CN104259304B - A kind of forming jig for suppressing aero-engine mesh piece and method - Google Patents
A kind of forming jig for suppressing aero-engine mesh piece and method Download PDFInfo
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- CN104259304B CN104259304B CN201410455672.1A CN201410455672A CN104259304B CN 104259304 B CN104259304 B CN 104259304B CN 201410455672 A CN201410455672 A CN 201410455672A CN 104259304 B CN104259304 B CN 104259304B
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Abstract
The present invention proposes a kind of forming jig for suppressing aero-engine mesh piece and method, and fixture comprises base, lower shape block, upper shape block, drift and boosting mechanism; Lower shape block is fixed on base, there is circular counter sink at Xia Xingkuai center, and there is hemispherical depression at circular counter sink center, and upper shape block lower surface has flanging round platform, and flanging frustum cone side coordinates with the circular counter sink side clearance of lower shape block, Shang Xingkuai center also has guide through hole; Ram bottom is spherical; The fit clearance of drift and upper shape block guide through hole is not more than 0.02mm, the step surface of drift and the upper surface laminating of upper shape block.By easy and simple to handle, safe and reliable during this fixture processing mesh piece, processing conditions is less demanding, and production cost is low, and the part shape processed and size all meet design drawing requirement.
Description
Technical field
The present invention relates to stamping field, specifically a kind of forming jig for suppressing aero-engine mesh piece and method.
Background technology
The metal net shaped part pressure network of certain aero-engine is that φ 0.14mm wire is interwoven by diameter, its forming property requires high, if adopt traditional press forming method, pressure-pad-force is difficult to control, in forming process, pressure-pad-force is excessive, can cause the stretching torsional deformation that tinsel is serious, in forming process, pressure-pad-force is too small, and mesh edge will be wrinkling.And traditional diel provides pressure-pad-force by equipment, plastic force is excessive, therefore adopts traditional press forming method to be difficult to realize, inadvisable.And adopt manual fixture to knock this mesh piece of shaping, then power can be given uneven, also easily make tinsel deformed region produce serious stretching torsional deformation or wrinkling.This part is domestic without manufacturer, adopts always and provides from Ukraine's import supply outsourcing, do not have referential manufacturing process and experience.
Summary of the invention
The object of this invention is to provide a kind of can the forming jig of easy to operate, the metal mesh shaped of shaping aero-engine fast and accurately part and manufacturing process, its clamp structure is simple, method is reliable, part working (machining) efficiency is high, and the accessory appearance quality of processing is good, dimensionally stable.
Technical scheme of the present invention is:
Described a kind of forming jig for suppressing aero-engine mesh piece, is characterized in that: comprise base, lower shape block, upper shape block, drift and boosting mechanism; Boosting mechanism comprises pillar, light face briquetting, housing screw, rotating clamp and handle; Base is support component, is fixedly connected with pillar by screwed hole; Lower shape block is fixed on base, and there is circular counter sink at Xia Xingkuai center, and there is hemispherical depression at circular counter sink center, and circular counter bore diameter is slightly larger than part blank diameter to be pressed; Upper shape block lower surface has flanging round platform, flanging round platform diameter is slightly larger than part blank diameter to be pressed, and flanging frustum cone side coordinates with the circular counter sink side clearance of lower shape block, the part blank thickness to be pressed of circular little one times of the counter sink degree of depth of flanging round platform Thickness Ratio; Shang Xingkuai center also has guide through hole; Drift is step segmental structure, and ram bottom is spherical, and active section length should meet netware forming requirements; The fit clearance of drift and upper shape block guide through hole is not more than 0.02mm, the step surface of drift and the upper surface laminating of upper shape block; In boosting mechanism, rotating clamp is by housing screw and stanchions, and handle passes perpendicularly through rotating clamp, and with rotating clamp threaded engagement, handle end is coordinated with drift by light face briquetting.
Described a kind of manufacturing process for suppressing aero-engine mesh piece, is characterized in that: comprise the following steps:
Step 1: prepare some circular blankses by accessory size requirement;
Step 2: be fixed on smooth workbench by forming jig, unclamp boosting mechanism, takes out drift and upper shape block, is put into by circular blanks in the circular counter sink of lower shape block, compresses, load onto drift with the flanging round platform of shape block, adjustment boosting mechanism;
Step 3: the handle steadily rotating boosting mechanism, make light face briquetting compress drift upper surface, drift steadily moves down along the bullport at Shang Xingkuai center, drives blank slowly to flow in lower shape block cavity, and part is adjacent to lower shape block completely, and part is compressing;
Step 4: unclamp boosting mechanism, takes off drift and upper shape block, from lower shape block, takes out part, continues the next part that is shaped.
Beneficial effect
When this part is purchased abroad, price is high, and is difficult to buying.By easy and simple to handle, safe and reliable during this fixture processing mesh piece, processing conditions is less demanding, and production cost is low, and the part shape processed and size all meet design drawing requirement.The method that this employing boosting mechanism force is shaped, be on average shaped a part for every 6 minutes.This invention solves this type of aero-engine mesh piece and there is no manufacturer at home and unmanageable technical barrier.Simultaneously also for the figuration manufacture of similar aero-engine mesh piece provides valuable experience for reference, have broad application prospects and good promotional value.
Accompanying drawing explanation
Fig. 1: aero-engine pressure network part clamp structural representation;
Wherein: 1-base; Shape block under 2-; The upper shape block of 3-; 4-drift; 5-boosting mechanism.
Fig. 2: afterburning structural representation;
Wherein: 6-light face briquetting; 7-screw; 8-rotating clamp; 9-handle; 10-pillar.
Fig. 3: rotating clamp structural representation.
Fig. 4: upper shape block structure schematic diagram;
Wherein: 11, bullport; 12, flanging round platform.
Fig. 5: punch structure schematic diagram.
Fig. 6: lower shape block structure schematic diagram;
Wherein: 13, locating slot.
Fig. 7: certain aero-engine pressure network part schematic diagram.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described:
With reference to accompanying drawing 7, the present embodiment is for certain engine net part, and the stainless steel metal wire 90 ° that this part material is Φ 0.14mm by diameter is interwoven, part height 11mm, flange diameter Φ 22mm, die cavity diameter of phi 10mm after being shaped.
The forming jig adopted as shown in Figure 1, comprises base 1, lower shape block 2, upper shape block 3, drift 4 and boosting mechanism 5.Boosting mechanism comprises pillar 10, light face briquetting 6, housing screw 7, rotating clamp 8 and handle 9.
Base is support component, and profile is square, each side designs a screwed hole, for anchor post.
The material of upper and lower shape block is CrWMn, and lower shape block is fixed on base, and there is circular counter sink at Xia Xingkuai center, plays the role of positioning, and there is hemispherical depression at circular counter sink center, and be shaped for netware, circular counter bore diameter is slightly larger than part blank diameter to be pressed.
Upper shape block lower surface has flanging round platform, effect is that the flange compressing netware prevents it wrinkling, flanging round platform diameter is slightly larger than part blank diameter to be pressed, and flanging frustum cone side coordinates with the circular counter sink side clearance of lower shape block, the part blank thickness to be pressed of circular little one times of the counter sink degree of depth of flanging round platform Thickness Ratio.Part blank in fixture by the circular counter sink location of lower shape block, the clearance control blank flowing dependences in after shape block and lower shape block matched moulds, ensure part flange when shaping can not wrinkling with tear.Shang Xingkuai center also has guide through hole, passes through for pilot punch, and the fit clearance of drift and upper shape block guide through hole is not more than 0.02mm.
Drift is step segmental structure, and ram bottom is spherical, and active section length should meet netware forming requirements.Drift relies on the guide through hole guiding on upper shape block, avoid fixture matched moulds in forming process not good, part misplaces, by the through position's place's back chipping to drift, the upper surface of the step surface of drift and upper shape block is fitted, and the punch length of press-in should meet Product Process given size.
In boosting mechanism, rotating clamp is by housing screw and stanchions, and handle passes perpendicularly through rotating clamp, and with rotating clamp threaded engagement, handle end is coordinated with drift by light face briquetting.The former mode of knocking shaping that this mechanism changes, achieves the steady Accurate Shaping of part.
Carried out the method for aero-engine pressure network part processing by above device, comprise the following steps:
Step 1: prepare some circular blankses by accessory size requirement;
Step 2: be fixed on smooth workbench by forming jig, unclamp boosting mechanism, takes out drift and upper shape block, is put into by circular blanks in the circular counter sink of lower shape block, compresses, load onto drift with the flanging round platform of shape block, adjustment boosting mechanism;
Step 3: the handle steadily rotating boosting mechanism, make light face briquetting compress drift upper surface, drift steadily moves down along the bullport at Shang Xingkuai center, drives blank slowly to flow in lower shape block cavity, and part is adjacent to lower shape block completely, and part is compressing;
Step 4: unclamp boosting mechanism, takes off drift and upper shape block, from lower shape block, takes out part, continues the next part that is shaped.
Claims (2)
1. for suppressing a forming jig for aero-engine mesh piece, it is characterized in that: comprise base, lower shape block, upper shape block, drift and boosting mechanism; Boosting mechanism comprises pillar, light face briquetting, housing screw, rotating clamp and handle; Base is support component, is fixedly connected with pillar by screwed hole; Lower shape block is fixed on base, and there is circular counter sink at Xia Xingkuai center, and there is hemispherical depression at circular counter sink center, and circular counter bore diameter is slightly larger than part blank diameter to be pressed; Upper shape block lower surface has flanging round platform, flanging round platform diameter is slightly larger than part blank diameter to be pressed, and flanging frustum cone side coordinates with the circular counter sink side clearance of lower shape block, the part blank thickness to be pressed of circular little one times of the counter sink degree of depth of flanging round platform Thickness Ratio; Shang Xingkuai center also has guide through hole; Drift is step segmental structure, and ram bottom is spherical, and active section length should meet netware forming requirements; The fit clearance of drift and upper shape block guide through hole is not more than 0.02mm, the step surface of drift and the upper surface laminating of upper shape block; In boosting mechanism, rotating clamp is by housing screw and stanchions, and handle passes perpendicularly through rotating clamp, and with rotating clamp threaded engagement, handle end is coordinated with drift by light face briquetting.
2. adopt a manufacturing process for forming jig compacting aero-engine mesh piece described in claim 1, it is characterized in that: comprise the following steps:
Step 1: prepare some circular blankses by accessory size requirement;
Step 2: be fixed on smooth workbench by forming jig, unclamp boosting mechanism, takes out drift and upper shape block, is put into by circular blanks in the circular counter sink of lower shape block, compresses, load onto drift with the flanging round platform of shape block, adjustment boosting mechanism;
Step 3: the handle steadily rotating boosting mechanism, make light face briquetting compress drift upper surface, drift steadily moves down along the bullport at Shang Xingkuai center, drives blank slowly to flow in lower shape block hemispherical depression, part is adjacent to lower shape block completely, part is compressing;
Step 4: unclamp boosting mechanism, takes off drift and upper shape block, from lower shape block, takes out part, continues the next part that is shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410455672.1A CN104259304B (en) | 2014-09-09 | 2014-09-09 | A kind of forming jig for suppressing aero-engine mesh piece and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410455672.1A CN104259304B (en) | 2014-09-09 | 2014-09-09 | A kind of forming jig for suppressing aero-engine mesh piece and method |
Publications (2)
| Publication Number | Publication Date |
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| CN104259304A CN104259304A (en) | 2015-01-07 |
| CN104259304B true CN104259304B (en) | 2016-04-06 |
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| CN201410455672.1A Active CN104259304B (en) | 2014-09-09 | 2014-09-09 | A kind of forming jig for suppressing aero-engine mesh piece and method |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109505749A (en) * | 2018-11-16 | 2019-03-22 | 中国航发西安动力控制科技有限公司 | Retaining ring disconnects tooling and disconnects method |
| CN110561312A (en) * | 2019-07-25 | 2019-12-13 | 沈阳富创精密设备有限公司 | Aviation part press-fitting clamp |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6117332A (en) * | 1984-07-02 | 1986-01-25 | Yuasa Battery Co Ltd | Production of grid body for lead accumulator |
| CN2656042Y (en) * | 2003-11-10 | 2004-11-17 | 张春荣 | Network shape stepped production mould |
| CN2772670Y (en) * | 2005-02-28 | 2006-04-19 | 保定宝硕门窗发展有限公司 | Die of lattice bar between hollow glasses |
| CN201511071U (en) * | 2009-07-10 | 2010-06-23 | 张义卿 | Mold for processing of metal mesh |
| CN203470643U (en) * | 2013-06-17 | 2014-03-12 | 宁波骏腾模具科技有限公司 | Pressing swelling hole die |
-
2014
- 2014-09-09 CN CN201410455672.1A patent/CN104259304B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6117332A (en) * | 1984-07-02 | 1986-01-25 | Yuasa Battery Co Ltd | Production of grid body for lead accumulator |
| CN2656042Y (en) * | 2003-11-10 | 2004-11-17 | 张春荣 | Network shape stepped production mould |
| CN2772670Y (en) * | 2005-02-28 | 2006-04-19 | 保定宝硕门窗发展有限公司 | Die of lattice bar between hollow glasses |
| CN201511071U (en) * | 2009-07-10 | 2010-06-23 | 张义卿 | Mold for processing of metal mesh |
| CN203470643U (en) * | 2013-06-17 | 2014-03-12 | 宁波骏腾模具科技有限公司 | Pressing swelling hole die |
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| CN104259304A (en) | 2015-01-07 |
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Address after: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee after: AECC AVIATION POWER CO,LTD. Address before: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee before: XI'AN AVIATION POWER Co.,Ltd. |