CN102433420A - Strengthening method suitable for component hole in non-open area - Google Patents
Strengthening method suitable for component hole in non-open area Download PDFInfo
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- CN102433420A CN102433420A CN2011104270063A CN201110427006A CN102433420A CN 102433420 A CN102433420 A CN 102433420A CN 2011104270063 A CN2011104270063 A CN 2011104270063A CN 201110427006 A CN201110427006 A CN 201110427006A CN 102433420 A CN102433420 A CN 102433420A
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- hole
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- piece part
- pincers
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Abstract
The invention discloses a strengthening method suitable for a component hole in a non-open area. The method is characterized in that: impressions in a certain shape and depth are stamped around the component hole required to be strengthened by using special stamping pincers and a special stamping mold. By stamping, the stress conditions of the component hole and the periphery in the non-open area are improved, and the fatigue resistance of the hole is improved; the method can be popularized and applied to strengthening of bolt holes and the like of key stress structures of airplanes; and by the method, the fatigue resistance of a connecting hole is greatly improved, so that the fatigue life of a product is promoted.
Description
Technical field
The present invention relates to the surface strengthening field, relate to a kind of the non-upward method of the reinforcement of hole in piece part of zone of opening wide.
Background technology
On some metal parts, because function needs, need open some holes of system, like oil-through hole, ventilating pit etc. on the integral tank wallboard, the existence in these holes is functional requirements of product, does not generally do special processing originally.But the system of holding in these holes can have a negative impact to the intensity of structural part itself, forms stress raiser, has reduced the intensity and the anti-fatigue performance of member.
In order to improve component fatigue intensity, need carry out intensified process to these holes.Enhancement method to the hole generally has cold extrusion reinforcement, shot peening strengthening etc., but inapplicable to some non-positions that open wide of sealing; Also have a kind of stamping reinforced method, more suitable for the non-position that opens wide of sealing, but processing parameter and condition are not clear, need determine.
Summary of the invention
The object of the invention:, design a kind of non-enhancement method of opening wide the position hole in piece part that is applicable to for solving the problem of functional hole to structural part intensity and anti-fatigue performance deleterious impact.
Technical scheme of the present invention is: a kind ofly be applicable to the non-enhancement method of opening wide regional hole in piece part, use special impression pincers and impressing mould, the periphery of the hole in piece part of strengthening at needs extrudes the impression of the definite shape and the degree of depth, and its concrete steps are following:
1) hole in piece part that need strengthen of mechanical workout makes its processing requirement that reaches regulation, that is: radius 30mm scope inside surface roughness Ra is not more than 1.6 around hole wall and the hole, and the hole Edge Blend is R 0.5mm;
2) use straight pin location and installation impressing mould, hold the impression pincers and align stamping die;
3) install errorless after, the impression pincers are exerted pressure and are continued certain dwell time, pressure is 40～60Mpa, the dwell time is 1～5min; The impression preglabellar field is 2～5mm with the outer peripheral radial distance of the hole in piece part that is reinforced; Indentation width is 1～2.5mm;
4) occlusion pressure printing apparatus wind regime is removed pressure, takes off stamping die, prepares the impression in next hole.
Advantage of the present invention and beneficial effect: the present invention passes through coinging; Improved the non-stress situation of opening wide regional hole in piece part and periphery; Improve the anti-fatigue performance in hole; Can promote the use of the reinforcement of the bolt hole etc. of the crucial stress members of aircraft, improve the anti-fatigue performance of connecting hole greatly, thereby promote the fatigue lifetime of product.
Description of drawings
Fig. 1 is the inventive method work synoptic diagram;
Fig. 2 is the hole impression synoptic diagram of the specific embodiment of the invention.
Embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is described in further detail:
Like Fig. 1, it is following that the present invention specifically strengthens step:
1) need the state of the hole of reinforcement to regulation on the machining workpiece, processing requirement is that radius 30mm scope inside surface roughness Ra is not more than 1.6, hole Edge Blend R0.5mm around hole wall and the hole;
2) use straight pin location and installation impressing mould, hold the impression pincers and align stamping die;
3) install errorless after, the impression pincers are applied 50Mpa pressure and continue 3min, confirm that mould extrudes obvious marks on workpiece;
4) occlusion pressure printing apparatus wind regime is removed pressure, takes off stamping die, prepares the impression in next hole.
Like Fig. 2, in the present embodiment, the hole in piece part of need strengthening is 3, hole and the hole that diameter is 10mm that to be respectively two diameters be 9mm; Through after the reinforcement of the present invention, depth of indentation is 0.3mm, and indentation width is 1.2mm.
Through stamping reinforced tired simultaneous test, at σ
MaxUnder=200Mpa the stress level, when pressing dark 0.3 ± 0.05mm, the median life N when not impressing
50(inferior) increase reaches more than 3.3 times.Its ultimate principle is to utilize the ability of the plastoelastic deformation of metal, and axially with radially plastoelastic deformation is regional to make hole material production on every side through impression, in this zone, has two strengthening mechanisms:
A) cause very high macroscopical unrelieved stress, in fatigue process, reduce adding in the repeated load moment tensile stress level, the mean stress level is descended;
B) in the structural modification of strengthening layer inner tissue, dislocation desity increases, and the microcosmic internal stress raises, and in fatigue process, hinders the Metallic Solids slippage, hinders the dislocation to-and-fro movement;
More than the result of two strengthening mechanism comprehensive actions, can increase substantially limit, the hole fatigue strength of perforated metal part and the ability of stress corrosion resistant, thereby prolong crack initiation life-span and crack growth rate, reach the purpose in the work-ing life that prolongs part.
Claims (2)
1. one kind is applicable to the non-enhancement method of opening wide regional hole in piece part, it is characterized in that, uses special impression pincers and impressing mould, and the periphery of the hole in piece part of strengthening at needs extrudes the impression of the definite shape and the degree of depth.
2. as claimed in claim 1ly be applicable to the non-enhancement method of opening wide regional hole in piece part, it is characterized in that concrete steps are following:
1) hole in piece part that need strengthen of mechanical workout makes its processing requirement that reaches regulation, that is: radius 30mm scope inside surface roughness Ra is not more than 1.6 around hole wall and the hole, and the hole Edge Blend is R0.5mm;
2) use straight pin location and installation impressing mould, hold the impression pincers and align stamping die;
3) install errorless after, the impression pincers are exerted pressure and are continued certain dwell time, pressure is 40～60Mpa, the dwell time is 1～5min; The impression preglabellar field is 2～5mm with the outer peripheral radial distance of the hole in piece part that is reinforced; Indentation width is 1～2.5mm;
4) occlusion pressure printing apparatus wind regime is removed pressure, takes off stamping die, prepares the impression in next hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104270063A CN102433420A (en) | 2011-12-16 | 2011-12-16 | Strengthening method suitable for component hole in non-open area |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104270063A CN102433420A (en) | 2011-12-16 | 2011-12-16 | Strengthening method suitable for component hole in non-open area |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102433420A true CN102433420A (en) | 2012-05-02 |
Family
ID=45981766
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011104270063A Pending CN102433420A (en) | 2011-12-16 | 2011-12-16 | Strengthening method suitable for component hole in non-open area |
Country Status (1)
| Country | Link |
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| CN (1) | CN102433420A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107502718A (en) * | 2017-06-06 | 2017-12-22 | 西安冠泰检测技术有限公司 | A kind of antifatigue multiple strengthening process equipment of fastener hole |
| CN107674952A (en) * | 2017-09-15 | 2018-02-09 | 西安冠泰检测技术有限公司 | A kind of cold extrusion impressing coupling and intensifying process equipment and method |
| CN113579663A (en) * | 2021-09-26 | 2021-11-02 | 中国航发北京航空材料研究院 | Method for prolonging fatigue life of 2124-T851 aluminum alloy porous aviation part |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3803898A (en) * | 1972-08-02 | 1974-04-16 | Mc Donnell Douglas Corp | Ring pad stress coining tooling |
| JPS611438A (en) * | 1984-06-14 | 1986-01-07 | Kobe Steel Ltd | Reinforcing method of transmission shaft having circular hole |
| CN101962706A (en) * | 2010-10-08 | 2011-02-02 | 中国航空工业集团公司北京航空材料研究院 | Compound strengthening method of small hole in ultrahigh strength steel part |
-
2011
- 2011-12-16 CN CN2011104270063A patent/CN102433420A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3803898A (en) * | 1972-08-02 | 1974-04-16 | Mc Donnell Douglas Corp | Ring pad stress coining tooling |
| JPS611438A (en) * | 1984-06-14 | 1986-01-07 | Kobe Steel Ltd | Reinforcing method of transmission shaft having circular hole |
| CN101962706A (en) * | 2010-10-08 | 2011-02-02 | 中国航空工业集团公司北京航空材料研究院 | Compound strengthening method of small hole in ultrahigh strength steel part |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107502718A (en) * | 2017-06-06 | 2017-12-22 | 西安冠泰检测技术有限公司 | A kind of antifatigue multiple strengthening process equipment of fastener hole |
| CN107674952A (en) * | 2017-09-15 | 2018-02-09 | 西安冠泰检测技术有限公司 | A kind of cold extrusion impressing coupling and intensifying process equipment and method |
| CN113579663A (en) * | 2021-09-26 | 2021-11-02 | 中国航发北京航空材料研究院 | Method for prolonging fatigue life of 2124-T851 aluminum alloy porous aviation part |
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Application publication date: 20120502 |
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| WD01 | Invention patent application deemed withdrawn after publication |