CN103658544A - Designing and preparing method for conversion-free preliminary processing reference integral sand core - Google Patents
Designing and preparing method for conversion-free preliminary processing reference integral sand core Download PDFInfo
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- CN103658544A CN103658544A CN201310649862.2A CN201310649862A CN103658544A CN 103658544 A CN103658544 A CN 103658544A CN 201310649862 A CN201310649862 A CN 201310649862A CN 103658544 A CN103658544 A CN 103658544A
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Abstract
The invention relates to a designing and preparing method for a conversion-free preliminary processing reference integral sand core. According to the invention, preliminary processing references are designed in a processing reference plane, then the preliminary processing reference are integrated with sand cores where key workblank surfaces are located to form an integral sand core, so dimensional deviations between the workblank surfaces and machining surfaces are controlled to be in a small range. With the method provided by the invention, dimensional deviations between preliminary processing references, between the preliminary processing references and the workblank surfaces and between the workblank surfaces are reduced, so requirements on dimensional accuracy of a casting are met.
Description
Technical field
The present invention relates to a kind of core design in sand mold hot investment casting field and method of coremaking of being applied to, especially a kind of without conversion preliminary working benchmark integral sand core design core-making method.
Background technology
The design of original sand core for casting and core-making technique are: casting design → preliminary working reference design → casting process scheme design → core and core assembly design → Core Box → core box manufacture → core box are prepared → penetrated the solidify → core depanning → core inspection → core repairing → coremaking of sand (back-up sand) → consolidation → core and complete.
This technology is by pouring into a mould after a plurality of core combinations, mainly having following deficiency: 1) have dimensional discrepancy between the preliminary working benchmark on different cores; 2) between the preliminary working benchmark on different cores and black skin, there is dimensional discrepancy; 3) between the black skin on different cores, there is dimensional discrepancy.These are not enough can will be delivered on foundry goods after deviation accumulation, causes the black skin of foundry goods and preliminary working benchmark to have larger dimensional discrepancy, causes after Mechanical processing of casting the dimension overproof between black skin and machined surface.
Summary of the invention
The object of the invention is provides a kind of without conversion preliminary working benchmark integral sand core design core-making method for foundry goods, make black skin and preliminary working benchmark keep stable and dimensional accuracy accurately, thereby guarantee after foundry goods machined the dimension precision requirement between machined surface and black skin.Technology solution scheme of the present invention is:
1) casting design;
2) casting process scheme design: determine pouring position, carry out running gate system, assembly and parting Surface Design;
3) preliminary working reference design: design preliminary working benchmark on core corresponding to spray face, concrete scheme is: in foundry goods Z-X design basis plane, 4 standard stations are set, one of them is checking benchmark; In foundry goods Z-Y design basis plane, 4 standard stations are set, one of them is checking benchmark; In foundry goods X-Y design basis plane, 3 standard stations are set;
4) integral sand core design: each core Integration Design at preliminary working benchmark and crucial black skin place is become to an integral sand core, and described crucial black skin is the plane that in part, basic size is positioned at;
5) integral sand core coremaking: adopt 3D rapid prototyping machine to carry out core, design parameter: former fineness of sand is 110 ~ 140 orders, and slicing layer thickness is 0.15 ~ 0.20mm;
6) core is risen again: in stove, during temperature≤40 ℃, core is entered to stove, be incubated 2 ~ 2.5 hour after being slowly steadily warming up to 150 ℃～160 ℃ with stove, cool to the furnace≤40 ℃, come out of the stove;
7) core inspection is repaired;
8) coremaking completes.
High being of a size of of length and width of the preliminary working benchmark in described Z-X and Z-Y design basis plane: 15mm * 10mm * 10mm; Preliminary working reference dimension in X-Y design basis plane is: ф 15 * 1.5mm.
The present invention, by design preliminary working benchmark in design basis plane, then becomes an integral sand core with the core Integration Design at crucial black skin place, reaches the dimensional discrepancy that black skin and machine are added between face and is controlled at the object within the scope of 0.4mm.In order to solve the problem that integral sand core cannot depanning, adopt 3D rapid prototyping machine to carry out the preparation of integral sand core.Advantage of the present invention is that preliminary working benchmark and crucial black skin are designed on same integral sand core, apply again 3D technology and carry out coremaking, reduced between preliminary working benchmark, between black skin and preliminary working benchmark, the dimensional discrepancy between black skin, thereby guarantee the dimension precision requirement of foundry goods.
The specific embodiment
Step without conversion preliminary working benchmark integral sand core design core-making method is as follows:
1) casting design;
2) casting process scheme design: determine pouring position, carry out running gate system, assembly and parting Surface Design;
3) preliminary working reference design: design preliminary working benchmark on core corresponding to spray face, concrete scheme is: in foundry goods Z-X design basis plane, 4 standard stations are set, one of them is checking benchmark; In foundry goods Z-Y design basis plane, 4 standard stations are set, one of them is checking benchmark; In foundry goods X-Y design basis plane, 3 standard stations are set;
4) integral sand core design: each core Integration Design at preliminary working benchmark and crucial black skin place is become to an integral sand core, and described crucial black skin is the plane that in part, basic size is positioned at;
5) integral sand core coremaking: adopt 3D rapid prototyping machine to carry out core, design parameter: former fineness of sand is 110 ~ 140 orders, and slicing layer thickness is 0.15 ~ 0.20mm;
6) core is risen again: in stove, during temperature≤40 ℃, core is entered to stove, be incubated 2 ~ 2.5 hour after being slowly steadily warming up to 150 ℃～160 ℃ with stove, cool to the furnace≤40 ℃, come out of the stove;
7) core inspection is repaired;
8) coremaking completes.
High being of a size of of length and width of the preliminary working benchmark in described Z-X and Z-Y design basis plane: 15mm * 10mm * 10mm; Preliminary working reference dimension in X-Y design basis plane is: ф 15 * 1.5mm.
embodiment mono-
Helicopter particle separator front housing foundry goods, wall thickness 2.8mm, the CT6 level that dimensional accuracy is HB6103, minimum machining allowance is 0.5mm, machined face is 1.9mm with the minimum wall thickness (MINI W.) of black skin.
Implementation process:
1) casting design;
2) casting process scheme design: determine pouring position, carry out running gate system, assembly and parting Surface Design;
3) preliminary working reference design: design preliminary working benchmark on core corresponding to spray face, concrete scheme is: in foundry goods Z-X design basis plane, 4 standard stations are set, one of them is checking benchmark; In foundry goods Z-Y design basis plane, 4 standard stations are set, one of them is checking benchmark; In foundry goods X-Y design basis plane, 3 standard stations are set; High being of a size of of length and width of the preliminary working benchmark in described Z-X and Z-Y design basis plane: 15mm * 10mm * 10mm; Preliminary working reference dimension in X-Y design basis plane is: ф 15 * 1.5mm;
4) integral sand core design: each core Integration Design at preliminary working benchmark and crucial black skin place is become to an integral sand core, and described crucial black skin is is the surface of revolution of front housing and oil circuit;
5) integral sand core coremaking: adopt 3D rapid prototyping machine to carry out core, design parameter: former fineness of sand is 110～140 orders, and slicing layer thickness is 0.15mm;
6) core is risen again: when temperature is 30 ℃ in stove, core is entered to stove, be incubated 2 hour after being slowly steadily warming up to 155 ℃ with stove, cool to 30 ℃ with the furnace, come out of the stove;
7) core inspection is repaired;
8) coremaking completes.
The front housing foundry goods of applying this technology casting detects after processing, and critical size precision has reached the CT6 precision of HB6103, and the little surplus processing of 0.5mm has been realized in local oil circuit hole, has guaranteed the dimensional requirement of machined face with black skin minimum wall thickness (MINI W.) 1.9mm.
Claims (2)
1. without a conversion preliminary working benchmark integral sand core design core-making method, it is characterized in that, described method comprises the following steps:
1) casting design;
2) casting process scheme design: determine pouring position, carry out running gate system, assembly and parting Surface Design;
3) preliminary working reference design: design preliminary working benchmark on core corresponding to spray face, concrete scheme is: in foundry goods Z-X design basis plane, 4 standard stations are set, one of them is checking benchmark; In foundry goods Z-Y design basis plane, 4 standard stations are set, one of them is checking benchmark; In foundry goods X-Y design basis plane, 3 standard stations are set;
4) integral sand core design: each core Integration Design at preliminary working benchmark and crucial black skin place is become to an integral sand core, and described crucial black skin is the plane that in part, basic size is positioned at;
5) integral sand core coremaking: adopt 3D rapid prototyping machine to carry out core, design parameter: former fineness of sand is 110 ~ 140 orders, and slicing layer thickness is 0.15 ~ 0.20mm;
6) core is risen again: in stove, during temperature≤40 ℃, core is entered to stove, be incubated 2 ~ 2.5 hour after being slowly steadily warming up to 150 ℃～160 ℃ with stove, cool to the furnace≤40 ℃, come out of the stove;
7) core inspection is repaired;
8) coremaking completes.
2. as claimed in claim 1 without conversion preliminary working benchmark integral sand core design core-making method, it is characterized in that the high 15 mm * 10 mm * 10mm that are of a size of of length and width of the preliminary working benchmark in described Z-X and Z-Y design basis plane; Preliminary working reference dimension in X-Y design basis plane is ф 15 * 1.5mm.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109290523A (en) * | 2018-11-23 | 2019-02-01 | 安徽应流集团霍山铸造有限公司 | A kind of processing method of small-bore high pound grade valve body integral sand core |
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| WO2001032332A1 (en) * | 1997-08-19 | 2001-05-10 | Amaya Herman E | Fabrication of molds and mold components |
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| CN101497120A (en) * | 2008-01-31 | 2009-08-05 | 上海爱仕达汽车零部件有限公司 | Arrangement method of casting system of aluminium alloy cylinder metal mould low-pressure casting |
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| CN101618432A (en) * | 2009-07-31 | 2010-01-06 | 上海林飞铸造科技有限公司 | Casting method of casting with machining reference |
| CN101716649A (en) * | 2009-11-17 | 2010-06-02 | 中国航天科技集团公司第九研究院第十六研究所 | Lost sand casting process based on photocuring rapid forming |
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| WO2001032332A1 (en) * | 1997-08-19 | 2001-05-10 | Amaya Herman E | Fabrication of molds and mold components |
| CN101049652A (en) * | 2007-04-04 | 2007-10-10 | 大连理工大学 | Integral forming method for overlay film powder in complex shape of geometrical body of disabled laser selection |
| CN101497120A (en) * | 2008-01-31 | 2009-08-05 | 上海爱仕达汽车零部件有限公司 | Arrangement method of casting system of aluminium alloy cylinder metal mould low-pressure casting |
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| CN101716649A (en) * | 2009-11-17 | 2010-06-02 | 中国航天科技集团公司第九研究院第十六研究所 | Lost sand casting process based on photocuring rapid forming |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109290523A (en) * | 2018-11-23 | 2019-02-01 | 安徽应流集团霍山铸造有限公司 | A kind of processing method of small-bore high pound grade valve body integral sand core |
| CN109290523B (en) * | 2018-11-23 | 2020-11-03 | 安徽应流集团霍山铸造有限公司 | Method for processing and manufacturing small-caliber high-pound-grade valve body integral sand core |
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| CN103658544B (en) | 2017-11-07 |
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