CN115449665A - Titanium alloy and preparation method thereof - Google Patents
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- CN115449665A CN115449665A CN202210800805.9A CN202210800805A CN115449665A CN 115449665 A CN115449665 A CN 115449665A CN 202210800805 A CN202210800805 A CN 202210800805A CN 115449665 A CN115449665 A CN 115449665A
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 66
- 238000002360 preparation method Methods 0.000 title abstract description 20
- 239000000956 alloy Substances 0.000 claims abstract description 31
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 29
- 238000010438 heat treatment Methods 0.000 claims abstract description 23
- 238000000034 method Methods 0.000 claims abstract description 14
- 238000003723 Smelting Methods 0.000 claims abstract description 10
- 238000004519 manufacturing process Methods 0.000 claims abstract description 7
- 239000000243 solution Substances 0.000 claims description 10
- 238000002844 melting Methods 0.000 claims description 7
- 230000008018 melting Effects 0.000 claims description 7
- 239000000203 mixture Substances 0.000 claims description 5
- 238000004321 preservation Methods 0.000 claims description 5
- 239000006104 solid solution Substances 0.000 claims description 5
- 238000005303 weighing Methods 0.000 claims description 3
- 229920005668 polycarbonate resin Polymers 0.000 claims 2
- 239000004431 polycarbonate resin Substances 0.000 claims 2
- 230000000694 effects Effects 0.000 abstract description 5
- 239000012071 phase Substances 0.000 description 40
- 239000000463 material Substances 0.000 description 14
- 230000006835 compression Effects 0.000 description 8
- 238000007906 compression Methods 0.000 description 8
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 8
- 238000012360 testing method Methods 0.000 description 6
- 229910000883 Ti6Al4V Inorganic materials 0.000 description 5
- 238000013461 design Methods 0.000 description 5
- 239000010936 titanium Substances 0.000 description 5
- 229910052742 iron Inorganic materials 0.000 description 4
- 239000002245 particle Substances 0.000 description 4
- 238000010587 phase diagram Methods 0.000 description 4
- 238000011160 research Methods 0.000 description 4
- 229910001040 Beta-titanium Inorganic materials 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 3
- 238000002441 X-ray diffraction Methods 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 3
- 229910052739 hydrogen Inorganic materials 0.000 description 3
- 239000001257 hydrogen Substances 0.000 description 3
- 230000035882 stress Effects 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 229910052750 molybdenum Inorganic materials 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 238000010791 quenching Methods 0.000 description 2
- 230000000171 quenching effect Effects 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 229910052720 vanadium Inorganic materials 0.000 description 2
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910018084 Al-Fe Inorganic materials 0.000 description 1
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 229910018192 Al—Fe Inorganic materials 0.000 description 1
- 229910000640 Fe alloy Inorganic materials 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 229910010340 TiFe Inorganic materials 0.000 description 1
- 229910000756 V alloy Inorganic materials 0.000 description 1
- 241000276425 Xiphophorus maculatus Species 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 239000011825 aerospace material Substances 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 229910000905 alloy phase Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 230000009466 transformation Effects 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
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
-
- 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
- C22C1/02—Making non-ferrous alloys by melting
-
- 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
-
- 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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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Manufacture And Refinement Of Metals (AREA)
Abstract
The invention discloses a titanium alloy and a preparation method thereof, wherein the titanium alloy comprises the following main components in atomic percentage: ti:86at%, al:9at%, fe:2at%, mo:3at%. The preparation method comprises the following steps: 1. preparing required alloy components according to atomic percentage; 2. smelting the prepared alloy components by a vacuum arc smelting method; 3. carrying out solution treatment on the titanium alloy sample prepared in the step 2 through a vacuum tube furnace; 4. and (4) carrying out heat treatment on the titanium alloy sample prepared in the step (3). The invention has the technical effects that: the compressive strength of the titanium alloy is not lower than 1593MPa, the breaking strain is not lower than 20%, the good matching of high strength and excellent ductility is realized, and the production cost of the alloy is reduced.
Description
Technical Field
The invention relates to the technical field of new materials, in particular to a titanium alloy and a preparation method thereof.
Background
The aerospace industry is an important strategic industry of all countries in the world, and aerospace materials become one of the key development directions for developing aerospace industry of all countries in the world. Titanium and titanium alloy have the advantages of low density, high specific strength, good corrosion resistance and the like, are widely applied to the field of aerospace, and are important structural materials for manufacturing aeroengines, rockets and missiles. With the rapid development of the aerospace industry, higher requirements are put forward on the materials of the engine in order to meet the design targets of low oil consumption, large thrust-weight ratio and high reliability of the engine. However, the titanium alloy for the conventional structure has not only low elongation at room temperature but also insufficient high-temperature strength, and has not been able to meet the demand for engine materials. As a basic material suitable for engineering technology, particularly a structural material used in a severe environment for a long time, the material inevitably meets higher performance requirements proposed by product updating, and not only is the material required to have high strength, but also good toughness must be maintained. How to overcome the trade-off between strength and plasticity and realize the performance requirement of toughness integration of the titanium alloy is a technical problem which is always overcome in the field.
In the past decades of research, researchers have employed various methods to achieve the matching between the strength and plasticity of titanium alloy. Nano precipitation strengthening has become an effective method to simultaneously improve strength and plasticity. Existing titanium alloys can be classified into alpha titanium alloys, beta titanium alloys, and alpha + beta two-phase titanium alloys according to their phase composition. The alpha + beta two-phase titanium alloy has high plasticity of the alpha titanium alloy and high strength of the beta titanium due to the deformation coordination effect between the two phases.
Chinese patent document CN112410612A discloses a high-performance α + β type titanium alloy containing Fe, V, and Al alloy elements and a preparation method thereof in 10/29/2020, and the titanium alloy has the following components and component mass percentages: 3.0-4.5wt% of aluminum, 0.3-3.0wt% of iron, 8.0-10.5wt% of vanadium, and the balance of titanium and inevitable impurities. The alloy has an alpha + beta two-phase structure, and the mechanical properties of the alloy are as follows: tensile strength is 1000MPa, and elongation is 15%. The technical concept is that inexpensive alloy elements are used for partially replacing expensive elements in titanium alloy to design a novel titanium alloy, so that the mechanical property of the titanium alloy is improved, however, the manufacturing cost of the V-containing titanium alloy is expensive, but the performance of the existing low-cost titanium alloy is still not ideal, and therefore, the preparation of the titanium alloy with high mechanical property and lower cost has important significance for promoting the application of the titanium alloy in the civil field.
Disclosure of Invention
Aiming at the problems in the prior art, the technical problem to be solved by the invention is to provide a titanium alloy which has high strength and good ductility. The invention also provides a preparation method of the titanium alloy, which regulates and controls the composition of two phases and the size and the content of a nanometer precipitated phase through heat treatment, thereby improving the strength and the ductility of the titanium alloy.
In order to solve the technical problems, the invention provides a titanium alloy, which comprises the following main components in atomic percentage: ti:86at%, al:9at%, fe:2at%, mo:3at%.
The invention also provides a preparation method of the titanium alloy, which comprises the following steps:
step 2, smelting the prepared alloy components by adopting a vacuum arc smelting method to prepare a titanium alloy ingot;
and 4, carrying out heat treatment on the titanium alloy sample prepared in the step 3.
In the step 3, a vacuum tube furnace is adopted for the solution treatment, and the temperature of the solution treatment is 850-1600 ℃.
In the step 4, a vacuum tube furnace is adopted for heat treatment, and the heat treatment temperature is 650-850 ℃.
The invention takes the alpha phase of Ti as a matrix phase and the beta phase as a nano precipitated phase, and the size and the content of the precipitated phase are adjusted by a heat treatment mode, so that the titanium alloy with excellent mechanical property can be obtained; al, fe and Mo have good strengthening effect on the titanium alloy, and the Al and Fe are low in price, so that the mechanical property of the titanium alloy can be effectively improved and the production cost is greatly reduced by adding the metal main elements into the titanium alloy.
The invention has the advantages that:
the titanium alloy has the compression strength not lower than 1593MPa and the breaking strain not lower than 20%, realizes good matching of high strength and excellent ductility, and reduces the production cost of the alloy.
The preparation method is simple, low in cost, safe and environment-friendly, can meet the use requirements of the industries such as aerospace, weaponry and the like, and has wide application prospects.
Drawings
The drawings of the invention are illustrated as follows:
FIG. 1 is an XRD pattern of an alloy of the present invention;
FIG. 2 is a microstructure of an alloy of the present invention;
FIG. 3 is a graph of the compressive stress strain of the titanium alloy of the present invention;
FIG. 4 is a thermodynamic calculated phase diagram of the titanium alloy of the present invention;
FIG. 5 is a graph comparing the mechanical properties of the titanium alloy of the present invention with those of the conventional titanium alloy.
Detailed Description
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
the titanium alloy of the invention comprises the following main components in atomic percentage: ti:86at%, al:9at%, fe:2at%, mo:3at%.
The preparation method 1 comprises the following steps:
step 2, adopting a vacuum non-consumable electric arc melting furnace to prepare a mixtureSmelting the gold component for 5 times to obtain a titanium alloy ingot, wherein the arc smelting parameters are as follows: the current of the smelting furnace is 70 to 100A, the smelting temperature is more than 3000 ℃, the time of one smelting is 5 to 20min, and the vacuum degree is 6.6 multiplied by 10 -4 Pa；
and 4, carrying out heat treatment on the titanium alloy sample subjected to solution treatment by using a vacuum tube furnace, wherein the heat treatment temperature is 700 ℃, the temperature is increased from 20 ℃, the temperature increase rate is 10 ℃/min, the heat preservation time is 120min, and after the heat preservation is finished, rapidly cooling to room temperature by water quenching to obtain a final finished product.
And (4) performance testing:
the compression strength and the breaking strain of the material are measured by an electronic universal tester by adopting GB/T7314-1987 test standard, and the compression stress strain curve of the titanium alloy obtained by the preparation method is shown in figure 3, wherein the compression strength is 2160MPa, and the breaking strain is 42%.
The preparation method 2 comprises the following steps:
in contrast to preparation method 1: in step 4, the heat treatment temperature was 740 ℃.
And (3) performance testing:
the measured compressive stress-strain curve of the titanium alloy prepared by the preparation method is shown in figure 3, the compressive strength is 1671MPa, and the fracture strain is 20 percent.
The preparation method 3 comprises the following steps:
in contrast to preparation method 1: in step 4, the heat treatment temperature was 820 ℃.
And (3) performance testing:
for the titanium alloy prepared by the preparation method, the measured compressive stress strain curve is shown in figure 3, the compressive strength is 1593MPa, and the fracture strain is 27.8 percent.
X-ray diffraction (XRD) analysis: the phase compositions of the alloys obtained by the three preparation methods are characterized by adopting an X-ray diffractometer with the model of X' Pert PRO MPD, and relevant test parameters are as follows: the scanning speed is 2 degree/min, and the scanning angle is 10-90 degree. FIG. 1 is an XRD spectrum of Ti-9Al-3Mo-2Fe alloy at different heat treatment temperatures. It can be observed from the figure that the alloy after heat treatment has an alpha + beta dual-phase structure, and the relative content of the alpha phase is gradually reduced and the relative content of the beta phase is gradually increased as the heat treatment temperature is increased from 700 ℃ to 820 ℃, which shows that the temperature is increased to be beneficial to the transformation of the alpha phase to the beta phase.
Scanning Electron Microscope (SEM) analysis: the microstructure of the alloy obtained by the three preparation methods was observed using a scanning electron microscope of type czech TESCAN MIRA LMS, as shown in fig. 2. The main phases of the alloy after aging treatment at 700 ℃ are white platy alpha phase and black strip-shaped beta phase with irregular shape and size. As the temperature rises to 740 ℃, the content of the beta phase is obviously increased, the shape is mainly black thin strips, and meanwhile, the size of the phase is obviously reduced and the distribution is more uniform. The temperature is continuously increased to 820 ℃, the content of the beta phase is further increased, the size of the phase tends to be stable, and the distribution becomes more uniform.
In order to obtain the solid solution temperature parameter and the heat treatment temperature parameter of the TiAlFeMo titanium alloy, a phase diagram Calculation (CALPHAD) method is a multi-component phase diagram with enough accuracy without heavy experimental work. Based on Thermo-Calc software, thermodynamic phase diagram calculation is carried out on TiAlFeMo series titanium alloy, a database adopts steel alloy data and a nickel-based alloy database, and FIG. 4 is a calculation result of equilibrium phase evolution of the titanium alloy along with temperature change. In fig. 4, different line segment forms represent different phases, and a closed area surrounded by a line segment of the same form and a coordinate axis indicates that the phase exists in the area, and the phase does not exist beyond the area. Taking the black solid line as an example, the starting point is 600 ℃ and the end point is 1700 ℃. As seen from FIG. 4, when the temperature is between 650 ℃ and 860 ℃, the alloy phase is in an alpha + beta dual-phase structure, and the content of the beta phase is gradually increased and the content of the alpha phase is gradually reduced along with the increase of the temperature. The temperature is continuously raised, the alpha phase completely disappears, the alloy is in a single beta phase structure, and the temperature range is 850-1600 ℃.
The purpose of the solution treatment is to obtain a single-phase structure, and the single-phase structure is shown in the range of 850-1600 ℃ in FIG. 4, which can be used as the solution treatment temperature. In the phase evolution process of heating, the performance of the material is mainly influenced in the precipitation heat treatment stage, and the two-phase structure at 650-850 ℃ in figure 4 has satisfactory performance, so that the heat treatment can be 650-850 ℃.
In fig. 4, alTi3 and TiFe are impurity phases; LIQUID denotes the LIQUID phase, corresponding to the temperature at which the phase structure begins to melt.
Fig. 5 is a comparison of mechanical properties of the titanium alloy of the present invention and the existing titanium alloy, and the existing titanium alloy material and test data in fig. 5 are shown in the following documents:
1. abdula zizi Kurdi, AK base. Micro-mechanical behaviour of selective laser filtered Ti6Al4V under compression [ J ] Materials Science & Engineering a.2021.826. (abdula zizi Kurdi, AK base. Selective laser melting Ti6Al4V under compression [ J ] Materials Science and Engineering a.2021.826.);
2. MohamedG Elkhateb, yungC shin. Analysis of the effects of the properties on the mechanical properties of the structural properties [ J ] Materials and design.2021.204. (MohamedG Elkhateb, yungC shin. Utilizes structural genomic mechanics to analyze the effect of structural heterogeneity on the mechanical properties of additive manufactured Ti6Al4V [ J ] Materials and design.2021.204.);
3. baoguo Yuan, jiangfei Du, xiaooxue Zhang, et Al, microstrures and room-temperature compressive properties of Ti6Al4V alloy processed by y connected multi step Hydrogen generation process [ J ]. International Journal of Hydrogen energy 2020.45 (46): 25567-25579. (Baoguo Yuan, jiangfei Du, xiaooxue Zhang et Al. Microstructure and room temperature compressive properties of Ti6Al4V alloys subjected to continuous multi-step hydrotreatment [ J ]. International Hydrogen energy 2020.45 (46): 25567-25579.);
4. research on the tissue and mechanical properties of a Kuoholong Ti-Al-Fe-based alloy [ D ]. Hebei, university of Yanshan.2018;
5. xuyangqiang Ti-B20 high strength beta titanium alloy compression performance and high temperature deformation behavior research [ D ]. Heilongjiang Harbin university.2017;
6. rare metal materials and engineering [ J ] is researched on room temperature compression performance and microstructure evolution of Yangying, liu Quanming and high-strength Ti-26 alloy, 2018.47 (4) is 1232-1237;
7. xurethoudong, component design and tissue performance research of novel high-toughness titanium alloy [ D ]. Liaoning, shenyang aerospace university.2019.
As can be seen from fig. 5: compared with the existing titanium alloy material, the titanium alloy of the invention has high strength and good ductility. The invention replaces expensive vanadium V with cheap alloy of Fe, mo, etc., and the production cost of the titanium alloy is lower.
Claims (8)
1. A titanium alloy characterized by: the atomic percentage of each principal component is as follows: ti:86at%, al:9at%, fe:2at%, mo:3at%.
2. A method of making the titanium alloy of claim 1, comprising the steps of:
step 1, weighing each principal component according to atomic percentage to prepare required alloy components;
step 2, smelting the prepared alloy components by adopting a vacuum arc smelting method to prepare a titanium alloy ingot;
step 3, carrying out solid solution treatment on the titanium alloy sample prepared in the step 2;
and 4, carrying out heat treatment on the titanium alloy sample prepared in the step 3.
3. The method of claim 2, wherein: in step 3, a vacuum tube furnace is used for the solution treatment, and the temperature of the solution treatment is 850-1600 ℃.
4. The method for preparing a polycarbonate resin composition according to claim 3, wherein: the temperature of the solution treatment was 910 ℃.
5. The method of claim 3, wherein: in the step 4, a vacuum tube furnace is adopted for heat treatment, and the heat treatment temperature is 650-850 ℃.
6. The method for preparing a polycarbonate resin composition according to claim 5, wherein: the heat treatment temperature was 700 ℃.
7. The process according to any one of claims 3 to 6, characterized in that: the solution treatment is started to heat up from 20 ℃, the heating rate is 10 ℃/min, the heat preservation time is 30min, and the solution is rapidly cooled to the room temperature; the heat treatment time is 2h.
8. The process according to any one of claims 3 to 6, characterized in that: in step 2, a vacuum non-consumable arc melting furnace is adopted for melting, the melting is not less than 5 times, the melting temperature is more than 3000 ℃, the time of melting for one time is 5-20 min, and the vacuum degree is 6.6 multiplied by 10 -4 Pa。
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