and lower mould (3)；The mold (1) have punch-pin face and
Punch-pin face, middle mould (2) have punch-pin face, and lower mould (3) has punch-pin face；The mold (1), middle mould (2) and lower mould
Have (3) and the upper and lower flat of double acting hot forming forcing press is separately mounted to eurymeric face, mold (1) and lower mould (3) by positioning
On platform；The middle mould (2) is arranged on push rod (4), and the push rod (4) is connected with being taken blame for others under double acting hot forming forcing press,
The push rod (4) is applied on middle mould (2) through the power that lower mould (3) is taken blame for others by under；
The mold punch-pin face (7) can coordinate with middle female die of die face (5), and mold negative mold face (8) can be with lower mould
Have punch-pin face (6) to coordinate, the different shaped face during once-forming on two passage formation of parts；The middle mould (2) is
Used in a time forming process as cavity plate, middle female die of die face (5) and mold punch-pin face (7) under push rod (4) effect
Coordinate the curved surface of formation of parts, be used to realize blank holder function in the second passage forming process, pressure-pad-force can be by changing
State down the tonnage taken blame for others and realize adjustment；
The box-like that the mold matrix face (8) and lower mould convex face (6) are used to shape the part sink, the mold
Matrix face (8) has gap after being coupled with lower mould convex face (6)；The mold (1) and lower mould (3) are closed from touching
Pressure-pad-force needs to adjust during conjunction, and mold (1) is operation downwards of slowing down always；The middle mould matrix face (5) and
There is gap after the coupling of mold convex face (7).
2. device as claimed in claim 1, it is characterised in that the mold matrix face (8) and lower mould convex face (6) coupling
Gap width after conjunction is (1.5-2) times part maximum position wall thickness.
3. device as claimed in claim 1, it is characterised in that the middle mould matrix face (5) and mold convex face (7) coupling
Gap after conjunction is part maximum position wall thickness.
4. device as claimed in claim 1, it is characterised in that the part is aircraft nacelle.
5. the device as any one of Claims 1-4, it is characterised in that the part is TA15 materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711284283.7A CN107855395A (en) | 2017-12-07 | 2017-12-07 | A kind of titanium alloy box-shaped part Hot drawing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711284283.7A CN107855395A (en) | 2017-12-07 | 2017-12-07 | A kind of titanium alloy box-shaped part Hot drawing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107855395A true CN107855395A (en) | 2018-03-30 |
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ID=61705397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711284283.7A Pending CN107855395A (en) | 2017-12-07 | 2017-12-07 | A kind of titanium alloy box-shaped part Hot drawing device |
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| Country | Link |
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| CN (1) | CN107855395A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109967619A (en) * | 2017-12-28 | 2019-07-05 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of deep camber, variable cross-section titanium alloy covering hot forming mold |
| CN111687593A (en) * | 2020-05-25 | 2020-09-22 | 航天海鹰(哈尔滨)钛业有限公司 | Titanium alloy variable-curvature revolution solid structure sheet metal part forming process |
| CN116833289A (en) * | 2023-05-09 | 2023-10-03 | 吉林大学 | Bionic radiation heating stretch-forming system for difficult-to-deform plate |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS62224430A (en) * | 1986-03-25 | 1987-10-02 | Honda Motor Co Ltd | Manufacture of die for drawing steel plate |
| CN103252410A (en) * | 2013-05-16 | 2013-08-21 | 上汽通用五菱汽车股份有限公司 | Drawing die of wheel hub parts |
| CN104438537A (en) * | 2014-10-15 | 2015-03-25 | 中航飞机股份有限公司西安飞机分公司 | Bulging draw forming method for variable-camber half flat tube part |
| CN105344819A (en) * | 2015-11-27 | 2016-02-24 | 沈阳飞机工业（集团）有限公司 | Isothermal forming die of large-curvature titanium alloy covering part and forming method of isothermal forming die |
-
2017
- 2017-12-07 CN CN201711284283.7A patent/CN107855395A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS62224430A (en) * | 1986-03-25 | 1987-10-02 | Honda Motor Co Ltd | Manufacture of die for drawing steel plate |
| CN103252410A (en) * | 2013-05-16 | 2013-08-21 | 上汽通用五菱汽车股份有限公司 | Drawing die of wheel hub parts |
| CN104438537A (en) * | 2014-10-15 | 2015-03-25 | 中航飞机股份有限公司西安飞机分公司 | Bulging draw forming method for variable-camber half flat tube part |
| CN105344819A (en) * | 2015-11-27 | 2016-02-24 | 沈阳飞机工业（集团）有限公司 | Isothermal forming die of large-curvature titanium alloy covering part and forming method of isothermal forming die |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109967619A (en) * | 2017-12-28 | 2019-07-05 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of deep camber, variable cross-section titanium alloy covering hot forming mold |
| CN111687593A (en) * | 2020-05-25 | 2020-09-22 | 航天海鹰(哈尔滨)钛业有限公司 | Titanium alloy variable-curvature revolution solid structure sheet metal part forming process |
| CN111687593B (en) * | 2020-05-25 | 2022-07-22 | 航天海鹰(哈尔滨)钛业有限公司 | Titanium alloy variable-curvature revolution solid structure sheet metal part forming process |
| CN116833289A (en) * | 2023-05-09 | 2023-10-03 | 吉林大学 | Bionic radiation heating stretch-forming system for difficult-to-deform plate |
| CN116833289B (en) * | 2023-05-09 | 2024-01-23 | 吉林大学 | Bionic radiation heating stretch-forming system for difficult-to-deform plate |
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Application publication date: 20180330 |
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