CN115772616B - Ultrahigh-strength titanium alloy for aviation structural part - Google Patents
Ultrahigh-strength titanium alloy for aviation structural part Download PDFInfo
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- CN115772616B CN115772616B CN202211579352.8A CN202211579352A CN115772616B CN 115772616 B CN115772616 B CN 115772616B CN 202211579352 A CN202211579352 A CN 202211579352A CN 115772616 B CN115772616 B CN 115772616B
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 46
- 239000012535 impurity Substances 0.000 claims abstract description 10
- 239000010936 titanium Substances 0.000 claims abstract description 10
- 238000010438 heat treatment Methods 0.000 claims abstract description 9
- 229910052804 chromium Inorganic materials 0.000 claims description 2
- 229910052758 niobium Inorganic materials 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 abstract description 13
- 239000000956 alloy Substances 0.000 abstract description 13
- 229910000765 intermetallic Inorganic materials 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 229910052719 titanium Inorganic materials 0.000 abstract 1
- 238000005242 forging Methods 0.000 description 4
- 238000002844 melting Methods 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- 239000002994 raw material Substances 0.000 description 4
- 229910001040 Beta-titanium Inorganic materials 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
- 208000016261 weight loss Diseases 0.000 description 1
Classifications
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses an ultra-high strength titanium alloy for an aviation structural part, which comprises the following components in percentage by mass: al 4.0-6.0 wt%, cr 4.0-6.0 wt%, (Mo+V)/Cr= (1-1.5) 1, zr 2.0-4.0 wt%, nb 0.5-1.5 wt% and Ti and inevitable impurity for the rest. The ultra-high strength titanium alloy of the invention uses the fast eutectoid element Cr to ensure that the alloy has high strength and toughness, and the isomorphous beta stable element Mo+V with the Cr element content of 1-1.5 times is added to obviously improve the hardenability of the alloy, and simultaneously, the invention greatly inhibits the wrapping or eutectoid reaction possibly occurring after more elements such as Al, cr and the like are added, so that brittle intermetallic compounds are not easy to form, the plasticity of the alloy is prevented from being lost, the tensile strength after heat treatment is not less than 1500MPa, and the alloy is used for manufacturing key bearing parts in structural parts of aircraft bodies, wings and landing gear.
Description
Technical Field
The invention belongs to the technical field of ultra-high-strength titanium alloy, and particularly relates to ultra-high-strength titanium alloy for aviation structural parts.
Background
High-strength beta titanium alloys are one of the main directions of titanium alloy development. In seventies of the last century, two typical high-strength beta titanium alloys BT22 and Ti-1023 were used to replace high-strength steel successively for manufacturing aircraft load bearing members, resulting in weight reductions of more than 20% for aircraft structures.
With the development of aviation and aerospace technology, the strength of the high-strength titanium alloy with the strength level of 1000MPa to 1400MPa is generally improved, the strength of alloy plastic and toughness are reduced sharply, and the high-strength titanium alloy is difficult to be practically applied. Alloy steels are still being used for many components with service strengths above 1500mpa. Therefore, the ultra-high strength titanium alloy with tensile strength reaching more than 1500MPa and certain plastic toughness is developed, and the ultra-high strength titanium alloy has great propulsion effect on the development of aviation and aerospace industry in China.
Disclosure of Invention
The technical problem to be solved by the invention is to provide the ultra-high strength titanium alloy for the aviation structural component aiming at the defects in the prior art. The ultra-high strength titanium alloy has high strength and toughness by using a fast eutectoid element Cr, and meanwhile, the hardenability of the alloy is obviously improved by adding isomorphous beta stable element Mo+V with the Cr element content of 1-1.5 times, and meanwhile, the wrapping or eutectoid reaction possibly occurring after more elements such as Al, cr and the like are added is greatly inhibited, brittle intermetallic compounds are not easy to form, the plasticity of the alloy is prevented from being lost, and the tensile strength Rm is not less than 1500MPa after heat treatment.
In order to solve the technical problems, the invention adopts the following technical scheme: the ultra-high strength titanium alloy for the aviation structural component is characterized by comprising the following components in percentage by mass: al 4.0-6.0%, cr 4.0-6.0%, zr 2.0-4.0%, nb 0.5-1.5%, mo+V)/Cr= (1-1.5): 1, mo/V=1 (0.5-1.3), and the balance of Ti and unavoidable impurities.
The ultra-high-strength titanium alloy for the aviation structural component is characterized by comprising the following components in percentage by mass: 5.0 to 6.0 percent of Al, 5.0 to 6.0 percent of Cr, 3.0 to 4.0 percent of Zr3.0 to 1.0 percent of Nb, 0.5 to 1.0 percent of (Mo+V)/Cr= (1 to 1.4) 1, mo/V=1 (1 to 1.3), and the balance of Ti and unavoidable impurities.
The ultra-high-strength titanium alloy for the aviation structural component is characterized by comprising the following components in percentage by mass: al 5.0%, cr6.0%, zr 4.0%, nb0.5%, (Mo+V)/Cr=1:1, mo/V=1:1, the balance being Ti and unavoidable impurities.
The ultra-high strength titanium alloy for the aviation structural component is characterized in that the tensile strength Rm after heat treatment of the ultra-high strength titanium alloy is more than or equal to 1500MPa, the elongation A is more than or equal to 6 percent and the fracture toughness K is higher than or equal to 6 percent IC ≥45MPa·m 1/2 。
The ultra-high strength titanium alloy for the aviation structural component is prepared by the following steps:
step one, mixing raw materials, and then carrying out three times of vacuum consumable arc melting to obtain an ingot;
forging the cast ingot obtained in the first step to obtain the ultra-high strength titanium alloy;
and thirdly, performing heat treatment on the ultrahigh-strength titanium alloy obtained in the second step to obtain the heat-treated ultrahigh-strength titanium alloy.
Compared with the prior art, the invention has the following advantages:
1. the invention uses the fast eutectoid element Cr to make the alloy obtain high strength and toughness, and simultaneously, the isomorphous beta stable elements Mo and V with the Cr content of 1-1.5 times are added to obviously improve the hardenability of the alloy, and meanwhile, the invention greatly inhibits the wrapping or eutectoid reaction possibly occurring after more elements such as Al, cr and the like are added, so that brittle intermetallic compounds are not easy to form, and the plastic loss of the alloy is avoided.
2. The tensile strength Rm of the ultra-high strength titanium alloy after heat treatment is more than or equal to 1500MPa, the elongation A is more than or equal to 6 percent, and the fracture toughness KIC is more than or equal to 45 MPa.m 1/2 。
3. The ultra-high strength titanium alloy still has certain plasticity and toughness at the level of 1500MPa, and meets the requirement of being used for manufacturing forged parts in structural parts of airplane bodies, wings and landing gear.
The technical scheme of the invention is further described in detail by examples.
Detailed Description
Example 1
The embodiment comprises the following steps:
step one, mixing raw materials, and then carrying out three times of vacuum consumable arc melting to obtain an ingot;
forging the cast ingot obtained in the first step to obtain an ultrahigh-strength titanium alloy with the diameter of 180 mm; the ultra-high strength titanium alloy comprises the following components in percentage by mass: 5.0% of Al, 3.0% of V, 3.0% of Mo, 6.0% of Cr, 4.0% of Zr, 0.5% of Nb, and the balance of Ti and unavoidable impurities;
and thirdly, performing heat treatment on the ultrahigh-strength titanium alloy obtained in the second step to obtain the heat-treated ultrahigh-strength titanium alloy.
The test shows that the tensile strength Rm=1571 MPa, the elongation A=7.5% and the fracture toughness K of the heat treated ultrahigh-strength titanium alloy prepared in the embodiment IC ＝45.6MPa·m 1/2 。
Example 2
The embodiment comprises the following steps:
step one, mixing raw materials, and then carrying out three times of vacuum consumable arc melting to obtain an ingot;
forging the cast ingot obtained in the first step to obtain an ultrahigh-strength titanium alloy with the diameter of 150 mm; the ultra-high strength titanium alloy comprises the following components in percentage by mass: al 4.0%, V2.0%, mo 4.0%, cr 4.0%, zr2.0%, nb 1.5% and the balance Ti and unavoidable impurities;
and thirdly, performing heat treatment on the ultrahigh-strength titanium alloy obtained in the second step to obtain the heat-treated ultrahigh-strength titanium alloy.
The test shows that the tensile strength Rm=1511 MPa, the elongation A=8% and the fracture toughness K of the heat treated ultrahigh-strength titanium alloy prepared in the embodiment IC ＝49.6MPa·m 1/2 。
Example 3
The preparation method comprises the following steps of:
step one, mixing raw materials, and then carrying out three times of vacuum consumable arc melting to obtain an ingot;
forging the cast ingot obtained in the first step to obtain an ultrahigh-strength titanium alloy with the diameter of 200 mm; the ultra-high strength titanium alloy comprises the following components in percentage by mass: 6.0% of Al, 4.0% of V, 3.0% of Mo, 5.0% of Cr, 3.0% of Zr, 1% of Nb, and the balance of Ti and unavoidable impurities;
and thirdly, performing heat treatment on the ultrahigh-strength titanium alloy obtained in the second step to obtain the heat-treated ultrahigh-strength titanium alloy.
The test shows that the tensile strength Rm=1521 MPa, the elongation A=6.5% and the fracture toughness K of the heat treated ultra-high strength titanium alloy prepared in the embodiment IC ＝48.6MPa·m 1/2 。
The above description is only of the preferred embodiments of the present invention, and is not intended to limit the present invention. Any simple modification, variation and equivalent variation of the above embodiments according to the technical substance of the invention still fall within the scope of the technical solution of the invention.
Claims (4)
1. The ultra-high strength titanium alloy for the aviation structural component is characterized by comprising the following components in percentage by mass: al 4.0-6.0%, cr 4.0-6.0%, zr2.0-4.0%, nb 0.5-1.5%, (Mo+V)/Cr= (1-1.5): 1, mo/V=1 (0.5-1.3), and the balance of Ti and unavoidable impurities.
2. The ultra-high strength titanium alloy for an aerospace structural member according to claim 1, wherein the ultra-high strength titanium alloy is composed of the following components in percentage by mass: 5.0 to 6.0 percent of Al, 5.0 to 6.0 percent of Cr, 3.0 to 4.0 percent of Zr, 0.5 to 1.0 percent of Nb, (Mo+V)/Cr= (1 to 1.4) 1, mo/V=1 (1 to 1.3), and the balance of Ti and unavoidable impurities.
3. The ultra-high strength titanium alloy for an aerospace structural member according to claim 1, wherein the ultra-high strength titanium alloy is composed of the following components in percentage by mass: al 5.0%, cr6.0%, zr 4.0%, nb0.5%, (Mo+V)/Cr=1:1, mo/V=1:1, the balance being Ti and unavoidable impurities.
4. The ultra-high strength titanium alloy for aviation structural components according to claim 1, wherein the tensile strength Rm of the ultra-high strength titanium alloy after heat treatment is more than or equal to 1500MPa, the elongation A is more than or equal to 6%, and the fracture toughness K is higher than or equal to 6% IC ≥45MPa·m 1/2 。
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211579352.8A CN115772616B (en) | 2022-12-06 | 2022-12-06 | Ultrahigh-strength titanium alloy for aviation structural part |
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| CN202211579352.8A CN115772616B (en) | 2022-12-06 | 2022-12-06 | Ultrahigh-strength titanium alloy for aviation structural part |
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| CN115772616A CN115772616A (en) | 2023-03-10 |
| CN115772616B true CN115772616B (en) | 2024-03-19 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101010439A (en) * | 2004-10-15 | 2007-08-01 | 住友金属工业株式会社 | Near beta-type titanium alloy |
| CN106507844B (en) * | 2009-12-01 | 2012-01-18 | 西北有色金属研究院 | A kind of 1500MPa levels high-strength titanium alloy |
| CN103114224A (en) * | 2013-02-01 | 2013-05-22 | 宝钛集团有限公司 | Multi-component alloy composite reinforced high-strength titanium alloy and preparation method thereof |
| CN104862529A (en) * | 2015-06-06 | 2015-08-26 | 西北有色金属研究院 | Super-high strength and high-plasticity titanium alloy |
| CN109971999A (en) * | 2019-04-28 | 2019-07-05 | 西北有色金属研究院 | A kind of 1500MPa grades of superelevation be strong, in tough titanium alloy |
| WO2020101008A1 (en) * | 2018-11-15 | 2020-05-22 | 日本製鉄株式会社 | Titanium alloy wire rod and method for manufacturing titanium alloy wire rod |
| CN114836651A (en) * | 2022-05-17 | 2022-08-02 | 太原理工大学 | Ultrahigh-strength and toughness beta titanium alloy and preparation method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2577490B (en) * | 2018-09-24 | 2022-03-02 | Alloyed Ltd | A beta titanium alloy for additive manufacturing |
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- 2022-12-06 CN CN202211579352.8A patent/CN115772616B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101010439A (en) * | 2004-10-15 | 2007-08-01 | 住友金属工业株式会社 | Near beta-type titanium alloy |
| CN106507844B (en) * | 2009-12-01 | 2012-01-18 | 西北有色金属研究院 | A kind of 1500MPa levels high-strength titanium alloy |
| CN103114224A (en) * | 2013-02-01 | 2013-05-22 | 宝钛集团有限公司 | Multi-component alloy composite reinforced high-strength titanium alloy and preparation method thereof |
| CN104862529A (en) * | 2015-06-06 | 2015-08-26 | 西北有色金属研究院 | Super-high strength and high-plasticity titanium alloy |
| WO2020101008A1 (en) * | 2018-11-15 | 2020-05-22 | 日本製鉄株式会社 | Titanium alloy wire rod and method for manufacturing titanium alloy wire rod |
| CN109971999A (en) * | 2019-04-28 | 2019-07-05 | 西北有色金属研究院 | A kind of 1500MPa grades of superelevation be strong, in tough titanium alloy |
| CN114836651A (en) * | 2022-05-17 | 2022-08-02 | 太原理工大学 | Ultrahigh-strength and toughness beta titanium alloy and preparation method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 1500MPa级新型超高强中韧钛合金;辛社伟 等;《中国材料进展》;第40卷(第6期);441-445 * |
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