CN106955988A - Dissipation heat release composite is integrated with metal material to inlay preparation method - Google Patents
Dissipation heat release composite is integrated with metal material to inlay preparation method Download PDFInfo
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- CN106955988A CN106955988A CN201710188934.6A CN201710188934A CN106955988A CN 106955988 A CN106955988 A CN 106955988A CN 201710188934 A CN201710188934 A CN 201710188934A CN 106955988 A CN106955988 A CN 106955988A
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- metal
- integrated
- heat release
- dissipation heat
- metal material
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D19/00—Casting in, on, or around objects which form part of the product
- B22D19/04—Casting in, on, or around objects which form part of the product for joining parts
Abstract
Dissipation heat release composite is integrated with metal material to inlay preparation method, and the present invention relates to the high temperature preparing technical field of resistance to ablative composite material.The invention solves the problems that existing ablation resistant material such as C/C, C/C SiC due to machining accuracy is low and hot environment under poor mechanical property the problem of.Method：First, type of attachment is determined；2nd, processing metal parts and non-metal workpiece；3rd, combined member is assembled；4th, releasing agent is brushed, graphite fetal membrane is put into；5th, preheat, infiltration alloy is poured into mould, apply pressure, infiltration alloy is penetrated into combined member；Cooling, the demoulding obtains nonmetallic composite embedded with metal component.Present invention process is simple, low cost, structure-function integration, with good ablation resistance the dissipation heat-resistant composite material component that can obtain near net-shape.The inventive method is used for the preparation of ablation resistant material.
Description
Technical field
The present invention relates to the high temperature preparing technical field of resistance to ablative composite material.
Background technology
The ablation resistant material of the main heating part of current high-speed aircraft is C/C and C/C-SiC composites, high temperature
Ceramic material etc..Although above-mentioned ablation resistant material is preparing some privileged sites such as biography with good ablation resistance
During the components of resistance to ablation such as moving axis, because machining accuracy is low, connection and the assembling quality of fit that there are component and other parts are low, even
The problems such as connecing low intensity.Especially for some under conditions of HTHP, some components will not only bear high hot-fluid, also
Larger stress is born, and C/C and C/C-SiC composites are due to the limitation of material self-strength, it is impossible to meet component
Mechanical property requirements；Although and high-temperature ceramic materials intensity is higher, because the intrinsic fragility of material can not also meet ultrahigh speed
The impact for the power that air-flow is produced., can not for resistance to ablation position and connecting portion due to the limitation of the preparation technology of above-mentioned material
It is processed into after part and is assembled again respectively, can not more realizes integrated molding.
Patent CN201610474241.9 is the method being connected on metal material with plastics, patent
CN201610406278.8, CN201610339408.0, CN103231203A, CN104722919A, CN102794572A etc. are
It is the method for the welding manner connection on different metal materials.The more existing patent majority on dissimilar material joining is
Realized on the metal material by welding method of two kinds of unlike materials.And on nonmetallic ablation resistant material and metal it
Between the connection of foreign material yet there are no and report for work.
In summary, there is presently no it is a kind of can be by for the graphite of resistance to high temperature oxidation ablation or C/C materials and metal
Material inlay the process of preparing of integration connection shaping.
The content of the invention
The invention solves the problems that ablation resistant material processing and assembly connection precision is low and the bearing position intensity such as rotating shaft can not
The problem of meeting design requirement, and provide that dissipation heat release composite is integrated with metal material to inlay preparation method.
Dissipation heat release composite is integrated with metal material to inlay preparation method, it is characterised in that this method is specifically to press
Carried out according to following steps：
First, the type of attachment of metal parts and non-metal workpiece is designed as requested；
2nd, the type of attachment determined according to step one, processing metal parts and non-metal workpiece；
3rd, the metal parts and non-metal workpiece processed step 2 are assembled into combined member；
4th, the combined member for assembling step 3 brushes releasing agent, is put into graphite fetal membrane；Then graphite fetal membrane is put into
In mould；
5th, preheated mold and infiltration alloy, then pour into infiltration alloy in mould, put graphite pressure head, apply pressure, will
Infiltration alloy is penetrated into combined member；Cooling, the demoulding obtains nonmetallic composite embedded with metal component, completes dissipation heat release
Composite is integrated with metal material to inlay preparation method.
Metal parts is used for the position that component and other parts have assembly precision requirement in the present invention.Non-metallic part is used
In the position of resistance high temperature and airflow scouring.
The beneficial effects of the invention are as follows：Present invention process is simple, low cost, the heat resistance that can consider composite
Can be with being connected the advantage of metal parts good toughness, metal parts is completely embedded with nonmetallic dissipation heat insulation material, reliable, can be very
Structure-function integration, with good ablation resistance the dissipation solar heat protection that near net-shape is obtained in the short process-cycle is combined
Material members, and solve thermal protection struc ture part and integrally-built dimensional fits precision problem.
The inventive method is used for the preparation of ablation resistant material.
Brief description of the drawings
Fig. 1 is type of attachment schematic diagram in the step one of embodiment one, wherein 1 represents non-metal workpiece material, 2 represent band spiral shell
Line metal shaft；
Fig. 2 is type of attachment schematic diagram in the step one of embodiment three, and wherein a represents non-metal workpiece material, and b represents metal
Pin, c represents perforated metal axle.
Embodiment
Technical solution of the present invention is not limited to the embodiment of act set forth below, also including each embodiment it
Between any combination.
Embodiment one：Present embodiment dissipation heat release composite is integrated with metal material to inlay preparation side
Method, it is characterised in that this method is specifically what is followed the steps below：
First, the type of attachment of metal parts and non-metal workpiece is designed as requested；
2nd, the type of attachment determined according to step one, processing metal parts and non-metal workpiece；
3rd, the metal parts and non-metal workpiece processed step 2 are assembled into combined member；
4th, the combined member for assembling step 3 brushes releasing agent, is put into graphite fetal membrane；Then graphite fetal membrane is put into
In mould；
5th, preheated mold and infiltration alloy, then pour into infiltration alloy in mould, put graphite pressure head, apply pressure, will
Infiltration alloy is penetrated into combined member；Cooling, the demoulding obtains nonmetallic composite embedded with metal component, completes dissipation heat release
Composite is integrated with metal material to inlay preparation method.
Embodiment two：Present embodiment from unlike embodiment one：Type of attachment is in step one
Threaded connection or bearing pin connection.It is other identical with embodiment one.
Embodiment three：Present embodiment from unlike embodiment one or two：Shape is connected in step one
When formula is that bearing pin is connected, sell for circular or flat shape.It is other identical with embodiment one or two.
Embodiment four：Unlike one of present embodiment and embodiment one to three：It is golden in step one
The material for belonging to part is heat resisting steel, Fe bases/Ni based high-temperature alloys, Mo alloys, Ti alloys or W alloy.Other and specific embodiment party
One of formula one to three is identical.
Embodiment five：Unlike one of present embodiment and embodiment one to four：It is non-in step one
The material of metal parts be graphite or C C.It is other identical with one of embodiment one to four.
Embodiment six：Unlike one of present embodiment and embodiment one to five：Non-metal workpiece
Material be density be 1.6g/cm3~1.8g/cm3C/C composites.Other phases one of with embodiment one to five
Together.
Embodiment seven：Unlike one of present embodiment and embodiment one to six：It is non-in step one
The material of metal parts is electrode graphite or high purity graphite.It is other identical with one of embodiment one to six.
Embodiment eight：Unlike one of present embodiment and embodiment one to seven：Taken off in step 4
Mould agent is BN.It is other identical with one of embodiment one to seven.
Embodiment nine：Unlike one of present embodiment and embodiment one to eight：Soaked in step 5
Alloying is two kinds, three kinds or four kinds of mixing in Al, Mg, Si, Mo, Zr and Ta element.Other and embodiment one
It is identical to one of eight.
Embodiment ten：Unlike one of present embodiment and embodiment one to nine：It is golden in step one
Category part material is heat resisting steel, and non-metal workpiece material is that density is 1.7g/cm3High purity graphite when, by mould in step 5
600~700 DEG C are preheated in chamber type electric resistance furnace, infiltration alloy 750~900 DEG C are preheated to, infiltration alloy is that Al, Si press matter
Amount compares 4:The 1 AlSi alloys prepared.It is other identical with one of embodiment one to nine.
Embodiment 11：Unlike one of present embodiment and embodiment one to nine：In step 5
Infiltration alloy is AlSi Mo ternary alloy three-partalloys, and infiltration alloy is preheated into 860~980 DEG C.Other and embodiment one to nine
One of it is identical.
Embodiment 12：Unlike one of present embodiment and embodiment one to nine：In step 5
Infiltration alloy is AlSiZr ternary alloy three-partalloys, and infiltration alloy is preheated into 800~950 DEG C.Other and embodiment one to nine
One of it is identical.
Embodiment 13：Unlike one of present embodiment and embodiment one to nine：In step 5
Infiltration alloy is AlSiTa ternary alloy three-partalloys, and infiltration alloy is preheated into 880~1050 DEG C.Other and embodiment one to nine
One of it is identical.
Embodiment 14：Unlike one of present embodiment and embodiment one to nine：In step 5
Infiltration alloy is AlSiMoTa quaternary alloys, and infiltration alloy is preheated into 700~850 DEG C.It is other with embodiment one to
One of nine is identical.
Embodiment 15：Unlike one of present embodiment and embodiment one to nine：In step 5
Infiltration alloy is AlMg alloys, and infiltration alloy is preheated into 700~850 DEG C.Other phases one of with embodiment one to nine
Together.
Embodiment 16：Unlike one of present embodiment and embodiment one to nine：In step 5
Infiltration alloy is Al, Si in mass ratio 3:The 2 AlSi alloys prepared, 1000~1100 DEG C are preheated to by infiltration alloy.It is other with
One of embodiment one to nine is identical.
Embodiment 17：Present embodiment from unlike embodiment one to one of 16：Step 5
Middle preheating temperature is higher than 100~200 DEG C of infiltration alloy fusing point.It is other identical with embodiment one to one of 16.
Embodiment 18：Present embodiment from unlike embodiment one to one of 17：Step 5
Middle application pressure is 20~50MPa.It is other identical with embodiment one to one of 17.
Beneficial effects of the present invention are verified using following examples：
Embodiment one：
The present embodiment dissipation heat release composite is integrated with metal material to inlay preparation method, is specifically according to following step
Suddenly carry out：
First, design metal parts is to be threadedly coupled with the type of attachment of non-metal workpiece as requested；Wherein metal parts
Material is heat resisting steel, and non-metal workpiece material is that density is 1.7g/cm3High purity graphite；
2nd, the threaded connection determined according to step one, processing metal parts and non-metal workpiece；
3rd, the metal parts and non-metal workpiece processed step 2 are assembled into combined member；
4th, the combined member for assembling step 3 brushes releasing agent, is put into graphite fetal membrane；Then graphite fetal membrane is put into
In mould；Releasing agent is BN；
The 5th, mould is preheated to 650 DEG C in chamber type electric resistance furnace, infiltration alloy is preheated to 800 DEG C, infiltration alloy is
Al, Si in mass ratio 4:1 prepares AlSi alloys, then pours into infiltration alloy in mould, puts graphite pressure head, applies pressure
25MPa, keeps 10min, and infiltration alloy is penetrated into combined member；Cooling, the demoulding obtains nonmetallic composite embedded with metal
Component, completes that dissipation heat release composite is integrated with metal material inlays preparation method.
Type of attachment schematic diagram in the present embodiment step one is as shown in figure 1, wherein 1 represents non-metal workpiece material, and 2 represent
Threaded metal shaft.
Embodiment two：
The present embodiment dissipation heat release composite is integrated with metal material to inlay preparation method, is specifically according to following step
Suddenly carry out：
First, design metal parts is to be threadedly coupled with the type of attachment of non-metal workpiece as requested；Wherein metal parts
Material is heat resisting steel, and non-metal workpiece material is that density is 1.7g/cm3High purity graphite；
2nd, the threaded connection determined according to step one, processing metal parts and non-metal workpiece；
3rd, the metal parts and non-metal workpiece processed step 2 are assembled into combined member；
4th, the combined member for assembling step 3 brushes releasing agent, is put into graphite fetal membrane；Then graphite fetal membrane is put into
In mould；Releasing agent is BN；
The 5th, mould is preheated to 800 DEG C in chamber type electric resistance furnace, infiltration alloy is preheated to 1100 DEG C, infiltration alloy is
Al, Si in mass ratio 3:2 prepare AlSi alloys, then pour into infiltration alloy in mould, put graphite pressure head, apply pressure
25MPa, keeps 10min, and infiltration alloy is penetrated into combined member；Cooling, the demoulding obtains nonmetallic composite embedded with metal
Component, completes that dissipation heat release composite is integrated with metal material inlays preparation method.
Embodiment three：
The present embodiment dissipation heat release composite is integrated with metal material to inlay preparation method, is specifically according to following step
Suddenly carry out：
First, the type of attachment of design metal parts and non-metal workpiece connects for bearing pin as requested；Wherein, metal parts
Material is heat resisting steel, and non-metal workpiece material is that density is 1.7g/cm3High purity graphite；Sell for circle, the material sold with axle is
Heat resisting steel；
2nd, the bearing pin determined according to step one is connected, processing metal parts and non-metal workpiece；
3rd, the metal parts and non-metal workpiece processed step 2 are assembled into combined member；
4th, the combined member for assembling step 3 brushes releasing agent, is put into the graphite fetal membrane consistent with combined member profile
In；Then graphite fetal membrane is put into mould；Releasing agent is BN；
The 5th, mould is preheated to 650 DEG C in chamber type electric resistance furnace, infiltration alloy is preheated to 800 DEG C, infiltration alloy is
Al, Si in mass ratio 4:1 prepares AlSi alloys, then pours into infiltration alloy in mould, puts graphite pressure head, applies pressure
25MPa, keeps 10min, and infiltration alloy is penetrated into combined member；Cooling, the demoulding obtains nonmetallic composite embedded with metal
Component, completes that dissipation heat release composite is integrated with metal material inlays preparation method.
Type of attachment schematic diagram in the present embodiment step one is as shown in Fig. 2 wherein a represents non-metal workpiece material, and b is represented
Metallic pin, c represents perforated metal axle.
Example IV：
The present embodiment dissipation heat release composite is integrated with metal material to inlay preparation method, is specifically according to following step
Suddenly carry out：
First, the type of attachment of design metal parts and non-metal workpiece connects for bearing pin as requested；Wherein, metal parts
Material is heat resisting steel, and non-metal workpiece material is that density is 1.7g/cm3C/C composites；Sell for flat, the material of pin is W
Alloy, the material of axle is Mo alloys；
2nd, the bearing pin determined according to step one is connected, processing metal parts and non-metal workpiece；
3rd, the metal parts and non-metal workpiece processed step 2 are assembled into combined member；
4th, the combined member for assembling step 3 brushes releasing agent, is put into the graphite fetal membrane consistent with combined member profile
In；Then graphite fetal membrane is put into mould；Releasing agent is BN；
The 5th, mould is preheated to 650 DEG C in chamber type electric resistance furnace, infiltration alloy is preheated to 800 DEG C, infiltration alloy is
Al, Si, Mg in mass ratio 3:1:1 prepares AlSi alloys, then pours into infiltration alloy in mould, puts graphite pressure head, applies pressure
Power 25MPa, keeps 10min, and infiltration alloy is penetrated into combined member；Cooling, the demoulding obtains nonmetallic composite mosaic gold
Metal elements, complete that dissipation heat release composite is integrated with metal material inlays preparation method.
Present invention process is simple, and low cost, can to consider the thermal protective performance of composite tough with being connected metal parts
Property good advantage, metal parts is completely embedded with nonmetallic dissipation heat insulation material, reliable, can be obtained within the very short process-cycle
Structure-function integration, with good ablation resistance the dissipation heat-resistant composite material component of near net-shape, and solve
Thermal protection struc ture part and integrally-built dimensional fits precision problem.
Claims (10)
1. dissipation heat release composite is integrated with metal material to inlay preparation method, it is characterised in that this method be specifically according to
What following steps were carried out：
First, the type of attachment of metal parts and non-metal workpiece is designed as requested；
2nd, the type of attachment determined according to step one, processing metal parts and non-metal workpiece；
3rd, the metal parts and non-metal workpiece processed step 2 are assembled into combined member；
4th, the combined member for assembling step 3 brushes releasing agent, is put into graphite fetal membrane；Then graphite fetal membrane is put into mould
In；
5th, preheated mold and infiltration alloy, then pour into infiltration alloy in mould, put graphite pressure head, apply pressure, will infiltrate
Alloy is penetrated into combined member；Cooling, the demoulding obtains nonmetallic composite embedded with metal component, completes dissipation heat release and is combined
Material is integrated with metal material to inlay preparation method.
2. dissipation heat release composite according to claim 1 is integrated with metal material to inlay preparation method, its feature
It is that type of attachment is threaded connection or bearing pin connection in step one.
3. dissipation heat release composite according to claim 2 is integrated with metal material to inlay preparation method, its feature
When being that type of attachment is that bearing pin is connected in step one, sell for circular or flat shape.
4. dissipation heat release composite according to claim 1 is integrated with metal material to inlay preparation method, its feature
The material for being metal parts in step one is heat resisting steel, Fe bases/Ni based high-temperature alloys, Mo alloys, Ti alloys or W alloy.
5. dissipation heat release composite according to claim 1 is integrated with metal material to inlay preparation method, its feature
Be the material of non-metal workpiece in step one for graphite or C C.
6. dissipation heat release composite according to claim 5 is integrated with metal material to inlay preparation method, its feature
The material for being non-metal workpiece in step one is electrode graphite or high purity graphite.
7. dissipation heat release composite according to claim 1 is integrated with metal material to inlay preparation method, its feature
It is that infiltration alloy is two kinds, three kinds or four kinds of mixing in Al, Mg, Si, Mo, Zr and Ta element.
8. dissipation heat release composite according to claim 1 is integrated with metal material to inlay preparation method, its feature
It is that releasing agent is BN in step 4.
9. dissipation heat release composite according to claim 1 is integrated with metal material to inlay preparation method, its feature
It is that preheating temperature is higher than 100~200 DEG C of infiltration alloy fusing point in step 5.
10. dissipation heat release composite according to claim 1 is integrated with metal material to inlay preparation method, its feature
It is that to apply pressure in step 5 be 20~50MPa.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710188934.6A CN106955988B (en) | 2017-03-27 | 2017-03-27 | Dissipation heat-resistant composite material is integrated with metal material to inlay preparation method |
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| CN201710188934.6A CN106955988B (en) | 2017-03-27 | 2017-03-27 | Dissipation heat-resistant composite material is integrated with metal material to inlay preparation method |
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| CN106955988A true CN106955988A (en) | 2017-07-18 |
| CN106955988B CN106955988B (en) | 2019-01-08 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112853250A (en) * | 2020-12-28 | 2021-05-28 | 哈尔滨工业大学 | Preparation method of combined gas rudder component |
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| EP1477467A1 (en) * | 2003-05-16 | 2004-11-17 | Hitachi Metals, Ltd. | Composite material having high thermal conductivity and low thermal expansion coefficient, and heat-dissipating substrate |
| CN1563460A (en) * | 2004-03-26 | 2005-01-12 | 哈尔滨工业大学 | SiC/Cu composite materrial and preparation material |
| JP2005131676A (en) * | 2003-10-30 | 2005-05-26 | Honda Motor Co Ltd | Method for manufacturing fiber reinforced metal composite material |
| CN104190902A (en) * | 2014-08-14 | 2014-12-10 | 东莞颠覆产品设计有限公司 | Method of integrally forming non-metal part and metal part |
| 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 |
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2017
- 2017-03-27 CN CN201710188934.6A patent/CN106955988B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1477467A1 (en) * | 2003-05-16 | 2004-11-17 | Hitachi Metals, Ltd. | Composite material having high thermal conductivity and low thermal expansion coefficient, and heat-dissipating substrate |
| JP2005131676A (en) * | 2003-10-30 | 2005-05-26 | Honda Motor Co Ltd | Method for manufacturing fiber reinforced metal composite material |
| CN1563460A (en) * | 2004-03-26 | 2005-01-12 | 哈尔滨工业大学 | SiC/Cu composite materrial and preparation material |
| CN104190902A (en) * | 2014-08-14 | 2014-12-10 | 东莞颠覆产品设计有限公司 | Method of integrally forming non-metal part and metal part |
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112853250A (en) * | 2020-12-28 | 2021-05-28 | 哈尔滨工业大学 | Preparation method of combined gas rudder component |
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| CN106955988B (en) | 2019-01-08 |
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