CN106694633A - High-temperature alloy precise molding cold pressing thermal stability process method - Google Patents
High-temperature alloy precise molding cold pressing thermal stability process method Download PDFInfo
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- CN106694633A CN106694633A CN201611071650.0A CN201611071650A CN106694633A CN 106694633 A CN106694633 A CN 106694633A CN 201611071650 A CN201611071650 A CN 201611071650A CN 106694633 A CN106694633 A CN 106694633A
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- shape
- school
- shape correction
- fixed
- temperature alloy
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D3/00—Straightening or restoring form of metal rods, metal tubes, metal profiles, or specific articles made therefrom, whether or not in combination with sheet metal parts
- B21D3/16—Straightening or restoring form of metal rods, metal tubes, metal profiles, or specific articles made therefrom, whether or not in combination with sheet metal parts of specific articles made from metal rods, tubes, or profiles, e.g. crankshafts, by specially adapted methods or means
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Forging (AREA)
Abstract
The invention discloses a high-temperature alloy precise molding cold pressing thermal stability process method. The high-temperature alloy precise molding cold pressing thermal stability process method comprises the steps of firstly, machining and molding a sheet metal part; secondly, machining a flange which is used for fixed clamping on the edge of the part; thirdly, machining a threaded hole used for fixing of the part in the edge of the flange; and coating a solder resist on the upper surface and the lower surface of the part and the threaded hole; fourthly, fixing the part coated with the solder resist in a shape correction tool, wherein the shape correction tool comprises a shape correction upper die and a shape correction lower die, the part is fixed between the shape correction upper die and the shape correction lower die, and the shape correction tool with the part fixed is subject to high-pressure shape correction through a pressure machine; fifthly, maintaining pressure of the pressure machine, and putting the shape correction tool with the part fixed into a vacuum furance to be subject to heat treatment so as to remove stress. The sheet metal part molding size precision problem can be solved through the method.
Description
Technical field
The invention belongs to the technical field of Aerospace manufacturing metal plate precision form, and in particular to a kind of high temperature alloy precise forming
Cold pressing thermally-stabilised process.
Background technology
Apply increasing in airspace engine with sheet metal part, the importance of metal plate precision form is also more and more convex
Aobvious, high temperature alloy metal plate forming is generally cold forming, but high temperature alloy intensity is high, and resilience is big after shaping, part forming precision
It is difficult to ensure.
It is certain h type engine h key structure part that height leads rear flange, sees Fig. 2, by 3.8mm thickness GH4169 alloy drawing into
Shape, part has a flanged structure wider, and high temperature alloy inherent characteristic is big Form springback, due to material thickness flange big and wide etc. because
Element, part stretching rear flange jerk value is more than 2mm, the tensioning member later stage need to the machine of carrying out add, topical nickel galvanization and then soldering.Part is final
Dimension precision requirement is high.Therefore control forming parts precision is most important.
The content of the invention
In view of this, colded pressing thermally-stabilised process the invention provides a kind of high temperature alloy precise forming, can solve the problem that
Sheet metal part forming dimension precision problem.
Realize that technical scheme is as follows：
A kind of high temperature alloy precise forming is colded pressing thermally-stabilised process, is comprised the following steps：
Step one, by sheet metal part machine-shaping；
Step 2, process the flange for fixed clamp in part edge；
Step 3, the screwed hole for retaining element is processed in flange periphery, and in part upper surface, lower surface and spiral shell
Pit applies solder resist；
Step 4, the part that will scribble solder resist are fixed in the shape frock of school, the school shape frock include in the shape of school mould and
Mould under the shape of school, part is fixed in the shape of school under mould and school shape between mould, and the school shape frock that will be fixed with part is entered using forcing press
Horizontal high voltage school shape；
Step 5, the pressure for keeping forcing press, the school shape frock that will be fixed with part are put into vacuum drying oven and are heat-treated
Eliminate stress.
Beneficial effect：
, using the locking that pressed outside stove, hot sizing effect is obvious in vacuum drying oven for the present invention.After hot sizing, part flanges and the conical surface
Centering jerk value is less than 0.3mm on lathe, fully meets later stage machine plus Geometrical Tolerance Principle.The inventive method can be applied to
Similar high-precision sheet metal component processing.
Brief description of the drawings
Fig. 1 is lieutenant colonel's shape frock operation principle schematic diagram of the present invention.
Fig. 2 is design of part schematic diagram of the present invention.
Wherein, mould under the shape of 1- schools；2- bolts；3- nuts；Mould in the shape of 4- schools；5- pressure backing plates.
Specific embodiment
Develop simultaneously embodiment below in conjunction with the accompanying drawings, and the present invention will be described in detail.
High temperature alloy sheet-metal formed and machining are all relatively difficult, and especially sheet-metal formed, is molded big, shaping
Resilience is serious afterwards, and springback capacity is not easily controlled, for 3.8 after big thickness sheet-metal formed difficulty it is just bigger, rear method is led with regard to height
For orchid, shaping rear flange springback capacity (jerk value) is more than 2mm, and uniformity is poor.
Colded pressing thermally-stabilised process the invention provides a kind of high temperature alloy precise forming, comprised the following steps：
Step one, by sheet metal part machine-shaping；As shown in Figure 2.
Step 2, process the flange for fixed clamp in part edge；
Step 3, screwed hole for retaining element is processed on flange, and resistance is applied in piece surface and screwed hole
Solder flux；
Step 4, the part of solder resist will be scribbled it is fixed in the shape frock of school by bolt 2 and nut 3, the school shape work
Dress includes in the shape of school mould 1 under mould 4 and school shape, as shown in figure 1, part is fixed in the shape of school under mould 4 and school shape between mould 1, will consolidate
Surely pressure backing plate 5 is placed in the school shape frock top for having part, then enters horizontal high voltage school shape using forcing press；The step is outside hot stove
Pressure, convenient operation, and the external pressure needed for overcoming part elastic deformation enough can be provided, part is returned to resilience
Preceding size shape.
Step 5, the pressure for keeping forcing press offer, the school shape frock that will be fixed with part carry out stress-relieving by beat treatment.
The step eliminates inside parts stress, stabilizer elements size shape.
High temperature alloy precision form thermally-stabilised technology of colding pressing preferably resolves forming dimension precision problem, heat of colding pressing
Process for stabilizing technology is before heat stabilisation process, formation of parts frock to be shaped into ideal in stove external application large-tonnage press device
State, then makes part go de-stress, it is ensured that dimension precision requirement by heat treatment.
In sum, presently preferred embodiments of the present invention is these are only, is not intended to limit the scope of the present invention.
All any modification, equivalent substitution and improvements within the spirit and principles in the present invention, made etc., should be included in of the invention
Within protection domain.
Claims (1)
1. a kind of high temperature alloy precise forming is colded pressing thermally-stabilised process, it is characterised in that comprised the following steps：
Step one, by sheet metal part machine-shaping；
Step 2, process the flange for fixed clamp in part edge；
Step 3, the screwed hole for retaining element is processed in flange periphery, and in part upper surface, lower surface and screwed hole
Apply solder resist；
Step 4, the part that will scribble solder resist are fixed in the shape frock of school, and the school shape frock includes mould and school shape in the shape of school
Lower mould, part is fixed in the shape of school under mould and school shape between mould, and the school shape frock that will be fixed with part carries out height using forcing press
Pressure school shape；
Step 5, the pressure for keeping forcing press, the school shape frock that will be fixed with part are put into heat treatment elimination are carried out in vacuum drying oven
Stress.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611071650.0A CN106694633A (en) | 2016-11-28 | 2016-11-28 | High-temperature alloy precise molding cold pressing thermal stability process method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611071650.0A CN106694633A (en) | 2016-11-28 | 2016-11-28 | High-temperature alloy precise molding cold pressing thermal stability process method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106694633A true CN106694633A (en) | 2017-05-24 |
Family
ID=58934112
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611071650.0A Pending CN106694633A (en) | 2016-11-28 | 2016-11-28 | High-temperature alloy precise molding cold pressing thermal stability process method |
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| CN (1) | CN106694633A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107597934A (en) * | 2017-07-28 | 2018-01-19 | 武汉船用机械有限责任公司 | A kind of punching press frock and process for stamping |
| CN112139294A (en) * | 2020-09-15 | 2020-12-29 | 贵州安吉航空精密铸造有限责任公司 | Thermal shape correcting method for large casting |
| CN112588878A (en) * | 2020-11-27 | 2021-04-02 | 北京星航机电装备有限公司 | Local shape correcting method for aluminum alloy thin-wall special-shaped part |
| CN112692171A (en) * | 2020-12-29 | 2021-04-23 | 航天海鹰(哈尔滨)钛业有限公司 | Thermal shape correction die and method for high-temperature alloy large arc section thin-wall casting |
| CN113102868A (en) * | 2021-04-20 | 2021-07-13 | 中国直升机设计研究所 | Helicopter main nozzle lobe machining method |
| CN116765769A (en) * | 2023-08-16 | 2023-09-19 | 陕西长羽航空装备股份有限公司 | Welding and stress-relieving shape correcting method for high-temperature alloy welding piece |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05329694A (en) * | 1992-06-02 | 1993-12-14 | Nkk Corp | Method for molding aluminum alloy thin sheet by explosive pressure |
| JP2011256408A (en) * | 2010-06-04 | 2011-12-22 | Nippon Thermotech Kk | Method of manufacturing shape memory alloy |
| CN102896220A (en) * | 2012-09-28 | 2013-01-30 | 北京航星机器制造公司 | Hot forming/hot sizing/heat treatment integrated forming method and die |
| CN104999000A (en) * | 2015-07-15 | 2015-10-28 | 西安航空动力股份有限公司 | Machining method of wave spring |
| CN105290162A (en) * | 2015-11-11 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for shape correction of high-temperature alloy thin-wall aeroengine casing part through electric arc heating |
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2016
- 2016-11-28 CN CN201611071650.0A patent/CN106694633A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05329694A (en) * | 1992-06-02 | 1993-12-14 | Nkk Corp | Method for molding aluminum alloy thin sheet by explosive pressure |
| JP2011256408A (en) * | 2010-06-04 | 2011-12-22 | Nippon Thermotech Kk | Method of manufacturing shape memory alloy |
| CN102896220A (en) * | 2012-09-28 | 2013-01-30 | 北京航星机器制造公司 | Hot forming/hot sizing/heat treatment integrated forming method and die |
| CN104999000A (en) * | 2015-07-15 | 2015-10-28 | 西安航空动力股份有限公司 | Machining method of wave spring |
| CN105290162A (en) * | 2015-11-11 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for shape correction of high-temperature alloy thin-wall aeroengine casing part through electric arc heating |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107597934A (en) * | 2017-07-28 | 2018-01-19 | 武汉船用机械有限责任公司 | A kind of punching press frock and process for stamping |
| CN112139294A (en) * | 2020-09-15 | 2020-12-29 | 贵州安吉航空精密铸造有限责任公司 | Thermal shape correcting method for large casting |
| CN112588878A (en) * | 2020-11-27 | 2021-04-02 | 北京星航机电装备有限公司 | Local shape correcting method for aluminum alloy thin-wall special-shaped part |
| CN112692171A (en) * | 2020-12-29 | 2021-04-23 | 航天海鹰(哈尔滨)钛业有限公司 | Thermal shape correction die and method for high-temperature alloy large arc section thin-wall casting |
| CN112692171B (en) * | 2020-12-29 | 2024-06-07 | 航天海鹰(哈尔滨)钛业有限公司 | Hot shape correction die and method for high-temperature alloy large-scale arc section thin-wall casting |
| CN113102868A (en) * | 2021-04-20 | 2021-07-13 | 中国直升机设计研究所 | Helicopter main nozzle lobe machining method |
| CN116765769A (en) * | 2023-08-16 | 2023-09-19 | 陕西长羽航空装备股份有限公司 | Welding and stress-relieving shape correcting method for high-temperature alloy welding piece |
| CN116765769B (en) * | 2023-08-16 | 2023-10-31 | 陕西长羽航空装备股份有限公司 | Welding and stress-relieving shape correcting method for high-temperature alloy welding piece |
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Application publication date: 20170524 |
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| WD01 | Invention patent application deemed withdrawn after publication |