CN105779748A - Aging strengthened alloy ring creep aging shape correcting method - Google Patents
Aging strengthened alloy ring creep aging shape correcting method Download PDFInfo
- Publication number
- CN105779748A CN105779748A CN201410817153.5A CN201410817153A CN105779748A CN 105779748 A CN105779748 A CN 105779748A CN 201410817153 A CN201410817153 A CN 201410817153A CN 105779748 A CN105779748 A CN 105779748A
- Authority
- CN
- China
- Prior art keywords
- ageing
- annulus part
- creep
- strengthening type
- aging
- 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.)
- Pending
Links
Landscapes
- Prostheses (AREA)
- Materials For Medical Uses (AREA)
Abstract
The invention relates to an aging strengthened alloy ring creep aging shape correcting method, and belongs to the technical field of nonferrous metal material processing engineering. The method comprises the following steps: firstly, solution treatment is performed for an aging strengthened alloy ring; then, the water quenching is performed; the ring is loaded on a shape correcting mold for creep aging after the solution treatment, and the deformation is lower than 1%; and finally, the ring is unloaded from the shape correcting mold. The aging strengthened alloy ring, treated by the method, is lower in residual stress and higher in shape size precision; the outer diameter roundness is lower than 0.1 mm; and the outer diameter roundness after machining is lower than 0.15 mm.
Description
Technical field
The present invention relates to the creep ageing straightening method of a kind of ageing strengthening type alloy annulus part, belong to nonferrous materials processing engineering technology field.
Background technology
Alleviating weight to meet modern big aircraft, improve reliability, reduce the requirements such as performance such as amount of parts, the parts machining of large aircraft shapes just towards multi-direction development such as low stress, small deformation, long-lives.Shaping requirement in the face of what Aero-Space parts promoted day by day, creep ageing, as a kind of important forming technique, is increasingly paid attention to.
The application in Aero-Space of the annulus part is relatively broad, and its material mostly is the ageing strengthening type alloy such as aluminium alloy, titanium alloy, and it has excellent combination property.But, there is more problem in annulus part, for instance inside parts residual stress is excessive, dimensional accuracy is low in shaping engineering.
Summary of the invention
It is an object of the invention to provide a kind of ageing strengthening type alloy annulus part creep ageing straightening method, the method, by controlling temperature, deflection and springback capacity etc., obtains forming residual stress relatively low, and has the ageing strengthening type alloy annulus part of high dimensional accuracy.
A kind of ageing strengthening type alloy annulus part creep ageing straightening method, comprises the steps:
1) ageing strengthening type alloy annulus part is carried out solution treatment, then shrend；
2) creep ageing is orthopedic: by through step 1) annulus part after solution treatment is loaded on orthopedic mould, carries out creep ageing, and deflection is less than 1%；
3) from orthopedic mould, annulus part is unloaded.
Described ageing strengthening type alloy is aluminium alloy or titanium alloy etc.；Described annulus part is solid or hollow；Described annulus part cross sectional shape is rectangle or circle.
For aluminum alloy round ring, the temperature of solution treatment is 515-525 DEG C, and the solution treatment time is 15-30min；For titanium alloy annulus part, the temperature of solution treatment is 880-920 DEG C, and the solution treatment time is 30-60min.
For aluminum alloy round ring, the temperature of creep ageing is 150-175 DEG C, and temperature retention time is 14-16h；For titanium alloy annulus part, the temperature of creep ageing is 490-510 DEG C, and temperature retention time is 5-7h.
After shaping, annulus part overall dimensions is stable, external diameter circularity < 0.1mm；After shaping, annulus part residual stress is less, external diameter circularity < 0.15mm after machining.
In the present invention, annulus part circularity all adopts three-coordinate instrument to measure, and machining processes is primarily referred to as and carries out the simple and mechanical processing such as punching on annulus part.
The present invention utilizes the creep ageing of ageing strengthening type alloy to carry out orthopedic to it, can obtain residual stress less, and has the annulus part of high dimensional accuracy.
The major advantage of the present invention:
First, in conjunction with Design of Dies, Optimum Operation technique, operating process is simple, effective.Orthopaedic procedures is combined with ag(e)ing process, simplifies process, improve efficiency, and mechanical property and forming effect can be effectively ensured.
Second, the overall dimensions precision of orthopedic rear annulus part is high, and external diameter circularity is less than 0.1mm.The annulus part overall dimensions adopting the method orthopedic is stable, precision is high, can meet instructions for use.
3rd, orthopedic rear annulus part residual stress is little, and after machining, annulus part external diameter circularity is less than 0.15mm.Adopting the annulus part residual stress that the present invention shapes little, in follow-up perforation processing, circularity change is less, can effectively meet the instructions for use after machining.
Accompanying drawing explanation
Fig. 1 is open circles ring schematic diagram, and Fig. 1-1 is the schematic cross-section of open circles ring.
Fig. 2 is the orthopedic mould schematic diagram of square-section annulus part, and Fig. 2-1 is orthopedic mould front view.
Detailed description of the invention
Ageing strengthening type alloy annulus part is carried out solution treatment, shrend after insulation a period of time by (1) by the present invention；(2) carrying out creep ageing on orthopedic mould, annulus part is had certain internal stay effect by orthopedic mould；(3) from orthopedic mould, ageing strengthening type alloy annulus part is unloaded；Ageing strengthening type alloy annulus part is processed according to the flow process of " solid solution-creep ageing-unloading ", the orthopedic die size that creep ageing adopts can be varied from according to the internal diameter difference of annulus part, act primarily as internal stay effect, should ensure that deflection is less, deflection≤1%, deflection is calculated by the variable quantity of ring forward backward averaging diameter.
Embodiment 1
To the 6A02 aluminium alloy square-section open circles ring that wall thickness is 1mm, as shown in Fig. 1 and Fig. 1-1, carrying out solution treatment, solid solubility temperature is 525 DEG C, and the solution treatment time is 15min, then shrend；Annulus part after solid solution is loaded into diameter is on the orthopedic mould of 275.00mm, the square-section orthopedic mould of annulus part is such as shown in Fig. 2 and Fig. 2-1, total deformation less than 1%, orthopedic forward backward averaging diameter respectively 273.20mm and 274.40mm, aging temp is 150 DEG C, and temperature retention time is 16h；Finally unloading square-section open circles ring.Measuring circularity after square-section open circles ring shapes is 0.08mm, and after machining, circularity is 0.12mm.
Embodiment 2
The 6A02 aluminum alloy round tee section open circles ring of to be 5mm, diameter to wall thickness be 20mm carries out solution treatment, and solid solubility temperature is 515 DEG C, and the solution treatment time is 30min, then shrend；Annulus part after solid solution is loaded into diameter is on the orthopedic mould of 274.00mm, and total deformation is less than 1%, and orthopedic forward backward averaging diameter respectively 272.40mm and 273.50mm, aging temp is 175 DEG C, and temperature retention time is 14h；Finally unloading square-section open circles ring.Measuring circularity after circular cross-section hollow annulus part shapes is 0.09mm, and after machining, circularity is 0.13mm.
Embodiment 3
8mm × 8mm6A02 aluminium alloy square-section filled circles ring is carried out solution treatment, and solid solubility temperature is 520 DEG C, and the solution treatment time is 20min, then shrend；Being loaded on the orthopedic mould that diameter is 275.00 by the square-section annulus part after solid solution, total deformation is less than 1%, and orthopedic forward backward averaging diameter respectively 273.90mm and 274.30mm, aging temp is 165 DEG C, and temperature retention time is 15h；Finally unloading rectangular mould annulus part.Measuring circularity after square-section open circles ring shapes is 0.07mm, and after machining, circularity is 0.14mm.
Embodiment 4
The TC4 titanium alloy alloy circular cross-section hollow annulus part that wall thickness is 1mm is carried out solution treatment, and solid solubility temperature is 920 DEG C, and the solution treatment time is 30min, then shrend；Annulus part after solid solution is loaded into diameter is on the orthopedic mould of 274.00mm, and total deformation is less than 1%, and orthopedic forward backward averaging diameter respectively 272.60mm and 273.30mm, aging temp is 500 DEG C, and temperature retention time is 6h；Finally unloading square-section open circles ring.Measuring circularity after circular cross-section hollow annulus part shapes is 0.09mm, and after machining, circularity is 0.13mm.
The ageing strengthening type alloy annulus part residual stress that employing the inventive method processes is little and overall dimensions precision high.
Claims (9)
1. an ageing strengthening type alloy annulus part creep ageing straightening method, comprises the steps:
1) ageing strengthening type alloy annulus part is carried out solution treatment, then shrend；
2) being loaded on orthopedic mould by the annulus part after solution treatment, carry out creep ageing, deflection is less than 1%；
3) from orthopedic mould, annulus part is unloaded.
2. ageing strengthening type alloy annulus part creep ageing straightening method according to claim 1, it is characterised in that: described ageing strengthening type alloy is aluminium alloy or titanium alloy.
3. ageing strengthening type alloy annulus part creep ageing straightening method according to claim 1, it is characterised in that: described annulus part is solid or hollow.
4. ageing strengthening type alloy annulus part creep ageing straightening method according to claim 3, it is characterised in that: described annulus part cross sectional shape is rectangle or circle.
5. ageing strengthening type alloy annulus part creep ageing straightening method according to claim 1, it is characterised in that: for aluminum alloy round ring, the temperature of solution treatment is 515-525 DEG C, and the solution treatment time is 15-30min.
6. ageing strengthening type alloy annulus part creep ageing straightening method according to claim 1, it is characterised in that: for titanium alloy annulus part, the temperature of solution treatment is 880-920 DEG C, and the solution treatment time is 30-60min.
7. ageing strengthening type alloy annulus part creep ageing straightening method according to claim 1, it is characterised in that: for aluminum alloy round ring, the temperature of creep ageing is 150-175 DEG C, and temperature retention time is 14-16h.
8. ageing strengthening type alloy annulus part creep ageing straightening method according to claim 1, it is characterised in that: for titanium alloy annulus part, the temperature of creep ageing is 490-510 DEG C, and temperature retention time is 5-7h.
9. ageing strengthening type alloy annulus part creep ageing straightening method according to claim 1, it is characterised in that: the external diameter circularity < 0.1mm of annulus part after shaping；External diameter circularity < 0.15mm after machining.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410817153.5A CN105779748A (en) | 2014-12-24 | 2014-12-24 | Aging strengthened alloy ring creep aging shape correcting method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410817153.5A CN105779748A (en) | 2014-12-24 | 2014-12-24 | Aging strengthened alloy ring creep aging shape correcting method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105779748A true CN105779748A (en) | 2016-07-20 |
Family
ID=56378345
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410817153.5A Pending CN105779748A (en) | 2014-12-24 | 2014-12-24 | Aging strengthened alloy ring creep aging shape correcting method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105779748A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112338003A (en) * | 2020-09-29 | 2021-02-09 | 哈尔滨工业大学 | Shape correction method for manufacturing deformation of aluminum-magnesium alloy thin-wall cabin section |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102284589A (en) * | 2011-07-26 | 2011-12-21 | 中南大学 | Metal creep forming die |
| CN102912268A (en) * | 2012-09-20 | 2013-02-06 | 中南大学 | Creep aging forming method for Al-Cu-Mg series alloy sheet material |
| CN102978545A (en) * | 2012-11-21 | 2013-03-20 | 中南大学 | Method for creep age forming of Al-Zn-Mg-Cu series aluminium alloy plate |
| CN102978549A (en) * | 2012-11-21 | 2013-03-20 | 中南大学 | Method for bending creep age forming of Al-Zn-Mg-Cu series aluminium alloy plate |
| CN103691793A (en) * | 2013-12-20 | 2014-04-02 | 中南大学 | One-step forming method of aging-strengthening aluminum alloy integral wall plate based on autoclave |
| CN104174791A (en) * | 2014-07-22 | 2014-12-03 | 中国科学院金属研究所 | Preparation method of titanium alloy spring made of wire with specially-shaped section |
-
2014
- 2014-12-24 CN CN201410817153.5A patent/CN105779748A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102284589A (en) * | 2011-07-26 | 2011-12-21 | 中南大学 | Metal creep forming die |
| CN102912268A (en) * | 2012-09-20 | 2013-02-06 | 中南大学 | Creep aging forming method for Al-Cu-Mg series alloy sheet material |
| CN102978545A (en) * | 2012-11-21 | 2013-03-20 | 中南大学 | Method for creep age forming of Al-Zn-Mg-Cu series aluminium alloy plate |
| CN102978549A (en) * | 2012-11-21 | 2013-03-20 | 中南大学 | Method for bending creep age forming of Al-Zn-Mg-Cu series aluminium alloy plate |
| CN103691793A (en) * | 2013-12-20 | 2014-04-02 | 中南大学 | One-step forming method of aging-strengthening aluminum alloy integral wall plate based on autoclave |
| CN104174791A (en) * | 2014-07-22 | 2014-12-03 | 中国科学院金属研究所 | Preparation method of titanium alloy spring made of wire with specially-shaped section |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112338003A (en) * | 2020-09-29 | 2021-02-09 | 哈尔滨工业大学 | Shape correction method for manufacturing deformation of aluminum-magnesium alloy thin-wall cabin section |
| CN112338003B (en) * | 2020-09-29 | 2023-06-20 | 哈尔滨工业大学 | Shape correction method for manufacturing deformation of aluminum-magnesium alloy thin-wall cabin section |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103394545B (en) | The precision machining method of biodegradable magnesium alloy intravascular stent capillary | |
| CN103949588B (en) | The manufacturing process of elongate curved irregularly-shaped hole in a kind of aluminium alloy castings | |
| CN101954481B (en) | Titanium alloy rotor near-net manufacturing method | |
| CN108580579B (en) | Preparation method of medical magnesium alloy thin-wall pipe | |
| CN103170516B (en) | The short process making method of a kind of magnesium or magnesium alloy capillary | |
| Cui et al. | Investigation of large sheet deformation process in electromagnetic incremental forming | |
| CN103111482B (en) | Preparation method of magnesium alloy seamless pipe and extrusion die thereof | |
| CN105779748A (en) | Aging strengthened alloy ring creep aging shape correcting method | |
| CN104152730B (en) | A kind of preparation method with superplastic nickel manganese gallium alloy | |
| CN108262368B (en) | Preparation method of high-performance medical magnesium alloy thin-wall pipe | |
| Jeong et al. | Finite element analysis for inconel 625 fine tube bending to predict deformation characteristics | |
| CN104889359A (en) | Pressure casting die | |
| Wang et al. | Deformation analysis of elliptical cross-section spiral equal channel extrusion technique | |
| JP2011006087A5 (en) | ||
| CN102962294A (en) | Preparation method of super-thin wall seamless titanium pipe material | |
| CN103273035B (en) | The anti-deformation process of thin-walled oil pipe inserts steel pipe | |
| 郭良刚 et al. | Design method of rolling curve during radial-axial ring rolling process for difficult-to-deform materials | |
| CN204381079U (en) | A kind of minor diameter spinneret for high speed special steel wire production | |
| CN104128520B (en) | The reducing extruding manufacturing process of docking copper ring | |
| CN202963415U (en) | Die casting mold | |
| CN206676939U (en) | A kind of backward extrusion device of pipe fitting | |
| Yong et al. | Effect of internal pressure on corner radius and thickness distribution of shear hydro-bending of 5A02 aluminum alloy tube | |
| CN111375724A (en) | Manufacturing method of end socket with boss | |
| CN209783679U (en) | Anti-deformation thin-wall stainless steel water meter shell | |
| CN203110206U (en) | Helical cooling component of mould core of mould |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160720 |