CN111826538B - Preparation method of titanium alloy with bimodal structure and titanium alloy with bimodal structure - Google Patents
Preparation method of titanium alloy with bimodal structure and titanium alloy with bimodal structure Download PDFInfo
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- CN111826538B CN111826538B CN202010735965.0A CN202010735965A CN111826538B CN 111826538 B CN111826538 B CN 111826538B CN 202010735965 A CN202010735965 A CN 202010735965A CN 111826538 B CN111826538 B CN 111826538B
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/045—Alloys based on refractory metals
- C22C1/0458—Alloys based on titanium, zirconium or hafnium
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y40/00—Auxiliary operations or equipment, e.g. for material handling
- B33Y40/20—Post-treatment, e.g. curing, coating or polishing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
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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
- C22F1/02—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working in inert or controlled atmosphere or vacuum
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
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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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Abstract
The invention discloses a preparation method of a titanium alloy with a bimodal structure and the titanium alloy with the bimodal structure, which comprises the following steps: step (1): the Ti-55531 alloy spherical powder is subjected to selective laser sintering to generate a printed Ti-55531 alloy; step (2): putting the printed Ti-55531 alloy into a vacuum heat treatment furnace for vacuum circulating solution heat treatment to obtain an equiaxial alpha-phase TI55531 alloy; and (3): the TI55531 alloy with the equiaxial alpha phase is put into a vacuum heat treatment furnace for aging heat treatment to generate a secondary alpha phase, and the TI55531 alloy with a double-state structure is obtained. The titanium alloy with the bimodal structure prepared by the invention has excellent mechanical property and can meet the aerospace application standard.
Description
Technical Field
The invention relates to a preparation method of a titanium alloy with a bimodal structure and the titanium alloy with the bimodal structure.
Background
Titanium alloy is used as a novel light metal material which develops rapidly in recent decades and has excellent comprehensive performance matching of strength, modulus, toughness, high damage tolerance, weldability and the like, so that the titanium alloy becomes a main structural material of advanced airplanes and aeroengines.
With the improvement of the requirements of people on the aircraft and the change of the design concept of the aircraft, the development of the aviation industry puts higher and higher requirements on the comprehensive performance of the titanium alloy, and the titanium alloy not only requires high strength and high toughness, but also requires higher plasticity.
The existing titanium alloy can not meet the rapid development of the aviation industry.
Disclosure of Invention
Based on the above problems, in one aspect, the invention provides a preparation method of a titanium alloy with a dual-state structure, and the titanium alloy with the dual-state structure prepared by the preparation method of the titanium alloy with the dual-state structure has excellent mechanical properties and can meet the aerospace application standards.
The technical scheme is as follows: a preparation method of a titanium alloy with a two-state structure comprises the following steps:
step (1): the Ti-55531 alloy spherical powder is subjected to selective laser sintering to generate a printed Ti-55531 alloy;
step (2): putting the printed Ti-55531 alloy into a vacuum heat treatment furnace for vacuum circulating solution heat treatment to obtain an equiaxial alpha-phase TI55531 alloy;
and (3): the TI55531 alloy with the equiaxial alpha phase is put into a vacuum heat treatment furnace for aging heat treatment to generate a secondary alpha phase, and the TI55531 alloy with a double-state structure is obtained.
Further, the selective laser sintering process comprises the following steps: the power is 200W, the scanning speed is 1000-1200mm/s, the layer thickness is 30-50 μm, the line spacing is 90-130 μm, and strip scanning strategy is used for printing.
Further, the printed Ti-55531 alloy is a Ti-55531 alloy with a relative density of 99.96%.
Further, the equiaxed alpha phase is spherical or ellipsoidal and has a diameter of 1-3 μm.
Further, the vacuum circulating solid solution heat treatment comprises heating, heat preservation, heating, circulating temperature control and cooling.
Further, the circulation temperature is controlled to be slower from the high temperature to the low temperature than from the low temperature to the high temperature, and the circulation is performed sequentially.
Further, the high temperature is 835 ℃, the low temperature is 740 ℃, the speed from the high temperature to the low temperature is slower than the speed from the low temperature to the high temperature, the time from the high temperature to the low temperature is 50min, and the time from the low temperature to the high temperature is 30min.
On the other hand, the invention also provides a titanium alloy with a dual-state structure, which is prepared by the method, the fracture strength of the titanium alloy with the dual-state structure is more than 1350MPa, the yield strength is more than 1300MPa, the elongation is more than 9%, the fracture toughness is more than 65MPa.m1/2, and the titanium alloy has excellent mechanical properties and can meet the aerospace application standard.
The Ti-5Al-5Mo-5V-3Cr-1Zr alloy is printed by adjusting parameters such as laser power, layer thickness, lap joint rate, scanning speed and the like through a selective laser Sintering (SLM) process. As the printed alloy has a metastable beta structure, and the strength and the plasticity can not reach the aerospace standard, a circulating heat treatment technology is further developed, so that the alloy can obtain an equiaxed alpha phase. Since the equiaxed α phase is generally difficult to achieve by heat treatment, it can be achieved only by annealing after hot working, and since the titanium alloy member to be produced by additive manufacturing does not have the hot working condition, a heat treatment method has been developed which can achieve equiaxed α without damaging the member.
Drawings
FIG. 1 is a schematic view of temperature control of vacuum cyclic solution heat treatment according to the present invention;
FIG. 2 is a schematic temperature control diagram of aging heat treatment according to the present invention.
Detailed Description
The invention will be further explained with reference to the drawings.
In the present invention, relative density = measured density/theoretical density.
A preparation method of a titanium alloy with a bimodal structure comprises the following steps:
step (1): the Ti-55531 alloy spherical powder is subjected to selective laser sintering to generate a printed Ti-55531 alloy;
step (2): putting the printed Ti-55531 alloy into a vacuum heat treatment furnace for vacuum circulating solution heat treatment to obtain an equiaxial alpha-phase TI55531 alloy;
and (3): the Ti55531 alloy with the equiaxial alpha phase is put into a vacuum heat treatment furnace for aging heat treatment to generate a secondary alpha phase, and the TI55531 alloy with the duplex structure is obtained.
In the invention, the vacuum circulating solution heat treatment comprises heating, heat preservation, heating, circulating temperature control and cooling.
In the present invention, further, the circulation temperature control is performed such that the speed from the high temperature to the low temperature is slower than the speed from the low temperature to the high temperature, and the circulation is performed sequentially.
Example 1:
a preparation method of a TI55531 alloy with a two-state structure comprises the following steps:
step (1): the Ti-55531 alloy spherical powder is put into an SLM (selective laser melting) device, and is printed by using a stripe scanning strategy under the conditions that the power is 200W, the scanning speed is 1000-1200mm/s, the layer thickness is 30-50 mu m, and the line spacing is 90-130 mu m, so that the printed Ti-55531 alloy with the relative density of 99.96% is obtained.
Step (2): and (3) placing the printed Ti-55531 alloy into a vacuum heat treatment furnace for vacuum heat treatment to obtain the TI55531 alloy with the equiaxed alpha phase, wherein the equiaxed alpha phase is spherical or ellipsoidal and has the diameter of 1-3 mu m.
The temperature control of the vacuum circulating solution heat treatment is shown in figure 1, when the temperature is increased to 790 ℃ within 79min, the temperature is maintained at 790 ℃ for 80min, and when the temperature is increased to 835 ℃ within 5min, the circulating treatment is carried out: the temperature was decreased from 835 ℃ to 740 ℃ over 50min, then increased to 835 ℃ over 30min, followed by 5 cycles, and finally cooled with argon.
The aging treatment in the step (3) is shown in figure 2: and (3) putting the TI55531 alloy treated in the step (2) into a vacuum furnace, preserving the heat for 6 hours at the temperature of 600 ℃, generating a secondary alpha phase, and matching with the equiaxial alpha phase generated in the step (2) to obtain the TI55531 alloy with a two-state structure.
The mechanical property of the TI55531 alloy with the duplex structure of the embodiment is detected, and the detection conditions and standards are as follows: room temperature tensile and fracture toughness were tested according to ASTM E8/E8M-16a and ASTM E1820-2018. Fracture toughness CT type compact tensile test piece with height of 62.5mm, width of 60mm and thickness of 25mm is adopted, 2mm crack is prefabricated on a fatigue machine, and then the test is started.
The detection result is as follows: the fracture strength is more than 1350MPa, the yield strength is more than 1300MPa, the elongation is more than 9 percent, the fracture toughness is more than 65MPa.m1/2, and the composite material has excellent mechanical properties.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A preparation method of a titanium alloy with a two-state structure comprises the following steps:
step (1): the Ti-55531 alloy spherical powder is subjected to selective laser sintering to generate a printed Ti-55531 alloy; the selective laser sintering process comprises the following steps: the scanning speed is 1000-1200mm/s, the layer thickness is 30-50 μm, and the line spacing is 90-130 μm;
step (2): putting the printed Ti-55531 alloy into a vacuum heat treatment furnace for vacuum circulating solution heat treatment to obtain an equiaxial alpha-phase Ti55531 alloy; the equiaxial alpha phase is spherical or ellipsoidal, and the diameter of the equiaxial alpha phase is 1-3 mu m; the vacuum circulating solid solution heat treatment comprises heating, heat preservation, heating, circulating temperature control and cooling; the circulating temperature control is that the speed from high temperature to low temperature is slower than the speed from the low temperature to the high temperature, and the circulating temperature control is circulated in sequence;
and (3): the Ti55531 alloy with equiaxial alpha phase is put into a vacuum heat treatment furnace for aging heat treatment to generate secondary alpha phase, and the Ti55531 alloy with a duplex structure is obtained.
2. The method of claim 1, wherein the selective laser sintering process comprises: the power is 200W, and the printing is carried out by using a stripe scanning strategy.
3. The method of claim 1, wherein the printed Ti-55531 alloy is a Ti-55531 alloy having a relative density of 99.96%.
4. The method of claim 1, wherein the elevated temperature is 835 ℃, the reduced temperature is 740 ℃, the velocity from the elevated temperature to the reduced temperature is slower than the velocity from the reduced temperature to the elevated temperature by 50min, and the time from the reduced temperature to the elevated temperature is 30min.
5. The method of producing a titanium alloy of a bimodal structure as claimed in claim 1, characterized in that the number of said cycles is 5.
6. The method for producing a titanium alloy having a bimodal structure according to claim 1, wherein in said step (3), the aging heat treatment temperature is 600 ℃ for 6 hours.
7. A titanium alloy of bimodal structure, characterized in that it is produced by a method according to any one of claims 1 to 6.
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| CN113909496B (en) * | 2021-09-28 | 2023-04-18 | 四川大学 | Preparation method of titanium alloy printed part, titanium alloy printed part and aircraft |
| CN113927031B (en) * | 2021-10-18 | 2023-04-21 | 四川大学 | Method for improving performance of titanium alloy by doping Y with Ti-5Al-5Mo-5V-3Cr-Zr alloy |
| CN113927043B (en) * | 2021-10-18 | 2023-04-18 | 四川大学 | Method for preparing Ti-55531 high-strength high-toughness titanium alloy 3D printing-forging combined piece |
| CN115446329B (en) * | 2022-09-08 | 2024-04-19 | 辽宁五寰特种材料与智能装备产业技术研究院有限公司 | High-strength Ti-Al-V based alloy 3D printing manufacturing method based on SLM technology |
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| JPH08127802A (en) * | 1994-10-27 | 1996-05-21 | Janome Sewing Mach Co Ltd | Production of precision parts by powder hardening |
| FR2940319B1 (en) * | 2008-12-24 | 2011-11-25 | Aubert & Duval Sa | PROCESS FOR THERMALLY PROCESSING A TITANIUM ALLOY, AND PIECE THUS OBTAINED |
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