CN103498119B - Improve the thermal treatment process of aluminum alloy solution state pretensioning plate anti-fatigue performance - Google Patents
Improve the thermal treatment process of aluminum alloy solution state pretensioning plate anti-fatigue performance Download PDFInfo
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Abstract
The invention discloses a kind of heat treating method improving aluminum alloy solution state pretensioning plate anti-fatigue performance, carry out solution treatment by this aluminum alloy plate materials, and shrend, through 2-10% pre-tension deformation, then carry out artificial lack time effect or natural aging treatment.The present invention, by controlling the timeliness process of Al-Cu-Mg alloy solid solution state pre-stretching plate, forms the elementide and G.P district enhanced particles that can be cut by dislocation, and S ' the transition strengthening phase can only walked around by dislocation that unconventional timeliness is formed.These enhanced particles can cut by dislocation can not hinder the dislocation in crack tip region in fatigue process toward multiple slip, reduce the damage accumulation of pre-stretching plate in fatigue process, improve the fatigue crack growth resistance of pre-stretching plate.Artificial lack time effect also effectively reduces the dislocation desity in sheet material simultaneously, improves plasticity and the anti-fatigue performance of Al-Cu-Mg alloy pre-stretching plate.Be suitable for suitability for industrialized production.
Description
Technical field:
The present invention relates to a kind of thermal treatment process improving aluminum alloy solution state pretensioning plate anti-fatigue performance, refer to a kind of thermal treatment process improving Al-Cu-Mg alloy solid solution state pretensioning plate anti-fatigue performance especially.Belong to technical field of metal material heat treatment.
Background technology
Al-Cu-Mg alloy is owing to having medium tenacity, and good toughness is the aluminium alloy of widespread use in aerospace.After this sheet alloy solution hardening, the general pre-tension deformation that adopts eliminates the unrelieved stress produced in the course of processing; Then, carry out peak value timeliness, alloy is applied in Practical Project with peak aged.Pre-tension deformation after solution hardening, can introduce high density dislocation tissue, improve the intensity of sheet alloy in alloy substrate.But after usually applying pre-tension deformation and peak value timeliness, sheet alloy is while intensity improves, and its plasticity and anti-fatigue performance but significantly decline.And anti-fatigue performance is the key property parameter of aerolite, it is the problem that must solve.
Research shows, alloy carries out pre-tension deformation after solution hardening, can eliminate the unrelieved stress of Al-Cu-Mg alloy sheet material, but pre-tension deformation have also been introduced high density dislocation tissue simultaneously and produces strain hardening effect.The appearance of strain hardening effect, improves alloy strength, but reduces plasticity and the anti-fatigue performance of alloy.Meanwhile, highdensity dislocation, in peak value ag(e)ing process subsequently, becomes the nucleation site of precipitated phase, promotes heterogeneous nucleation, improves nucleation rate.Promote that the precipitation of precipitated phase will improve alloy strength undoubtedly, but this also will inevitably reduce alloy plasticity and anti-fatigue performance.Research shows, the precipitated phase tissue of the high density dislocation that pre-tension deformation is introduced and disperse, with the slip dislocation in Plastic Deformations at Fatigue Crack Tip district, strong interaction occurs, hinder the reciprocal sliding motion of dislocation in plastically deforming area, fatigue cracking front end; As everyone knows, precipitated phase hinders the dislocation under repeated stress effect to be that it can not be cut by dislocation toward the reason of multiple slip, dislocation can only be walked around and leave dislocation loop, add the resistance to follow-up dislocation glide, accelerate the fatigue damage accumulation of alloy under repeated stress effect, and reduce the fatigue crack growth resistance of alloy.So, under the prerequisite ensureing aluminum alloy pretensioning plate intensity, how to improve its anti-fatigue performance?
Analysis shows, the microtexture of carrying out the acquisition of peak value timeliness after pre-tension deformation is S ' transition strengthening phase, and it belongs to the strengthening phase that can not be cut by dislocation, therefore, carry out the Al-Cu-Mg alloy of peak value timeliness after pre-tension deformation, although intensity is higher, fatigue crack growth resistance is lower.How to improve Al-Cu-Mg alloy pre-stretching plate plasticity and anti-fatigue performance, become and wish for a long time in the industry to solve and a unsolved difficult problem.
Summary of the invention
The object of the invention is to unrelieved stress, the raising intensity of eliminating Al-Cu-Mg alloy sheet material for preliminary draft technique, but reduce the technical deficiency of plasticity and fatigue crack growth resistance, a kind of thermal treatment process improving aluminum alloy solution state pretensioning plate anti-fatigue performance is provided.The present invention is by controlling pre-stretching plate Precipitation process, the elementide that acquisition can be cut by dislocation and G.P. district enhanced particles, under the prerequisite keeping higher-strength, reduce pre-stretching plate fatigue crack tip dislocation toward the resistance of multiple slip and fatigue damage accumulation, improve pre-stretching plate plasticity and fatigue crack growth resistance.
The present invention improves the thermal treatment process of aluminum alloy solution state pretensioning plate anti-fatigue performance, is to adopt following proposal to realize:
Solution treatment is carried out artificial lack time effect or natural aging through the aluminum alloy plate materials of pre-tension deformation after shrend.
The present invention improves the thermal treatment process of aluminum alloy solution state pretensioning plate anti-fatigue performance, and described artificial lack time effect processing parameter is: Heating temperature 120-168 DEG C, soaking time 30-240 minute.
The present invention improves the thermal treatment process of aluminum alloy solution state pretensioning plate anti-fatigue performance, and described natural aging processing parameter is: ambient temperatare puts at least 96 hours.
The present invention improves the thermal treatment process of aluminum alloy solution state pretensioning plate anti-fatigue performance, aluminum alloy plate materials comprises following component, form by weight percentage: Cu 3.35-3.85%, Mg1.40-1.80%, Mn 0.40-0.70%, Zr 0.08-0.16%, Ti0.03-0.07%, Be0.0003-0.0008%, Fe≤0.15%, Si≤0.05% surplus is aluminium.
The present invention improves the thermal treatment process of aluminum alloy solution state pretensioning plate anti-fatigue performance, and solid solution treatment process is: 485-505 DEG C/0.5-2 hour.
The present invention improves the thermal treatment process of aluminum alloy solution state pretensioning plate anti-fatigue performance, and pre-tension deformation technique is: room temperature tensile distortion 2-10% after solid solution.
Mechanism of the present invention sketch under:
Research shows, the Precipitation sequence of the Al-Cu-Mg alloy of low Cu/Mg ratio is: SSS → elementide → G.P. district → S ' → S.Wherein elementide and G.P. district particle are the enhanced particles can cut by dislocation completely.These particles are while reinforced alloys matrix, can be cut by the slip dislocation in Plastic Deformations at Fatigue Crack Tip district, dislocation in Crack Tip Deformation district is not hindered toward multiple slip, reduces the fatigue damage accumulation of alloy, thus carries heavy alloyed anti-fatigue performance.Therefore, after alloy pre-tension deformation, by controlling timeliness process, the enhanced particles such as the elementide that formation can be cut by dislocation and G.P. district are the keys improving Al-Cu-Mg alloy pre-stretching plate plasticity and anti-fatigue performance.This, for the plasticity and the anti-fatigue performance that improve existing Al-Cu-Mg alloy pre-stretching plate, expands its Application Areas and has great importance.
The present invention, by controlling the timeliness process of Al-Cu-Mg alloy pre-stretching plate, obtains the enhanced particles can cut by dislocation completely.Simultaneously, in the process controlling timeliness, owing to being subject to extraneous heat activated effect, the partial dislocation that pre-tension deformation is introduced, the motion that sign dislocation is offset can be there is, also and can climb to crystal boundary disappearance by slippage, also some dislocation can cause a large amount of atomic migrations and diffusion because of the segregation of a large amount of solute atoms with to the differentiation of G.P. district, and loses the characteristic of dislocation.The combination of these factors, result in dislocation desity actual in alloy and reduces, and then reduce the inhibition of reciprocal slip dislocation and the fatigue damage accumulation of alloy, improve the anti-fatigue performance of alloy pre-stretching plate.
Advantage of the present invention and positively effect:
The present invention is directed to that the intensity after Al-Cu-Mg alloy pre-stretching plate timeliness is high, the problem of plasticity and anti-fatigue performance difference, by controlling pre-stretching plate Precipitation process, the elementide that acquisition can be cut by dislocation and G.P. district enhanced particles, under the prerequisite keeping higher-strength, reduce pre-stretching plate fatigue crack tip dislocation toward the resistance of multiple slip and fatigue damage accumulation, improve pre-stretching plate plasticity and fatigue crack growth resistance.Relative traditional aging technique, the present invention can make the plasticity of Al-Cu-Mg alloy pre-stretching plate and fatigue crack growth resistance be greatly improved.
The aging temp of aluminum alloy pre-stretching plate and time controling remain within the scope of G.P district just making the growth of elementide by the present invention, obtain to be cut by dislocation and not affect the dislocation in fatigue process in crack tip plastic zone toward the strengthening microstructure of multiple slip and organize, this dislocation that do not affect is organized in fatigue process toward the microstructure of multiple slip and can bears the reciprocating cutting effect that repeated stress drives dislocation, reduces repeated stress in fatigue process and accumulates the fatigue damage that pre-stretching plate produces.
Material Thermodynamics theory shows, in pre-stretching plate ag(e)ing process, the a large amount of dislocations introduced by pre-tension deformation become the place of elementide segregation, and the elementide that alloy pretensioning plate is formed in ag(e)ing process and G.P. district all tend to segregation at these dislocation places.Because the formation in elementide and G.P. district is because a large amount of atomic migrations and diffusion produce, migration and the diffusion at a large amount of atom dispiration place will inevitably make a part of dislocation lose original dislocation behavior.Meanwhile, the heat activation in ag(e)ing process, also can make the dislocation generation sign dislocation in alloy pretensioning plate offset and disappear in slippage in crystal boundary, climb motion.This not only reduces the dislocation desity in alloy pre-stretching plate, decrease pre-stretching plate Dislocations and be organized in interaction with slip dislocation in fatigue process, and the fatigue damage to pre-stretching plate caused thus accumulates.
In sum, the present invention is by the institution of prescription of research alloy pre-stretching plate, the aging technique obtained can form the elementide and G.P. district that can be cut by dislocation in Al-Cu-Mg alloy pre-stretching plate, and the dislocation desity in reduction sheet material, reduce the damage accumulation of sheet material in fatigue process, the plasticity improving Al-Cu-Mg alloy pre-stretching plate and anti-fatigue performance.Be suitable for suitability for industrialized production.
Accompanying drawing explanation
Accompanying drawing 1 is that the natural aging state TEM of the Al-Cu-Mg alloy of embodiment 2 organizes.
Accompanying drawing 2 is that the 168 DEG C/0.5h artificial aging state TEM of the Al-Cu-Mg alloy of embodiment 9 organizes.
Accompanying drawing 3 is that the 150 DEG C/1h artificial aging state TEM of the Al-Cu-Mg alloy of embodiment 10 organizes.
Accompanying drawing 4 is that the 160 DEG C/120h peak value aging state TEM of the Al-Cu-Mg alloy of comparative example 1 organizes.
Accompanying drawing 5 is Al-Cu-Mg alloy pre-stretching plate fatigue crack growth rate curves in natural aging state of embodiment 2.
Accompanying drawing 6 is Al-Cu-Mg alloy pre-stretching plate fatigue crack growth rate curves at 168 DEG C/0.5h aging state of embodiment 9.
Accompanying drawing 7 is Al-Cu-Mg alloy pre-stretching plate fatigue crack growth rate curves at 150 DEG C/1h aging state of embodiment 10.
Accompanying drawing 8 is Al-Cu-Mg alloy pre-stretching plate fatigue crack growth rate curves at 160 DEG C/120h peak value aging state of comparative example 1.
Comparison diagram 1,2,3 and 4 can be known, after natural aging and artificial aging process in short-term, be elementide and the G.P district of Cu, Mg atom segregation formation, and the tissue after the process of peak value aging state is S ' transition strengthening phase in Al-Cu-Mg alloy.
Comparison diagram 5,6,7,8 can be known, Al-Cu-Mg pre-stretching plate is after owing artificial aging or natural aging in short-term, and fatigue crack growth rate obviously reduces.
Embodiment
Embodiment 1
Alloying constituent is: 3.35%Cu, 1.40%Mg, 0.70%Mn, 0.15%Zr, 0.03Ti, 0.0003%Be, 0.13%Fe, 0.04%Si, and surplus is aluminium.Carried out following thermal treatment process:
505 DEG C of solution treatment 40 minutes, through 2% pre-tension deformation, then at room temperature natural aging 96 hours, the mechanical property of sheet material is: tensile strength is 427MPa, and yield strength is 294MPa, and unit elongation is 17.8%; At △ K=25MPa*m
1/2time, da/dN=2.0E-03mm/cycle.
Embodiment 2
Alloying constituent is: 3.53%Cu, 1.60%Mg, 0.48%Mn, 0.10%Zr, 0.05Ti, 0.0006%Be, 0.13%Fe, 0.04%Si, and surplus is aluminium.Carried out following thermal treatment process:
Solution treatment 1 hour is carried out and shrend, then through 5% pre-tension deformation, then at room temperature natural aging 96 hours at 500 DEG C.Mechanical property under room temperature after this process: tensile strength is 424MPa, yield strength is 322.2MPa, and unit elongation is 16.8%; At △ K=25MPa*m
1/2time, da/dN=2.53E-03mm/cycle
Embodiment 3
Alloying constituent is: 3.85%Cu, 1.47%Mg, 0.40%Mn, 0.08%Zr, 0.07Ti, 0.0008%Be, 0.15%Fe, 0.05%Si, and surplus is aluminium.Carried out following thermal treatment process:
Solution treatment 2 hours is carried out and shrend, then through 10% pre-tension deformation, then at room temperature natural aging 96 hours at 485 DEG C.Mechanical property under room temperature after this process: tensile strength is 439.6MPa, yield strength is 355.9MPa, and unit elongation is 19.0%; At △ K=30MPa*m
1/2time, da/dN=4.83.E-03mm/cycle
Embodiment 4
Alloying constituent is: 3.71%Cu, 1.58%Mg, 0.47%Mn, 0.1%Zr, 0.06Ti, 0.0004%Be, 0.12%Fe, 0.05%Si, and surplus is aluminium.Carried out following thermal treatment:
Solution treatment 1 hour is carried out and shrend, then through 10% pre-tension deformation, then at room temperature natural aging 7 days at 505 DEG C.Mechanical property under room temperature after this process: tensile strength is 426.6MPa, yield strength is 345.9MPa, and unit elongation is 14.8%; At △ K=30MPa*m
1/2time, da/dN=4.46E-03mm/cycle
Embodiment 5
Alloying constituent is: 3.35%Cu, 1.45%Mg, 0.40%Mn, 0.12%Zr, 0.06Ti, 0.0007%Be, 0.13%Fe, 0.04%Si, and surplus is aluminium.Carried out following thermal treatment process:
Solution treatment is carried out 1 hour, then through 5% pre-tension deformation, then at room temperature natural aging 96 hours at 485 DEG C.Mechanical property under room temperature after this process: tensile strength is 446.0MPa, yield strength is 315MPa, and unit elongation is 19.4%; At △ K=25MPa*m
1/2time, da/dN=1.0E-03mm/cycle.
Embodiment 6
Alloying constituent is: 3.73%Cu, 1.65%Mg, 0.58%Mn, 0.09%Zr, 0.05Ti, 0.0004%Be, 0.13%Fe, 0.04%Si, and surplus is aluminium.Carried out following thermal treatment process:
Solution treatment is carried out 0.5 hour, then through 5% pre-tension deformation, then at room temperature natural aging 96 hours at 495 DEG C.Mechanical property under room temperature after this process: tensile strength is 431.0MPa, yield strength is 343.8MPa, and unit elongation is 18.9%; , at △ K=30MPa*m
1/2time, da/dN=3.56E-03mm/cycle.
Embodiment 7
Alloying constituent is: 3.40%Cu, 1.47%Mg, 0.41%Mn, 0.13%Zr, 0.05Ti, 0.0006%Be, 0.12%Fe, 0.03%Si, and surplus is aluminium.Carried out following thermal treatment process:
Solution treatment is carried out 1 hour, then through 10% pre-tension deformation, then at room temperature natural aging 96 hours at 495 DEG C.Mechanical property under room temperature after this process: tensile strength is 456.7MPa, yield strength is 356.6MPa, and unit elongation is 19.8%; At △ K=30MPa*m
1/2time, da/dN=3.79E-03mm/cycle.
Embodiment 8
Alloying constituent is: 3.71%Cu, 1.58%Mg, 0.42%Mn, 0.10%Zr, 0.03Ti, 0.0006%Be, 0.12%Fe, 0.05%Si, and surplus is aluminium.Carried out following thermal treatment:
Solution treatment is carried out 1 hour, then through 10% pre-tension deformation, then at room temperature natural aging 96 hours at 495 DEG C.Mechanical property under room temperature after this process: tensile strength is 438.3MPa, yield strength is 385.8MPa, and unit elongation is 19.9%; At △ K=30MPa*m
1/2time, da/dN=2.77E-03mm/cycle.
Embodiment 9
Alloying constituent is: 3.50%Cu, 1.50%Mg, 0.52%Mn, 0.1%Zr, 0.07Ti, 0.0008%Be, 0.13%Fe, 0.04%Si, and surplus is aluminium.Carried out following thermal treatment process:
Solution treatment is carried out 0.5 hour, then through 5% pre-tension deformation, then 168 DEG C of timeliness 0.5 hour at 505 DEG C.Mechanical property under room temperature after this process: tensile strength is 447.0MPa, yield strength is 362.0MPa, and unit elongation is 20.7%; At △ K=30MPa*m
1/2time, da/dN=2.0E-03mm/cycle.
Embodiment 10
Alloying constituent is: 3.60%Cu, 1.80%Mg, 0.45%Mn, 0.11%Zr, 0.04Ti, 0.0006%Be, 0.13%Fe, 0.04%Si, and surplus is aluminium.Carried out following thermal treatment process:
Solution treatment is carried out 1.5 hours, then through 5% pre-tension deformation, then 150 DEG C of timeliness 1 hour at 485 DEG C.Mechanical property under room temperature after this process: tensile strength is 445MPa, yield strength is 367MPa, and unit elongation is 19.7%; At △ K=30MPa*m
1/2time, da/dN=2.5E-03mm/cycle.
Embodiment 11
Alloying constituent is: 3.55%Cu, 1.45%Mg, 0.5%Mn, 0.12%Zr, 0.06Ti, 0.0007%Be, 0.13%Fe, 0.04%Si, and surplus is aluminium.Carried out following thermal treatment process:
Solution treatment is carried out 1 hour, then through 5% pre-tension deformation, then 120 DEG C of timeliness 4 hours at 495 DEG C.Mechanical property under room temperature after this process: tensile strength is 435MPa, yield strength is 337MPa, and unit elongation is 23.7%; At △ K=30MPa*m
1/2time, da/dN=2.25E-03mm/cycle.
Comparative example 1
Alloying constituent is: 3.85%Cu, 1.75%Mg, 0.5%Mn, 0.12%Zr, 0.06Ti, 0.13%Fe, 0.14%Si, and surplus is aluminium.Carried out following thermal treatment process:
Solution treatment is carried out 1 hour, then through 5% pre-tension deformation, then 160 DEG C of timeliness 120 hours at 495 DEG C.Mechanical property under room temperature after this process: tensile strength is 495MPa, yield strength is 437MPa, and unit elongation is 9.0%; At △ K=28MPa*m
1/2time, da/dN > 5.0E-03mm/cycle.
The mechanical property contrast of table 1 alloy of the present invention
| Example | σ b/MPa | σ 0.2/MPa | δ/% | da/dN（mm/cycle） |
| Embodiment 1 | 427.0 | 294.0 | 17.8 | (△K=25MPa*m 1/2)0.002 |
| Embodiment 2 | 424.0 | 322.2 | 14.8 | (△K=25MPa*m 1/2)0.00283 |
| Embodiment 3 | 439.6 | 355.9 | 19.0 | (△K=30MPa*m 1/2)0.00483 |
| Embodiment 4 | 426.6 | 345.9 | 14.8 | (△K=30MPa*m 1/2)0.00446 |
| Embodiment 5 | 446.0 | 315.0 | 19.4 | (△K=25MPa*m 1/2)0.001 |
| Embodiment 6 | 431.0 | 343.8 | 18.9 | (△K=30MPa*m 1/2)0.00356 |
| Embodiment 7 | 456.7 | 356.6 | 19.8 | (△K=30MPa*m 1/2)0.00379 |
| Embodiment 8 | 438.3 | 385.8 | 19.9 | (△K=30MPa*m 1/2)0.00277 |
| Embodiment 9 | 447.0 | 362.0 | 20.7 | (△K=30MPa*m 1/2)0.00200 |
| Embodiment 10 | 445.0 | 367.0 | 19.7 | (△K=30MPa*m 1/2)0.00250 |
| Embodiment 11 | 435.0 | 337.0 | 23.7 | (△K=30MPa*m 1/2)0.00225 |
| Comparative example 1 | 495.0 | 437.0 | 9.0 | (△K=27MPa*m 1/2)＞0.0050 |
Thermal treatment process provided by the invention not only increases the plasticity of alloy pretensioning plate as can be seen from Table 1, and significantly improves the anti-fatigue performance of alloy, widens its range of application.
Claims (3)
1. improve the thermal treatment process of aluminum alloy solution state pretensioning plate anti-fatigue performance, be by solution treatment and carry out artificial aging through the aluminum alloy plate materials of pre-tension deformation after shrend; Described artificial aging processing parameter is: Heating temperature 120-168 DEG C, soaking time 30-240 minute;
Aluminum alloy plate materials comprises following component, forms by weight percentage: Cu 3.35-3.85%, Mg 1.40-1.80%, Mn 0.40-0.70%, Zr 0.08-0.16%, Ti0.03-0.07%, Be0.0003-0.0008%, Fe≤0.15%, Si≤0.05% surplus is aluminium.
2. the thermal treatment process of raising aluminum alloy solution state pretensioning plate anti-fatigue performance according to claim 1, is characterized in that: solid solution treatment process is: 485-505 DEG C/0.5-2 hour.
3. raising aluminum alloy solution state pretensioning plate fatigue resistance according to claim 1
The thermal treatment process of energy, is characterized in that: pre-tension deformation technique is: room temperature tensile after solid solution
Distortion 2-10%.
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| CN104694858A (en) * | 2015-02-12 | 2015-06-10 | 湖南大学 | Hot working method capable of simultaneously improving electrical conductivity and strength of aluminum alloy |
| CN107119246B (en) * | 2017-04-27 | 2019-01-25 | 中南大学 | A method of improving the magnesium alloy hot forming of Mg-Al-Zn system and military service performance |
| CN109576543B (en) * | 2019-01-18 | 2020-09-01 | 中南大学 | Method for improving long-time service life of magnesium alloy by baking |
| CN110527808B (en) * | 2019-08-26 | 2021-05-18 | 武汉科技大学 | Low-temperature residual stress regulation and control method for hot-rolled high-strength strip steel |
| CN110952011B (en) * | 2019-11-22 | 2021-01-05 | 天津忠旺铝业有限公司 | 2-series high-damage-tolerance aluminum alloy plate and preparation method thereof |
| CN112030085B (en) * | 2020-08-06 | 2022-05-06 | 中南大学 | Al-Cu-Mg-Si series alloy deformation heat treatment process |
| CN115110012B (en) * | 2022-06-20 | 2023-10-20 | 中国航发北京航空材料研究院 | Preparation method of 2024 aluminum alloy sheet for chemically-milled parts of aircraft |
| CN115945873B (en) * | 2023-03-09 | 2023-06-13 | 太原理工大学 | Method for improving fatigue performance of material by compounding pre-stretching and surface mechanical rolling |
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