CN102049462A - Improved structure of forging machine tool C-shaped body - Google Patents
Improved structure of forging machine tool C-shaped body Download PDFInfo
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- CN102049462A CN102049462A CN 201010545479 CN201010545479A CN102049462A CN 102049462 A CN102049462 A CN 102049462A CN 201010545479 CN201010545479 CN 201010545479 CN 201010545479 A CN201010545479 A CN 201010545479A CN 102049462 A CN102049462 A CN 102049462A
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Abstract
A working mechanism cantilever consisting of a crank, a connecting rod and a sliding block, as well as an upper die and a lower die on an open type pressing machine can enter a working region from three directions in front of the C-shaped body, thus the great convenience is brought for the operator. But, the C-shaped structure causes the defects of poor rigidity of the machine body, especially large angular deformation, reduced accuracy, shortened service life of the dies and the sliding block as well as a guide rail, and the like. The invention is characterized in that a base part [10] for fixing the guide rail on an upper machine body [8-1] is separated from the upper machine body [8-1], the separated base part [10] extends backwards and downwards on the outer side of the upper machine body [8-1] to form a support plate [12], and the upper plate [12] and a side plate [14] of a lower machine body [8-2] are made into a whole. Therefore, when the open type pressing machine bears working pressure, the upper die can not generate angular deformation relative to the lower die, thus the defects are thoroughly eliminated. The invention can maintain the advantage of convenient operation of the open type pressing machine and has the advantage of high accuracy of a closed type pressing machine. Moreover, by the invention, the working property of the open type pressing machine can be improved and the manufacture cost of the open type pressing machine can be lowered.
Description
One. technical field
The present invention relates to the C type airframe structure of forging machine tool, particularly gap-framepress.
Two. background technology
The fuselage of some forging machine tool is the C font structure, the fuselage [8] of wherein most typical gap-framepress (generally being punch press again) as shown in Figure 1a.By crank [1], connecting rod [2], slide block [3], be installed in the patrix [4] on the slide block [3] and be installed in this operating mechanism's cantilever that the counterdie [5] on the workbench [6] formed in the place ahead of fuselage [8], operating personnel can be from a front A and a left side, right two sides B, three directions of C enter operation interval, this is for the mounting or dismounting and the adjustment of mould, the sending to and taking out of workpiece, the adjusting of guide clearance and mechanization, the installation of automatic feeding device and use, all bring great convenience, so, aspect middle-size and small-size forcing press, with respect to the straight side press that can only enter operation interval from former and later two directions, gap-framepress has obtained to use more widely.But, the fuselage of this C type cantilever design has also brought serious problems to gap-framepress, be exactly forcing press when bearing operating pressure, frame deflection is big, rigidity is poor, and particularly the angular deformation that fuselage is very big will have influence on the wearing and tearing of forcing press precision, die life and slide block, guide rail.
As shown in Figure 1a, gap-framepress is before starting working, and operating personnel adjust the gap of patrix [4] and counterdie [5], makes around it gap even, before the δ=δ after.But, shown in Fig. 1 b, after forcing press is started working, patrix [4] and counterdie [5] be subjected to operating pressure P, fuselage [8] will produce vertical deformation Δ h on the one hand, fuselage [8] also will produce angular deformation on the other hand, and this angular deformation is divided into two parts: fuselage [8] top produces angular deformation α upwards
On, fuselage [8] bottom produces downward angular deformation α
Down, theoretical research and experiment all show: the neutral surface that does not produce angular deformation is near the X-X of workbench horizontal direction face, and just neutral surface X-X is divided into upper fuselage [8-1] and lower fuselage [8-2] two parts with fuselage [8].Shown in Fig. 1 c, when work will finish, this angular deformation was more and more serious, and upper fuselage [8-1] and crank [1] and connecting rod [2] mounted thereto all will produce angular deformation α upwards
OnAnd slide block [3] slides up and down in guide rail [11], and guide rail [11] is to be screwed on the base [10] that is made of one with upper fuselage [8-1], so base [10], guide rail [11], slide block [3] and patrix [4] all will follow upper fuselage [8-1] to produce angular deformation α
OnLower fuselage [8-2] and counterdie [5] then will produce downward angular deformation α
DownLike this, patrix [4] is with respect to total angular deformation α of counterdie [5]
Always=α
On+ α
DownAlso increasing, this will bring following defective to the work of forcing press:
1. reduced the forcing press precision, made the gap, front and back of upper die and lower die inhomogeneous, δ
Before≠ δ
After, so that workpiece produces deviation and burr, just reduced the precision of workpiece;
2. produce the lateral pressure of horizontal direction on patrix, upper die and lower die are come in contact even collide, acceleration die wear even fracture has reduced die life;
3. the wearing and tearing of slide block and guide rail have been quickened.
Since 19th-century occur latter stage gap-framepress 100 for many years, people have found its these defectives for a long time, and have designed some and improved structures, but all thoroughly do not deal with problems:
1. be early stage improvement structure shown in Fig. 2 a, between the upper end and workbench of the both sides, front of gap-framepress, fuselage, install two pull bars additional, to reduce angular deformation.Producing effect really of this, still, the existence of two pull bars is got in the way, and operates very inconveniently, and two pull bars are often dismantled in actual the use.So this structure is eliminated already.
2. the improvement structure shown in Fig. 2 b, Fig. 2 c is to add pull bar in the fuselage inboard, because pull bar is in the back of fuselage Center of Pressure line, so the effect of doing like this is also not obvious, and will increase manufacturing cost, so, do not obtain to use.
3. be the structure that generally adopts at present shown in Fig. 2 d, strengthen the appearance and size and the cross sectional dimensions of fuselage exactly, increase the weight of fuselage, to reduce the angular deformation of fuselage.So, the profile of fuselage has become " C " font of capitalization by " c " font of small letter, even has become " П " font fuselage shown in Fig. 2 e.Recently, many scholars adopt the fuselage of FInite Element opposite opened forcing press to carry out a large amount of analysis and research, and the shape of cross section of fuselage carried out optimizing (lightweight) design, improving to some extent really of fuselage appearance that these researchs and design blindly strengthened the past and cross section, fuselage weight alleviates to some extent, and angular deformation reduces to some extent.But, thoroughly do not eliminate the angular deformation of patrix, and will increase many manufacturing costs, so this neither optimal structure with respect to counterdie.
4. do not solve the problem of angular deformation fully just because of increasing fuselage, optimal design, so, so-called half-closed fuselage shown in Fig. 2 f had appearred again afterwards, the biside plate of its operation interval forward, extend downwards, fuse with workbench, perhaps between both sides, front, fuselage upper end and the workbench of forcing press, install reinforced door or lath additional, form " O " font or be " D " fuselage of font, its purpose just in order to reduce the angular deformation of fuselage, improves the precision of forcing press.But the result who does like this is just as the structure shown in Fig. 2 a, operates very inconveniently, weakened the superiority of gap-framepress greatly.
From having detail file and the half-closed fuselage product on the domestic and international gap-framepress product sample now, the angular deformation of C type fuselage still exists for the influence of its service behaviour (particularly die life), have to adopt half-closed fuselage in order to eliminate this influence, this angular deformation problem that proves absolutely present gap-framepress does not thoroughly solve.
Three. summary of the invention
The objective of the invention is: under the situation that does not increase manufacturing cost, eliminate the angular deformation of patrix,, improve the service behaviour of gap-framepress to overcome above-mentioned many disadvantages with respect to counterdie.
As everyone knows, it is always inevitable that the C type fuselage of cantilever design will produce angular deformation after bearing operating pressure.With the method that installs pull bar additional or gain in weight come " pressures " it indeformable be worthless, scientific methods is to change airframe structure, when fuselage generation angular deformation, " avoiding " it to upper and lower mould generation angular deformation.
Shown in Fig. 1 c, the lower end of the connecting rod [2] that is connected with slide block [3] is sphere or the face of cylinder [13], when upper fuselage [8-1] and crank [1] mounted thereto and connecting rod [2] produce upwards angular deformation, connecting rod [2] will rotate around sphere or the face of cylinder [13] of its lower end, so connecting rod [2] can not drive slide block [3] and angular deformation takes place patrix [4]; Drive that angular deformation takes place slide block [3] and patrix [4] be fixed guide [11], also and the base [10] that is made of one of upper fuselage [8-1].Design of the present invention is: the targeting part and the part of the force of fuselage is separated, just that this part of base of fixed guide on the upper fuselage is separated with upper fuselage, make the base portion that splits extend to form support plate backward, downwards in the outside or the inboard of fuselage again, the side plate of this support plate and lower fuselage or workbench back, following web are made of one.So, as shown in Figure 3, when gap-framepress bears operating pressure, though upper fuselage [8-1] will produce angular deformation α upwards
On, but because the base portion [10] of fixed guide [11] is separated with upper fuselage [8-1], so, can not drive slide block [3] and patrix [4] angular deformation takes place; Though lower fuselage [8-2] and counterdie [5] will produce downward angular deformation α
DownBut, the support plate [12] that has base [10] is made of one because being side plate [14] with lower fuselage [8-2], so, be fixed on guide rail [11] and the slide block [3] in the guide rail [11] on the base [10] and be contained in patrix [4] on the slide block [3] and all will follow lower fuselage [8-2] to produce same downward angular deformation α
DownConsequently patrix [4] does not produce angular deformation with respect to counterdie [5], so the present invention has: 1. improve the forcing press precision; 2. improve die life; 3. improve the advantages such as friction durability of slide block, guide rail.The present invention has creatively solved gap-framepress existing aforementioned disadvantages over more than 100 year with so simple method.
At present, when the fuselage of design gap-framepress, carry out intensitometer earlier and calculate, and then carry out rigidity and veritify.Do not but research and experiment illustrate at present: in order thoroughly to overcome the above-mentioned defective that the fuselage angular deformation is brought, will get great angular rigidity actually and be only rational angular rigidity? the national standard that does not also have at present angular rigidity.So, in actual design,, just blindly strengthening the appearance and size and the cross sectional dimensions of fuselage in order to improve the angular rigidity of gap-framepress, the allowable stress of material is all obtained lower, so that has wasted lot of materials.In airframe structure of the present invention, because the angular deformation that fuselage produces can not make patrix produce angular deformation with respect to counterdie, therefore, in calculating, the intensity of fuselage do not carry out the veritification of angular rigidity again, under the prerequisite that guarantees the necessary requirement of strength of fuselage, can improve the allowable stress of material, dwindle the profile and the sectional dimension of fuselage, little " c " font fuselage before getting back to really makes the fuselage lightweight, and the material of being saved will be more than the material of support plate described in the present invention, so, adopt airframe structure of the present invention, not only can improve the service behaviour of gap-framepress, but also can reduce the manufacturing cost of forcing press.
Past is generally all thought: the shortcoming of straight side press is to enter operation interval from former and later two directions, and inconvenient operation, its advantage are the stiffness of fuselage height, and the forcing press precision is good, is mainly used on the big-and-middle-sized forcing press; And gap-framepress is on the contrary, and its advantage is to enter operation interval from three directions, and operation is very convenient, and its shortcoming is that frame deflection is big, and particularly angular deformation makes the precision of forcing press reduce, and is mainly used on the middle-size and small-size forcing press.Now, the present invention can eliminate the shortcoming that the gap-framepress precision reduces, and keep its easy to operate advantage, so, adopt patented technology of the present invention, can enlarge and be applied on the big-and-middle-sized forcing press, particularly change medium-sized straight side press into gap-framepress, improve its serviceability and productivity ratio greatly, will be subjected to users' welcome.
The above is for gap-framepress, and patented technology of the present invention also is same practical for other forging machine tools with C type fuselage.
This shows, adopt patent of the present invention,, 1. can reduce production costs for manufacturer; 2. can improve the technology gold content of product, just improve the product brand popularity and strengthen the market competitiveness; 3. the easy to operate and good advantage of straight side press precision of gap-framepress ideally can be combined, the art of this patent is extended to big-and-middle-sized forcing press, further enlarges occupation rate of market.For the user, 1. can improve die life; 2. can improve the stamping parts quality; 3. can improve the service life of slide block guide rail.
Four. description of drawings
Fig. 1 a is that the gap-framepress former mould of starting working is adjusted situation.
Fig. 1 b is that gap-framepress is subjected to the situation that operating pressure produces angular deformation later on.
Fig. 1 c is the angular deformation situation of gap-framepress work upper die and lower die will finish the time.
Fig. 2 is the existing various improvement structures of gap-framepress.
Fig. 3 is conception plans figure of the present invention.
Fig. 4 is the 1st embodiment of the present invention.
Fig. 5 is the 2nd embodiment of the present invention.
Fig. 6 is the 3rd embodiment of the present invention
Fig. 7 is the 4th embodiment of the present invention.
Five. the specific embodiment
The 1st embodiment such as Fig. 4 and shown in Figure 3, this part of base [10] that upper fuselage [8-1] is gone up fixed guide [11] is separated with upper fuselage [8-1], make the base portion [10] that splits behind the lateral of upper fuselage [8-1], extend to form support plate [12] downwards again, the side plate [14] of this support plate [12] and lower fuselage [8-2] is made of one.So, when gap-framepress bears operating pressure, though upper fuselage [8-1] will produce angular deformation α upwards
On, but because the base portion [10] of fixed guide [11] is separated with upper fuselage [8-1], so, can not drive slide block [3] and patrix [4] upwards angular deformation α takes place
OnThough lower fuselage [8-2] and counterdie [5] will produce downward angular deformation α
Down, produce same downward angular deformation α but also will drive side plate [14], support plate [12], base [10], guide rail [11] and the slide block [3] and the patrix [4] that are made of one with lower fuselage [8-2] simultaneously
DownConsequently patrix [4] does not produce angular deformation with respect to counterdie [5].
The 2nd embodiment such as Fig. 5 and shown in Figure 3, this part of base [10] that upper fuselage [8-1] is gone up fixed guide [i1] is separated with upper fuselage [8-1], make the base portion [10] that splits extend to form support plate [12] backward, downwards in the inboard of upper fuselage [8-1] again, the web [9] of this support plate [12] and workbench [6] back is made of one.Equally, when gap-framepress bears operating pressure, though upper fuselage [8-1] will produce angular deformation α upwards
On, but because the base portion [10] of fixed guide [11] is separated with upper fuselage [8-1], so, can not drive slide block [3] and patrix [4] upwards angular deformation α takes place
OnThough lower fuselage [8-2] and counterdie [5] will produce downward angular deformation α
Down, produce same downward angular deformation α but also will drive web [9], support plate [12], base [10], guide rail [11] and the slide block [3] and the patrix [4] that are made of one with lower fuselage [8-2] simultaneously
DownConsequently patrix [4] does not produce angular deformation with respect to counterdie [5].
The 3rd embodiment such as Fig. 6 and shown in Figure 3, this part of base [10] that upper fuselage [8-1] is gone up fixed guide [11] is separated with upper fuselage [8-1], make the base portion [10] that splits extend to form support plate [12] backward, downwards again in the inboard of upper fuselage [8-1], if there is web [9] workbench [6] back, then the hole [15], the web [16] below workbench [6] that pass on the web [9] of workbench [6] back of this support plate [12] is made of one; If workbench [6] back does not have web [9], then this support plate [12] web [16] direct and that workbench [6] is following is made of one; Equally, when gap-framepress bears operating pressure, though upper fuselage [8-1] will produce angular deformation α upwards
On, but because the base portion [10] of fixed guide [11] is separated with upper fuselage [8-1], so, can not drive slide block [3] and patrix [4] upwards angular deformation α takes place
OnThough lower fuselage [8-2] and counterdie [5] will produce downward angular deformation α
Down, produce same downward angular deformation α but also will drive following web [16], support plate [12], base [10], guide rail [11] and the slide block [3] and the patrix [4] that are made of one with lower fuselage [8-2] simultaneously
Down, consequently patrix [4] does not produce angular deformation with respect to counterdie [5].
The 4th embodiment such as Fig. 7 and shown in Figure 3, this part of base [10] that upper fuselage [8-1] is gone up fixed guide [11] is separated with upper fuselage [8-1], make the base portion [10] that splits extend to form support plate [12] backward, downwards again in the inboard of upper fuselage [8-1], if workbench [6] back have web [9], below web [16] is arranged, then this support plate [12] passes hole [15] on workbench [6] the back web [9] and the hole [17] on the following web [16], is made of one with the bottom surface of workbench [6]; If workbench [6] back do not have web [9], below do not have web [16], then this support plate [12] directly and the bottom surface of workbench [6] be made of one.Equally, when gap-framepress bears operating pressure, though upper fuselage [8-1] will produce angular deformation α upwards
On, but because the base portion [10] of fixed guide [11] is separated with upper fuselage [8-1], so, can not drive slide block [3] and patrix [4] upwards angular deformation α takes place
OnThough lower fuselage [8-2] and counterdie [5] will produce downward angular deformation α
Down, produce same downward angular deformation α but also will drive workbench [6], support plate [12], base [10], guide rail [11] and the slide block [3] and the patrix [4] that are made of one with lower fuselage [8-2] simultaneously
Down, consequently patrix [4] does not produce angular deformation with respect to counterdie [5].
Six. list of references
1. what moral is praised " crank press " China Machine Press in 1987
2. Jiangsu YangLi Group Co.,Ltd's 200820186011.3 press frame bodies
3. Jiangsu YangLi Group Co.,Ltd's 200820160333.0 gap-framepress fuselage lateral plate structures
4. the reinforcement fuselage of 200720044057.7 1 kinds of forcing presses of Yangzhou Forging Machine-Tools Co., Ltd.
5. Jiangsu YangLi Group Co.,Ltd's 200520073008.7 half-closed hydropress frames
6. Jiangsu YangLi Group Co.,Ltd's 200520073007.2 half-closed hydropress frame interior plates
7. Jiangsu YangLi Group Co.,Ltd's 200520073006.8 frame-type hydropress frames
8. the finite element analysis and 2009 12 phases of optimal design " machinery " of JG21-250A type press frame such as Zhang Peng
9. 2008 29 4 phases of volume of the optimal design " coal mine machinery " of JG21-250A gap-framepress fuselage such as model sky
10. father-in-law Ji Zhao hydraulic press primary structure design optimization and experimental study " Guangdong University of Technology " Master's thesis are 2008
11. 2008 35 04 phases of volume of the optimal design " machinery " of JM21-200 ton gap-framepress fuselages such as model sky
12. refined 2006 35 05 phases of volume of finite element analysis " machine-building and automation " of waiting JH21-160 gap-framepress fuselage of Li Jun
13. the research of 160 tons of C types of the luxuriant grade of Chen Song press frame finite element analysis " second the advanced Technology of Plastic Processing Conference Papers of global Chinese collection " 2005
14. the finite element analysis of ancestral's virtue gap-framepress fuselage and optimal design Southeast China University Master's thesis thereof 2004
15. open lightening design research of openback press frame such as Zu Fang " forging and pressing equipment and manufacturing technology " 03 phase in 2003
16. the mechanical modeling of Li Ying JZ21 type gap-framepress airframe structure and optimization thereof " forging and pressing equipment and manufacturing technology " 03 phase in 2003
17. sternly celebrate C shape multi-point forming hydropress frame structural finite element analysis and 2002 3 phases of optimal design " metal forming machinery " such as light
18. gap-framepress lathe bed finite element analysis such as Shi Bao army and structure optimization " mechanics with put into practice " 3 phases in 2000
19. JL21 such as king's bowling series press frame intensity and toughness calculates and " metal forming machinery " 1999 4 phases of analysis
20. the great grade of surplus generation is also talked 1996 3 phases of optimal design " metal forming machinery " in gap-framepress fuselage cross section
21. 1992 4 phases of Liu Yao army gap-framepress fuselage section optimal design " metal forming machinery "
22. the optimization of gap-framepress fuselage main cross sections such as Yang Jin light and eight node isoparametric elements were calculated second nd Annual Meeting collection 1985
23. the strong rigidity test report of Shanghai second Casting Machine Tools Plant J31-160 press 1973
24. forging press factory, Tsing-Hua University Beijing
J23-80 open type double-column inclinable press major part intensity and toughness test 1973
25. the rigidity research of open-type inclinable presses such as Jinan Casting And Forging Machinery Research Institute 1964
26. Cai plays the rigidity of open-type inclinable presses such as state and improves the preliminary discussion 1963 of measure
27. Xiao Song industrial machine (Shanghai) Co., Ltd. product sample
28. Jinfeng's product sample
29. association is scientific and technological smart machine (China) Co., Ltd product sample easily
30. Yang Li group product sample
31. Yangzhou Forging Machine-Tools Co., Ltd.'s product sample
32. Xuzhou forging machine tool Group Co.,Ltd product sample
33. Guangdong forging machine tool Co., Ltd product sample
34. Zhejiang metal forming machinery group company product sample
35. Shanghai second Casting Machine Tools Plant product sample
Claims (4)
1. forging machine tool with C type airframe structure, it is characterized in that: the base portion [10] that upper fuselage [8-1] is gone up fixed guide [11] is separated with upper fuselage [8-1], make the base portion [10] that splits behind the lateral of upper fuselage [8-1], extend to form support plate [12] downwards again, the side plate [14] of this support plate [12] and lower fuselage [8-2] is made of one.
2. forging machine tool with C type airframe structure, it is characterized in that: the base portion [10] that upper fuselage [8-1] is gone up fixed guide [11] is separated with upper fuselage [8-1], make the base portion [10] that splits extend to form support plate [12] backward, downwards in the inboard of upper fuselage [8-1] again, the web [9] of this support plate [12] and workbench [6] back is made of one.
3. forging machine tool with C type airframe structure, it is characterized in that: the base portion [10] that upper fuselage [8-1] is gone up fixed guide [11] is separated with upper fuselage [8-1], make the base portion [10] that splits extend to form support plate [12] backward, downwards again in the inboard of upper fuselage [8-1], if there is web [9] workbench [6] back, then the hole [15], the web [16] below workbench [6] that pass on the web [9] of workbench [6] back of this support plate [12] is made of one; If workbench [6] back does not have web [9], then this support plate [12] web [16] direct and that workbench [6] is following is made of one;
4. forging machine tool with C type airframe structure, it is characterized in that: the base portion [10] that upper fuselage [8-1] is gone up fixed guide [11] is separated with upper fuselage [8-1], make the base portion [10] that splits extend to form support plate [12] backward, downwards again in the inboard of upper fuselage [8-1], if workbench [6] back have web [9], below web [16] is arranged, then this support plate [12] passes hole [15] on the web [9] of workbench [6] back and the hole [17] on the following web [16], is made of one with the bottom surface of workbench [6]; If workbench [6] back do not have web [9], below do not have web [16], then this support plate [12] directly and the bottom surface of workbench [6] be made of one.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102241146A (en) * | 2011-05-17 | 2011-11-16 | 昆山市人人发机械五金有限公司 | Punching machine facilitating mounting of punching mold |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102241146A (en) * | 2011-05-17 | 2011-11-16 | 昆山市人人发机械五金有限公司 | Punching machine facilitating mounting of punching mold |
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Application publication date: 20110511 |