CN103924180A - Thermal treatment method for TC18 titanium alloy - Google Patents
Thermal treatment method for TC18 titanium alloy Download PDFInfo
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 55
- 238000007669 thermal treatment Methods 0.000 title claims abstract description 38
- 238000000034 method Methods 0.000 title abstract description 27
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 47
- 239000000956 alloy Substances 0.000 claims abstract description 47
- 238000001816 cooling Methods 0.000 claims abstract description 43
- 230000007704 transition Effects 0.000 claims abstract description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 3
- 238000009413 insulation Methods 0.000 claims description 25
- 239000002131 composite material Substances 0.000 claims description 6
- 238000005242 forging Methods 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 4
- 239000011159 matrix material Substances 0.000 claims description 3
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- 239000007787 solid Substances 0.000 abstract description 13
- 230000008569 process Effects 0.000 abstract description 11
- 238000000137 annealing Methods 0.000 abstract description 7
- 239000000463 material Substances 0.000 abstract description 7
- 230000032683 aging Effects 0.000 abstract description 4
- 230000009977 dual effect Effects 0.000 abstract 1
- 230000001105 regulatory effect Effects 0.000 abstract 1
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- 230000000052 comparative effect Effects 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000001568 sexual effect Effects 0.000 description 3
- 238000000354 decomposition reaction Methods 0.000 description 2
- 230000008570 general process Effects 0.000 description 2
- 238000002791 soaking Methods 0.000 description 2
- 102100035593 POU domain, class 2, transcription factor 1 Human genes 0.000 description 1
- 101710084414 POU domain, class 2, transcription factor 1 Proteins 0.000 description 1
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- 238000009776 industrial production Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
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- 230000000630 rising effect Effects 0.000 description 1
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Abstract
The invention relates to a thermal treatment process for a TC18 titanium alloy and belongs to the technical field of materials. A method comprises the following steps: preserving heat of the TC18 titanium alloy at the temperature between Tbeta-60 DEG C and Tbeta-100 DEG C (Tbeta is the beta-phase transition temperature of the alloy) for 2-8 hours, and cooling to the room temperature through air cooling or water cooling; aging the alloy at the temperature of 540-600 DEG C for 4-12 hours, and cooling to the room temperature through air cooling. By selecting the heat-preserving temperature, time and cooling way, the microscopic structure of the alloy can be regulated and controlled effectively, a microscopic structure in which an equiaxial phase alpha (the content is higher than 10 percent by volume, and the size is greater than 2 microns), a flaky phase alpha (the thickness is greater than 0.5 micron) as well as a large number of fine needle phase-alpha and phase-beta substrates are matched is realized, the TC18 titanium alloy is high in strength, plasticity and toughness, and the problems of poor alloy strength in a dual annealing process and difficulty in meeting the use requirements on the plasticity and toughness of the alloy in a solid solution-aging process are solved. The method is suitable for industrial application.
Description
Technical field
The invention discloses a kind of TC18 titanium alloy thermal treatment method, belong to metallic substance heat treatment technics field.
Background technology
TC18 titanium alloy nominal composition is Ti-5Al-5V-5Mo-1Cr-1Fe, belongs near β type titanium alloys, has that viscous deformation is good, hardening capacity is dark, the high (σ of intensity
b>=1100MPa), the high (K of fracture toughness property
1C>=50MPam
1/2) etc. advantage, be applicable to manufacturing the aerospace component of high capacity load, be subject to extensive concern at aerospace field.In recent years, TC18 titanium alloy, because of its superior performance, increases gradually in the application in the fields such as boats and ships, sea water desaltination, automotive industry, physical culture.
Thermal treatment has vital role to the regulation and control of TC18 titanium alloy microstructure and mechanical property.The microstructure of TC18 titanium alloy is mainly by α phase and β phase composite, and wherein α is mutually as main strengthening phase, and the mechanical property of its pattern, content and size alloy has very important impact.For example phase content such as α such as axle such as grade is higher, size is larger, and alloy plasticity is better; The fine needle α of high level is conducive to significantly improve alloy strength mutually; The increase of thick sheet α phase content and thickness is conducive to improve alloy fracture toughness etc.Therefore, formulate suitable thermal treatment process, the microscopic feature such as content and size of regulation and control different-shape α phase, makes product obtain the mechanical property that meets service requirements, in the production process of TC18 alloy, has vital role.
At present the conventional thermal treatment process of TC18 titanium alloy has two kinds of double annealing and solid solution-timeliness.Double annealing is by Russian OCT1 specification recommends, and its general process is: 740～760 DEG C of insulation 1～3h → air cooling → 500～650 of 820～850 DEG C of insulation 1～3h → cool to the furnace DEG C insulation 2～6h → air cooling.TC18 alloy microscopic structure after double annealing is mainly by waiting axle α, thick sheet α and β matrix composition, and alloy has good plasticity (δ>=14%) and fracture toughness property (K
1C>=70MPam
1/2), in industrial production, be widely used.But double annealing process comprises holding stage three times, after insulation, adopt stove cold especially for the first time, whole technological process is longer, and is being difficult to ensure card aspect the accuracy of technology controlling and process, consistence; Particularly after double annealing, the fine needle α phase content in alloy microscopic structure is lower, causes tensile strength and yield strength generally lower than 1200MPa, is difficult to meet more high-intensity service requirements.Therefore, solid solution-aging technique more and more receives publicity in recent years.
Solid solution-timeliness general process is: T
βnear-150 DEG C, be incubated 1～3h → quenching → 400～600 DEG C insulation 2～6h → air cooling.Compared with double annealing, solid solution-timeliness only needs twice insulation, and adopts shrend cooling after insulation for the first time, therefore its technological process is shorter; Meanwhile, in the TC18 alloy microscopic structure after solid solution-timeliness, contain the fine needle α phase that a large amount of disperses distribute, make the tensile strength of alloy and yield strength significantly improve (>=1250MPa), can meet more high-intensity service requirements.But, in the alloy microscopic structure after solid solution-timeliness, wait axle α phase lower with the content of thick sheet α phase, cause the plasticity of alloy and fracture toughness property poor, be often difficult to meet elongation>=6%, fracture toughness property>=55MPam
1/2russian OCT190173-75 standard-required; In addition, existing solid solution-aging technique has only been considered the impact of thermal treatment temp alloy tissue and performance mostly, and considers less to the parameter such as soaking time, the type of cooling.Therefore, on the basis of solid solution-aging technique, consider the impact of multiple parameters such as temperature, time and the type of cooling, develop and a kind ofly not only ensured TC18 titanium alloy high strength, but also to make the thermal treatment process of alloy plasticity and tough sexual satisfaction service requirements be one of new direction of this alloy.
Summary of the invention
The object of the present invention is to provide a kind of TC18 titanium alloy thermal treatment process, the present invention's TC18 titanium alloy after treatment, not only there is higher intensity, and overcome traditional double reannealing technique and exist the lower and solid solution-aging technique of alloy strength to be difficult to make the problem of alloy plasticity and tough sexual satisfaction service requirements.
The present invention relates to a kind of TC18 titanium alloy thermal treatment process, comprise the steps:
The first step: one-level thermal treatment
Forging state TC18 titanium alloy is heated to β phase transition temperature T
βafter 60 DEG C below～100 DEG C insulation 2～8h, be cooled to room temperature with the speed of cooling of 2～20 DEG C/s; Described Duan Tai TC18 titanium alloy microstructure is matrix mutually by β and waits axle α phase composite;
Second step: secondary thermal treatment
The alloy obtaining after the first step is cooling is heated to 540 DEG C～600 DEG C, and after insulation 4～12h, air cooling is to room temperature.
The present invention relates to a kind of TC18 titanium alloy thermal treatment process, the nominal chemical composition of described forging state TC18 titanium alloy is: Ti-5Al-5Mo-5V-1Cr-1Fe.
The present invention relates to a kind of TC18 titanium alloy thermal treatment process, the volume fraction of the medium axle α of described Duan Tai TC18 titanium alloy microstructure phase is 28～35%, mean sizes is 3～5 μ m.
The present invention relates to a kind of TC18 titanium alloy thermal treatment process, after one-level thermal treatment insulation, alloy takes forced air-cooling or cooling by water to room temperature.
The present invention relates to a kind of TC18 titanium alloy thermal treatment process, the first step, is cooled to room temperature with the speed of cooling of 5～18 DEG C/s after one-level thermal treatment insulation; More preferably be cooled to room temperature with the speed of cooling of 8～15 DEG C/s; Optimum is that the speed of cooling of 10～12 DEG C/s is cooled to room temperature.
The present invention relates to a kind of TC18 titanium alloy thermal treatment process, in TC18 after treatment titanium alloy microstructure, the volume fraction that waits axle α phase is 10～18%, mean sizes is 2-5 μ m, and sheet α phase thickness is 0.5-1 μ m.
Compared with prior art, the invention has the advantages that:
(1) select the TC18 alloy of axle α phase (size 3～5 μ m, the about 30vol% of the content)+β phase matrixes such as initial structure is, the axle α that waits in tissue forms in thermal deformation process, and can put forward heavy alloyed plasticity.Therefore, select above-mentioned tissue to provide the foundation for content and the size of the axle α phases such as subsequent heat treatment regulation and control, thereby reach the object of regulation and control alloy plasticity.
(2) compared with traditional solid solution-aging technique, improve one-level thermal treatment temp, extend soaking time, make the content of the medium axle α of microstructure phase be greater than 10vol%, size is greater than 2 μ m, sheet α phase thickness is greater than 0.5 μ m, can ensure plasticity and the tough sexual satisfaction OCT190173-75 standard-required of alloy; Meanwhile, rising one-level thermal treatment temp can retain more metastable β phase, and then in follow-up ag(e)ing process, impels and separate out more fine needle α phases, improves alloy strength.
(3) type of cooling after one-level thermal treatment, has adopted water-cooled and forced air-cooling.Wherein: water-cooled can suppress the decomposition of metastable β in process of cooling, making in the heat treatment process of the second stage is significantly increased mutually by metastable β phase decomposition, the fine needle α that separates out, i.e. dispersion-strengthened effect strengthens, and makes alloy have higher intensity; Compared with water-cooled, although forced air-cooling speed of cooling is relatively slow, can make metastable β that decomposed occurs in process of cooling, cause that sheet α grows up mutually, thickening, and then only slightly reducing under the condition of alloy strength, put forward heavy alloyed fracture toughness property.
(4) compared with the aging temp of traditional technology, aging temp of the present invention is selected 540～600 DEG C of relatively high scopes, within the scope of this, can not only ensure fine needle α separating out in a large number in β crystal grain, make alloy there is higher intensity, and can impel the axle α phases such as a small amount of α depends on mutually to separate out mutually with sheet α, and make to wait content increase, the Size growth of axle α phase and sheet α phase, promote to a certain extent plasticity and the toughness of alloy.
In sum, compared with traditional solid solution aging technique, the present invention changes the impact of alloy microstructure and property by considering the parameters such as thermal treatment temp, time, the type of cooling, in can Effective Regulation alloy microtexture, wait axle α phase, thick sheet α phase and fine needle α phase content and size, the axle such as guarantee α phase content is greater than 10vol%, size is greater than 2 μ m, sheet α phase thickness is greater than 0.5 μ m, possess again the fine needle α phase of high level simultaneously, thereby make TC18 alloy possess higher intensity, and realize the matched well between intensity, plasticity and toughness; And technique simple and stable, easy to operate, treatment cycle is short, energy consumption is low, is suitable for suitability for industrialized production.
Brief description of the drawings
The microstructure of the TC18 titanium alloy that accompanying drawing 1 is prepared for embodiment 1.
The microstructure of the TC18 titanium alloy that accompanying drawing 2 is prepared for embodiment 2.
The microstructure of the TC18 titanium alloy that accompanying drawing 3 is prepared for embodiment 3.
The microstructure of the TC18 titanium alloy that accompanying drawing 4 is prepared for comparative example.
Scheming content and the size of medium axle α phase, sheet α phase and fine needle α phase is all added up and is determined by pixels statistics method.
Can find out from accompanying drawing 1: black is α phase mutually, and the volume fraction of its medium axle α phase is 12%, is of a size of 3～4 μ m, sheet α phase thickness approximately 1 μ m, fine needle α phase length is 2～3 μ m; White is β phase mutually.
Can find out from accompanying drawing 2: black is α mutually, and the volume fraction of its medium axle α phase is 16%, is of a size of 2～3 μ m, sheet α phase thickness approximately 0.5 μ m, fine needle α phase length is 2～4 μ m; White is β phase mutually.
Can find out from accompanying drawing 3: black is α mutually, and the volume fraction of its medium axle α phase is 15%, is of a size of 4～5 μ m, sheet α phase thickness approximately 1.5 μ m, fine needle α phase length is 1～2 μ m; White is β phase mutually.
Can find out from accompanying drawing 4: black is mutually for α, the volume fraction of its medium axle α phase is 9%, is of a size of 1～3 μ m, and fine needle α phase length is 1～3 μ m; White is β phase mutually.
Embodiment:
Below in conjunction with embodiment, the present invention will be further described.
Embodiment 1
The TC18 titanium alloy forge hot state bar that adopts Φ 120mm × 150mm, its microstructure is by axle α phase composites such as β Xiang He; Deng the volume fraction of axle α phase be 31%, mean sizes is 3～5 μ m.
The beta transus temperature of measuring TC18 titanium alloy forge hot state bar is 865 ± 5 DEG C.The first step is heated to alloy bar material after 760 DEG C of insulation 6h, and controlling speed of cooling is 2～3 DEG C/s, and forced air-cooling is to room temperature; Alloy bar material is heated to 540 DEG C of insulation 8h by second step, and then air cooling is to room temperature.
The present embodiment TC18 titanium alloy rod bar after treatment room-temperature mechanical property parameter is in table 1.
TC18 bar room-temperature mechanical property in table 1 example 1
Embodiment 2
The TC18 titanium alloy forge hot state bar that adopts Φ 180mm × 200mm, its microstructure is by axle α phase composites such as β Xiang He; Deng the volume fraction of axle α phase be 29%, mean sizes is 4-5 μ m.
The beta transus temperature of measuring TC18 titanium alloy forge hot state bar is 865 ± 5 DEG C.The first step is heated to alloy bar material after 790 DEG C of insulation 2h, and controlling speed of cooling is 15～20 DEG C/s, and water-cooled is to room temperature; Alloy bar material is heated to 570 DEG C of insulation 6h by second step, and then air cooling is to room temperature.
The present embodiment TC18 titanium alloy rod bar after treatment room-temperature mechanical property parameter is in table 2.
TC18 bar room-temperature mechanical property in table 2 embodiment 2
Embodiment 3
The TC18 titanium alloy forge hot state bar that adopts Φ 180mm × 200mm, its microstructure is by axle α phase composites such as β Xiang He; Deng the volume fraction of axle α phase be 33%, mean sizes is 2-4 μ m.
The beta transus temperature of measuring TC18 titanium alloy forge hot state bar is 865 ± 5 DEG C.The first step is heated to alloy bar material after 770 DEG C of insulation 4h, and controlling speed of cooling is 10～15 DEG C/s, and water-cooled is to room temperature; Alloy bar material is heated to 600 DEG C of insulation 4h by second step, and then air cooling is to room temperature.
The present embodiment TC18 titanium alloy rod bar after treatment room-temperature mechanical property parameter is in table 3.
TC18 bar room-temperature mechanical property in table 3 embodiment 3
Comparative example
Adopt the TC18 titanium alloy of Φ 140mm × 180mm to forge rod, the beta transus temperature of mensuration is 865 ± 5 DEG C.The first step is heated to alloy after 750 DEG C of insulation 2h, and water-cooled is to room temperature; Second step is heated to alloy after 530 DEG C of insulation 6h, and air cooling is to room temperature.
Comparative example TC18 titanium alloy rod bar after treatment room-temperature mechanical property parameter is in table 3.
TC18 bar room-temperature mechanical property in table 4 comparative example
Comparative example is to adopt traditional solid solution-aging technique to prepare the specific embodiments of TC18 alloy.
By the embodiment of the present invention and comparative example contrast, can find out from microstructure:
In embodiment, the content of fine needle α phase and sheet α phase, size are apparently higher than comparative example.
Can find from mechanical property:
In embodiment, the intensity of TC18 alloy and toughness are all better than comparative example, and plasticity is slightly poor, but still meet service requirements (> 6%).
Above examples prove TC18 titanium alloy of the present invention thermal treatment process is obviously better than traditional solid solution-aging technique.
Claims (8)
1. a TC18 titanium alloy thermal treatment process, comprises the steps:
The first step: one-level thermal treatment
Forging state TC18 titanium alloy is heated to β phase transition temperature T
βafter 60 DEG C below～100 DEG C insulation 2～8h, be cooled to room temperature with the speed of cooling of 2～20 DEG C/s; Described Duan Tai TC18 titanium alloy microstructure is matrix mutually by β and waits axle α phase composite;
Second step: secondary thermal treatment
The alloy obtaining after the first step is cooling is heated to 540 DEG C～600 DEG C, and after insulation 4～12h, air cooling is to room temperature.
2. a kind of TC18 titanium alloy thermal treatment process according to claim 1, is characterized in that: the nominal chemical composition of described forging state TC18 titanium alloy is: Ti-5Al-5Mo-5V-1Cr-1Fe.
3. a kind of TC18 titanium alloy thermal treatment process according to claim 2, is characterized in that: the volume fraction of the medium axle α of described Duan Tai TC18 titanium alloy microstructure phase is 28～35%, mean sizes is 3～5 μ m.
4. according to a kind of TC18 titanium alloy thermal treatment process described in claim 1,2 or 3, it is characterized in that: after one-level thermal treatment insulation, alloy takes forced air-cooling or cooling by water to room temperature.
5. a kind of TC18 titanium alloy thermal treatment process according to claim 4, is characterized in that: the first step, is cooled to room temperature with the speed of cooling of 5～18 DEG C/s after one-level thermal treatment insulation.
6. a kind of TC18 titanium alloy thermal treatment process according to claim 4, is characterized in that: the first step, is cooled to room temperature with the speed of cooling of 8～15 DEG C/s after one-level thermal treatment insulation.
7. a kind of TC18 titanium alloy thermal treatment process according to claim 4, is characterized in that: the first step, is cooled to room temperature with the speed of cooling of 10～12 DEG C/s after one-level thermal treatment insulation.
8. a kind of TC18 titanium alloy thermal treatment process according to claim 4, is characterized in that: in TC18 after treatment titanium alloy microstructure, the volume fraction that waits axle α phase is 10～18%, mean sizes is 2-5 μ m, and sheet α phase thickness is 0.5-1 μ m.
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104213060A (en) * | 2014-09-23 | 2014-12-17 | 西北有色金属研究院 | Heat treating method of TC4-DT titanium alloy bar |
| CN105935776A (en) * | 2016-06-24 | 2016-09-14 | 中国航空工业集团公司西安飞机设计研究所 | Composite manufacturing method for titanium alloy lug |
| CN106756694A (en) * | 2016-12-22 | 2017-05-31 | 贵州大学 | A kind of TA19 titanium alloys obtain the solid solution treatment process of half isometry tissue |
| CN109504875A (en) * | 2018-11-05 | 2019-03-22 | 贵州大学 | A kind of heat treatment method obtaining Ti alloy with high performance different levels tissue |
| CN110605456A (en) * | 2018-06-15 | 2019-12-24 | 天津大学 | Titanium alloy CMT-heat treatment composite additive manufacturing method |
| CN111270102A (en) * | 2020-03-25 | 2020-06-12 | 中国航空制造技术研究院 | Near β ultrahigh-strength titanium alloy with tensile strength of more than 1450MPa and preparation method thereof |
| CN111458360A (en) * | 2020-04-30 | 2020-07-28 | 中国航发北京航空材料研究院 | Preparation method of EBSD sample for Ti6242 bar two-phase texture determination |
| CN113416907A (en) * | 2021-07-01 | 2021-09-21 | 西北工业大学 | Grading heat treatment method for Ti555211 titanium alloy |
| CN113981346A (en) * | 2021-09-16 | 2022-01-28 | 攀枝花容则钒钛有限公司 | Heat treatment method of titanium alloy with beta-phase columnar crystal TC18 |
| CN114273672A (en) * | 2021-12-14 | 2022-04-05 | 攀枝花容则钒钛有限公司 | Preparation method of TC18 titanium alloy part |
| CN114273673A (en) * | 2021-12-14 | 2022-04-05 | 攀枝花容则钒钛有限公司 | Preparation method of TC18 titanium alloy part |
| CN115058673A (en) * | 2022-06-21 | 2022-09-16 | 湖南金天钛业科技有限公司 | Heat treatment method for regulating and controlling mechanical property matching and consistency of TC11 titanium alloy |
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| CN115725916A (en) * | 2021-08-26 | 2023-03-03 | 宝武特冶钛金科技有限公司 | Thermal treatment method of TC18 titanium alloy with high fracture toughness |
| CN115786767A (en) * | 2021-09-10 | 2023-03-14 | 中国石油天然气集团有限公司 | High-toughness titanium alloy oil pipe and heat treatment method thereof |
| CN115976441A (en) * | 2023-03-03 | 2023-04-18 | 中南大学 | Heat treatment method of TC18 titanium alloy |
| CN116005090A (en) * | 2023-01-06 | 2023-04-25 | 中国航空制造技术研究院 | Heat treatment process for improving toughness of 1500 MPa-level titanium alloy |
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| CN105935776A (en) * | 2016-06-24 | 2016-09-14 | 中国航空工业集团公司西安飞机设计研究所 | Composite manufacturing method for titanium alloy lug |
| CN106756694A (en) * | 2016-12-22 | 2017-05-31 | 贵州大学 | A kind of TA19 titanium alloys obtain the solid solution treatment process of half isometry tissue |
| CN106756694B (en) * | 2016-12-22 | 2018-07-03 | 贵州大学 | A kind of TA19 titanium alloys obtain the solid solution treatment process of half isometry tissue |
| CN110605456A (en) * | 2018-06-15 | 2019-12-24 | 天津大学 | Titanium alloy CMT-heat treatment composite additive manufacturing method |
| CN109504875A (en) * | 2018-11-05 | 2019-03-22 | 贵州大学 | A kind of heat treatment method obtaining Ti alloy with high performance different levels tissue |
| CN111270102A (en) * | 2020-03-25 | 2020-06-12 | 中国航空制造技术研究院 | Near β ultrahigh-strength titanium alloy with tensile strength of more than 1450MPa and preparation method thereof |
| CN111270102B (en) * | 2020-03-25 | 2021-09-10 | 中国航空制造技术研究院 | Near-beta ultrahigh-strength titanium alloy with tensile strength of more than 1450MPa and preparation method thereof |
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| CN111458360B (en) * | 2020-04-30 | 2023-08-04 | 中国航发北京航空材料研究院 | Preparation method of EBSD sample for measuring two-phase texture of Ti6242 bar |
| CN113416907A (en) * | 2021-07-01 | 2021-09-21 | 西北工业大学 | Grading heat treatment method for Ti555211 titanium alloy |
| CN113416907B (en) * | 2021-07-01 | 2022-08-23 | 西北工业大学 | Grading heat treatment method for Ti555211 titanium alloy |
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| CN115725916A (en) * | 2021-08-26 | 2023-03-03 | 宝武特冶钛金科技有限公司 | Thermal treatment method of TC18 titanium alloy with high fracture toughness |
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| CN114273673B (en) * | 2021-12-14 | 2024-03-15 | 攀枝花容则钒钛有限公司 | Preparation method of TC18 titanium alloy part |
| CN114273672A (en) * | 2021-12-14 | 2022-04-05 | 攀枝花容则钒钛有限公司 | Preparation method of TC18 titanium alloy part |
| CN114273672B (en) * | 2021-12-14 | 2024-03-15 | 攀枝花容则钒钛有限公司 | Preparation method of TC18 titanium alloy part |
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| CN116005090A (en) * | 2023-01-06 | 2023-04-25 | 中国航空制造技术研究院 | Heat treatment process for improving toughness of 1500 MPa-level titanium alloy |
| CN115976441A (en) * | 2023-03-03 | 2023-04-18 | 中南大学 | Heat treatment method of TC18 titanium alloy |
| CN115976441B (en) * | 2023-03-03 | 2023-05-12 | 中南大学 | Heat treatment method of TC18 titanium alloy |
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