CN201338066Y - Frame of hot die forging press - Google Patents
Frame of hot die forging press Download PDFInfo
- Publication number
- CN201338066Y CN201338066Y CNU2009201048642U CN200920104864U CN201338066Y CN 201338066 Y CN201338066 Y CN 201338066Y CN U2009201048642 U CNU2009201048642 U CN U2009201048642U CN 200920104864 U CN200920104864 U CN 200920104864U CN 201338066 Y CN201338066 Y CN 201338066Y
- Authority
- CN
- China
- Prior art keywords
- frame
- forging press
- fuselage
- hotdie forging
- hotdie
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model relates to a frame of a hot die forging press, which can be widely used in the hot die forging press. The frame comprises a hollow and integrally cast body; wherein a plurality of pull rod holes are arranged in the body; a pull rod which is provided with screw thread at both ends is arranged in the pull rod hole; and a nut is arranged on the screw thread section of the pull rod and is closely crimped on the body. The frame of the hot die forging press has the characteristics of light weight, high intensity, good rigidity, good damping performance, improved machining precision of forgings, long service life, low manufacturing cost and the like.
Description
Technical field
The utility model relates to a kind of frame of hotdie forging press, and this kind frame can be widely used in the hotdie forging press.
Background technology
The frame of existing hotdie forging press, the casting fuselage rack construction that generally adopts split casting fuselage frame or unitary solid to cast.
The fuselage frame of split casting mainly relies on the prestressing force of pull bar that the split fuselage is connected as a single entity, split air conditioner experience pull bar static pressure and shorten, be mainly bearing strain.When work, the tension of fuselage all concentrates on the pull bar that connects fuselage, makes its stress deformation, produces strain, and this elasticity hands over the size of shape then directly to affect the operating accuracy of equipment.Because the cross-sectional area of pull bar is subjected to fuselage endoporus and the restriction of self, be difficult to strengthen rigidity, the problem of bringing is that the attack precision of complete machine is not high.If pull bar adopts high-strength material, only can improve the intensity of pull bar, and cross-sectional area can not strengthen, therefore, the rigidity of fuselage just can not be significantly improved: if strengthen the cross-sectional area of fuselage, then bring cost and weight to increase greatly, cause very big waste.
And the integral body frame of solid casting though its strength and stiffness all improve a lot, can go out first massive casting parts, makes that the casting difficulty of frame strengthens, weight increases, the problems such as whole cost raising of frame.
The utility model content
The purpose of this utility model is to overcome defective of the prior art, provides that a kind of in light weight, intensity is big, good rigidly, forging precision height, damping property are good, the frame of the hot forging village power machine of long service life.
For achieving the above object, the technical solution of the utility model is to adopt a kind of frame of hotdie forging press, comprise hollow integral casting fuselage, in described fuselage, be provided with several tie rod holes, the pull bar of TBE (threaded both ends) is installed in described tie rod hole, on the thread segment of described pull bar nut is housed, described nut tightly is crimped on the described fuselage.
Wherein, described fuselage is left and right symmetrical structure.
Wherein, the cross section of described fuselage is rectangular, and going up of described rectangle is following for connecting gusset, and the limit, the left and right sides of described rectangle is the pressure-bearing limit.
Wherein, the vertical projection of described connection gusset is trapezoidal shape.
Wherein, on described pressure-bearing limit, be provided with laterally and/or through hole longitudinally.
Wherein, described tie rod hole is arranged on the intersection point place of described rectangle.
Wherein, be provided with supporting surface, between described supporting surface and described fuselage, be connected with reinforcement at an end of described fuselage.
Wherein, two its longitudinal projections were trapezoidal shape about described supporting surface was divided into.
Wherein, described fuselage is ironcasting or is steel-casting.
Advantage of the present utility model and beneficial effect are, the frame of this hotdie forging press adopts hollow-core construction and monoblock cast fuselage to add the prestressed draw-bar structure, with pre-tightening apparatus fuselage is carried out pretension, pull bar had both been strengthened the intensity of fuselage, strengthened the loaded area of fuselage again, therefore, frame strength and rigidity have all obtained reinforcement, can improve the machining accuracy of forging, alleviate the weight of frame simultaneously.This hot die forging press frame owing to adopted the cast-in-block fuselage, also has the good reduction noise and the performance of vibration damping, thereby has prolonged the service life of forcing press and mould in addition.
In sum, the frame of the utility model hotdie forging press has in light weightly, and intensity is big, good rigidly, and damping property is good, can improve the machining accuracy of forging, long service life, characteristics such as low cost of manufacture.
Description of drawings
Fig. 1 is the structural representation of the frame of the utility model hotdie forging press;
Fig. 2 be among Fig. 1 A-A to cutaway view.
Among the figure: 1, fuselage; 2, tie rod hole; 3, pull bar; 4, nut; 5, connect gusset; 6, pressure-bearing limit; 7, through hole; 8, supporting surface; 9, reinforcement.
The specific embodiment
Below in conjunction with drawings and Examples, the specific embodiment of the present utility model is further described.Following examples only are used for the technical solution of the utility model more clearly is described, and can not limit protection domain of the present utility model with this.
As attached illustrated in figures 1 and 2, the concrete technical scheme of implementing of the utility model is:
The utility model is a kind of frame of hotdie forging press, this frame comprises the fuselage 1 that adopts the casting of hollow integral forging type, in described fuselage 1, be provided with 4 tie rod holes 2, the pull bar 3 of TBE (threaded both ends) is installed in described tie rod hole 2, nut 4 is housed on the thread segment of described pull bar 3, described nut 4 can be crimped on the described fuselage 1 tightly, and described pull bar 3 and the pressure that described nut 4 cooperatively interacts and produced have constituted preload pressure in described fuselage 1.
In the present embodiment, preferable technical scheme is that described fuselage 1 is designed to left and right symmetrical structure.
In the present embodiment, preferable technical scheme is that the cross section with described fuselage 1 is designed to rectangle, and wherein, going up of described rectangle is following for connecting gusset 5, and the limit, the left and right sides of described rectangle is the pressure-bearing limit 6 of fuselage 1.
In the present embodiment, preferable technical scheme is described connection gusset 5 to be designed to vertical projection be trapezoidal structure.
In the present embodiment, on described pressure-bearing limit 6, be provided with laterally and/or through hole 7 longitudinally.
In the present embodiment, preferable technical scheme is the intersection point place that described tie rod hole 2 is arranged on described rectangle.
In the present embodiment, preferable technical scheme is that the end at described fuselage 1 is provided with supporting surface 8, is connected with reinforcement 9 between described supporting surface 8 and described fuselage 1.
In the present embodiment, preferable technical scheme be described supporting surface 8 minutes design is become about two, and its longitudinal projection is trapezoidal structure.
In the present embodiment, described fuselage 1 is ironcasting or is steel-casting.
The advantage of present embodiment and being, the frame of this hotdie forging press adopts hollow-core construction and monoblock cast fuselage to add the prestressed draw-bar structure, with pre-tightening apparatus fuselage is carried out pretension, pull bar had both been strengthened the intensity of fuselage, strengthened the loaded area of fuselage again, therefore, frame strength and rigidity have all obtained reinforcement, can improve the machining accuracy of forging, alleviate the weight of frame simultaneously.This hot die forging press frame owing to adopted the cast-in-block fuselage, also has the good reduction noise and the performance of vibration damping, thereby has prolonged the service life of forcing press and mould in addition.
The above only is a preferred implementation of the present utility model; should be understood that; for those skilled in the art; under the prerequisite that does not break away from the utility model know-why; can also make some improvements and modifications, these improvements and modifications also should be considered as protection domain of the present utility model.
Claims (9)
1, a kind of frame of hotdie forging press, it is characterized in that, comprise hollow integral casting fuselage, in described fuselage, be provided with several tie rod holes, the pull bar of TBE (threaded both ends) is installed in described tie rod hole, on the thread segment of described pull bar nut is housed, described nut tightly is crimped on the described fuselage.
2, the frame of hotdie forging press as claimed in claim 1 is characterized in that, described fuselage is left and right symmetrical structure.
3, the frame of hotdie forging press as claimed in claim 2 is characterized in that, the cross section of described fuselage is rectangular, and going up of described rectangle is following for connecting gusset, and the limit, the left and right sides of described rectangle is the pressure-bearing limit.
4, the frame of hotdie forging press as claimed in claim 3 is characterized in that, the vertical projection of described connection gusset is trapezoidal shape.
5, the frame of hotdie forging press as claimed in claim 3 is characterized in that, is provided with laterally on described pressure-bearing limit and/or through hole longitudinally.
6, the frame of hotdie forging press as claimed in claim 1 is characterized in that, described tie rod hole is arranged on the intersection point place of described rectangle.
7, the frame of hotdie forging press as claimed in claim 1 is characterized in that, is provided with supporting surface at an end of described fuselage, is connected with reinforcement between described supporting surface and described fuselage.
8, the frame of hotdie forging press as claimed in claim 7 is characterized in that, two its longitudinal projections were trapezoidal shape about described supporting surface was divided into.
As the frame of each described hotdie forging press in the claim 1 to 8, it is characterized in that 9, described fuselage is ironcasting or is steel-casting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2009201048642U CN201338066Y (en) | 2009-01-09 | 2009-01-09 | Frame of hot die forging press |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2009201048642U CN201338066Y (en) | 2009-01-09 | 2009-01-09 | Frame of hot die forging press |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201338066Y true CN201338066Y (en) | 2009-11-04 |
Family
ID=41233601
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2009201048642U Expired - Fee Related CN201338066Y (en) | 2009-01-09 | 2009-01-09 | Frame of hot die forging press |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201338066Y (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105346044A (en) * | 2015-11-05 | 2016-02-24 | 大连橡胶塑料机械股份有限公司 | Novel casting support of rubber twin-screw extrusion tablet press |
-
2009
- 2009-01-09 CN CNU2009201048642U patent/CN201338066Y/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105346044A (en) * | 2015-11-05 | 2016-02-24 | 大连橡胶塑料机械股份有限公司 | Novel casting support of rubber twin-screw extrusion tablet press |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20091104 Termination date: 20140109 |