CN101144140A - Flying shear blade and preparation method thereof - Google Patents
Flying shear blade and preparation method thereof Download PDFInfo
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- CN101144140A CN101144140A CNA2006101161186A CN200610116118A CN101144140A CN 101144140 A CN101144140 A CN 101144140A CN A2006101161186 A CNA2006101161186 A CN A2006101161186A CN 200610116118 A CN200610116118 A CN 200610116118A CN 101144140 A CN101144140 A CN 101144140A
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Abstract
The present invention discloses a flying shear blade. The component has the weight percentage that C is 0.40-0.70, Si is 0.50-1.20, Mn is 0.20-0.50, Cr is 4.00-6.00, Mo is 0.50-2.00, V is 0.30-1.50, P is less than or equal to 0.02, S is less than or equal to 0.02, and Fe and inevitable impurity are the residual. The present invention provides a manufacture method of electric furnace smelting, and ingot casting; hydrogen removing and annealing treatment, and forging; preliminary heat treatment, rough machining, quenching and tempering heat treatment (primary quenching and high temperature tempering), semi finishing, ultimate heat treatment (secondary quenching, primary low temperature tempering, and secondary low temperature tempering), and fine finishing. By effectively controlling the material texture and the morphology, the quantity, the size and the distribution of carbonide, the quenching temperature and the tempering temperature of the quenching and tempering heat treatment, and the quenching temperature and the tempering temperature of the ultimate heat treatment are controlled, the texture crystal grains are more refined, the carbonide is distributed in a dispersed way, and simultaneously, the thermal stability and the retentivity are remarkably enhanced, thereby being advantageous for improving the operational performance of the blade.
Description
Technical field
The present invention relates to metallurgical tool material field, particularly be applicable to the flying shear blade and the manufacture method thereof of hot-rolled high-strength slab scale or double length shearing.
Background technology
Fast development along with China railways, bridge, building, oil, automobile, household electrical appliances industry, high-strength hot-rolled merchantable timber ratio improves constantly, and comprising: series of productss such as pipe line steel, auto truck beam, high-strength container plate, high-strength engineering machinery steel, tool steel, cutting die steel saw blade.
Because the internal stress of high-strength plate supplied materials is big, plate shape and cross section quality are poor, it is bigger to shear the production difficulty, causes cutting edge chipping, uneven wear and passivation fast easily, causes frequent shutdown to change blade.Blade abrasion is very inhomogeneous, and also there is certain deformation in the greatest wear amount simultaneously up to 0.4mm, and this will have a strong impact on shearing quality and flying shear operation stability.
At present, flying shear blade material commonly used is GC-3, and its design composition is as shown in table 1.This material processing characteristics is better, because it is lower that its C content and Cr, Mo etc. can form the alloying element content of carbide, especially the Mo constituent content only has 0.15～0.45%, mainly plays the effect that improves hardening capacity, does not add other strong carbide forming elements.According to the Fe-Cr-C phasor as can be known, can only separate out a small amount of cementite in its tissue, not have an alloy carbide of high rigidity substantially, thereby hardness is lower, wear resistance is relatively poor.
In order to improve blade hardness, to satisfy the blade service requirements, have to reduce modified heat treated quenching temperature and tempering temperature, final heat treated quenching temperature and tempering temperature in the making processes, thereby the thermostability of its tissue and hardness and retentivity are relatively poor, can only be applicable to the applying working condition of cold conditions flying shear, simultaneously, owing to do not have attrition resistant alloy carbide phase in the tissue, thereby the wear resistance of material and scratch resistance performance are bad, during using, blade easily produces uneven wear and passivation phenomenon fast.
The material composition of table 1 flying shear blade (Wt.%)
| The trade mark | C | Si | Mn | Cr | Mo | Ni | P | S |
| GC-3 | 0.40～ 0.50 | 0.10～ 0.40 | 0.15～ 0.45 | 1.20～ 1.50 | 0.15～ 0.35 | 3.80～ 4.30 | ≤0.02 | ≤0.015 |
Chinese patent application numbers 89106815.5 discloses a kind of mono-material autogenous grinding sword Razor Steel and manufacture method thereof, the Chemical Composition weight percent of blade is: 0.81～1.20%C, 0.10～0.40%Si, 0.10～0.40%Mn is an amount of norium (RE) and an amount of Nb or Ti or V in addition, blade is quenched 820 ± 10 ℃ of heating single-side sprays, after the thermal treatment process of air cooling and low-temperaturetempering, hardness has high-wearing feature and self-grinding greater than 62HRC, has suitable toughness simultaneously concurrently.This blade material belongs to the tool steel of microalloying, only is applicable to the standard machinery blade.
Summary of the invention
The purpose of this invention is to provide a kind of flying shear blade and manufacture method thereof, satisfy the high-strength plate production requirement, improve flying shear shear ability and shearing area quality, solve the bottleneck that high-strength plate is sheared, create conditions for the production capacity of hot-rolled high-strength steel promotes, what be suitable for that the crosscut flying shear uses has good abrasion resistance and an anti-deformation.
Because the ultimate failure of flying shear blade mainly is due to wearing and tearing and the cracking, therefore, the greatest factor that influences flying shear blade work-ing life is a wear resistance.Improve the work-ing life of flying shear blade, require cutting edge still to keep its dimensional precision bearing under big surging force and the frictional force situation.When guaranteeing blade high rigidity and wear resistance, also must have certain intensity and toughness, to prevent early failure phenomenas such as cracking, chipping.And the toughness of material, intensity and wear resisting property index are conflicting, the material of blade and thermal treatment process are determining quantity, pattern, size and the distribution situation of grain fineness number, carbide and inclusion in the tissue, have only the optimum matching that adopts rational composition and thermal treatment process could realize wear resistance, obdurability.
Based on this, technical thought of the present invention is to increase strong carbide forming element content such as Cr, Mo in the new material of flying shear blade, adds strong carbide forming element V simultaneously, the M that can diffusion-precipitation distributes
7C
3Type, M
2C type, MC type alloy carbide have improved the wear resisting property of blade, have improved the hardening capacity of material again.
Flying shear blade of the present invention, its composition weight percent is:
C 0.40-0.70
Si 0.50-1.20
Mn 0.20-0.50
Cr 4.00-6.00
Mo 0.50-2.00
V 0.30-1.50
P ≤0.02
S ≤0.02
Surplus is Fe and inevitable impurity.
By above-mentioned composition, produce flying shear blade of the present invention through following technical process:
Electrosmelting → external refining → ingot casting → esr → ingot casting → expansion hydrogen anneal process → forging → conditioning heat treatment (normalizing+Spheroidizing Annealing) → roughing → modified thermal treatment (primary quenching+high tempering) → semi-finishing → final thermal treatment (secondary quenching+one time low-temperaturetempering+secondary low-temperaturetempering) → precision work.
Particularly, the manufacture method of flying shear blade of the present invention, it comprises the steps:
A) electrosmelting, ingot casting;
B) expand hydrogen anneal process, go into stove → 880-920 ℃ of insulation → 700-740 ℃ of insulation → stove for≤400 ℃ and be chilled to the 300-500 ℃ of air cooling of coming out of the stove;
C) forge,
D) conditioning heat treatment is gone into stove → 850-880 ℃ of insulation → 700-740 ℃ of insulation → stove for≤400 ℃ and is chilled to the 300-500 ℃ of air cooling of coming out of the stove;
E) scale on surface etc. is removed in roughing;
F) modified thermal treatment, 930-950 ℃ of oil quenching+730-750 ℃ of high tempering;
G) semi-finishing is machined to basic size;
H) final thermal treatment, 1020-1060 ℃ oil quenching+550-570 ℃ low-temperaturetempering+540-560 ℃ of secondary low-temperaturetempering;
I) precision work is machined to specified dimension and precision, produces the flying shear blade finished product.Further, adopt external refining to water ingot casting again behind the step a) electrosmelting.
In addition, can also adopt electroslag remelting process ingot casting again behind step a) electrosmelting, external refining, the ingot casting.
External refining, electroslag remelting process can further guarantee slab quality, and it is existing technology commonly used, does not repeat them here.
Different with existing material GC-3, the present invention adopts 4.00-6.00%Cr, according to the Fe-Cr-C phasor as can be known, can form the M that disperse distributes
7C
3The type alloy carbide, hardness can reach 1500-1800HV, and small amount of Fe among the GC-3
3The hardness of C only is 800-1000HV; The Mo constituent content is brought up to 0.50-2.00% in the simultaneously new material, can separate out a large amount of M
2C type carbide hardness reaches 2000-2300HV, promotes the material secondary sclerosis, suppresses temper brittleness; Increased strong carbide forming element V newly, its content is 0.30-1.50%, can precipitation strength type MC carbide, and hardness is up to 2600-2800HV, can crystal grain thinning, improve the hardening capacity of material; New in addition material improves the content of Si, can play the molten admittedly effect of strengthening, and can improve the secondary hardening temperature.Because the acting in conjunction of elements such as Cr, Mo, V is evenly separated out the high hardness alloy carbide in a large number and can be strengthened matrix, form the hard phase, thereby improved abrasion resistance properties greatly in the new material tissue.
For the effectively new material tissue of control and carbide morphology, quantity, size and distribution, must strictly control modified heat treated quenching temperature and tempering temperature, final heat treated quenching temperature and tempering temperature, quenching temperature and tempering temperature obviously improve than existing material GC-3, organize crystal grain refinement and carbide dispersion distribution more, thermostability and retentivity significantly improve simultaneously, and this all helps improving the use properties of blade.
Beneficial effect of the present invention
The present invention adds strong carbide forming element V simultaneously by increasing strong carbide forming element content such as Cr, Mo, the M that can diffusion-precipitation distributes
7C
3Type, M
2C type, MC type alloy carbide have improved the wear resisting property of blade, have improved the hardening capacity of material again.
Simultaneously, the strict control of forging stock making processes is smelted, forging quality, reduces the content of impurity and harmful element, changes inclusion size, form, distribution, improves the homogeneity and the purity of material, improves forging stock delivery attitude quality; Adopt the thermal treatment process of energy crystal grain thinning and tissue, improve the fracture toughness property of blade material, suppress crack propagation.
Under ordinary production specification working conditions, it is more than 2 times of common material flying shear blade that the flying shear blade single uses tonnage, can satisfy the normal shearing demand of the following high-strength plank of 22mm.
Embodiment
Embodiment is referring to table 2, table 3.
Table 2 (Wt.%)
| C | Si | Mn | Ni | Cr | Mo | V | P | S | |
| Embodiment 1 | 0.70 | 1.20 | 0.48 | 4.50 | 0.50 | 0.30 | 0.015 | 0.008 | |
| Embodiment 2 | 0.50 | 1.00 | 0.35 | 5.10 | 1.40 | 1.00 | 0.015 | 0.008 | |
| Embodiment 3 | 0.55 | 0.50 | 0.20 | 5.50 | 2.00 | 1.50 | 0.015 | 0.008 | |
| Embodiment 4 | 0.55 | 0.70 | 0.50 | 5.20 | 1.00 | 0.80 | 0.015 | 0.008 | |
| Embodiment 5 | 0.40 | 0.80 | 0.40 | 4.00 | 0.80 | 1.20 | 0.015 | 0.008 | |
| Embodiment 6 | 0.55 | 0.60 | 0.40 | 6.00 | 0.80 | 0.50 | 0.015 | 0.008 | |
| Comparative Examples | 0.45 | 0.30 | 0.30 | 4.10 | 1.40 | 0.25 | 0.015 | 0.008 |
Comparative Examples and difference of the present invention are: contain higher Ni element in the Comparative Examples material, Cr, Mo constituent content are lower, do not contain V element; Contain in the material of the present invention by higher Cr, Mo, V element, do not contain the Ni element.
Make flying shear blade of the present invention by following operational path:
Electrosmelting → external refining → ingot casting → esr → ingot casting → expansion hydrogen anneal process → forging → conditioning heat treatment (normalizing+Spheroidizing Annealing) → roughing → modified thermal treatment (primary quenching+high tempering) → semi-finishing → final thermal treatment (secondary quenching+one time low-temperaturetempering+secondary low-temperaturetempering) → precision work.
Concrete modified thermal treatment, final process of thermal treatment parameter are as shown in table 3.
Table 3 heat treatment process parameter
| Primary quenching | High tempering | Secondary quenching | A low-temperaturetempering | The secondary low-temperaturetempering | |
| Embodiment 1 | 930℃ | 730℃ | 1020℃ | 570℃ | 540℃ |
| Embodiment 2 | 940℃ | 740℃ | 1040℃ | 550℃ | 560℃ |
| Embodiment 3 | 950℃ | 750℃ | 1060℃ | 560℃ | 555℃ |
| Embodiment 4 | 945℃ | 745℃ | 1040℃ | 565℃ | 550℃ |
| Embodiment 5 | 938℃ | 742℃ | 1040℃ | 560℃ | 560℃ |
| Embodiment 6 | 942℃ | 740℃ | 1060℃ | 562℃ | 560℃ |
| Comparative Examples | 870℃ | 680℃ | 860℃ | 200℃ | 200℃ |
The blade of making according to present embodiment material and manufacturing process in kind uses on the machine, and be 3000 tons flying shear blade single mean life of Comparative Examples, and embodiment flying shear blade single reaches more than 6000 tons mean life.
Facts have proved, band steel crosscut flying shear blade of the present invention, be applicable to hot-rolled high-strength slab scale or double length shearing, for hot fine rolling crop flying shear machine good result of use is arranged also, also can be applicable to the crosscut flying shearing machine of cold rolled strip, also have promotional value and application prospect for non-ferrous metal band steel crosscut flying shearing machine.
Claims (4)
1. flying shear blade, its composition weight percent is:
C 0.40-0.70
Si 0.50-1.20
Mn 0.20-0.50
Cr 4.00-6.00
Mo 0.50-2.00
V 0.30-1.50
P ≤0.02
S ≤0.02
Surplus is Fe and inevitable impurity.
2. the manufacture method of a flying shear blade, it comprises the steps:
A) electrosmelting, ingot casting, its composition weight percent is:
C 0.40-0.70
Si 0.50-1.20
Mn 0.20-0.50
Cr 4.00-6.00
Mo 0.50-2.00
V 0.30-1.50
P ≤0.02
S ≤0.02
Surplus is Fe and inevitable impurity;
B) expand hydrogen anneal process, above-mentioned ingot casting is gone into stove → 880-920 ℃ of insulation → 700-740 ℃ of insulation → stove with≤400 ℃ be chilled to the 300-500 ℃ of air cooling of coming out of the stove;
C) forge, ingot casting is forged;
D) conditioning heat treatment is gone into stove → 850-880 ℃ of insulation → 700-740 ℃ of insulation → stove with the forging after the above-mentioned forging with≤400 ℃ and is chilled to the 300-500 ℃ of air cooling of coming out of the stove;
E) scale on surface etc. is removed in roughing;
F) modified thermal treatment, 930-950 ℃ of oil quenching+730-750 ℃ of high tempering;
G) semi-finishing is machined to basic size;
H) final thermal treatment, 1020-1060 ℃ oil quenching+550-570 ℃ low-temperaturetempering+540-560 ℃ of secondary low-temperaturetempering;
I) precision work is machined to specified dimension and precision, produces the flying shear blade finished product.
3. the manufacture method of flying shear blade as claimed in claim 2 is characterized in that: adopt external refining to water ingot casting again behind the step a electrosmelting.
4. the manufacture method of flying shear blade as claimed in claim 3 is characterized in that: adopt electroslag remelting process ingot casting again behind step a) electrosmelting, external refining, the ingot casting.
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| CNA2006101161186A CN101144140A (en) | 2006-09-15 | 2006-09-15 | Flying shear blade and preparation method thereof |
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