CN104233065A - Silicon carbide-enhanced iron/aluminum composite material and preparation method thereof - Google Patents
Silicon carbide-enhanced iron/aluminum composite material and preparation method thereof Download PDFInfo
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- CN104233065A CN104233065A CN201410427838.9A CN201410427838A CN104233065A CN 104233065 A CN104233065 A CN 104233065A CN 201410427838 A CN201410427838 A CN 201410427838A CN 104233065 A CN104233065 A CN 104233065A
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Abstract
The invention relates to a composite material, and particularly relates to a silicon carbide-enhanced iron/aluminum composite material and a preparation method thereof. The composite material comprises a silicon carbide reinforcement and an iron/aluminum alloy matrix, wherein the reinforcement accounts for 0.1-1% of total mass; the balance is the iron/aluminum alloy matrix; and the silicon carbide reinforcement is SiC particle and is 1-5nm in particle size. The preparation method comprises the following processes: burdening; preprocessing the silicon carbide reinforcement; smelting; homogenizing annealing; forging; carrying out hot rolling; carrying out wire drawing; and carrying out thermal treatment. The material product prepared by the method has good high-temperature strength and inoxidizability, and low coefficient of thermal expansion, the defects in the prior art are overcome, and the composite material has a good industrial application prospect.
Description
Technical field:
The present invention relates to a kind of matrix material, particularly a kind of SiC reinforcement iron aluminum composite and preparation method thereof.
Background technology:
Electrical heating alloys material is the resistance alloy utilizing the resistance characteristic of material to manufacture heating element.Current electrical heating alloys material has become a kind of important engineering alloy material, is applicable to the industries such as machinery, metallurgy, electronics, chemical industry, occupies an important position in national economy.The industrial electrical heating element for less than 1300 DEG C mainly adopts nichrome and Aludirome.Nichrome is expensive, and when temperature is greater than 1000 DEG C, oxidation-resistance significantly reduces.Aludirome carbon content is higher, and alloying element is single, and when applied at elevated temperature, internal grain is grown up, and on crystal boundary, netted precipitate easily causes brittle failure, has a strong impact on industrial application.Prior art discloses a kind of novel high-resistance electrothermal alloy material (CN1155590A), its alloy formula to be Fe-(24-32) Al-(0.01-0.2) Ce-(1-6) a, a be in Cr and Mn one or both; Fe-(24-32) Al-(0.01-0.2) Ce (or B)-(0.01-0.3) Zr-(1-6) a-(0.1-2) b, a is one or both in Cr and Mn, b is one or more in W, Mo, Nb, the resistivity of above-mentioned alloy, high temperature oxidation resistance are better than nichrome and Aludirome, but its performance still exists the space promoted further.
Summary of the invention:
The object of the invention is to overcome deficiency of the prior art, a kind of SiC reinforcement iron aluminum composite with good hot strength, oxidation-resistance and less thermal expansivity and preparation method thereof is provided.
A kind of SiC reinforcement iron aluminum composite, it is characterized in that, described matrix material is made up of SiC reinforcement body and ferro-aluminium matrix, and described reinforcement accounts for the 0.1-1% of matrix material total mass, and all the other are ferro-aluminium matrix; Described SiC reinforcement body is SiC particle, particle diameter is 1-5nm, elementary composition and the mass percent of ferro-aluminium matrix is: C:0.01-0.02%, Si:0.2-0.6%, Al:24-26%, Zr:3-4%, Ni:0.2-0.4%, Hf:1-2%, Nb:1-2%, V:1-2%, Mo:0.8-1.3%, Ce:0.8-1.4%, B:0.01-0.015%, S≤0.001%, P≤0.001%, surplus is iron and inevitable impurity, the iron material part used is iron powder, and other is iron block.
The preparation method of above-mentioned SiC reinforcement iron aluminum composite, it is characterized in that, described preparation method comprises:
(1) prepare burden: SiC reinforcement body accounts for the 0.1-1% of matrix material total mass, elementary composition and the mass percent of ferro-aluminium matrix is: C:0.01-0.02%, Si:0.2-0.6%, Al:24-26%, Zr:3-4%, Ni:0.2-0.4%, Hf:1-2%, Nb:1-2%, V:1-2%, Mo:0.8-1.3%, Ce:0.8-1.4%, B:0.01-0.015%, S≤0.001%, P≤0.001%, surplus is iron and inevitable impurity, the iron material part used is iron powder, and other is iron block;
(2) SiC reinforcement body pre-treatment: for improving the wettability of SiC particle in alloy melt, first by the iron powder Homogeneous phase mixing in SiC particle and raw material, and be placed in vacuum sphere grinding machine ball milling 18-24 hour;
(3) melting: the mixed powder after ferro-aluminium matrix material and ball milling is put into the melting of magnetic levitation vacuum induction melting furnace and obtain ingot casting;
(4) homogenizing annealing: cooled ingot casting is put into vacuum heat treatment furnace, in vacuum tightness 1 × 10
-3furnace cooling after being incubated 10 hours at Pa, temperature 900 DEG C;
(5) forge: the ingot casting after homogenizing annealing is put into isothermal forging machine and forges, total deformation is greater than 50%, and forging temperature is 1000 DEG C, obtains the square billet of length of side 100mm, oil quenching after forging;
(6) hot rolling, wire drawing and thermal treatment: first the sample after forging is carried out hot rolling, every time deflection≤25%, obtain the silk material of diameter 8-10mm, carry out solution heat treatment in 1100 DEG C, 2 hours subsequently, then implement three passage wire drawings, first time, Wire Drawing was to diameter 6mm, second time Wire Drawing is to diameter 3mm, third time, Wire Drawing was to diameter 1mm, finally carried out destressing thermal treatment in 400 DEG C, 8 hours, obtained SiC reinforcement iron aluminum composite finished product.
SiC reinforcement iron aluminum composite prepared by the present invention has good hot strength, oxidation-resistance and less thermal expansivity.The existence of nanometer silicon carbide, can play the effect of dispersion-strengthened, is at high temperature formed dislocation glide and hinders, effectively improve the intensity under alloy high-temp, carry heavy alloyed high-temperature oxidation resistance simultaneously.Because the thermal expansivity of silicon carbide is much smaller than ferro-aluminium matrix, therefore, the existence of silicon carbide also effectively can lower the thermal expansivity of matrix material.
With Fe
3al superalloy is matrix, and adding Rare-Earth Ce can purify alloy substrate, improves inclusion pattern, crystal grain thinning, and the oxygen enrichment particle simultaneously formed at grain boundaries can be formed dislocation glide and hinder, thus improves alloy strength; Trace B adds for improving alloy plasticity and processing characteristics has vital role; Heavy alloyed high temperature resistance oxidation-resistance and resistivity effectively can be put forward by adding Zr, Ni, Hf, Nb, V, Mo element.In addition, the present invention improves hot rolling, wire drawing and thermal treatment process further, by implementing three passage wire drawings, (first time, Wire Drawing was to diameter 6mm, second time Wire Drawing is to diameter 3mm, third time, Wire Drawing was to diameter 1mm), effectively enhance productivity, fully reach the effect of reinforcement fibre material, solution heat treatment in 1100 DEG C, 2 hours and destressing thermal treatment in 400 DEG C, 8 hours can optimize morphology of carbides, fully release silk material internal stress, improve silk material work-ing life.
Embodiment:
Set forth further below by embodiment and understand the present invention.
(1) prepare burden: SiC reinforcement body accounts for 0.9% of matrix material total mass, elementary composition and the mass percent of ferro-aluminium matrix is: C:0.015%, Si:0.4%, Al:25%, Zr:3.2%, Ni:0.3%, Hf:1.6%, Nb:1.7%, V:1.2%, Mo:1%, Ce:0.9%, B:0.013%, S≤0.001%, P≤0.001%, surplus is iron and inevitable impurity, the iron material part used is iron powder, and other is iron block;
(2) pre-treatment of SiC reinforcement body is melted: for improving the wettability of SiC particle in alloy body, first by the iron powder Homogeneous phase mixing in SiC particle and raw material, and be placed in vacuum sphere grinding machine ball milling 20 hours;
(3) melting: the mixed powder after ferro-aluminium matrix material and ball milling is put into the melting of magnetic levitation vacuum induction melting furnace and obtain ingot casting;
(4) homogenizing annealing: cooled ingot casting is put into vacuum heat treatment furnace, in vacuum tightness 1 × 10
-3furnace cooling after being incubated 10 hours at Pa, temperature 900 DEG C;
(5) forge: the ingot casting after homogenizing annealing is put into isothermal forging machine and forges, total deformation is greater than 50%, and forging temperature is 1000 DEG C, obtains the square billet of length of side 100mm, oil quenching after forging;
(6) hot rolling, wire drawing and thermal treatment: first the sample after forging is carried out hot rolling, every time deflection≤25%, obtain the silk material of diameter 9mm, carry out solution heat treatment in 1100 DEG C, 2 hours subsequently, then implement three passage wire drawings, first time, Wire Drawing was to diameter 6mm, second time Wire Drawing is to diameter 3mm, third time, Wire Drawing was to diameter 1mm, finally carried out destressing thermal treatment in 400 DEG C, 8 hours, obtained SiC reinforcement iron aluminum composite finished product.
Composite finished product prepared by the embodiment of the present invention has higher hot strength and oxidation-resistance, has less thermal expansivity simultaneously, and 600 DEG C of Tensile strength reach 610MPa, and 1200 DEG C of oxidation weight gains are only Fe under equal conditions
340%, 800 DEG C of thermal expansions of Al alloy oxidation weightening finish are only Fe under equal conditions
350% of Al alloy, overcomes deficiency of the prior art, has wider prospects for commercial application.
Obviously, above-described embodiment is only for example of the present invention is clearly described, and is not the restriction to embodiments of the present invention.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without the need to also giving all embodiments.And these belong to spirit institute's apparent change of extending out of the present invention or change and are still among protection scope of the present invention.
Claims (2)
1. a SiC reinforcement iron aluminum composite, is characterized in that, described matrix material is made up of SiC reinforcement body and ferro-aluminium matrix, and described reinforcement accounts for the 0.1-1% of matrix material total mass, and all the other are ferro-aluminium matrix; Described SiC reinforcement body is SiC particle, particle diameter is 1-5nm, elementary composition and the mass percent of ferro-aluminium matrix is: C:0.01-0.02%, Si:0.2-0.6%, Al:24-26%, Zr:3-4%, Ni:0.2-0.4%, Hf:1-2%, Nb:1-2%, V:1-2%, Mo:0.8-1.3%, Ce:0.8-1.4%, B:0.01-0.015%, S≤0.001%, P≤0.001%, surplus is iron and inevitable impurity, the iron material part used is iron powder, and other is iron block.
2. the preparation method of a kind of SiC reinforcement iron aluminum composite as claimed in claim 1, it is characterized in that, described preparation method comprises: (1) prepares burden: prepare burden according to proportioning according to claim 1; (2) SiC reinforcement body pre-treatment: for improving the wettability of SiC particle in alloy melt, first by the iron powder Homogeneous phase mixing in SiC particle and raw material, and be placed in vacuum sphere grinding machine ball milling 18-24 hour; (3) melting: the mixed powder after ferro-aluminium matrix material and ball milling is put into the melting of magnetic levitation vacuum induction melting furnace and obtain ingot casting; (4) homogenizing annealing: cooled ingot casting is put into vacuum heat treatment furnace, in vacuum tightness 1 × 10
-3furnace cooling after being incubated 10 hours at Pa, temperature 900 DEG C; (5) forge: the ingot casting after homogenizing annealing is put into isothermal forging machine and forges, total deformation is greater than 50%, and forging temperature is 1000 DEG C, obtains the square billet of length of side 100mm, oil quenching after forging; (6) hot rolling, wire drawing and thermal treatment: first the sample after forging is carried out hot rolling, every time deflection≤25%, obtain the silk material of diameter 8-10mm, carry out solution heat treatment in 1100 DEG C, 2 hours subsequently, then implement three passage wire drawings, first time, Wire Drawing was to diameter 6mm, second time Wire Drawing is to diameter 3mm, third time, Wire Drawing was to diameter 1mm, finally carried out destressing thermal treatment in 400 DEG C, 8 hours, obtained SiC reinforcement iron aluminum composite finished product.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107264682A (en) * | 2017-05-31 | 2017-10-20 | 成都小柑科技有限公司 | A kind of bicycle seat of height-adjustable |
| CN107299286A (en) * | 2017-05-31 | 2017-10-27 | 成都小柑科技有限公司 | A kind of inorganic nano-particle strengthens ferroalloy composite |
| CN108149150A (en) * | 2017-12-07 | 2018-06-12 | 北京科技大学 | One kind contains ZrO2Nano particle reinforced abrasion-resistant stee and preparation method |
| CN110216288A (en) * | 2019-07-03 | 2019-09-10 | 江西宝航新材料有限公司 | A method of the printing of aluminum silicon carbide composite material silk material is carried out by electric arc increasing material manufacturing |
| CN110548829A (en) * | 2019-09-06 | 2019-12-10 | 哈尔滨工业大学 | forging method for controlling directional arrangement of aluminum matrix composite whiskers |
| CN111764968A (en) * | 2020-05-19 | 2020-10-13 | 有研金属复材技术有限公司 | Aluminum-based composite material supercharging-stage integral vane ring structure of aircraft engine and preparation method thereof |
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| CN1080665A (en) * | 1993-05-05 | 1994-01-12 | 东南大学 | The Fe-Al-Ce superalloy |
| CN1155590A (en) * | 1996-01-22 | 1997-07-30 | 东南大学 | Ferrous aluminum based high electric resistance alloy for electric heating |
| CN1661267A (en) * | 2001-03-27 | 2005-08-31 | 肯桑特拉海洋和动力股份公司 | Wear resistant composition |
| CN103725972A (en) * | 2014-01-13 | 2014-04-16 | 盐城市鑫洋电热材料有限公司 | Low-carbon multi-element high-resistance electrothermal alloy and preparation method thereof |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB387971A (en) * | 1931-10-15 | 1933-02-16 | Ver Stahlwerke Ag | Improvements in and relating to the manufacture of electrical heating wires |
| CN1080665A (en) * | 1993-05-05 | 1994-01-12 | 东南大学 | The Fe-Al-Ce superalloy |
| CN1155590A (en) * | 1996-01-22 | 1997-07-30 | 东南大学 | Ferrous aluminum based high electric resistance alloy for electric heating |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107264682A (en) * | 2017-05-31 | 2017-10-20 | 成都小柑科技有限公司 | A kind of bicycle seat of height-adjustable |
| CN107299286A (en) * | 2017-05-31 | 2017-10-27 | 成都小柑科技有限公司 | A kind of inorganic nano-particle strengthens ferroalloy composite |
| CN108149150A (en) * | 2017-12-07 | 2018-06-12 | 北京科技大学 | One kind contains ZrO2Nano particle reinforced abrasion-resistant stee and preparation method |
| CN110216288A (en) * | 2019-07-03 | 2019-09-10 | 江西宝航新材料有限公司 | A method of the printing of aluminum silicon carbide composite material silk material is carried out by electric arc increasing material manufacturing |
| CN110216288B (en) * | 2019-07-03 | 2021-07-30 | 江西宝航新材料有限公司 | Method for printing aluminum silicon carbide composite material wire through electric arc additive manufacturing |
| CN110548829A (en) * | 2019-09-06 | 2019-12-10 | 哈尔滨工业大学 | forging method for controlling directional arrangement of aluminum matrix composite whiskers |
| CN111764968A (en) * | 2020-05-19 | 2020-10-13 | 有研金属复材技术有限公司 | Aluminum-based composite material supercharging-stage integral vane ring structure of aircraft engine and preparation method thereof |
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