CN105240150A - Powder metallurgy engine front cover and manufacturing methods thereof - Google Patents
Powder metallurgy engine front cover and manufacturing methods thereof Download PDFInfo
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- CN105240150A CN105240150A CN201510671973.2A CN201510671973A CN105240150A CN 105240150 A CN105240150 A CN 105240150A CN 201510671973 A CN201510671973 A CN 201510671973A CN 105240150 A CN105240150 A CN 105240150A
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Abstract
The invention discloses a powder metallurgy engine front cover which is a disc-shaped component with a powder metallurgy part as the main part. The powder metallurgy engine front cover comprises a disc-shaped body. A center hole is formed in the center of a disc body of the body, and a chute is formed in the end face. The chute is in a J shape and is formed by an arc-shaped groove extending outwards along an arc line with the center of the center hole as a circle center. Furthermore, an improvement is characterized in that multiple process grooves arranged at intervals are formed in the outer wall of the disc body of the body. The invention further discloses three manufacturing methods of the powder metallurgy engine front cover. The powder metallurgy engine front cover is good in mechanical performance, and a sliding rod is in a self-locked state in the chute in the use process.
Description
Technical field
The present invention relates to a kind of engine front cover and manufacture method thereof, more particularly, the present invention relates to a kind of adopt powder metallurgy process to manufacture engine front cover and manufacture method.
Background technique
Powder metallurgy engine front cover, it is the disc-shaped component based on powder metallurgy, comprise disk-shaped main body, disk body center is provided with center hole, and end face is provided with chute, during use, slide bar slides in chute, the arc groove that chute in the engine front cover of prior art is is the center of circle with center hole center, in use, slide bar cannot be in self-locking state to this engine front cover in chute.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art, provide one can in use, slide bar can be in self-locking state powder metallurgy engine front cover in chute, in addition, present invention also offers the manufacture method of this protecgulum.
The present invention is achieved through the following technical solutions technical goal.
Powder metallurgy engine front cover, is the disc-shaped component based on powder metallurgy, comprises disk-shaped main body; The disk body center of described main body is provided with center hole, and end face is provided with chute; It is characterized in that: described chute is J type, being stretched out along circular arc line by the arc groove one end being the center of circle with center hole center forms.
In said structure, the external wall of described main body panel is along the circumferential direction provided with several spaced apart technology groove.
In said structure, described chute inwall is provided with wear-resistant composite bed.
In said structure, described wear-resistant composite bed be rare earth compound composite bed.
The manufacture method of above-mentioned powder metallurgy engine front cover has three kinds:
Method one, described powder metallurgy engine front cover formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, all the other are iron powder, and each component sum is 100 ﹪; Corresponding technique is green density 7.5g/cm3, and sintering temperature 1200 ~ 1240 DEG C, without temper, its yield strength is 575MPa, and tensile strength reaches 955MPa, and hardness is 98HRB, and impact toughness is 31.3J/cm
2.
Further improvement is, in above-mentioned formula, chromium and part iron reach part by weight by interpolation containing the subparticle Cr-Fe alloy powder that Mean particle diameter is 4.65 μm.
Method two, described powder metallurgy engine front cover formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, molybdenum disulfide 0.5 ﹪, rare-earth elements La 0.6%, all the other are iron powder, and each component sum is 100 ﹪; Corresponding technique is green density 7.5g/cm
3, sintering temperature 1200-1240 DEG C, without temper, its yield strength is 578MPa, tensile strength reaches 962MPa, hardness is 80-85HRA, impact toughness is 58J/cm
2.
Further improvement is, in above-mentioned formula, chromium and part iron reach part by weight by interpolation containing the subparticle Cr-Fe alloy powder that Mean particle diameter is 4.65 μm.
Method three, described powder metallurgy engine front cover formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, molybdenum disulfide 0.5 ﹪, rare-earth elements La 0.6%, boron 2, all the other are iron powder, each component sum is 100 ﹪, makes through batch mixing, compacting, sintering, heating, forge hot, postprocessing working procedures step.
The present invention compared with prior art, has following good effect:
1, chute is J type, and being stretched out along circular arc line by the arc groove one end being the center of circle with center hole center forms, and the present invention in use, when slide bar slides into outward extending one section of chute in chute, can be in self-locking state.
2, the external wall of main body panel is along the circumferential direction provided with several spaced apart technology groove, is convenient to assembling.
3, chute inwall is provided with wear-resistant composite bed, can significantly improve the wear resistance of chute.
4, the present invention's formula by weight, and nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, all the other are iron powder, and each component sum is 100 ﹪.Prepared sintered alloy is with compared with the matrix composition alloy Fe.1.75Ni.0.5Mo.1.5Cu.0.5C optimized, and yield strength improves 175MPa, tensile strength improves 355MPa, hardness improves 17HRB, impact toughness improves 5J/cm
2, solve preparation cost high problem when prior art improves sintered alloy obdurability.Prior art improves the problem of the measure of sintered alloy obdurability: add expensive alloying element Ni or Mo, increases the problem of cost of material; Adopt new compacting or sintering process usually to need new equipment, equipment investment is high: increase subsequent treatment process, then add the manufacture cycle, and cost is often higher.
5, the present invention's formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, molybdenum disulfide 0.5 ﹪, rare-earth elements La 0.6%, all the other are iron powder, and each component sum is 100 ﹪.Add rare-earth elements La in formula, the intensity of made powder metallurgy, impact toughness can be significantly improved; Add molybdenum disulfide, play good lubrication regulating action.Prepared sintered alloy yield strength improves 8MPa, and tensile strength improves 12MPa, and impact toughness improves 26.7J/cm
2, hardness is suddenlyd change to 80-85HRA from 98HRB.
6, the present invention's formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, molybdenum disulfide 0.5 ﹪, rare-earth elements La 0.6%, boron 2, all the other are iron powder, each component sum is 100 ﹪, prepared sintered alloy significantly improves decay resistance, extends more than one times working life.
7, the present invention's formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, all the other are iron powder, each component sum is 100 ﹪, in formula, chromium and part iron reach part by weight by interpolation containing the subparticle Cr-Fe alloy powder that Mean particle diameter is 4.65 μm, prepared sintered alloy tensile strength improves 257MPa, and hardness is suddenlyd change to 31HRC from 80-85HRA.
8, the present invention's formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, molybdenum disulfide 0.5 ﹪, rare-earth elements La 0.6%, all the other are iron powder, each component sum is 100 ﹪, in formula, chromium and part iron reach part by weight by interpolation containing the subparticle Cr-Fe alloy powder that Mean particle diameter is 4.65 μm, prepared sintered alloy tensile strength improves 253MPa, and hardness is suddenlyd change to 32HRC from 81-87HRA.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is the A-A rotation profile in Fig. 1.
Fig. 3 is I enlarged schematic partial view in Fig. 1.
Embodiment
Below in conjunction with embodiment, the invention will be further described.
Powder metallurgy engine front cover shown in the drawings is the disc-shaped component based on powder metallurgy, comprises disk-shaped main body 1; The disk body center of main body 1 is provided with center hole 1.2, and end face is provided with chute 1.1; Chute 1.1, in J type, to be stretched out along circular arc line by the arc groove 1.1.1 one end being the center of circle with center hole 1.2 center and forms; In the present embodiment, chute 1.1 inwall is provided with wear-resistant composite bed 2, and wear-resistant composite bed 2 is rare earth compound composite bed.
Main body 1 disk body outer wall is along the circumferential direction provided with 2-6 spaced apart technology groove 1.3.
Embodiment prepared by main body 1 material of the present invention is as follows:
Embodiment 1:
By weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, all the other are iron powder, and each component sum is 100 ﹪; Corresponding technique is green density 7.5g/cm3, and sintering temperature 1200 ~ 1240 DEG C, without temper.
After testing, the yield strength of made sintered alloy is 575MPa, and tensile strength reaches 955MPa, and hardness is 98HRB, and impact toughness is 31.3J/cm
2.
Embodiment 2:
During embodiment 1 fills a prescription, chromium and part iron reach part by weight by interpolation containing the subparticle Cr-Fe alloy powder that Mean particle diameter is 4.65 μm.
After testing, the tensile strength of made sintered alloy reaches 1212MPa, and hardness is 31HRC.
Embodiment 3:
By weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, molybdenum disulfide 0.5 ﹪, rare-earth elements La 0.6%, all the other are iron powder, and each component sum is 100 ﹪; Corresponding technique is green density 7.5g/cm
3, sintering temperature 1200-1240 DEG C, without temper.
After testing, the yield strength of made sintered alloy is 578MPa, tensile strength reaches 962MPa, hardness is 80-85HRA, impact toughness is 58J/cm
2.
Embodiment 4:
During embodiment 3 fills a prescription, chromium and part iron reach part by weight by interpolation containing the subparticle Cr-Fe alloy powder that Mean particle diameter is 4.65 μm.
After testing, the tensile strength of made sintered alloy reaches 1215MPa, and hardness is 32HRC.
Embodiment 5:
By weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, molybdenum disulfide 0.5 ﹪, rare-earth elements La 0.6%, boron 2, all the other are iron powder, each component sum is 100 ﹪, makes through batch mixing, compacting, sintering, heating, forge hot, postprocessing working procedures step.
After testing, the yield strength of made sintered alloy is 577MPa, tensile strength reaches 961MPa, hardness is 81-87HRA, impact toughness is 58J/cm
2, reach 2 years working life.
Claims (9)
1. a powder metallurgy engine front cover is the disc-shaped component based on powder metallurgy, comprises disk-shaped main body (1); The disk body center of described main body (1) is provided with center hole (1.2), and end face is provided with chute (1.1); It is characterized in that: described chute (1.1) in J type, by being that arc groove (1.1.1) one end in the center of circle to stretch out along circular arc line and forms with center hole (1.2) center.
2. powder metallurgy engine front cover according to claim 1, is characterized in that: described main body (1) disk body outer wall is along the circumferential direction provided with several spaced apart technology groove (1.3).
3. powder metallurgy engine front cover according to claim 1 and 2, is characterized in that: described chute (1.1) inwall is provided with wear-resistant composite bed (2).
4. powder metallurgy engine front cover according to claim 3, is characterized in that: described wear-resistant composite bed (2) are rare earth compound composite bed.
5. the manufacture method of the powder metallurgy engine front cover that one of claim 1 ~ 2 is described, it is characterized in that: described powder metallurgy engine front cover formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, all the other are iron powder, and each component sum is 100 ﹪; Corresponding technique is green density 7.5g/cm
3, sintering temperature 1200 ~ 1240 DEG C, without temper, its yield strength is 575MPa, and tensile strength reaches 955MPa, and hardness is 98HRB, and impact toughness is 31.3J/cm
2.
6. the manufacture method of the powder metallurgy engine front cover that one of claim 1 ~ 2 is described, it is characterized in that: described powder metallurgy engine front cover formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, molybdenum disulfide 0.5 ﹪, rare-earth elements La 0.6%, all the other are iron powder, and each component sum is 100 ﹪; Corresponding technique is green density 7.5g/cm
3, sintering temperature 1200-1240 DEG C, without temper, its yield strength is 578MPa, tensile strength reaches 962MPa, hardness is 80-85HRA, impact toughness is 58J/cm
2.
7. the manufacture method of the powder metallurgy engine front cover that one of claim 1 ~ 2 is described, it is characterized in that: described powder metallurgy engine front cover formula by weight, nickel powder 1.75, molybdenum powder 0.5, copper powder 1.5, chromium powder 1.7, manganese powder 1.0, plumbago 0.8, cerium dioxide 0.2, zine stearate 0.05 ﹪, molybdenum disulfide 0.5 ﹪, rare-earth elements La 0.6%, boron 2, all the other are iron powder, each component sum is 100 ﹪, makes through batch mixing, compacting, sintering, heating, forge hot, postprocessing working procedures step.
8. the manufacture method of powder metallurgy engine front cover according to claim 5, is characterized in that: in described formula, chromium and part iron reach part by weight by interpolation containing the subparticle Cr-Fe alloy powder that Mean particle diameter is 4.65 μm.
9. the manufacture method of powder metallurgy engine front cover according to claim 6, is characterized in that: in described formula, chromium and part iron reach part by weight by interpolation containing the subparticle Cr-Fe alloy powder that Mean particle diameter is 4.65 μm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510671973.2A CN105240150A (en) | 2015-10-19 | 2015-10-19 | Powder metallurgy engine front cover and manufacturing methods thereof |
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| CN201510671973.2A CN105240150A (en) | 2015-10-19 | 2015-10-19 | Powder metallurgy engine front cover and manufacturing methods thereof |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105736575A (en) * | 2016-04-20 | 2016-07-06 | 广东美芝制冷设备有限公司 | Compressor bearing and manufacturing method thereof |
| CN110382144A (en) * | 2017-03-09 | 2019-10-25 | Gkn烧结金属有限公司 | Form the method with the powder metal insert of horizontal through hole |
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| JPS5844140B2 (en) * | 1978-07-11 | 1983-10-01 | 大豊工業株式会社 | Composite sliding material |
| CN1090017A (en) * | 1993-01-12 | 1994-07-27 | 李玉堂 | Internal combustion engine |
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| CN105736575A (en) * | 2016-04-20 | 2016-07-06 | 广东美芝制冷设备有限公司 | Compressor bearing and manufacturing method thereof |
| CN110382144A (en) * | 2017-03-09 | 2019-10-25 | Gkn烧结金属有限公司 | Form the method with the powder metal insert of horizontal through hole |
| CN110382144B (en) * | 2017-03-09 | 2022-02-22 | Gkn烧结金属有限公司 | Method of forming a powder metal insert with horizontal through holes |
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