CN102009160A - Method for preparing high volume fraction particle reinforced metal matrix composites through near net shaping - Google Patents
Method for preparing high volume fraction particle reinforced metal matrix composites through near net shaping Download PDFInfo
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- CN102009160A CN102009160A CN 201010584480 CN201010584480A CN102009160A CN 102009160 A CN102009160 A CN 102009160A CN 201010584480 CN201010584480 CN 201010584480 CN 201010584480 A CN201010584480 A CN 201010584480A CN 102009160 A CN102009160 A CN 102009160A
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Abstract
The invention provides a method for preparing high volume fraction particle reinforced metal matrix composites through near net shaping, comprising the following steps: batching: manufacturing metal material cores; carrying out thermal spraying treatment on the surfaces of the cores; assembling dies and positioning the cores; preparing the composites through infiltration; and extracting the cores. The method has the following advantages: the cavities of the high volume fraction metal matrix composite components are conveniently obtained by prearranging the extractable metal material cores with surfaces subjected to thermal spraying in the composites, thus avoiding the technical bottleneck that the high volume fraction ceramic particle reinforced metal matrix composites are hard to process, greatly reducing the manufacturing cost of the high volume fraction particle reinforced metal matrix composite components and improving the product production efficiency.
Description
Technical field
The present invention is a kind of near clean shape preparation method of high volume fraction particulate reinforced metal-matrix composite, belongs to Manufacturing Technology of Metal-Based Composites.
Background technology
The ceramic particle reinforced metal base composites of high body part (〉=40%) can have thermal control function and unique anti-resonance function of excellent structural bearing function, brilliance simultaneously, with high body part SiC
p/ Al composite is an example, its specific modulus can reach aluminium alloy and titanium alloy three times, thermal coefficient of expansion is also lower than titanium alloy, thermal conductivity is then far above aluminium alloy, average resonance frequencies exceeds more than 60% than aluminium, titanium, steel three big structural metallic materials, and the combination property advantage of this structure/function integration makes this new material in fields such as Aero-Space precision instrument structural member, microelectronic device package elements wide application prospect be arranged.
High its ceramic content of body part ceramic particle reinforced metal base composites higher (40%～70%), thus processing difficulties, cost height, long in time limit, this has limited applying of this advanced material to a great extent.Nearly clean shape technology is emerging advanced technology in the manufacturing industry, the core of this technology is exactly to realize the preparation of material-moulding integrated, make material in preparation process, approach the net shape and the profile of its product as much as possible, farthest reduce subsequent process steps and allowance.The unique advantage that is difficult to machining characteristics and nearly clean shape technology based on high body part ceramic particle reinforced metal base composites, if can be nearly clean shape technology is introduced the preparation of high body part ceramic particle reinforced metal base composites, that will be undoubtedly can obtain large scale, complex-shaped high volume fraction particulate reinforced metal-matrix composite product with acceptable cost, and then applying of this advanced material had great significance.Many scholars both domestic and external also study the near clean shape technology of preparing of high volume fraction particulate reinforced metal-matrix composite, but all be that the method that adopts bonding earlier to make pressure-free impregnation behind the powder precast body of nearly clean shape or pressure infiltration is realized this goal, the adding of binding agent stays pore easily in the composite of subsequent preparation, and bringing the impurity phase of poor thermal conductivity, this just has a foreshadowing for the deterioration of composite property.In addition, for the large scale structural member, ceramics preparative is body formed very difficult, almost invariably can ftracture during presintering.
Summary of the invention
The present invention designs the near clean shape preparation method that a kind of high volume fraction particulate reinforced metal-matrix composite is provided just at the shortcoming that exists in the above-mentioned prior art, its objective is provide a kind of need not or less processing method of carrying out the high volume fraction particulate reinforced metal-matrix composite member die cavity of machining, the difficulty of solution processing blind hole on high hardness material, and satisfy efficient and requirement cheaply.
Technical solution of the present invention is:
The near clean shape preparation method of this kind high volume fraction particulate reinforced metal-matrix composite; with aluminium silicon magnesium Birmasil; fine aluminium; cast magnesium alloy; 2000 is wrought aluminium alloy; 6000 is that wrought aluminium alloy or 7000 is that in the wrought aluminium alloy any one is as matrix material; with silicon-carbide particle; alumina particle; any one ceramic particle in titanium carbide granule or the boron carbide particles and matrix material are formed high volume fraction particulate reinforced metal-matrix composite; described ceramic particle shared volume parts in high volume fraction particulate reinforced metal-matrix composite is 40%～70%, and it is characterized in that: the step of this method is:
(1) batching
Prescription according to needed high volume fraction particulate reinforced metal-matrix composite is prepared burden, and the granularity of ceramic particle is 1 μ m～120 μ m;
(2) make core
Aluminium alloy, titanium alloy or steel are processed into core, and the core shape is coincide with the cavity structure and the profile of composite element, appearance and size is littler than cavity dimension, and has 1～5 ° pattern draft;
(3) core is carried out surface treatment
Adopt hot-spraying technique to apply the MgO coating in whose surfaces, coating layer thickness is about 200～600 μ m;
(4) assembly jig
To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form can be selected from graphite mo(u)ld backboard face screw-driving, the graphite template that core will be installed then is positioned over the bottom of graphite crucible or heat resisting steel mould, ceramic particle is poured into and evenly, entirely covered and the embedding core;
(5) composite infiltration preparation
This process is carried out one of as follows:
5.1 pressure-free impregnation preparation
Covering and the upper surface placement matrix material ingot bar of the ceramic particle accumulation body of embedding core, put into the firing equipment that is connected with nitrogen atmosphere and be heated to 800 ℃～950 ℃, be incubated 2～15 hours, behind the cool to room temperature core is extracted from composite blank bottom, thus the cavity structure of acquisition member;
5.2 pressure infiltration preparation
After the assembly jig that above-mentioned steps (4) is finished places and is preheating to 500 ℃～750 ℃ on the pressurized equipment workbench, the matrix material liquation of fusing is poured in the mould, environmental pressure with mould is increased to 20～30MPa then, pressurize 3～5min, treat that strand solidifies and cools off the back fully and takes out, at last core is extracted from composite blank bottom, thus the cavity structure of acquisition member.
The advantage of technical solution of the present invention is: obtain the die cavity of high body part metal-base composites member easily by adopting the mode that presets the surface heat spray metal material core that can extract in composite, thereby avoided the unmanageable technical bottleneck of high body part ceramic particle reinforced metal base composites, and greatly reduce the high volume fraction particulate reinforced metal-matrix composite member manufacturing cost, improved production efficient.
The specific embodiment
Below with reference to embodiment technical solution of the present invention is further described:
Embodiment 1:
It is that SiC particle and the Al-Si-Mg of 53 μ m is special-purpose aluminum matrix alloy ingot bar that raw material adopt nominal granularity, and strengthening body shared body part in composite is 53%.Core material as forming composite die cavity (blind hole) is the 45# steel, and the appearance and size of core is 79.5mm * 29.5mm * 19.8mm, and fillet is R2, and pattern draft is 3 °, and the thickness of surface heat spraying MgO coating is about 200 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is from graphite mo(u)ld backboard face screw-driving, the graphite template that core will be installed then is positioned over the graphite crucible inside bottom, next the SiC reinforced particulate is poured into and evenly, entirely covered core in the graphite crucible, thus the SiC particle stack of formation embedding core.The aluminium alloy ingot bar is placed SiC particle stack upper surface, this device is put into the equipment that is connected with nitrogen atmosphere be heated to 860 ℃, be incubated 5 hours, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 80mm * 30mm * 20mm.
Embodiment 2:
It is that SiC particle and the Al-Si-Mg of 42.5 μ m is special-purpose aluminum matrix alloy ingot bar that raw material adopt nominal granularity, and strengthening body shared body part in composite is 48%.Core material as forming composite die cavity (blind hole) is that Al-Si-Mg is special-purpose aluminum matrix alloy, the appearance and size of core is 69.3mm * 19.4mm * 9.7mm, fillet is R1, and pattern draft is 1 °, and the thickness of surface heat spraying MgO coating is about 300 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is from graphite mo(u)ld backboard face screw-driving, the graphite template that core will be installed then is positioned over the graphite crucible inside bottom, next the SiC reinforced particulate is poured into and evenly, entirely covered core in the graphite crucible, thus the SiC particle stack of formation embedding core.The aluminium alloy ingot bar is placed SiC particle stack upper surface, this device is put into the equipment that is connected with nitrogen atmosphere be heated to 880 ℃, be incubated 3 hours, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 70mm * 20mm * 10mm.
Embodiment 3:
It is the Al of 3.5 μ m that raw material adopt nominal granularity
2O
3Particle and 7075 aluminium alloy ingot bars, strengthening body shared body part in composite is 40%.Core material as forming composite die cavity (blind hole) is the 40Cr steel, and the appearance and size of core is 68.9mm * 68.9mm * 49.4mm, and fillet is R3, and pattern draft is 5 °, and the thickness of surface heat spraying MgO coating is about 500 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is that the graphite template that core will be installed then is positioned over the graphite crucible inside bottom, next with Al from graphite mo(u)ld backboard face screw-driving
2O
3Reinforced particulate is poured into and evenly, is entirely covered core in the graphite crucible, thereby forms the Al of embedding core
2O
3Particle stack.The aluminium alloy ingot bar is placed Al
2O
3The particle stack upper surface, this device is put into the equipment that is connected with nitrogen atmosphere be heated to 905 ℃, be incubated 12 hours, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 70mm * 70mm * 50mm.
Embodiment 4:
It is that SiC particle and the Al-Si-Mg of 17.3 μ m is special-purpose aluminum matrix alloy ingot bar that raw material adopt nominal granularity, and strengthening body shared body part in composite is 44%.Core material as forming composite die cavity (blind hole) is the TC4 titanium alloy, and the appearance and size of core is 99.1mm * 79.1mm * 59.5mm, and fillet is R3, and pattern draft is 4 °, and the thickness of surface heat spraying MgO coating is about 400 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is from graphite mo(u)ld backboard face screw-driving, the graphite template that core will be installed then is positioned over the graphite crucible inside bottom, next the SiC reinforced particulate is poured into and evenly, entirely covered core in the graphite crucible, thus the SiC particle stack of formation embedding core.The aluminium alloy ingot bar is placed SiC particle stack upper surface, this device is put into the equipment that is connected with nitrogen atmosphere be heated to 900 ℃, be incubated 11 hours, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 100mm * 80mm * 60mm.
Embodiment 5:
It is that SiC particle and the Al-Si-Mg of 120 μ m is special-purpose aluminum matrix alloy ingot bar that raw material adopt nominal granularity, and strengthening body shared body part in composite is 58%.Core material as forming composite die cavity (blind hole) is that Al-Si-Mg is special-purpose aluminum matrix alloy, the appearance and size of core is 158.6mm * 78.7mm * 59.4mm, fillet is R3, and pattern draft is 3 °, and the thickness of surface heat spraying MgO coating is about 600 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is from graphite mo(u)ld backboard face screw-driving, the graphite template that core will be installed then is positioned over the graphite crucible inside bottom, next the SiC reinforced particulate is poured into and evenly, entirely covered core in the graphite crucible, thus the SiC particle stack of formation embedding core.The aluminium alloy ingot bar is placed SiC particle stack upper surface, this device is put into the equipment that is connected with nitrogen atmosphere be heated to 800 ℃, be incubated 10 hours, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 160mm * 80mm * 60mm.
Embodiment 6:
It is that 17 μ m are special-purpose aluminum matrix alloy ingot bar with SiC particle and the Al-Si-Mg that 120 μ m mix in 2: 8 ratio that raw material adopt nominal granularity, and strengthening body shared body part in composite is 70%.Core material as forming composite die cavity (blind hole) is that Al-Si-Mg is special-purpose aluminum matrix alloy, the appearance and size of core is 158.6mm * 78.7mm * 59.4mm, fillet is R3, and pattern draft is 3 °, and the thickness of surface heat spraying MgO coating is about 600 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is from graphite mo(u)ld backboard face screw-driving, the graphite template that core will be installed then is positioned over the graphite crucible inside bottom, next the SiC reinforced particulate is poured into and evenly, entirely covered core in the graphite crucible, thus the SiC particle stack of formation embedding core.The aluminium alloy ingot bar is placed SiC particle stack upper surface, this device is put into the equipment that is connected with nitrogen atmosphere be heated to 880 ℃, be incubated 13 hours, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 160mm * 80mm * 60mm.
Embodiment 7:
It is SiC particle and the cast magnesium alloy ingot bar of 53 μ m that raw material adopt nominal granularity, and strengthening body shared body part in composite is 53%.Core material as forming composite die cavity (blind hole) is the 1Cr18Ni9Ti stainless steel, and the appearance and size of core is 78.7mm * 78.7mm * 59.4mm, and fillet is R3, and pattern draft is 3 °, and the thickness of surface heat spraying MgO coating is about 600 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is from graphite mo(u)ld backboard face screw-driving, the graphite template that core will be installed then is positioned over the graphite crucible inside bottom, next the SiC reinforced particulate is poured into and evenly, entirely covered core in the graphite crucible, thus the SiC particle stack of formation embedding core.The magnesium alloy ingot bar is placed SiC particle stack upper surface, this device is put into the equipment that is connected with nitrogen atmosphere be heated to 800 ℃, be incubated 2 hours, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 80mm * 80mm * 60mm.
Embodiment 8:
It is TiC particle and the 2024 aluminium alloy ingot bars of 1 μ m that raw material adopt nominal granularity, and strengthening body shared body part in composite is 40%.Core material as forming composite die cavity (blind hole) is the TC4 titanium alloy, and the appearance and size of core is 78.7mm * 78.7mm * 59.4mm, and fillet is R3, and pattern draft is 3 °, and the thickness of surface heat spraying MgO coating is about 600 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is from graphite mo(u)ld backboard face screw-driving, the graphite template that core will be installed then is positioned over the graphite crucible inside bottom, next the TiC reinforced particulate is poured into and evenly, entirely covered core in the graphite crucible, thus the TiC particle stack of formation embedding core.The aluminium alloy ingot bar is placed TiC particle stack upper surface, this device is put into the equipment that is connected with nitrogen atmosphere be heated to 950 ℃, be incubated 15 hours, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 80mm * 80mm * 60mm.
Embodiment 9:
It is the B of 28 μ m that raw material adopt nominal granularity
4C particle and commercial-purity aluminium L3, strengthening body shared body part in composite is 48%.Core material as forming composite die cavity (blind hole) is the 45# steel, and the appearance and size of core is 78.7mm * 78.7mm * 19.4mm, and fillet is R3, and pattern draft is 2 °, and the thickness of surface heat spraying MgO coating is about 600 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is that the graphite template that core will be installed then is positioned over the heat resisting steel mold bottom, then with B from graphite mo(u)ld backboard face screw-driving
4Pack into heat resisting steel mould and cover core equably of C particle forms B
4The C particle stack.To the B that core in embedding be housed
4After the mould of C particle stack is positioned over and is preheating to 500 ℃ on the pressurized equipment workbench, the L3 aluminium liquid that fusing is good is separately watered ceramic particle accumulation body upper surface, the environmental pressure with mould is increased to 20MPa then, pressurize 5min, thus aluminium liquid is penetrated into B
4In the C particle stack, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 80mm * 80mm * 20mm.
Embodiment 10:
It is SiC particle and 6061 aluminium alloys of 3.5 μ m that raw material adopt nominal granularity, and strengthening body shared body part in composite is 45%.Core material as forming composite die cavity (blind hole) is the 40Cr steel, and the appearance and size of core is 78.7mm * 78.7mm * 19.4mm, and fillet is R3, and pattern draft is 3 °, and the thickness of surface heat spraying MgO coating is about 600 μ m.To be fixed in preposition on the graphite template through the core of surface heat spray treatment, fixed form is from graphite mo(u)ld backboard face screw-driving, the graphite template that core will be installed then is positioned over the heat resisting steel mold bottom, the heat resisting steel mould of then the SiC particle being packed into also covers core equably, forms the SiC particle stack.Be equipped with mould that embedding the SiC particle stack of core be positioned over be preheating to 750 ℃ on the pressurized equipment workbench after, the 6061 aluminium liquid that fusing is good are separately watered SiC particle stack upper surface, environmental pressure with mould is increased to 30MPa then, pressurize 3min, thereby aluminium liquid is penetrated in the SiC particle stack, cooling obtains the composite strand after finishing the infiltration recombination process, then the equipment that can apply external force by hydraulic press etc. is extracted core from the composite strand, thereby obtains the member type cavity configuration that size is about 80mm * 80mm * 20mm.
Compared with prior art, the present invention adopts the mode that presets the thermal spraying on surface metal material type core that can extract in composite to obtain easily the die cavity of high body part metal-base composites member, thereby avoided the technical bottleneck of the difficult processing of high body part ceramic particle reinforced metal base composites, and greatly reduce the high volume fraction particulate reinforced metal-matrix composite member manufacturing cost, improved production efficient.
Claims (1)
1. the nearly clean shape preparation method of a high volume fraction particulate reinforced metal-matrix composite; with aluminium silicon magnesium Birmasil; fine aluminium; cast magnesium alloy; 2000 is wrought aluminium alloy; 6000 is that wrought aluminium alloy or 7000 is that in the wrought aluminium alloy any one is as matrix material; with silicon-carbide particle; alumina particle; any one ceramic particle in titanium carbide granule or the boron carbide particles and matrix material are formed high volume fraction particulate reinforced metal-matrix composite; described ceramic particle shared volume parts in high volume fraction particulate reinforced metal-matrix composite is 40%～70%, and it is characterized in that: the step of this method is:
(1) batching
Prescription according to needed high volume fraction particulate reinforced metal-matrix composite is prepared burden, and the granularity of ceramic particle is 1 μ m～120 μ m;
(2) make core
Aluminium alloy, titanium alloy or steel are processed into core, and the core shape is coincide with the cavity structure and the profile of composite element, appearance and size is littler than cavity dimension, and has 1～5 ° pattern draft;
(3) core is carried out surface treatment
Adopt hot-spraying technique to apply the MgO coating in whose surfaces, coating layer thickness is about 200～600 μ m;
(4) assembly jig
To be fixed in preposition on the graphite template through the core of surface heat spray treatment, the graphite template that core will be installed then is positioned over the bottom of graphite crucible or heat resisting steel mould, ceramic particle is poured into and evenly, entirely covered and the embedding core;
(5) composite infiltration preparation
This process is carried out one of as follows:
5.1 pressure-free impregnation preparation
Covering and the upper surface placement matrix material ingot bar of the ceramic particle accumulation body of embedding core, put into the firing equipment that is connected with nitrogen atmosphere and be heated to 800 ℃～950 ℃, be incubated 2～15 hours, behind the cool to room temperature core is extracted from composite blank bottom, thus the cavity structure of acquisition member;
5.2 pressure infiltration preparation
After the assembly jig that above-mentioned steps (4) is finished places and is preheating to 500 ℃～750 ℃ on the pressurized equipment workbench, the matrix material liquation of fusing is poured in the mould, environmental pressure with mould is increased to 20～30MPa then, pressurize 3～5min, treat that strand solidifies and cools off the back fully and takes out, at last core is extracted from composite blank bottom, thus the cavity structure of acquisition member.
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| CN103121831A (en) * | 2013-02-06 | 2013-05-29 | 燕山大学 | Preparation method of boron carbide/borax glass composite |
| CN104475702A (en) * | 2014-12-18 | 2015-04-01 | 哈尔滨工业大学 | Preparation method of ZrO2/ hot work die steel composite die material on basis of infiltration connection |
| CN105349817A (en) * | 2015-10-29 | 2016-02-24 | 无锡桥阳机械制造有限公司 | Technology for preparing composite material |
| CN105543519A (en) * | 2015-12-30 | 2016-05-04 | 淮北师范大学 | Preparation method of SiC-(Al-Si) alloy composite material |
| CN107150120A (en) * | 2017-04-14 | 2017-09-12 | 洛阳鹏飞耐磨材料股份有限公司 | A kind of preparation technology of alloy silicate complex matrix ceramic wafer |
| CN109293363A (en) * | 2018-10-24 | 2019-02-01 | 浙江吉成新材股份有限公司 | A kind of preparation method of aluminium boron carbide composite material |
| CN115637354A (en) * | 2022-09-16 | 2023-01-24 | 湖南省大禹科技发展有限公司 | Forming method and forming equipment for rare earth aluminum carbon silicon brake disc |
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| CN102389962B (en) * | 2011-11-22 | 2014-12-24 | 北京科技大学 | Particle infiltration casting process for preparing hard alloy/steel laminated composite material |
| CN103121831A (en) * | 2013-02-06 | 2013-05-29 | 燕山大学 | Preparation method of boron carbide/borax glass composite |
| CN103121831B (en) * | 2013-02-06 | 2015-01-07 | 燕山大学 | Preparation method of boron carbide/borax glass composite |
| CN104475702A (en) * | 2014-12-18 | 2015-04-01 | 哈尔滨工业大学 | Preparation method of ZrO2/ hot work die steel composite die material on basis of infiltration connection |
| CN104475702B (en) * | 2014-12-18 | 2016-08-24 | 哈尔滨工业大学 | The ZrO connected based on infiltration2the preparation method of/hot die steel composite die material |
| CN105349817A (en) * | 2015-10-29 | 2016-02-24 | 无锡桥阳机械制造有限公司 | Technology for preparing composite material |
| CN105543519A (en) * | 2015-12-30 | 2016-05-04 | 淮北师范大学 | Preparation method of SiC-(Al-Si) alloy composite material |
| CN107150120A (en) * | 2017-04-14 | 2017-09-12 | 洛阳鹏飞耐磨材料股份有限公司 | A kind of preparation technology of alloy silicate complex matrix ceramic wafer |
| CN109293363A (en) * | 2018-10-24 | 2019-02-01 | 浙江吉成新材股份有限公司 | A kind of preparation method of aluminium boron carbide composite material |
| CN109293363B (en) * | 2018-10-24 | 2021-10-22 | 浙江吉成新材股份有限公司 | Preparation method of aluminum boron carbide composite material |
| CN115637354A (en) * | 2022-09-16 | 2023-01-24 | 湖南省大禹科技发展有限公司 | Forming method and forming equipment for rare earth aluminum carbon silicon brake disc |
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Application publication date: 20110413 |