CN104174752B - A kind of manufacture method of different alloys doubling plate shell composite structure part - Google Patents
A kind of manufacture method of different alloys doubling plate shell composite structure part Download PDFInfo
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- CN104174752B CN104174752B CN201410328330.3A CN201410328330A CN104174752B CN 104174752 B CN104174752 B CN 104174752B CN 201410328330 A CN201410328330 A CN 201410328330A CN 104174752 B CN104174752 B CN 104174752B
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Abstract
The present invention is to provide a kind of manufacture method of different alloys doubling plate shell composite structure part, superplasticity barometric pressure load is widely used in magnesium alloy, copper alloy, aluminium alloy, stainless steel, in the shaping of the plate such as titanium alloy and high temperature alloy shells, the superplasticity inflatable temperature range of different-alloy overlaps each other, superplasticity inflatable temperature range as magnesium alloy and aluminium alloy is overlapping between 400 ~ 525 DEG C, titanium alloy, the superplasticity inflatable temperature range of stainless steel and high temperature alloy is overlapping between 900 ~ 1000 DEG C, so, the superplasticity inflatable temperature range of different-alloy is utilized to overlap each other and the difference of thermal coefficient of expansion, by barometric pressure load forming board shells during heating, the enclasping force between doubling plate is provided by shrinkage adhesion during cooling, realize shaping and the combination of different alloys doubling plate shell composite structure.
Description
Technical field
Patent of the present invention relates to a kind of manufacture method of different alloys doubling plate shell composite structure part.
Background technology
Different alloys doubling plate shell composite structure is by two kinds of different material formings and combination, has fully utilized the different performance of inner plating and lamina rara externa, has played the performance advantage of different-alloy, optimize the combination property of composite construction.
In prior art, the preparation method of foreign material two-layer composite mainly contains rolling, welding and Hydraulic expansion-jointing etc.: rolling can only realize plate compound, and when the mechanical performance of double layer of metal differs greatly, the metal that resistance of deformation is large easily deforms the unstable phenomenon even ruptured; The property of welded joint that welding obtains is good, but easily forms intermetallic compound between weld seam, causes fire check, has a strong impact on the quality of component; Hydraulic expansion-jointing is the effective ways produced complicated tubular member and realize tube sheet connection, Hydraulic expansion-jointing belongs to cold machining process, but the relation be difficult between conservative control displacement and interior pressure, and difficult-to-deformation material is shaped and plate and shell structure shaping under being not suitable for room temperature, so shaping and the associated methods of studying a kind of new two-layer composite are imperative.
Summary of the invention
The object of this invention is to provide the barometric pressure load/shrinkage of a kind of different alloys doubling plate shell composite structure in conjunction with preparation method, superplasticity barometric pressure load is widely used in magnesium alloy, copper alloy, aluminium alloy, stainless steel, in the shaping of the plate such as titanium alloy and high temperature alloy shells, the superplasticity inflatable temperature range of different-alloy overlaps each other, superplasticity inflatable temperature range as magnesium alloy and aluminium alloy is overlapping between 400 ~ 525 DEG C, titanium alloy, the superplasticity inflatable temperature range of stainless steel and high temperature alloy is overlapping between 900 ~ 1000 DEG C, so, the superplasticity inflatable temperature range of different-alloy is utilized to overlap each other and the difference of thermal coefficient of expansion, by barometric pressure load forming board shells during heating, the enclasping force between doubling plate is provided by shrinkage adhesion during cooling, realize shaping and the combination of different alloys doubling plate shell composite structure
The preparation method of two-layer composite of the present invention carries out according to the following steps
A manufacture method for different alloys doubling plate shell composite structure part, is characterized in that comprising the following steps:
Step one, the preparation of double-deck blank plate
Select the first alloy sheets (4) and the second alloy sheets (5), to clean and after drying, stacked placement, forms double-deck blank plate;
Step 2, heating
Double-deck blank plate is placed between die (6) and inlet plate (3), the upper surface of the first alloy sheets (4) contacts with inlet plate (3), the lower surface of the second alloy sheets (5) contacts with die (6), afterwards this double-deck blank version is heated, be heated to design temperature, described design temperature between the overlay region of the superplasticity barometric pressure load temperature of the first alloy sheets (4) and the second alloy sheets (5), insulation 5-10min;
Step 3, pressurization
The air pressure applying 0.5MPa-2.0MPa makes to form seal cavity between double-deck blank plate and inlet plate (3), this inlet plate (3) has an inlet channel (1), by this inlet channel (1) for gas is delivered in seal cavity, the pressure of stable molding forming 1.0MPa-5.0MPa makes plate bulging be close to the inner surface of die (6) under the above design temperature and load path, forms different alloys doubling plate shell composite structure part;
Step 4, cooling
By this different alloys doubling plate shell composite structure part cool to room temperature.
The coefficient of expansion of described first alloy sheets (4) is less than the second alloy sheets (5).
The material of described first alloy sheets (4) is selected from aluminium alloy, titanium alloy or high temperature alloy, and the material of the second alloy sheets (5) is selected from magnesium alloy, kirsite, stainless steel or high temperature alloy.
Mode of heating described in step 2 is selected from, and resistance furnace heating, mould are directly heated or electromagnetic induction heating etc.
Gas described in step 3 can be argon gas, nitrogen or other inert gas.
In the cooling procedure of step 4 when doubling plate shell composite structure internal layer bottom surface forms projection, the pressurize type of cooling can be adopted to eliminate protruding, namely keep gas pressure P
1be cooled to a certain temperature, removal gas pressure P
1after, take out bulging part, cool to room temperature.
In the cooling procedure of step 4 when doubling plate shell composite structure internal layer bottom surface forms projection, detachable except gas pressure P
1, take out bulging part, cool to room temperature, thus eliminate protruding.
Beneficial effect:
(1) adopt barometric pressure load/shrinkage associated methods operation simple, shaping and the combination of two-layer composite can be realized by single operation simultaneously;
(2) under superplastic forming temperature, the resistance of deformation of sheet material is little, and Plastic Forming performance is high, can realize the shaping of difficult-to-deformation material;
(3) two-layer composite realizes combining by interference fit, avoids the formation of intermetallic compound, for the different alloys composite construction easily producing brittlement phase provides effective forming mode;
(4) can the complex-shaped different alloys doubling plate shell composite structure of one time to produce;
(5) drip molding quality is good, do not exist due to the resilience that causes of hardening cause bulging part to be shaped after problem on deformation, therefore accessory size is stablized.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
Fig. 1 is the shaping original state schematic diagram of concrete embodiment;
Fig. 2 is the free bulge stage schematic diagram of concrete embodiment;
Fig. 3 is the cavity filling stage schematic diagram of concrete embodiment;
Fig. 4 is the bulging ending phase schematic diagram of concrete embodiment;
Fig. 5 is that the shaping of embodiment bulging part terminates moment cross section cooperation schematic diagram;
Fig. 6 is bulging part cross section interference fit schematic diagram after the cooling of concrete embodiment.
Wherein P is sealing load, P
0for initial formation pressure, P
xfor instantaneous pressure in forming process, P
1for final forming pressure, e is value of interference fit.
Detailed description of the invention
Below in conjunction with specific embodiment, set forth the present invention further.
Barometric pressure load/shrinkage in conjunction with the double-deck cylindrical member of AA5083/AZ31 different alloys is further described the present invention in conjunction with preparation method.
The die 6 die cavity diameter of the double-deck cylindrical member that is shaped is 80mm, is highly 24mm, and die 6 entrance circular angle radius is 4mm.
Selecting thickness of slab to be the AA5083 rolled aluminium alloy plate 4 of 1.0mm and thickness of slab is that the AZ31 rolling magnesium alloy plate 5 of 1.5mm is as experiment material, before experiment, plate cutting is become the flat board of 140 × 140mm size, with acetone wiping plate surface, keep sheet material surface cleaning, for ease of putting into heater, cut off corner.
The suitable barometric pressure load temperature of AZ31 magnesium alloy is 400 DEG C, thermal coefficient of expansion about 2.4 × 10
-5/ DEG C, the suitable barometric pressure load temperature of AA5083 aluminium alloy is 525 DEG C, thermal coefficient of expansion about 2.1 × 10
-5/ DEG C, therefore the forming temperature of doubling plate 4 and 5 should between 400 DEG C and 525 DEG C, AZ31 magnesium alloy plate 6 is positioned at skin, and AA3083 aluminium alloy plate 4 is positioned at internal layer, forms doubling plate and tests.
Doubling plate 4 and 5 is put between inlet plate 3 and die 6 jointly, then doubling plate 4 and 5 and mould 6 are put into high temperature resistance furnace, 10 minutes are incubated after being heated to 450 DEG C, thrust is provided with hydraulic press, by in the metal of plate 4 press-in seal groove 2, play sealing function, between inlet plate 3 and doubling plate 4 and 5, form seal cavity.Keeping shaping temperature stabilization at 450 DEG C, in medium channel 1, pass into gas medium nitrogen, providing steady pressure, initial pressure P for being shaped
0be 1.2 ~ 1.6MPa, ladder is forced into maximum pressure P
1be 4.2 ~ 4.8MPa, pressurize a period of time at this pressure, make doubling plate 4 and 5 paste mould completely in the gentle pressure of design temperature, realize the shaping of double-deck tubular composite construction, as Figure 1-4.After bulging terminates, removal medium air pressure P
1take out double-deck cylindrical member (cross section as shown in Figure 5), cool, in cooling procedure, AA5083 aluminium alloy amount of contraction is little, and AZ31 magnesium alloy amount of contraction is large, is equivalent to define value of interference fit e between inside and outside cylindrical member, thus the combination of double-deck tubular composite construction is realized, as shown in Figure 6.As forming temperature is too low, then double-deck cylindrical member bottom surface radius of corner is excessive; As final forming pressure P
1excessive, then in forming process, cylindrical member bottom surface fillet breaks, as final forming pressure P
1too small, then cylindrical member bottom surface radius of corner is excessive, and drip molding profile is unintelligible.Adopt the mode of pressurize cooling can prevent internal layer bottom surface projection, after namely bulging terminates, first do not unload air pressure, but keep air pressure to be cooled to a certain temperature, and then unload air pressure, remove bulging part air cooling to room temperature.During pressurize cooling, bottom surface can produce micro-plastic deformation, and lax compression, after unloading air pressure like this, bottom surface institute compression chord would not exceed the critical buckling stress of bottom panel, avoids projection.
After bulging terminates, one of following two kinds of modes can be selected to cool: a. removal gas pressure P
1, take out bulging part, cool to room temperature; B. gas pressure P is kept
1be cooled to a certain temperature such as 350 DEG C, removal gas pressure P
1after, take out bulging part, cool to room temperature.
Should be understood that these embodiments are only not used in for illustration of the present invention to limit the scope of the invention.In addition should be understood that those skilled in the art can make various changes or modifications the present invention, and these equivalent form of values fall within the application's appended claims limited range equally after the content of having read the present invention's instruction.
Claims (6)
1. a manufacture method for different alloys doubling plate shell composite structure part, is characterized in that comprising the following steps:
Step one, the preparation of double-deck blank plate:
Select the first alloy sheets (4) and the second alloy sheets (5), to clean and after drying, stacked placement, forms double-deck blank plate;
Step 2, heating:
Double-deck blank plate is placed between die (6) and inlet plate (3), the upper surface of the first alloy sheets (4) contacts with inlet plate (3), the lower surface of the second alloy sheets (5) contacts with die (6), afterwards this double-deck blank plate is heated, be heated to design temperature, described design temperature between the overlay region of the superplasticity barometric pressure load temperature of the first alloy sheets (4) and the second alloy sheets (5), insulation 5-10min;
Step 3, pressurization:
The air pressure applying 0.5MPa-2.0MPa makes to form seal cavity between double-deck blank plate and inlet plate (3), this inlet plate (3) has an inlet channel (1), by this inlet channel (1) for gas is delivered in seal cavity, the pressure of stable molding forming 1.0MPa-5.0MPa makes double-deck blank plate bulging be close to the inner surface of die (6) under the above design temperature and load path, forms different alloys doubling plate shell composite structure part;
Step 4, cooling:
By this different alloys doubling plate shell composite structure part cool to room temperature.
2. the manufacture method of a kind of different alloys doubling plate shell composite structure part as claimed in claim 1, is characterized in that the coefficient of expansion of described first alloy sheets (4) is less than the second alloy sheets (5).
3. the manufacture method of a kind of different alloys doubling plate shell composite structure part as claimed in claim 2, it is characterized in that the material of described first alloy sheets (4) is selected from aluminium alloy, titanium alloy or high temperature alloy, the material of the second alloy sheets (5) is selected from magnesium alloy, kirsite, stainless steel or high temperature alloy.
4. the manufacture method of a kind of different alloys doubling plate shell composite structure part as claimed in claim 1, is characterized in that the mode of heating in step 2 is selected from resistance furnace heating, mould directly heats or electromagnetic induction heating.
5. the manufacture method of a kind of different alloys doubling plate shell composite structure part as claimed in claim 1, is characterized in that the gas described in step 3 is argon gas, nitrogen or other inert gas.
6. the manufacture method of a kind of different alloys doubling plate shell composite structure part as claimed in claim 1, to it is characterized in that in the cooling procedure of step 4 when doubling plate shell composite structure part internal layer bottom surface forms projection, the pressurize type of cooling is adopted to eliminate protruding, namely gas pressure P1 is kept to be cooled to a certain temperature, after removal gas pressure P1, take out doubling plate shell composite structure part, cool to room temperature.
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| CN201410328330.3A CN104174752B (en) | 2014-07-10 | 2014-07-10 | A kind of manufacture method of different alloys doubling plate shell composite structure part |
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| CN104174752B true CN104174752B (en) | 2016-04-06 |
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| CN104669596B (en) * | 2015-03-10 | 2018-02-02 | 哈尔滨理工大学 | Gas pressure compacting mould and pneumatic shaping method for lithium ion battery packaging film |
| CN106183220B (en) * | 2016-09-14 | 2018-09-11 | 哈尔滨工业大学（威海） | A kind of composite bimetal pipe Thermal expansion-shrinkage combination production method |
| CN107297412B (en) * | 2017-08-23 | 2019-11-15 | 哈尔滨工业大学 | The quick air pressure expanding method of thermal state metal plate |
| CN107971383B (en) * | 2017-11-06 | 2020-03-20 | 北京航星机器制造有限公司 | Blank determining method for realizing superplastic forming of industrial plate |
| CN109807247A (en) * | 2018-12-14 | 2019-05-28 | 宁波信泰机械有限公司 | A kind of battery case aluminium alloy inflation type water cooling board production technology |
| CN110125229B (en) * | 2018-12-18 | 2020-01-21 | 哈尔滨工业大学 | Synchronous high-pressure air-bulking forming method for large-size titanium alloy curved bus double-layer conical barrel component |
| US11485096B2 (en) * | 2019-05-17 | 2022-11-01 | The Boeing Company | Method and system for manufacturing composite structures using a magnesium bladder |
| CN113022045B (en) * | 2021-01-29 | 2022-05-24 | 中南大学 | Preparation method of titanium/aluminum bimetal composite material with curved surface self-forming characteristic |
| CN113305192B (en) * | 2021-05-27 | 2022-05-17 | 吉林大学 | Method and device for cooperatively enhancing gas-bulging superplastic forming of thin-wall curved surface by vibrating steel ball group |
| CN114669651B (en) * | 2022-04-13 | 2024-08-09 | 中国航空制造技术研究院 | Method for manufacturing magnesium-aluminum metal composite structure |
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| US6997025B2 (en) * | 2003-03-06 | 2006-02-14 | Ford Motor Company | Sealing system for super-plastic gas-pressure forming of aluminum sheets |
| DE102011102087A1 (en) * | 2011-05-19 | 2012-11-22 | Formtech Gmbh | Method for processing a surface element |
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| JPH0515931A (en) * | 1991-02-19 | 1993-01-26 | Honda Motor Co Ltd | Molding method for metallic molding and metallic molding |
| CN1631576A (en) * | 2004-12-24 | 2005-06-29 | 哈尔滨理工大学 | Method for billow forming magnet alloy thin plate |
| JP2009028761A (en) * | 2007-07-27 | 2009-02-12 | Sumitomo Light Metal Ind Ltd | Material to be molded for hot blow molding |
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