CN205341647U - Isothermal forming die of big camber titanium alloy covering part - Google Patents
Isothermal forming die of big camber titanium alloy covering part Download PDFInfo
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- CN205341647U CN205341647U CN201520958280.7U CN201520958280U CN205341647U CN 205341647 U CN205341647 U CN 205341647U CN 201520958280 U CN201520958280 U CN 201520958280U CN 205341647 U CN205341647 U CN 205341647U
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Abstract
The utility model relates to an isothermal forming die of big camber titanium alloy covering part, the structure is: be equipped with the blank holder between terrace die and die, the lower surface and the cooperation of terrace die profile of blank holder, surface profile cooperation under upper surface and the die, the underrun ejector pin of blank holder and terrace die surface connections, and the blank holder side is equipped with the spacing groove are with guide structure's on the terrace die outer fringe sliding connection, the laminating of the upper surface of blank holder and the lower surface of die is equipped with the deflector at the side of die, deflector and guide structure's inner edge groove sliding connection, spacing downthehole on the upper surface of blank holder is equipped with the cylindric lock and is located the die. This isothermal forming die of big camber titanium alloy covering part is the effectual mould that provides of the shaping step of preliminary isothermal, has guaranteed that the final of big camber titanium alloy covering part takes shape, adopt first isothermal to take shape in the method that takes shape simultaneously, adopted superplastic forming's technology step again, made the homogenizing wall thickness of the basin shape part after taking shape, satisfied technical requirement.
Description
Technical field
The invention relates to the isothermal forming mould of a kind of deep camber titanium alloy covering part, belongs to metal blank Plastic Forming field.
Background technology
In China's aviation panel beating manufactures, the expanded application of multiple manufacturing process of titanium alloy plate.Titanium alloy owing to density is little, specific strength and, fatigue strength higher than fracture toughness and the excellent combination property such as resistance to crack extension ability is good, low-temperature good toughness, corrosion resistance are strong, it is thus achieved that the industrial department such as Aeronautics and Astronautics, shipbuilding widely uses.Owing to conventional Cold-forming process is difficult to the shaping of titanium alloy sheet metal component, so adopting isothermal thermal forming method and superplastic forming method more.Isothermal thermal forming refers to and below metal material heating to recrystallization temperature, the feature that metal material at high temperature plasticity improves, resistance of deformation reduces will be utilized to manufacture a kind of pressure processing technology of part.Superplastic forming technology is metal material (material composition under specific internal condition, tissue and phase transformation ability etc.) and external condition (temperature, mode of heating, pressure and strain rate etc.) under, present the characteristic without constriction and abnormal high elongation percentage, the deflection deformation more than 100% all becomes superplastic deformation, the method that material superplasticity carrys out formation of parts is utilized to be referred to as superplastic forming, it it is the most integral fabrication technique without surplus of a kind of advanced person, there is big extension, without necking down, little stress, the feature easily shaped, which improve the formability of material, reduce forming pressure, improve product quality, more freedom is provided for design.
Deep camber TC4 titanium alloy covering part is two pieces of bird eyelid coverings, the part of two splits as shown in Figure 1, the direct superplastic forming of lamina adopting thickness to be δ 1.8mm, owing to curvature is too big, first pad pasting place plate is difficult to flow due to rubbing action, thinning basic stopping, the material of last shaping is difficult to supplement, the thinning of thickness can only be relied on to reach the purpose that material flowing is filled, last pad pasting position discharging material is thinning excessive, 3 to 6 position weak points in Fig. 1, out-of-size requirement, wherein weak points 3 and the performance of weak points 4 position are the most serious, do not meet designing requirement.
Summary of the invention
The invention to solve the technical problem that the isothermal forming mould being to provide a kind of deep camber titanium alloy covering part, the isothermal forming mould of this deep camber titanium alloy covering part be preliminary ausforming step provide effective mould, it is ensured that the final shaping of deep camber titanium alloy covering part.
For solving problem above, the concrete technical scheme of the invention is as follows: the isothermal forming mould of a kind of deep camber titanium alloy covering part, Isothermal Hot molding for skin part, blank holder it is provided with between punch and die, the lower surface of blank holder coordinates with punch surface, upper surface and die lower surface positive；The underrun push rod of blank holder is connected with punch upper surface, and blank holder side is provided with stopper slot, is slidably connected with the outer rim of the guide frame on punch；The upper surface of blank holder is fitted with the lower surface of die, and the side at die is provided with the inner edge groove of guide plate, guide plate and guide frame and is slidably connected；Upper surface at blank holder is provided with straight pin, and straight pin is positioned at the spacing hole on die.
The side of described punch, die and blank holder is respectively equipped with lifting rod；Parallel pressing plate groove it is provided with in the front and back end of punch；It is provided with machining benchmark hole at the edge of blank holder；End face at die is provided with lightening grooves, forms reinforcement between several lightening grooves；It is respectively provided with survey hole of thermocouple in the front and back end of die.
The isothermal forming mould of this deep camber titanium alloy covering part adopts blank holder structure, and by box-shaped part flange portion station press forming, and die and moving up and down of blank holder are played guide effect by the outer rim and inside groove by guide frame, it is ensured that closing precision.
Accompanying drawing explanation
Fig. 1 is two basin shape part weak points structural representations.
Fig. 2 is the basin shape part schematic diagram after technique is supplemented.
Fig. 3 is isothermal forming mould structure chart.
Fig. 4 is initial plate schematic shapes.
Fig. 5 is superplastic forming die structure chart.
Fig. 6 is superplastic forming die counterdie top view.
Detailed description of the invention
As shown in Figure 3, the isothermal forming mould of a kind of deep camber titanium alloy covering part, for the Isothermal Hot molding of skin part, is provided with blank holder 9 between punch 7 and die 8, the lower surface of blank holder 9 and punch 7 positive, upper surface and die 8 lower surface positive；The underrun push rod 4 of blank holder 9 is connected with punch 7 upper surface, and blank holder 9 side is provided with stopper slot, is slidably connected with the outer rim of the guide frame 15 on punch 7；The lower surface of the upper surface of blank holder 9 and die 8 is fitted, and the side at die 8 is provided with guide plate 10, and the inner edge groove of guide plate 10 and guide frame 15 is slidably connected；Upper surface at blank holder 9 is provided with straight pin 11, and straight pin 11 is positioned at the spacing hole on die 8.For reducing machining area at blank holder 9 and punch 7 opposite position, the upper surface at punch 7 is provided with plane contact boss 20.
The side of described punch 7, die 8 and blank holder 9 is respectively equipped with lifting rod 12, is used for lifting part；Parallel pressing plate groove 13 it is provided with, for installing with external equipment in the front and back end of punch 7；It is provided with machining benchmark hole 19 at the edge of blank holder 9；End face at die 8 is provided with lightening grooves 16, forms reinforcement 17 1 aspect and make die loss of weight between several lightening grooves 16, increases die top intensity on the other hand；It is respectively provided with survey hole of thermocouple 18, its height distance die face about 30mm in the front and back end of die 8.
The forming technology of a kind of deep camber titanium alloy covering part, comprises the following steps:
1) as in figure 2 it is shown, in digital-to-analogue program, by the program of process complementary surface by 2-in-1 with part for the part 1 in Fig. 1 become " basin " shape part, then the plate digital-to-analogue according to one initial manufacture of hot-forming die quasi spline；
2) being actual plate to be processed according to plate digital-to-analogue blanking, sharpened edge, surface roughness is Ra6.3, and arranges draw-in groove at the two ends of plate to be processed, as shown in Figure 4；
3) isothermal thermal forming technique, adopts the isothermal forming mould of deep camber titanium alloy covering part, and in mould, shape is the sub-elliptical shape close to basin shape part；
3.1) clear up plate to be processed, and be coated with lubricant graphite in panel surface；
3.2) pre-heating temperature elevation program is started, heating rate is 60～70 DEG C/h, when isothermal forming mould temperature stabilization is at 650 DEG C, the draw-in groove at plate two ends is connected with the blank holder 9 of isothermal forming mould, and preheat 4～5min to forming temperature, blank holder 9, by push rod 14 lifting and die 8 matched moulds the 100KN that pressurizes, forms the flange position of basin shape part；
3.3) blank holder 9 and die 8 decline jointly, pressurize 400KN with punch 7 matched moulds, and the dwell time is 8～10min, and the elliptical shape of approximate basin shape opens mould pickup after shaping, and are placed on asbestos pad natural cooling；
4) SPF Technology, adopts and requires, with technology, the superplastic forming die that shape is consistent, as shown in Figure 5 and Figure 6；
4.1) cleaning panel surface is to clean without greasy dirt, and plate two sides and mold tool topcoating are stopped solder flux；
4.2) heating superplastic forming die is to 300 DEG C, and upper and lower mould is pressurizeed by forcing press, starts evacuation and reaches vacuum 2 × 10-3Pa～5 × 10-3Pa and by external pressure Loading Control System be filled with high-purity argon gas protection plate；
4.3) continue heating to forming temperature 920 DEG C, applying argon gas, on-load pressure 1.8MPa, time 2 h, carry out superplastic forming；
4.4) after air pressure-loading terminates, namely complete superplastic forming process, air pressure is gradually lowered to 0, stop heating, treat that mold temperature is reduced to less than 200 DEG C, blow-on pickup；
5) the superplastic forming box-shaped part after cooling is adopted numerical-control processing method cutting slab edge, form two split basin shape parts that technology requires.
Claims (2)
1. the isothermal forming mould of a deep camber titanium alloy covering part, Isothermal Hot molding for skin part, it is characterized in that: between punch (7) and die (8), be provided with blank holder (9), the lower surface of blank holder (9) and punch (7) positive, upper surface and die (8) lower surface positive；The underrun push rod (4) of blank holder (9) is connected with punch (7) upper surface, and blank holder (9) side is provided with stopper slot, is slidably connected with the outer rim of the guide frame (15) on punch (7)；The lower surface of the upper surface of blank holder (9) and die (8) is fitted, and the side at die (8) is provided with guide plate (10), and the inner edge groove of guide plate (10) and guide frame (15) is slidably connected；Upper surface at blank holder (9) is provided with straight pin (11), and straight pin (11) is positioned at the spacing hole on die (8).
2. the isothermal forming mould of deep camber titanium alloy covering part as claimed in claim 1, it is characterised in that: the side of described punch (7), die (8) and blank holder (9) is respectively equipped with lifting excellent (12)；Parallel pressing plate groove (13) it is provided with in the front and back end of punch (7)；It is provided with machining benchmark hole (19) at the edge of blank holder (9)；End face at die (8) is provided with lightening grooves (16), forms reinforcement (17) between several lightening grooves (16)；It is respectively provided with survey hole of thermocouple (18) in the front and back end of die (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520958280.7U CN205341647U (en) | 2015-11-27 | 2015-11-27 | Isothermal forming die of big camber titanium alloy covering part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520958280.7U CN205341647U (en) | 2015-11-27 | 2015-11-27 | Isothermal forming die of big camber titanium alloy covering part |
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| CN205341647U true CN205341647U (en) | 2016-06-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520958280.7U Expired - Fee Related CN205341647U (en) | 2015-11-27 | 2015-11-27 | Isothermal forming die of big camber titanium alloy covering part |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108296402A (en) * | 2018-03-02 | 2018-07-20 | 沈阳飞机工业（集团）有限公司 | A kind of manufacturing process of welding covering entirety isothermal thermal forming mold |
| CN108704950A (en) * | 2018-05-31 | 2018-10-26 | 北京航星机器制造有限公司 | A kind of hot-pressed mold of saddle-shape beam member and component forming method |
| CN109604444A (en) * | 2018-11-13 | 2019-04-12 | 北京航星机器制造有限公司 | A kind of shaping dies and manufacturing process of large-sized aluminium alloy covering |
-
2015
- 2015-11-27 CN CN201520958280.7U patent/CN205341647U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105344819B (en) * | 2015-11-27 | 2017-11-28 | 沈阳飞机工业（集团）有限公司 | The isothermal forming mould and its manufacturing process of deep camber titanium alloy covering part |
| CN108296402A (en) * | 2018-03-02 | 2018-07-20 | 沈阳飞机工业（集团）有限公司 | A kind of manufacturing process of welding covering entirety isothermal thermal forming mold |
| CN108704950A (en) * | 2018-05-31 | 2018-10-26 | 北京航星机器制造有限公司 | A kind of hot-pressed mold of saddle-shape beam member and component forming method |
| CN108704950B (en) * | 2018-05-31 | 2020-06-19 | 北京航星机器制造有限公司 | Saddle-shaped cross beam member hot extrusion forming die and member forming method |
| CN109604444A (en) * | 2018-11-13 | 2019-04-12 | 北京航星机器制造有限公司 | A kind of shaping dies and manufacturing process of large-sized aluminium alloy covering |
| CN109604444B (en) * | 2018-11-13 | 2020-03-20 | 北京航星机器制造有限公司 | Forming die and forming method for large-size aluminum alloy skin |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160629 Termination date: 20201127 |