CN115874128A - Heat treatment method for annealing and low-temperature aging of TA15 forge piece - Google Patents
Heat treatment method for annealing and low-temperature aging of TA15 forge piece Download PDFInfo
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- CN115874128A CN115874128A CN202211588388.2A CN202211588388A CN115874128A CN 115874128 A CN115874128 A CN 115874128A CN 202211588388 A CN202211588388 A CN 202211588388A CN 115874128 A CN115874128 A CN 115874128A
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- 238000000137 annealing Methods 0.000 title claims abstract description 41
- 230000032683 aging Effects 0.000 title claims abstract description 38
- 238000010438 heat treatment Methods 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000001816 cooling Methods 0.000 claims abstract description 41
- 238000005242 forging Methods 0.000 claims abstract description 34
- 238000007599 discharging Methods 0.000 claims abstract description 10
- 230000008569 process Effects 0.000 claims description 5
- 239000007769 metal material Substances 0.000 abstract description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 7
- 230000000694 effects Effects 0.000 description 7
- 230000009467 reduction Effects 0.000 description 5
- 238000005728 strengthening Methods 0.000 description 5
- 239000013078 crystal Substances 0.000 description 4
- 238000001953 recrystallisation Methods 0.000 description 4
- 229910045601 alloy Inorganic materials 0.000 description 3
- 239000000956 alloy Substances 0.000 description 3
- 238000004321 preservation Methods 0.000 description 3
- 238000000354 decomposition reaction Methods 0.000 description 2
- 238000009776 industrial production Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
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- 230000008439 repair process Effects 0.000 description 2
- 238000010079 rubber tapping Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002431 foraging effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
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- 239000000126 substance Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention belongs to the field of heat treatment of metal materials, and particularly relates to a heat treatment method for annealing and low-temperature aging of a TA15 forge piece. The method comprises the following steps: the method comprises the following steps: annealing the formed TA15 forging: heating the TA15 forging to 850-870 ℃, preserving heat for 1-4 h, discharging from a furnace, and performing dispersed air cooling or dispersed air cooling; step two: and (3) carrying out low-temperature aging on the annealed forging: heating the annealed forge piece to 560-580 ℃, preserving heat for 2.5-4 h, discharging and cooling.
Description
Technical Field
The invention belongs to the field of heat treatment of metal materials, and particularly relates to a heat treatment method for annealing and low-temperature aging of a TA15 forge piece.
Background
The TA15 titanium alloy has the nominal component of Ti-6Al-2Zr-1Mo-1V, belongs to near-alpha type titanium alloy, has medium strength and good comprehensive performance, has a strengthening mechanism of solid solution strengthening of Al and other elements, and is mainly used for manufacturing various blades and casings of engines, various sheet metal parts of airplanes, beams, joints, large-scale wall plates, welding bearing frames and the like. The heat treatment state of the TA15 titanium alloy forging is generally common annealing, the strengthening effect is very limited, and in the production of some large-size TA15 titanium alloy forgings, the allowance of the product performance is often small or the performance can not meet the standard requirement after only common annealing is adopted.
Disclosure of Invention
The purpose of the invention is as follows: the TA15 forging treated by the method has a microstructure meeting the requirements, can greatly improve the strength, finally obtains the strength index and the toughness index meeting the requirements, and solves the problem that the existing performance can not meet the standard requirements.
The technical scheme is as follows:
a heat treatment method for annealing and low-temperature aging of a TA15 forge piece comprises the following steps:
the method comprises the following steps: annealing the formed TA15 forging:
heating the TA15 forge piece to 850-870 ℃, preserving heat for 1-4 h, discharging from the furnace, and dispersing and air-cooling or dispersing and air-cooling;
step two: and (3) carrying out low-temperature aging on the annealed forging:
heating the annealed forge piece to 560-580 ℃, preserving heat for 2.5-4 h, discharging and cooling.
Further, the heat preservation time of the annealing process in the step one is determined according to the effective thickness of the forged piece, and the heat preservation time is within 60min/1 inch.
Further, in step 1, the discharging and air cooling or the air cooling specifically comprises:
and when the effective thickness of the TA15 forging piece is less than or equal to 20mm, adopting scattered air cooling.
Further, in step 1, the discharging of the furnace is performed with dispersed air cooling or dispersed air cooling, and the method specifically comprises the following steps:
when the effective thickness of the TA15 forging is larger than 20mm, adopting dispersed air cooling.
Further, step two, tapping and cooling, specifically comprising:
and when the effective thickness of the TA15 forging piece is less than or equal to 20mm, air cooling is adopted.
Further, step two, tapping and cooling, specifically comprising:
and when the effective thickness of the TA15 forging is more than 20mm, adopting dispersed air cooling.
Further, in the first step, the cooling transfer time after annealing is not more than 60s.
Furthermore, in the second step, in the low-temperature aging process, the temperature rise time is less than or equal to 1.5h.
Has the advantages that:
the TA15 forged piece treated by the method has a microstructure meeting the requirements, and obtains the strength index and the toughness index meeting the requirements. The method can obtain the effects of greatly improving the tensile strength and the yield strength of the TA15 forge piece, ensuring that the elongation and the reduction of area are not changed greatly, reducing the impact property in a small range, and being simple and stable in process, convenient to operate and suitable for industrial production.
Detailed Description
The invention provides a heat treatment method for annealing and low-temperature aging of the TA15 forge piece, which makes clear regulations on annealing temperature, annealing duration, low-temperature aging temperature and low-temperature aging duration, greatly improves the strength of the TA15 forge piece, and finally achieves the effect of comprehensively improving the mechanical property of the TA15 forge piece.
The annealing temperature ranges currently determined in the current specifications are: keeping the temperature at 700-850 ℃ for 1-4 h, and cooling in air without the low-temperature aging system standard. The technical indexes determined by the specification are as follows: the tensile strength is 930-1130 MPa, the yield strength is more than or equal to 855MPa, the elongation is more than or equal to 10/8/7% (longitudinal/transverse/high), the reduction of area is more than or equal to 25/20/16% (longitudinal/transverse/high), and the impact performance is more than or equal to 40/30 (longitudinal/transverse).
Multiple times of verification proves that the low-temperature aging temperature is lower than 560 ℃, the strengthening effect is not ideal as that of 560-580 ℃, and when the temperature is higher than 580 ℃, the impact performance is greatly reduced and even the standard requirement is difficult to meet. When the duration of the low-temperature aging is less than 2.5 hours, the strengthening effect is not optimal, and when the duration is longer than 4 hours, the impact performance is greatly reduced, so that the duration of the low-temperature aging needs to be controlled to be between 2.5 and 4 hours most appropriately.
The invention provides a TA15 forge piece annealing and low-temperature aging heat treatment method which specifically comprises the following steps:
firstly, annealing the formed TA15 forge piece.
And heating the TA15 forging to 850-870 ℃ for annealing, and selecting a dispersing air cooling and air cooling mode according to different thicknesses, wherein crystal nuclei form at crystal boundary positions and grow to form crystal boundary beta in the crystal boundary areas, and the microstructure after air cooling or air cooling is a needle-shaped (alpha + beta) phase and a small amount of primary alpha phase.
The recrystallization starting temperature of the TA15 titanium alloy is about 800 ℃, and the final temperature is about 950 ℃, so that the phase recovery process mainly occurs when annealing is carried out at the temperature lower than 800 ℃, and recrystallization and phase decomposition are not carried out; when annealing is carried out at 800 ℃ or higher, in addition to recrystallization of the alpha phase and the beta phase, decomposition of metastable beta phase and precipitation of secondary alpha phase also occur; when the alloy is annealed at the temperature of above 850 ℃, the precipitation of needle-shaped secondary alpha phase can occur, so that the strength of the forged piece is improved, but when the temperature exceeds 870 ℃, the defects of accumulated dislocation accumulation and the like in the alloy disappear, so that the distortion energy is released, the comprehensive effect of the two is realized, the strength of the alloy is reduced, and the plasticity is further improved. Therefore, the method is suitable for annealing the forged piece at 850-870 ℃.
And secondly, performing 560-580 ℃ heat preservation on the annealed forge piece for 2.5-4 h, and performing air cooling at low temperature for aging.
The TA15 titanium alloy has the composition in the alpha + beta two-phase region, is not a generally considered near-alpha type titanium alloy, so that after being annealed at 850-870 ℃, the low-temperature aging is carried out at 560-580 ℃, and actually, the double annealing heat treatment is carried out, so that not only recrystallization but also phase composition change is generated. The lower the low-temperature aging temperature is, the finer the secondary alpha phase is, and the higher the strength of the forged piece is, but the TA15 forged piece generally has the requirements on plasticity and toughness, the tensile strength exceeds 1050MPa, and the yield strength exceeds 950MPa, which easily causes the situation that the toughness of the forged piece is greatly reduced, so the low-temperature aging temperature is not higher than 580 ℃ after multiple verifications; when the aging temperature is lower than 560 ℃, the strength improvement effect is not ideal, so that the low-temperature aging of 560-580 ℃ is increased after annealing the TA15 forge piece at 850-870 ℃, and the optimal matching of strength, plasticity and toughness can be realized at the same time.
In conclusion, the invention defines the heat treatment process parameters of annealing and low-temperature aging of the TA15 forge piece by comprehensively considering the influence of the parameters such as annealing temperature, annealing time, low-temperature aging temperature, low-temperature aging time and the like on the structure and the performance of the forge piece, can ensure that the TA15 forge piece obtains a qualified microstructure through parameter control, simultaneously greatly improves the tensile strength and the yield strength of the forge piece, basically keeps the elongation and the reduction of area constant, has small impact toughness and is reduced in a small amplitude, simple and stable in process and convenient to operate, and is suitable for industrial production.
Example one
In this embodiment, a long rod type die forging with a contour dimension of 1176 × 113 × 117 is used, and the annealing heat treatment system is as follows: dispersing air cooling at 870 deg.C for 240 min; the physicochemical property data after annealing are shown in Table 1.
TABLE 1
And (3) continuing to supplement low-temperature aging on the forging: the temperature is kept at 580 ℃ for 180min, air cooling is carried out, and data after repair are shown in table 2.
TABLE 2
After low-temperature aging at the supplementary low temperature of 580 ℃, the tensile strength is improved by 80-90 MPa, the yield strength is improved by about 60-100 MPa, the elongation and the reduction of area are not changed greatly, and the impact toughness is slightly reduced.
Example two
In this embodiment, a thin plate TA15 forging with an external dimension of 1001 × 430 × 44 is used, and the effective thickness thereof is: 44mm, and the annealing heat treatment system is as follows: the temperature is 850 ℃ multiplied by 240min, the physical and chemical performance data after air cooling and annealing are shown in table 3, and the yield strength is unqualified.
TABLE 3
And (3) supplementing low-temperature aging to the forging: keeping the temperature at 560 ℃ for 180min, cooling in air, and finding the data after repair as shown in Table 4.
TABLE 4
After the low-temperature aging at the supplementary low temperature of 560 ℃, the tensile strength is improved by 100-40 MPa, the yield strength is improved by about 40-70 MPa, the elongation and the reduction of area are not changed greatly, and the impact toughness is slightly reduced.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think of various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (8)
1. A heat treatment method for annealing and low-temperature aging of a TA15 forge piece is characterized by comprising the following steps:
the method comprises the following steps: annealing the formed TA15 forging:
heating the TA15 forging to 850-870 ℃, preserving heat for 1-4 h, discharging from a furnace, and performing dispersed air cooling or dispersed air cooling;
step (ii) of II, secondly: and (3) carrying out low-temperature aging on the annealed forging:
heating the annealed forge piece to 560-580 ℃, preserving heat for 2.5-4 h, discharging and cooling.
2. The TA15 forging annealing plus low temperature aging heat treatment method according to claim 1, wherein the holding time of the annealing process in the first step is determined according to the effective thickness of the forging, and is satisfied every 60min/1 inch.
3. The heat treatment method for annealing and low-temperature aging of the TA15 forging according to claim 1, wherein in the step 1, the TA15 forging is discharged to be dispersed for air cooling or air cooling, and specifically comprises the following steps:
and when the effective thickness of the TA15 forging piece is less than or equal to 20mm, adopting dispersed air cooling.
4. The heat treatment method for annealing and low-temperature aging of the TA15 forging according to claim 1, wherein in the step 1, the TA15 forging is discharged to be dispersed for air cooling or air cooling, and specifically comprises the following steps:
when the effective thickness of the TA15 forging is larger than 20mm, adopting scattered air cooling.
5. The heat treatment method for annealing and low-temperature aging of the TA15 forging according to claim 1, wherein the step II of discharging and cooling comprises the following steps:
and when the effective thickness of the TA15 forging piece is less than or equal to 20mm, air cooling is adopted.
6. The heat treatment method for annealing and low-temperature aging of the TA15 forging according to claim 1, wherein in the second step, the discharging and cooling specifically comprise:
and when the effective thickness of the TA15 forging is more than 20mm, adopting dispersed air cooling.
7. The heat treatment method for annealing and low-temperature aging of the TA15 forging according to claim 1, wherein in the first step, the cooling transfer time after annealing is less than or equal to 60s.
8. The heat treatment method for annealing and low-temperature aging of the TA15 forging according to claim 1, wherein in the second step, the temperature rise time is less than or equal to 1.5h in the low-temperature aging process.
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| CN202211588388.2A CN115874128B (en) | 2022-12-09 | 2022-12-09 | Heat treatment method for TA15 forging annealing and low-temperature aging |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100065158A1 (en) * | 2008-09-18 | 2010-03-18 | Sheehan Kevin C | Solution heat treatment and overage heat treatment for titanium components |
| CN106591754A (en) * | 2016-12-12 | 2017-04-26 | 陕西宏远航空锻造有限责任公司 | Forging method using flat-die hammer to improve structure property of TC21 titanium alloy |
| CN109226622A (en) * | 2018-09-18 | 2019-01-18 | 西安三角防务股份有限公司 | A kind of TA15 titanium alloy forging forging forming method with high-intensity and high-tenacity |
| CN112662974A (en) * | 2020-12-18 | 2021-04-16 | 陕西宏远航空锻造有限责任公司 | Heat treatment method of TC21 alloy forging |
| CN112708839A (en) * | 2020-12-18 | 2021-04-27 | 陕西宏远航空锻造有限责任公司 | Heat treatment method of TC25 alloy forging |
| CN114618970A (en) * | 2022-03-14 | 2022-06-14 | 江西景航航空锻铸有限公司 | Forging process for improving strength of thick-section TA15 titanium alloy forging |
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2022
- 2022-12-09 CN CN202211588388.2A patent/CN115874128B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100065158A1 (en) * | 2008-09-18 | 2010-03-18 | Sheehan Kevin C | Solution heat treatment and overage heat treatment for titanium components |
| CN106591754A (en) * | 2016-12-12 | 2017-04-26 | 陕西宏远航空锻造有限责任公司 | Forging method using flat-die hammer to improve structure property of TC21 titanium alloy |
| CN109226622A (en) * | 2018-09-18 | 2019-01-18 | 西安三角防务股份有限公司 | A kind of TA15 titanium alloy forging forging forming method with high-intensity and high-tenacity |
| CN112662974A (en) * | 2020-12-18 | 2021-04-16 | 陕西宏远航空锻造有限责任公司 | Heat treatment method of TC21 alloy forging |
| CN112708839A (en) * | 2020-12-18 | 2021-04-27 | 陕西宏远航空锻造有限责任公司 | Heat treatment method of TC25 alloy forging |
| CN114618970A (en) * | 2022-03-14 | 2022-06-14 | 江西景航航空锻铸有限公司 | Forging process for improving strength of thick-section TA15 titanium alloy forging |
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