CN109234653B - Method for reducing residual stress of large complex aluminum alloy die forging - Google Patents
Method for reducing residual stress of large complex aluminum alloy die forging Download PDFInfo
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- CN109234653B CN109234653B CN201811237077.5A CN201811237077A CN109234653B CN 109234653 B CN109234653 B CN 109234653B CN 201811237077 A CN201811237077 A CN 201811237077A CN 109234653 B CN109234653 B CN 109234653B
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
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Abstract
The invention relates to a method for reducing residual stress of a large complex aluminum alloy die forging, which is mainly applied to a multi-rib aluminum alloy die forging and belongs to the field of aluminum alloy material processing. The method is characterized in that the die forging piece after solution quenching is subjected to cold-pressing and drawing treatment to reduce the residual stress of the forging piece. According to the invention, 2-4% of compression deformation is applied to the forge piece by designing and manufacturing the finishing cold drawing die, so that the ribs of the forge piece are compressed and deformed, and meanwhile, the forge piece is stretched towards the periphery, so that the effect of reducing and balancing the residual stress of the forge piece is achieved. According to the method, a set of finishing cold-pressing and drawing die needs to be designed according to the appearance of the forged piece, the residual stress reduction effect is obvious, and the mechanical property and subsequent processing of the workpiece are not influenced.
Description
Technical Field
The invention belongs to the technical field of aluminum alloy material processing, and particularly relates to a method for reducing residual stress of a large complex aluminum alloy die forging.
Background
The high-strength aluminum alloy is widely applied to the field of aerospace by virtue of excellent mechanical properties. The 7XXX series aluminum alloy is the most widely applied high-strength high-toughness aluminum alloy in the field of aerospace at present, and the components of the aluminum alloy are usually subjected to solid solution-quenching-aging heat treatment to improve the strength, toughness, fatigue resistance and corrosion resistance of the aluminum alloy. However, solution quenching can cause large residual quenching stresses in the aluminum alloy component, especially in large, monolithic, structurally complex components, where the residual quenching stresses are close to the yield strength of the material. In the subsequent machining process of the component, due to the change of external conditions, the balance state of quenching residual stress in the component is broken, so that the residual stress is released and redistributed, and the machined parts have severe deformation phenomena such as bending, torsion and the like under the condition of no constraint. In addition, the existence of quenching residual stress in the component can also reduce the corrosion resistance and the fatigue resistance of the material, so that the component has the problems of stress corrosion cracking and the like during service, and the service life and the safety performance of the component are greatly reduced. Therefore, how to effectively control and reduce the quenching residual stress in the 7XXX series aluminum alloy member is an extremely important research direction in the fields of aerospace and the like at present.
The currently used methods for reducing residual stress are mainly classified into heat treatment and mechanical methods. The heat treatment process for reducing the quenching residual stress mainly comprises artificial aging, cryogenic treatment and the like. The mechanical method mainly comprises a pre-stretching method, a cold compression method, vibration aging and the like.
(1) And (5) artificial aging. The artificial aging is one of the important processes for obtaining excellent mechanical properties of the high-strength high-toughness aluminum alloy. Generally, the quenched aluminum alloy is heated to 120-180 ℃, kept warm for a certain time and then cooled. When the residual stress in the quenching component is large, the quenching component is heated to a certain temperature and is kept warm for a certain time, and the alloy material generates creep in the modes of grain boundary diffusion, dislocation motion and the like, so that the quenching residual stress in the component is gradually released and tends to be stable, and the effect of reducing the residual stress by the method is only about 30%. Too long artificial aging treatment time or too high temperature can cause the mechanical property of the aluminum alloy to be obviously reduced.
(2) And (4) carrying out cryogenic treatment. The cryogenic treatment is a method for reducing residual stress in the component by putting the component into a low-temperature medium (such as liquid nitrogen and dry ice) for heat preservation for a certain time, then quickly transferring the component into a high-temperature medium for heat preservation, and finally cooling the component to room temperature after the temperature reaches equilibrium. This method can only eliminate residual stress of 30%. Although the residual stress of the aluminum alloy can be reduced by carrying out the back quenching in the high-temperature steam, the shape of the component is greatly changed due to overlarge temperature difference change of the component with a quite complex structure, so that the method for reducing the residual stress by carrying out the back quenching in the high-temperature steam is more suitable for the component with a simpler shape.
(3) And (5) vibration aging. The working principle of the vibration aging elimination method is that a certain vibration load is applied to a member by using portable excitation equipment, so that the metal member generates one or more vibration states, and plastic deformation is generated under the combined action of the vibration load and residual stress, and the amplitude of the residual stress in the workpiece is reduced. The vibration aging has better reduction effect on the stress with larger stress gradient (shot blasting, welding, rolling and the like), overcomes the defect that the residual stress of the large-scale component can not be reduced by the thermal aging, and is widely applied to the stress reduction of the large-scale component and the welding component.
(4) A pre-stretching method. The principle of reducing quenching residual stress by a pre-stretching method is that a certain amount of stretching plastic deformation is applied along a certain specific direction of a component, so that the generated additional residual stress is superposed with the original quenching residual stress, and the purpose of reducing the stress is achieved. The stretching amount is between 2 and 3 percent, which is the best stretching effect, namely, the internal stress is greatly reduced, and the mechanical property sacrifice is the minimum. The method is only suitable for workpieces with simple shapes, has poor adaptability to workpieces with complex shapes, and is mainly used for reducing the residual stress of rolled plates in production.
(5) Cold compression method. The cold compression is to apply a certain compression external load to the workpiece, so that the workpiece and the residual stress in the member act together to cause the material to generate uneven plastic deformation, thereby reducing the quenching residual stress. The molding method in the cold compression method can relieve part of residual stress of a structural complex component, but can also increase the residual stress of other parts. Thus, molding is a process that adjusts the distribution of residual stresses in the structural member rather than a purely subtractive process. For large workpieces, the load required by the die pressing method is large, and the common press machine cannot meet the requirement.
The common aluminum alloy residual stress reduction method has respective characteristics and defects, and has a certain application range. Because the aviation aluminum alloy die forging at the present stage is mainly designed and manufactured by adopting 7XXX high-strength aluminum alloy, the size specification is large, the structure is complex, the residual stress is reduced on the premise of keeping the excellent mechanical property, and the use standard is reached. Therefore, the requirements for reducing and controlling the quenching residual stress of the large-scale complex aluminum alloy die forging are increasingly urgent.
Disclosure of Invention
The present application is directed to solving at least one of the problems in the prior art. Therefore, the invention aims to provide a method for reducing residual stress of a large complex aluminum alloy die forging. The method combines the characteristics of the die cold pressing method and the pre-stretching method, cold drawing is carried out on the die forging piece while cold pressing is carried out, so that the defect of large load required by the die cold pressing method is overcome, and meanwhile, the residual stress can be effectively reduced.
In order to solve the technical problems, the invention adopts the following technical scheme:
a method for reducing residual stress of a large complex aluminum alloy die forging comprises the following steps:
the method comprises the following steps: carrying out solution quenching treatment on the large complex aluminum alloy die forging;
step two: carrying out cold die pressing and band drawing treatment on the die forging subjected to the solution quenching treatment;
wherein, the die-cooling belt-drawing treatment process comprises the following steps: applying load to the die forging by using a cold pressing die, wherein a cavity of the cold pressing die basically follows the shape of the die forging, the cold pressing die only carries out die pressing on the top of a rib plate of the die forging, a web plate of the die forging is not subjected to die pressing, and the width of a groove of the cold pressing die is larger than that of the rib plate corresponding to the cold pressing die; and for the rib plate of the outer ring of the die forging, a male die of the cold pressing die is embedded into the draft angle of the rib plate of the outer ring of the die forging, so that combined deformation of stretching and compression is generated, and a gap for outward expansion of the die forging is reserved in a die groove corresponding to the rib plate of the outer ring of the die forging.
Furthermore, the width of the rib plate of the outer ring of the die forging is larger than the thickness of the web plate.
Furthermore, the fillet of the cold pressing die is larger than or equal to the fillet corresponding to the die forging.
Further, the die forging forming process is as follows:
heating the pre-forging blank to 400-420 ℃, preserving heat for 5-6 hours, discharging from the furnace and forging for one time, wherein the die forging temperature is 350-420 ℃, the die temperature is not lower than 380 ℃, and the pre-forging blank is formed by pre-forging the rolling plate blank.
Furthermore, the solid solution temperature is 470-480 ℃, the heat preservation time is 2-5h, the quenching delay time is less than or equal to 15s, the quenching medium is water with the temperature of 50-70 ℃, and the quenching process is accompanied by strong stirring.
Further, the cold die strip drawing treatment was performed within 4 hours after the solution treatment.
Further, the lubricant used for the die-cooling belt drawing treatment is oil-based graphite, and is uniformly coated on the die forging.
Further, the molding amount of the molding cold belt drawing treatment is 2% to 4%, preferably 3%.
The principle and the advantages are as follows:
the difference between the cold pressing method and the cold pressing method lies in that the force application direction and the deformation are different, and the cold pressing method compresses the forge piece along the forging compression direction to generate micro deformation along the side surface of the forge piece so as to reduce the residual stress; the die cold drawing method of the invention applies pressure along the side surface of the forging, so that the web plate and the like generate the effect of tensile deformation while the side surface of the rib plate of the forging is compressed, and the magnitude of the applied force is far smaller than that of the cold drawing method. The difference with the cold drawing method lies in that the force application structure is different, the cold drawing method uses the clamp to clamp two ends of the workpiece for stretching deformation, the forge piece has a complex structure and cannot be stretched by the clamp, and the cold pressing die in the die cold drawing method can enable the forge piece to generate micro deformation expanding outwards.
The method has the advantages that the ribs of the forge piece are compressed and deformed, meanwhile, the forge piece is stretched towards the periphery, so that the effect of reducing and balancing the residual stress of the forge piece is achieved, the load application is small, the residual stress reducing effect is obvious (the average residual stress value is reduced from 216MPa to 123MPa, the elimination rate reaches 57%), the mechanical property and the subsequent processing of the workpiece are not influenced, the treatment cost is low, and the method has the comprehensive advantages of a cold-drawing method and a cold-pressing method.
Drawings
FIG. 1 is a schematic view of a die-cooled belt drawing process;
FIG. 2 is a drawing cross-sectional view of an embodiment forging stamping belt;
FIG. 3 is a residual stress distribution diagram of a solid solution forged piece according to the embodiment;
FIG. 4 is a graph of the residual stress distribution after the cold strip drawing treatment of the forging of the embodiment.
Detailed Description
The invention will be further described with reference to the accompanying drawings and specific embodiments.
A method for reducing residual stress of a large complex aluminum alloy die forging comprises the following steps:
the method comprises the following steps: carrying out solution quenching treatment on the large complex aluminum alloy die forging;
preferably, the die forging forming process is as follows:
heating the pre-forging blank to 400-420 ℃, preserving heat for 5-6 hours, discharging the pre-forging blank from a furnace for one-time forging forming, wherein the die forging temperature is 350-420 ℃, the die temperature is not lower than 380 ℃, the pre-forging blank is pre-forged by a rolling plate blank, the solid solution temperature is 470-480 ℃, the heat preservation time is 2-5 hours, the quenching delay time is less than or equal to 15s, the quenching medium is water at 50-70 ℃, and the quenching process is accompanied with strong stirring.
Step two: carrying out cold die pressing and band drawing treatment on the die forging subjected to the solution quenching treatment;
wherein, the die-cooling belt-drawing treatment process comprises the following steps: applying load to the die forging by using a cold pressing die, wherein a cavity of the cold pressing die basically follows the shape of the die forging, the cold pressing die only carries out die pressing on the top of a rib plate of the die forging, a web plate of the die forging is not subjected to die pressing, and the width of a groove of the cold pressing die is larger than that of the rib plate corresponding to the cold pressing die; and for the rib plate of the outer ring of the die forging, a male die of the cold pressing die is embedded into the draft angle of the rib plate of the outer ring of the die forging, so that combined deformation of stretching and compression is generated, and a gap for outward expansion of the die forging is reserved in a die groove corresponding to the rib plate of the outer ring of the die forging.
Preferably, the cold-die belt drawing treatment is performed within 4 hours after the solution treatment, the lubricant used in the cold-die belt drawing treatment is oil-based graphite, the oil-based graphite is uniformly coated on a die forging piece, and the die pressing amount of the cold-die belt drawing treatment is 2% -4%.
Cold die pressing (drawing) process: a specific cold pressing die is needed, a die cavity is basically along with the appearance of the forging, only ribs are selected to be pressed, a web plate is not pressed, and the cold pressing amount is 2% -4%; reserving space on the web plate, wherein metal flows in space when the ribs are pressed to generate micro deformation; and for the draft angle of the outer ring rib of the forging, the cold pressing die has an outward expanding effect on the cold pressing die, so that the male die is embedded into the draft angle of the reinforcing rib on the end face of the die forging to generate combined deformation of stretching and compression, thereby eliminating residual stress in the aluminum alloy die forging and achieving the purpose of eliminating residues by a finish die drawing and pressing method. The lubricant used in the cold pressing and drawing process is oil-based graphite which is uniformly coated on the forging.
The cold die pressing (drawing) method is characterized in that: the cold pressing method compresses the forge piece along the forging compression direction, so that the forge piece generates tiny deformation along the side surface of the forge piece to reduce the residual stress; the cold die pressing and drawing method applies pressure along the side face of the forging, so that the web plate and the like generate the effect of tensile deformation while the side face of the rib plate of the forging is compressed, and the magnitude of the applied force is far smaller than that of the cold pressing method. The difference between the cold drawing method and the cold drawing method lies in that the force application structure is different, the cold drawing method uses a clamp to clamp two ends of a workpiece for stretching deformation, and the forging piece has a complex structure and cannot be stretched by the clamp; and the specific die in the die cold drawing and pressing method can make the forging generate micro deformation expanding outwards all around.
In the invention, the whole forging is subjected to micro tensile deformation, the width of the tension rib of the forging is not less than the thickness of the web, the width of the outer rib is greater than the thickness of the web as shown in figure 1, and the fillet of the die is not less than the corresponding fillet of the forging so as to ensure that the stress is as uniform as possible. The deformed gap of the forging is reserved on the die, that is, the width of the groove is larger than the width of the rib at the position of the die where the top of the rib needs to be pressed, and the expanded gap of the forging is reserved in the corresponding die groove at the outer side of the forging, as shown in fig. 2.
The present invention will be further described with reference to specific examples.
The 7050 aluminum alloy blank is processed into a designed shape, heated to 425 ℃ in a special aluminum alloy resistance furnace and kept for 8 hours, and then forged in a preforging die, wherein the temperature of the preforging die is between 400 and 450 ℃. And air cooling to room temperature after the preforging is finished, machining the preforging to the designed shape, heating to 420 ℃, keeping the temperature for 8h, forging in a finish forging die at the temperature of 400-450 ℃, and air cooling after the die forging is finished. And then, reheating the forge piece to 470 ℃, preserving heat for 5 hours, quenching the forge piece by warm water at 60 ℃, intensively stirring, and carrying out die cold pressing and drawing treatment on a cold pressing die with the compression amount of 3%. The distribution of the residual stress of the forged piece after solution quenching and the distribution of the residual stress of the forged piece after die cold pressing and pulling are shown in figures 3 and 4, and it can be seen from the figures that the average value of the residual stress of the forged piece after die cold pressing and band pulling treatment is reduced from 216MPa to 123MPa, and the elimination rate reaches 57%.
The above examples are merely illustrative for clearly illustrating the present invention and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. Nor is it intended to be exhaustive of all embodiments. And obvious variations or modifications of the invention may be made without departing from the scope of the invention.
Claims (8)
1. The method for reducing the residual stress of the large-scale complex aluminum alloy die forging is characterized by comprising the following steps of:
the method comprises the following steps: carrying out solution quenching treatment on the large complex aluminum alloy die forging;
step two: carrying out cold die pressing and band drawing treatment on the die forging subjected to the solution quenching treatment;
wherein, the die-cooling belt-drawing treatment process comprises the following steps: applying load to the die forging by using a cold pressing die, wherein a cavity of the cold pressing die basically follows the shape of the die forging, the cold pressing die only carries out die pressing on the top of a rib plate of the die forging, a web plate of the die forging is not subjected to die pressing, and the width of a groove of the cold pressing die is larger than that of the rib plate corresponding to the cold pressing die; for the rib plate of the outer ring of the die forging, a male die of a cold pressing die is embedded into the draft angle of the rib plate of the outer ring of the die forging, so that combined deformation of stretching and compression is generated, and a gap for outward expansion of the die forging is reserved in a die groove corresponding to the rib plate of the outer ring of the die forging;
the aluminum alloy die forging is a 7XXX series aluminum alloy die forging.
2. The method for reducing the residual stress of the large-scale complex aluminum alloy die forging according to claim 1, characterized in that: the width of the rib plate of the outer ring of the die forging is larger than the thickness of the web plate.
3. The method for reducing the residual stress of the large-scale complex aluminum alloy die forging according to claim 1 or 2, characterized in that: and the fillet of the cold pressing die is more than or equal to the fillet corresponding to the die forging.
4. The method for reducing the residual stress of the large-scale complex aluminum alloy die forging according to claim 1 or 2, wherein the die forging forming process comprises the following steps:
heating the pre-forging blank to 400-420 ℃, preserving heat for 5-6 hours, discharging from the furnace and forging for one time, wherein the die forging temperature is 350-420 ℃, the die temperature is not lower than 380 ℃, and the pre-forging blank is formed by pre-forging the rolling plate blank.
5. The method for reducing the residual stress of the large-scale complex aluminum alloy die forging according to claim 1 or 2, characterized in that: the solid solution temperature is 470-480 ℃, the heat preservation time is 2-5h, the quenching delay time is less than or equal to 15s, the quenching medium is water with the temperature of 50-70 ℃, and the quenching process is accompanied by strong stirring.
6. The method for reducing the residual stress of the large-scale complex aluminum alloy die forging according to claim 1 or 2, characterized in that: the cold die strip drawing treatment was performed within 4 hours after the solution treatment.
7. The method for reducing the residual stress of the large-scale complex aluminum alloy die forging according to claim 1 or 2, characterized in that: the lubricant used for the die-cooling belt drawing treatment is oil-based graphite which is uniformly coated on the die forging.
8. The method for reducing the residual stress of the large-scale complex aluminum alloy die forging according to claim 1 or 2, characterized in that: the molding amount of the molding press belt drawing treatment is 2-4%.
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Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2879217A1 (en) * | 2004-12-13 | 2006-06-16 | Pechiney Rhenalu Sa | STRONG ALLOY SHEETS AI-ZN-CU-MG WITH LOW INTERNAL CONSTRAINTS |
| CN101037748A (en) * | 2007-04-29 | 2007-09-19 | 东北轻合金有限责任公司 | Aviation aluminum alloy pre-stretching plate and production method thereof |
| CN101445886A (en) * | 2008-12-31 | 2009-06-03 | 东北轻合金有限责任公司 | High-strength high-toughness aluminum alloy pre-tensioned thick plate and preparation method thereof |
| US8323427B1 (en) * | 2009-09-14 | 2012-12-04 | The Boeing Company | Engineered shapes from metallic alloys |
| CN103305670A (en) * | 2013-07-09 | 2013-09-18 | 中南大学 | Technology for reducing residual stress of complex aviation die forging through adopting local die pressing method |
| JP2014159038A (en) * | 2013-02-20 | 2014-09-04 | Aisin Keikinzoku Co Ltd | Press molding article of extrusion material |
| CN104745985A (en) * | 2013-12-25 | 2015-07-01 | 青岛玉光精铸厂 | Heat treatment technology of 7050 high-strength aluminum alloy forge piece |
| CN106270142A (en) * | 2016-08-31 | 2017-01-04 | 无锡派克新材料科技股份有限公司 | A kind of aluminium alloy punching cold bulging method |
| CN106623713A (en) * | 2015-11-03 | 2017-05-10 | 重庆天彩铝业有限公司 | Making method for aluminum-alloy T-type section die-forging parts |
| CN106893909A (en) * | 2017-03-28 | 2017-06-27 | 山东南山铝业股份有限公司 | A kind of aluminum alloy plate materials and preparation method thereof |
| CN107740012A (en) * | 2017-10-16 | 2018-02-27 | 西南铝业（集团）有限责任公司 | A kind of aerolite forging part preparation method |
| CN108531836A (en) * | 2018-05-09 | 2018-09-14 | 湖南人文科技学院 | A kind of heat treatment technics preparing the low residual stress aluminium alloy of high-performance |
| CN108637602A (en) * | 2018-05-11 | 2018-10-12 | 航天材料及工艺研究所 | A kind of large size, thin walled Aluminum alloys tank Loadings On Hemispherical Shell manufacturing process |
-
2018
- 2018-10-23 CN CN201811237077.5A patent/CN109234653B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2879217A1 (en) * | 2004-12-13 | 2006-06-16 | Pechiney Rhenalu Sa | STRONG ALLOY SHEETS AI-ZN-CU-MG WITH LOW INTERNAL CONSTRAINTS |
| CN101037748A (en) * | 2007-04-29 | 2007-09-19 | 东北轻合金有限责任公司 | Aviation aluminum alloy pre-stretching plate and production method thereof |
| CN101445886A (en) * | 2008-12-31 | 2009-06-03 | 东北轻合金有限责任公司 | High-strength high-toughness aluminum alloy pre-tensioned thick plate and preparation method thereof |
| US8323427B1 (en) * | 2009-09-14 | 2012-12-04 | The Boeing Company | Engineered shapes from metallic alloys |
| JP2014159038A (en) * | 2013-02-20 | 2014-09-04 | Aisin Keikinzoku Co Ltd | Press molding article of extrusion material |
| CN103305670A (en) * | 2013-07-09 | 2013-09-18 | 中南大学 | Technology for reducing residual stress of complex aviation die forging through adopting local die pressing method |
| CN104745985A (en) * | 2013-12-25 | 2015-07-01 | 青岛玉光精铸厂 | Heat treatment technology of 7050 high-strength aluminum alloy forge piece |
| CN106623713A (en) * | 2015-11-03 | 2017-05-10 | 重庆天彩铝业有限公司 | Making method for aluminum-alloy T-type section die-forging parts |
| CN106270142A (en) * | 2016-08-31 | 2017-01-04 | 无锡派克新材料科技股份有限公司 | A kind of aluminium alloy punching cold bulging method |
| CN106893909A (en) * | 2017-03-28 | 2017-06-27 | 山东南山铝业股份有限公司 | A kind of aluminum alloy plate materials and preparation method thereof |
| CN107740012A (en) * | 2017-10-16 | 2018-02-27 | 西南铝业（集团）有限责任公司 | A kind of aerolite forging part preparation method |
| CN108531836A (en) * | 2018-05-09 | 2018-09-14 | 湖南人文科技学院 | A kind of heat treatment technics preparing the low residual stress aluminium alloy of high-performance |
| CN108637602A (en) * | 2018-05-11 | 2018-10-12 | 航天材料及工艺研究所 | A kind of large size, thin walled Aluminum alloys tank Loadings On Hemispherical Shell manufacturing process |
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