CN102974829A - Compound hard alloy plane compounding method - Google Patents
Compound hard alloy plane compounding method Download PDFInfo
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- CN102974829A CN102974829A CN2012105093126A CN201210509312A CN102974829A CN 102974829 A CN102974829 A CN 102974829A CN 2012105093126 A CN2012105093126 A CN 2012105093126A CN 201210509312 A CN201210509312 A CN 201210509312A CN 102974829 A CN102974829 A CN 102974829A
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Abstract
The invention discloses a compound hard alloy plane compounding method, which relates to the technical field of hard alloy manufacturing and is used for solving the technical problems of difficulty in controlling finished product shapes, easiness in causing over burning or under burning occurring in sintering, incapability of ensuring that hard alloy tissue structures are in normal states, and the like. The compound hard alloy plane compounding method disclosed by the invention comprises the following steps of: (a) sintering a plurality of hard alloy blocks of marks which are shaped by pressing at corresponding sintering temperatures respectively to make hard alloy products of single marks; (b) milling the plurality of hard alloy products of single marks made in the step (a) respectively, and polishing and grinding respectively; (c) laminating a plurality of hard alloys from bottom to top according to process requirements; and (d) sintering a plurality of laminated hard alloy plates, and controlling the sintering temperature and heat-preserving time.
Description
Technical field
The present invention relates to carbide alloy manufacturing technology field, particularly a kind of composite hard alloy Planar Compound method.
Background technology
Composite and composite goods are one of key areas of new material research and development.With regard to the performance study of various homogenous materials in composite and the composite goods and manufacturing technology, be very ripe.The technology of composite and composite goods most critical is composite manufacturing.The core of composite manufacturing is exactly to make the combination of the faying face of multiple different materials and unlike material goods can satisfy and reach corresponding specification requirement, also wants simultaneously to guarantee that the intrinsic material capability of various materials remains unchanged.
The composite carbide alloy refers to that two kinds are realized the combination of sintering metallurgical grade with the faying face of the carbide alloy of the two or more different trades mark, and the Mathematical Analysis of Al-li Alloy Containing Rare Earth structure of the variant trade mark keeps the new hard metal article of normal condition.By the different trade mark carbide alloy mixture chargings of layering gradation, then suppress, can realize that the pressed compact of lamination trade mark compound is shaped; Through oversintering, also can realize the combination of faying face metallurgical grade again.But, because the difference that different trade mark carbide alloy mixture pressed compact sintering shrinkage coefficients exist can affect the control of lamination composite hard metal article pattern, the sintering temperature of different trade mark carbide alloy is not identical again in addition, sintering can only carry out with a temperature, sintering temperature is high can to produce burning, sintering temperature is low can to produce underburnt, without sinking burning or underburnt can not guarantee that all the Mathematical Analysis of Al-li Alloy Containing Rare Earth structure is normal condition, can only treat as the carbide alloy waste product.
The composite carbide alloy can compatible different trade mark carbide alloy material capability characteristics, realize having complementary advantages, and have high application prospect and use value.Make the composite carbide alloy can become qualified goods, just must solve the technical problem of the composite manufacturing of composite carbide alloy.
Summary of the invention
The present invention is intended to solve and has in the existing composite carbide alloy manufacturing that the finished product pattern is restive, is prone to burning or underburnt in the sintering, can not guarantees that the Mathematical Analysis of Al-li Alloy Containing Rare Earth structure is the technical problems such as normal condition, can realize that with the faying face that the carbide alloy that can make two or more different trades mark is provided the Mathematical Analysis of Al-li Alloy Containing Rare Earth structure of the combination of sintering metallurgical grade and the variant trade mark keeps the manufacture method of the lamination composite carbide alloy of normal condition.
The objective of the invention is to be achieved through the following technical solutions.
A kind of composite hard alloy Planar Compound method of the present invention comprises the steps:
A) respectively the carbide alloy of the different trades mark of the polylith of repressed shaping is carried out sintering under its corresponding sintering temperature, make the hard metal article of the single trade mark;
B) respectively the hard metal article of the aforementioned single trade mark of polylith of making is ground processing and process, so that its surperficial roughness is not more than 0.8; Polish respectively afterwards attrition process, so that its surperficial flatness is not more than 0.00087mm;
C) the polylith carbide alloy after step b) is processed is superimposed together from bottom to top by technological requirement, the plane through attrition process of adjacent two superimposed carbide alloy boards is fitted;
D) superimposed good polylith carbide alloy is carried out sintering, get the minimum in the corresponding sintering temperature of polylith carbide alloy difference, the control sintering temperature is lower than aforementioned minimum 30-50 degree; The control temperature retention time is 30-40 minute.
A kind of composite hard alloy Planar Compound method of the present invention, wherein said step are the carbide alloy of two different trades mark in a); Described step b) in two blocks of carbide alloy is ground processing and process, so that its roughness for the treatment of coating surface is not more than 0.8; Polish respectively afterwards attrition process, so that its flatness for the treatment of coating surface is not more than 0.00087mm; Described step c) in two blocks of carbide alloy after step b) is processed is superimposed together from bottom to top by technological requirement, makes through two planes to be fitted of attrition process to fit; Described steps d) in superimposed two blocks of good carbide alloy is carried out sintering, get two minimums in the corresponding sintering temperature of carbide alloy boards difference.
The beneficial effect of a kind of composite hard alloy Planar Compound method of the present invention:
1. need not to increase new equipment and install the manufacturing that just can finish lamination composite carbide alloy;
2. the combination of the lamination composite carbide alloy faying face of manufacturing reaches the combination of sintering metallurgical grade, and the Mathematical Analysis of Al-li Alloy Containing Rare Earth structure of the variant trade mark keeps normal condition;
3. be applicable to the manufacturing of multiple trade mark lamination composite carbide alloy.
Description of drawings
Two kinds of trade mark laminations of Fig. 1 composite carbide alloy lamination schematic diagram
Four kinds of trade mark laminations of Fig. 2 composite carbide alloy lamination schematic diagram
Fig. 3 lamination composite carbide alloy breaks the experiment schematic diagram
The number in the figure explanation:
1 mixed binding plane, F break cutting force
The specific embodiment
A kind of composite hard alloy Planar Compound method of the present invention is further described by following embodiment.
Carbide alloy be sintered to liquid-phase sintering, Binder Phase metallic cobalt or nickel liquid phase will occur in the carbide alloy more than 1200 degree, because the driving liquid phase of surface tension effects moves to fill a vacancy to the space that has the space to exist and fills a vacancy, the faying face flatness of the lamination composite carbide alloy of process polishing attrition process is not more than 0.00087mm, need the space of filling seldom, it is very limited to fill the amount of liquid phase that needs, can not affect Binder Phase content and the distribution of the normal structure structure needs of each carbide alloy, the carbide hard that is in contact with one another on the faying face can produce solid-phase sintering when identical, form the carbide skeleton, finally make faying face reach the combination of sintering metallurgical grade, the temperature of lamination sintering is lower than wherein low 30 to 50 degree of the minimum sintering temperature of single trade mark carbide alloy, can not produce burning and destroy the original institutional framework of carbide alloy, thereby realize the manufacturing of lamination composite carbide alloy.
Below the invention will be further described by specific embodiment.
Embodiment 1:
To group Hard alloy, YG6X and YG13C
The specification of YG6X hard metal article is 20mmX20mmX10mm, and first repressed shaping is carried out sintering under the sintering temperature of 1450 degree, make the YG6X hard metal article.
The specification of YG13C hard metal article is 20mmX20mmX10mm, and repressed shaping is carried out sintering under the sintering temperature of 1420 degree, make the YG13C hard metal article.
With the mixed binding plane of two kinds of hard metal articles of vertical surface grinding machine mill processing, roughness is not more than 0.8.Then to mixed binding plane polishing attrition process, flatness is not more than 0.00087mm.
Then the mixed binding flat stack of two kinds of hard metal articles is fit together, put into and carry out sintering in the vacuum sintering furnace, sintering temperature is 1380 degree, and temperature retention time 30 minutes is made YG6X and YG13C lamination composite carbide alloy.
1500 times of structures of mixed binding section are normal, and two kinds of hard metal article structure indifferences, and the fracture that breaks experiment is normal condition, and fracture is not on the mixed binding plane.
Embodiment 2:
To group Hard alloy, YN6 and YG13C
The specification of YN6 hard metal article is 20mmX20mmX10mm, and repressed shaping is carried out sintering under the sintering temperature of 1465 degree, make the YN6 hard metal article.
The specification of YG13C hard metal article is 20mmX20mmX10mm, and repressed shaping is carried out sintering under the sintering temperature of 1420 degree, make the YG13C hard metal article.
With the mixed binding plane of two kinds of hard metal articles of vertical surface grinding machine mill processing, roughness is not more than 0.8.Then to mixed binding plane polishing attrition process, flatness is not more than 0.00087mm.
Then the mixed binding flat stack of two kinds of hard metal articles is fit together, put into and carry out sintering in the vacuum sintering furnace, sintering temperature is 1390 degree, and temperature retention time 35 minutes is made YN6 and YG13C lamination composite carbide alloy.
1500 times of structures of mixed binding section are normal, and two kinds of hard metal article structure indifferences, and the fracture that breaks experiment is normal condition, and fracture is not on the mixed binding plane.
Embodiment 3:
To group Hard alloy, YT15 and YG8
The specification of YT15 hard metal article is 20mmX20mmX10mm, and repressed shaping is carried out sintering under the sintering temperature of 1470 degree, make the YT15 hard metal article.
The specification of YG8 hard metal article is 20mmX20mmX10mm, and repressed shaping is carried out the sintering place under the sintering temperature of 1440 degree, make the YG8 hard metal article.
With the mixed binding plane of two kinds of hard metal articles of vertical surface grinding machine mill processing, roughness is not more than 0.8.Then to mixed binding plane polishing attrition process, flatness is not more than 0.00087mm.
Then the mixed binding flat stack of two kinds of hard metal articles is fit together, put into and carry out sintering in the vacuum sintering furnace, sintering temperature is 1410 degree, and temperature retention time 40 minutes is made YT15 and YG8 lamination composite carbide alloy.
1500 times of structures of mixed binding section are normal, and two kinds of hard metal article structure indifferences, and the fracture that breaks experiment is normal condition, and fracture is not on the mixed binding plane.
In sum, the manufacture method of lamination composite carbide alloy of the present invention, made 1500 times of structures of lamination composite carbide alloy are normal, the fracture that breaks experiment is normal condition, and fracture is not on the mixed binding plane, and the combination of faying face reaches the combination of sintering metallurgical grade.The present invention has can make two kinds can realize the combination of sintering metallurgical grade with the faying face of the carbide alloy of the two or more different trades mark, and the Mathematical Analysis of Al-li Alloy Containing Rare Earth structure of the variant trade mark keeps many technological merits such as normal condition.
Claims (2)
1. a composite hard alloy Planar Compound method is characterized in that comprising the steps:
A) respectively the carbide alloy of the different trades mark of the polylith of repressed shaping is carried out sintering under its corresponding sintering temperature, make the hard metal article of the single trade mark;
B) respectively the hard metal article of the aforementioned single trade mark of polylith of making is ground processing and process, so that its surperficial roughness is not more than 0.8; Polish respectively afterwards attrition process, so that its surperficial flatness is not more than 0.00087mm;
C) the polylith carbide alloy after step b) is processed is superimposed together from bottom to top by technological requirement, the plane through attrition process of adjacent two superimposed carbide alloy boards is fitted;
D) superimposed good polylith carbide alloy is carried out sintering, get the minimum in the corresponding sintering temperature of polylith carbide alloy difference, the control sintering temperature is lower than aforementioned minimum 30-50 degree; The control temperature retention time is 30-40 minute.
2. a kind of composite hard alloy Planar Compound method according to claim 1 is characterized in that: described step is the carbide alloy of two different trades mark in a); Described step b) in two blocks of carbide alloy is ground processing and process, so that its roughness for the treatment of coating surface is not more than 0.8; Polish respectively afterwards attrition process, so that its flatness for the treatment of coating surface is not more than 0.00087mm; Described step c) in two blocks of carbide alloy after step b) is processed is superimposed together from bottom to top by technological requirement, makes through two planes to be fitted of attrition process to fit; Described steps d) in superimposed two blocks of good carbide alloy is carried out sintering, get two minimums in the corresponding sintering temperature of carbide alloy boards difference.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112774799A (en) * | 2020-12-17 | 2021-05-11 | 株洲硬质合金集团有限公司 | Hard alloy composite edge tooth for high-pressure roller mill and preparation method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS62271606A (en) * | 1986-05-20 | 1987-11-25 | Nippon Oil & Fats Co Ltd | High hardness sintered material cutting tool |
| JPH09300104A (en) * | 1996-05-10 | 1997-11-25 | Sumitomo Coal Mining Co Ltd | Complex tool material of super-hard alloy system |
| CN101356031A (en) * | 2005-11-10 | 2009-01-28 | 贝克休斯公司 | Earth-boring rotary drill bits and methods of manufacturing earth-boring rotary drill bits having particle-matrix composite bit bodies |
| CN201960133U (en) * | 2011-03-03 | 2011-09-07 | 湖南博云东方粉末冶金有限公司 | Multilayer composite hard alloy product |
| CN102606082A (en) * | 2012-03-29 | 2012-07-25 | 成都比拓超硬材料有限公司 | Diamond compact and manufacturing process for same |
-
2012
- 2012-12-04 CN CN2012105093126A patent/CN102974829A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS62271606A (en) * | 1986-05-20 | 1987-11-25 | Nippon Oil & Fats Co Ltd | High hardness sintered material cutting tool |
| JPH09300104A (en) * | 1996-05-10 | 1997-11-25 | Sumitomo Coal Mining Co Ltd | Complex tool material of super-hard alloy system |
| CN101356031A (en) * | 2005-11-10 | 2009-01-28 | 贝克休斯公司 | Earth-boring rotary drill bits and methods of manufacturing earth-boring rotary drill bits having particle-matrix composite bit bodies |
| CN201960133U (en) * | 2011-03-03 | 2011-09-07 | 湖南博云东方粉末冶金有限公司 | Multilayer composite hard alloy product |
| CN102606082A (en) * | 2012-03-29 | 2012-07-25 | 成都比拓超硬材料有限公司 | Diamond compact and manufacturing process for same |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112774799A (en) * | 2020-12-17 | 2021-05-11 | 株洲硬质合金集团有限公司 | Hard alloy composite edge tooth for high-pressure roller mill and preparation method thereof |
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Application publication date: 20130320 |