CN113249667B - Heat treatment method for obtaining high-toughness high-damage-tolerance dual-phase titanium alloy - Google Patents
Heat treatment method for obtaining high-toughness high-damage-tolerance dual-phase titanium alloy Download PDFInfo
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 59
- 238000000034 method Methods 0.000 title claims abstract description 38
- 238000010438 heat treatment Methods 0.000 title claims abstract description 34
- 238000001816 cooling Methods 0.000 claims abstract description 53
- 230000008569 process Effects 0.000 claims abstract description 21
- 239000000654 additive Substances 0.000 claims abstract description 16
- 230000000996 additive effect Effects 0.000 claims abstract description 16
- 238000004519 manufacturing process Methods 0.000 claims abstract description 16
- 238000005242 forging Methods 0.000 claims abstract description 13
- 238000000137 annealing Methods 0.000 claims abstract description 12
- 238000005266 casting Methods 0.000 claims abstract description 6
- 230000009977 dual effect Effects 0.000 claims abstract description 4
- 238000010791 quenching Methods 0.000 claims description 2
- 230000000171 quenching effect Effects 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 238000003672 processing method Methods 0.000 claims 2
- 230000006872 improvement Effects 0.000 abstract description 3
- 238000003466 welding Methods 0.000 abstract 1
- 230000000052 comparative effect Effects 0.000 description 16
- 239000000463 material Substances 0.000 description 13
- 230000009467 reduction Effects 0.000 description 10
- 239000000956 alloy Substances 0.000 description 9
- 230000007704 transition Effects 0.000 description 8
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- 229910045601 alloy Inorganic materials 0.000 description 4
- 230000009466 transformation Effects 0.000 description 3
- 241000446313 Lamella Species 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
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Abstract
The invention discloses a heat treatment method for obtaining a high-toughness high-damage tolerance dual-phase titanium alloy, which comprises the following steps of: the high-temperature annealing treatment comprises the following processes: t is1Keeping the temperature for 0.1 to 2 hours at the temperature, and coolingSpeed needs to be reasonably controlled, preferably from T1Cooling to TβThe temperature is controlled within the range of-200 ℃ to be 2-50 ℃/s, wherein T1Value range of Tβ-10 ℃ to TβT isβIs the beta transus temperature of the dual phase titanium alloy. The method realizes the improvement of the toughness and damage tolerance performance of the dual-phase titanium alloy by controlling the heat treatment temperature and the cooling speed. The method can be used for the two-phase titanium alloy with two tissues under the room temperature conditions of TC11, TA15, TC4, TC17, TC18 and the like, is not limited by the original manufacturing process of the titanium alloy, and is suitable for the two-phase titanium alloy forging, casting, welding and additive manufacturing.
Description
Technical Field
The invention relates to the field of titanium alloy, in particular to a heat treatment method for obtaining high-toughness high-damage-tolerance double-phase titanium alloy.
Background
Based on the damage tolerance design concept of safe use of the structure, the structural materials such as titanium alloy and the like are developed towards the directions of high toughness and high damage tolerance, and the high-toughness high-damage tolerance titanium alloy becomes the key point of research in the field of titanium alloy. The most widely used high-toughness high-damage tolerance titanium alloy in foreign countries is TC4ELI, the most widely used high-toughness high-damage tolerance titanium alloy in China is TC4DT, the high-toughness high-damage tolerance titanium alloy is mainly characterized by high-toughness and high-damage tolerance characteristics obtained by reducing elements such as oxygen, nitrogen and the like, the alloy strength is reduced due to the reduction of the elements such as oxygen and nitrogen, and the ultimate strength is less than 900 MPa. Because the strength of the titanium alloy is improved mainly by the increase of alloy elements, the toughness and damage tolerance performance of the titanium alloy with high alloy element content are always poor, and the strength, the toughness and the damage tolerance performance are difficult to be considered. Therefore, the concept of adjusting the damage tolerance of titanium alloys by composition has significant limitations. From the development requirements of light weight and high reliability of a bearing structure, the toughness and damage tolerance performance improvement of the medium-high strength titanium alloy has important application value under the condition of not changing components, can obviously improve the safety of the structure, and has the potential of reducing the weight of the structure.
Disclosure of Invention
The invention aims to provide a method for improving the toughness and damage tolerance performance of a dual-phase titanium alloy without changing components. The method obtains a full-lamellar double-state structure consisting of strip primary alpha-phase and beta-phase transformation structures through special high-temperature annealing heat treatment, thereby realizing the improvement of the toughness and damage tolerance performance of the double-phase titanium alloy, and the fracture toughness of the double-phase titanium alloyK ICThe fatigue crack propagation rate da/dN can be improved by more than 30 percent, the fatigue crack propagation rate da/dN is reduced in a steady-state region, the fatigue safety of the structure can be obviously improved, and the method is suitable for being used in a key force-bearing component designed in damage tolerance. The method can be used for the two-phase titanium alloy with two structures under the room temperature conditions of TC11, TA15, TC4, TC17, TC18 and the like, is not limited by the original manufacturing process of the titanium alloy, and is used for forging and casting the two-phase titanium alloyWelding parts and additive manufacturing parts are all suitable.
The technical scheme of the invention is specifically that a heat treatment method for obtaining the high-toughness high-damage tolerance dual-phase titanium alloy comprises the following steps: the high-temperature annealing treatment comprises the following processes: t is1Keeping the temperature for 0.1-2 hours at the temperature, then cooling, wherein the cooling speed is controlled between furnace cooling and water quenching, specifically from T1Cooling to TβThe cooling speed is controlled within the range of minus 200 ℃ to be 2-50 ℃/s, wherein T1Value range of Tβ-10 ℃ to TβT isβIs the beta transus temperature of the dual phase titanium alloy.
Further preferably, T is1Value range of Tβ-4 ℃ to TβIn the meantime.
More preferably, the cooling speed is controlled to be 5-20 ℃/second.
Further preferably, the heat treatment method does not perform low-temperature annealing heat treatment after the high-temperature annealing treatment.
Further preferably, for the original structure containing equiaxed primary phases, the pretreatment is performed before the high-temperature annealing treatment, and the pretreatment process comprises the following steps: at T2Keeping the temperature for 0.5 to 2 hours at the temperature, then cooling, and performing T2Cooling to TβIn the temperature range of-200 ℃, the cooling speed is controlled to be not less than 50 ℃/s, wherein T2The temperature value range is TβTo Tβ+10 ℃.
Further preferably, T is2Value range of TβDEG C to Tβ+5 ℃.
Further preferably, the cooling rate is controlled to be not less than 50 ℃/s, specifically, the cooling rate is controlled to be at 100-.
Further preferably, the titanium alloy to be treated is a forging, casting, weld or additive manufacturing of TC11, TA15, TC4, TC17 or TC 18.
Wherein, T1The temperature influences the content of primary phase and secondary transformation tissue in the heat-treated tissue, provides conditions for controlling the size of the primary phase and the secondary phase, and controls coolingThe velocity is to obtain the morphology of the primary and secondary phases. T is1Temperature selection near TβIn the two-phase region of (1), T1Exceeding the point of phase transformation results in coarsening of the original lamellar structure and grains, which adversely affects performance, T1At TβAway from TβIn the tissue, the content of primary phases of the lamellar layers is too high, the content of secondary phases is reduced, and the matching of fracture toughness and damage tolerance performance is poor. The cooling speed is controlled at a high temperature section at a medium and high cooling speed to obtain a fine secondary lamellar structure, the thickness of the secondary lamellar structure is increased and the size of the primary phase is increased if the cooling speed is too low, the thickness of the secondary photo is reduced if the cooling speed is too high, and the toughness of the alloy is reduced, so that the proper cooling speed needs to be controlled. T is2The temperature is controlled to be T mainly for obtaining the proper size of the pretreated beta grainsβAbove 10 ℃, and over high, the beta crystal grain size is obviously grown, the plasticity and the strength of the material are reduced and are lower than TβThe original equiaxed primary phase structure cannot be altered. The cooling speed of the pretreatment is not less than 50 ℃/s, the lamella size is larger due to too low pretreatment, the size of a primary phase is large during subsequent treatment, a thinner initial lamella tissue is difficult to obtain, and the toughness and the matching of the material are poor after high-temperature heat treatment.
Compared with the prior art, the invention has the beneficial effects that: the heat treatment method provided by the invention is used for obtaining a full lamellar structure with flaky primary alpha phase and superfine lamellar secondary alpha/beta, the full lamellar structure is different from a traditional duplex titanium alloy widmannstatten structure and a basket structure, the primary lamellar structure and the secondary lamellar structure are matched in thickness, the orientation is rich, the crack expansion is obviously hindered, the secondary alpha/beta clusters are small in size and different in orientation among different clusters, so that the crack expansion path is tortuous during the period, the structure has higher fracture toughness and lower fatigue crack expansion rate than a traditional titanium alloy duplex structure, and the toughness and damage tolerance performance of the duplex titanium alloy are obviously improved.
In addition, the method does not change the components of the titanium alloy, is suitable for the two-phase titanium alloy, can ensure that the medium-high strength titanium alloy obtains high toughness and high damage tolerance performance, does not change the components of the titanium alloy, and is suitable for being used in key bearing members designed in the damage tolerance.
Detailed Description
The following will specifically describe the technical solutions by taking the embodiments of the present invention as examples.
Example 1
The material of the embodiment is TC11 titanium alloy manufactured by additive manufacturing, the maximum thickness of the manufactured product is 20mm, and the beta transition temperature T of the manufactured product isβAt 1010 ℃, the following high-temperature heat treatment process is adopted: keeping the temperature at 1007 ℃ for 0.5 hour, and controlling the cooling speed to be 20 +/-5 ℃/second within the temperature range of cooling to 800 ℃. Additive manufacturing TC11 titanium alloy material after treatment and room temperature strength Rm1070 MPa; room temperature fracture toughnessK ICIs 115 MPa.m1/2About 53% higher than before treatment; the fatigue crack propagation rate da/dN is significantly reduced in the steady state region compared to that before the treatment, when ΔK=15 MPa·m1/2The da/dN reduction is about 53%.
Example 2
The material of the embodiment is TC11 titanium alloy forging with the maximum thickness of 40mm and the beta transition temperature TβThe temperature is 1010 ℃, the original structure is a forging duplex structure, and the following pretreatment process is adopted: keeping the temperature at 1020 ℃ for 1 hour, and controlling the cooling speed to be 150 +/-20 ℃/second; then carrying out high-temperature heat treatment, wherein the high-temperature heat treatment process comprises the following steps: keeping the temperature at 1007 ℃ for 0.5 hour, and controlling the cooling speed to be 20 +/-5 ℃/second in the temperature range of cooling from high temperature to 800 ℃. The treated TC11 titanium alloy forging has room temperature strength Rm1060MPa, room temperature fracture toughnessK ICIs 105MPa · m1/2About 38% higher than before treatment; the fatigue crack propagation rate da/dN is significantly reduced in the steady state region compared to that before the treatment, when ΔK=15 MPa·m1/2The da/dN reduction is about 39%.
Example 3
The material of the embodiment is TC4 titanium alloy casting with the maximum thickness of 18mm and the beta transition temperature TβAt 995 ℃, the original structure is a Widmannstatten structure, and the following high-temperature heat treatment process is adopted: 992 ℃, keeping the temperature for 1 hour, and controlling the cooling speed to be 30 +/-5 ℃/second in the temperature range of cooling the high temperature to 790 ℃. Treated TC4 castings, Room temperature Strength Rm905MPa, room temperature fracture toughnessK ICIs 90.5 MPa.m1/2About 15% higher than before treatment; the fatigue crack propagation rate is significantly reduced in the steady state region as compared to before treatment, whenK=15 MPa·m1/2The da/dN reduction is about 28%.
Example 4
The material of the embodiment is additive manufacturing TA15 titanium alloy, the maximum thickness of which is 30mm, and the beta transition temperature T of whichβThe temperature is 1005 ℃, the original structure is Widmannstatten structure, and the following high-temperature heat treatment process is adopted: keeping the temperature at 1000 ℃ for 1 hour, and controlling the cooling speed to be 20 +/-5 ℃/second in the temperature range of cooling from high temperature to 800 ℃. Additive manufacturing TA15 titanium alloy after treatment, Room temperature Strength Rm985MPa, room temperature fracture toughnessK ICIs 95.8 MPa.m1/2About 34% higher than before treatment; the fatigue crack propagation rate is significantly reduced in the steady state region as compared to before treatment, whenK=15 MPa·m1/2The da/dN reduction is about 35%.
Comparative example 1
Comparative example 1 is different from example 1 in the selection of heat treatment temperature, and after the high temperature annealing treatment, one annealing is added. The comparative example material was an additive TC11 titanium alloy, the maximum thickness of which was 20mm, and the beta transus temperature TβThe temperature is 1005 ℃, and the following high-temperature heat treatment process is adopted: keeping the temperature at 1000 ℃ for 0.5 hour, and controlling the cooling speed to be 20 +/-5 ℃/second within the temperature range of cooling to 800 ℃; then, the temperature was maintained at 700 ℃ for 3 hours, and air-cooled. The treated titanium alloy material TC11 is manufactured by additive manufacturing, the room temperature strength Rm is 1080MPa, and the room temperature fracture toughnessK ICIs 99.2 MPa.m1/2About 35% higher than before treatment; the fatigue crack propagation rate da/dN is reduced in the steady-state region as compared to that before the treatment, when ΔK=15 MPa·m1/2The da/dN reduction is about 22%. The fracture toughness and fatigue crack propagation properties were lower than those of example 1.
Comparative example 2
Comparative example 2 differs from example 1 in the selection of the heat treatment temperature. The comparative example material was an additive TC11 titanium alloy, the maximum thickness of which was 20mm, and the beta transus temperature TβAt 1010 ℃, the following high-temperature heat treatment process is adopted: 990 deg.C, keeping the temperature for 0.5 hr, coolingThe cooling speed is controlled within 20 plus or minus 5 ℃/second within the temperature range of 800 ℃. The treated titanium alloy material TC11 is manufactured by additive manufacturing, the room temperature strength Rm is 1085MPa, and the room temperature fracture toughnessK ICIs 92.1 MPa.m1/2(ii) a The fatigue crack propagation rate da/dN is slightly lower in the steady state region than before treatment, when ΔK=15 MPa·m1/2The da/dN reduction was 12%. The fracture toughness and fatigue crack propagation properties were lower than those of example 1.
Comparative example 3
Comparative example 3 differs from example 1 in the selection of the cooling rate for the heat treatment. The material of the embodiment is TC11 titanium alloy manufactured by additive manufacturing, the maximum thickness of the manufactured product is 20mm, and the beta transition temperature T of the manufactured product isβAt 1010 ℃, the following high-temperature heat treatment process is adopted: keeping the temperature at 1007 ℃ for 0.5 hour, and controlling the cooling speed to be 80 +/-10 ℃/second within the temperature range of cooling to 800 ℃. The treated titanium alloy material with TC11 additive manufacturing has the room temperature strength Rm of 1095MPa and the room temperature fracture toughnessK ICIs 68.5MPa · m1 /2Slightly lower than before treatment; the fatigue crack propagation rate da/dN is slightly higher in the steady state region than before the treatment, when ΔK=15 MPa·m1/2The da/dN increase is about 11%. The fracture toughness and fatigue crack propagation properties obtained for this comparative example are significantly lower than for example 1.
Comparative example 4
Comparative example 4 differs from example 1 in the selection of the cooling rate for the heat treatment. The material of the embodiment is TC11 titanium alloy manufactured by additive manufacturing, the maximum thickness of the manufactured product is 20mm, and the beta transition temperature T of the manufactured product isβAt 1010 ℃, the following high-temperature heat treatment process is adopted: the temperature is kept at 1007 ℃ for 0.5 hour, and the cooling speed is controlled at 0.1 ℃/second in the temperature range of cooling to 800 ℃. The room temperature strength Rm of the TC11 titanium alloy material after being processed and manufactured by additive manufacturing is 1045MPa, and the room temperature fracture toughnessK ICIs 75.8 MPa.m1/2Slightly lower than before treatment; the fatigue crack propagation rate da/dN is slightly higher in the steady state region than before the treatment, when ΔK=15 MPa·m1/2The da/dN is reduced by about 6%. The fracture toughness and fatigue crack propagation properties obtained for this comparative example are significantly lower than for example 1.
Comparative example 5
The comparative example 5 is different from the example 2 mainly in the pretreatment process. The material is TC11 titanium alloy forging with the maximum thickness of 40mm and the beta transition temperature TβThe temperature is 1010 ℃, the original structure is a forging duplex structure, and the following pretreatment process is adopted: keeping the temperature for 1 hour at 1030 ℃, and controlling the cooling speed to be 150 +/-20 ℃/second; then carrying out high-temperature heat treatment, wherein the high-temperature heat treatment process comprises the following steps: the temperature is kept at 1007 ℃ for 0.5 hour, and the cooling speed is controlled within the temperature range of cooling from high temperature to 800 ℃ to be 25 +/-5 ℃/second. The treated TC11 titanium alloy forging has the room temperature strength Rm of 1025MPa and the room temperature fracture toughnessK ICIs 90 MPa.m1/2(ii) a The fatigue crack propagation rate da/dN is reduced in the steady-state region as compared to that before the treatment, when ΔK=15 MPa·m1/2The da/dN reduction is about 21%. Room temperature strength R in comparison with example 2mThe reduction in fracture toughness and fatigue crack propagation properties are poor.
Comparative example 6
Comparative example 6 differs from example 2 mainly in the pretreatment process. The material is TC11 titanium alloy forging with the maximum thickness of 40mm and the beta transition temperature TβThe temperature is 1010 ℃, the original structure is a forging duplex structure, and the following pretreatment process is adopted: keeping the temperature for 1 hour at 1030 ℃, and controlling the cooling speed to be 30 +/-5 ℃/second; then carrying out high-temperature heat treatment, wherein the high-temperature heat treatment process comprises the following steps: the temperature is kept at 1007 ℃ for 0.5 hour, and the cooling speed is controlled within the temperature range of cooling from high temperature to 800 ℃ to be 25 +/-5 ℃/second. The treated TC11 titanium alloy forging has the room temperature strength Rm of 1025MPa and the room temperature fracture toughnessK ICIs 93 MPa.m1/2(ii) a The fatigue crack propagation rate da/dN is reduced in the steady-state region as compared to that before the treatment, when ΔK=15 MPa·m1/2The da/dN is reduced by about 25%. Room temperature strength R in comparison with example 2mThe reduction in fracture toughness and fatigue crack propagation properties are poor.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (6)
1. A heat treatment process for obtaining a high toughness, high damage tolerant dual phase titanium alloy comprising: the high-temperature annealing treatment is carried out on the titanium alloy to be treated, and the process comprises the following steps: t is1Keeping the temperature for 0.1-2 hours at the temperature, then cooling, wherein the cooling speed is controlled between furnace cooling and water quenching, specifically from T1Cooling to TβThe cooling speed is controlled within the range of minus 200 ℃ to be 2-50 ℃/s, wherein T1Value range of TβTo 4 ℃ to TβT isβIs the beta transus temperature of the dual phase titanium alloy;
the heat treatment method does not carry out low-temperature annealing heat treatment after high-temperature annealing treatment.
2. The heat treatment method according to claim 1, wherein the cooling rate is controlled to be 5 to 20 ℃/sec.
3. The heat treatment method according to claim 1, wherein a pretreatment is further performed before the high-temperature annealing treatment for the titanium alloy raw structure to be treated containing equiaxed primary phases, and the pretreatment comprises: at T2Keeping the temperature for 0.5 to 2 hours at the temperature, then cooling, and performing T2Cooling to TβIn the temperature range of-200 ℃, the cooling speed is controlled to be not less than 50 ℃/s, wherein T2The temperature value range is TβTo Tβ+10 ℃.
4. The thermal processing method of claim 3, wherein T is2Value range of TβDEG C to Tβ+5 ℃.
5. The thermal processing method according to claim 3, wherein the cooling rate is controlled to be not less than 50 ℃/sec, and particularly to be controlled to be 200 ℃/sec at 100-.
6. The heat treatment process of claim 1, wherein the titanium alloy to be treated is a forging, casting, weld or additive manufacturing of TC11, TA15, TC4, TC17 or TC 18.
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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 |
| CN114472897B (en) * | 2022-01-28 | 2023-06-06 | 有研工程技术研究院有限公司 | Gradient titanium alloy with low adiabatic shear sensitivity and preparation method thereof |
| CN114790533B (en) * | 2022-04-09 | 2023-07-21 | 中国科学院金属研究所 | Heat treatment process of TC11 titanium alloy castings |
| CN114540734B (en) * | 2022-04-27 | 2022-07-15 | 北京煜鼎增材制造研究院有限公司 | Heat treatment method for obtaining high-damage-tolerance titanium alloy |
| CN114606455B (en) * | 2022-05-11 | 2022-07-15 | 北京煜鼎增材制造研究院有限公司 | Spray type heat treatment method for large titanium alloy component |
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| JPH01127653A (en) * | 1987-11-12 | 1989-05-19 | Sumitomo Metal Ind Ltd | Manufacture of alpha+beta type titanium alloy cold rolled plate |
| JP2000273598A (en) * | 1999-03-24 | 2000-10-03 | Kobe Steel Ltd | Manufacture of high strength coil cold rolled titanium alloy sheet excellent in workability |
| CN1159472C (en) * | 2001-09-04 | 2004-07-28 | 北京航空材料研究院 | Titanium alloy quasi-beta forging process |
| EP1786943A4 (en) * | 2004-06-10 | 2008-02-13 | Howmet Corp | Near-beta titanium alloy heat treated casting |
| CN101353772A (en) * | 2007-07-24 | 2009-01-28 | 北京有色金属研究总院 | Heat treatment process improving two-phase titanium alloy damage tolerance property |
| CN101429637B (en) * | 2008-12-02 | 2010-09-08 | 北京航空航天大学 | Biphase titanium alloy thermal treatment method for acquiring two-state organization with raft-shape primary alpha phase |
| CN102230097B (en) * | 2011-03-31 | 2012-06-27 | 西北有色金属研究院 | Preparation method of titanium alloy bars |
| KR101643838B1 (en) * | 2012-08-15 | 2016-07-28 | 신닛테츠스미킨 카부시키카이샤 | Resource-saving titanium alloy member having excellent strength and toughness, and method for manufacturing same |
| CN107099764B (en) * | 2017-04-25 | 2018-08-07 | 西北有色金属研究院 | A kind of heat treatment process improving titanium alloy forging damage tolerance performance |
| CN107779801A (en) * | 2017-11-02 | 2018-03-09 | 中国兵器科学研究院宁波分院 | The heat treatment method of armoring titanium alloy TC 4 |
| CN109321855B (en) * | 2018-10-24 | 2020-09-18 | 南京理工大学 | Mechanical heat treatment method for obtaining metastable beta titanium alloy duplex structure |
| CN111876706A (en) * | 2020-06-30 | 2020-11-03 | 成都飞机工业（集团）有限责任公司 | Heat treatment method of thin-wall damage tolerance type TC4-DT titanium alloy part |
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