CN115772616A - Ultrahigh-strength titanium alloy for aviation structural component - Google Patents
Ultrahigh-strength titanium alloy for aviation structural component Download PDFInfo
- Publication number
- CN115772616A CN115772616A CN202211579352.8A CN202211579352A CN115772616A CN 115772616 A CN115772616 A CN 115772616A CN 202211579352 A CN202211579352 A CN 202211579352A CN 115772616 A CN115772616 A CN 115772616A
- Authority
- CN
- China
- Prior art keywords
- ultrahigh
- titanium alloy
- percent
- strength titanium
- strength
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 46
- 238000010438 heat treatment Methods 0.000 claims abstract description 10
- 239000012535 impurity Substances 0.000 claims abstract description 10
- 239000010936 titanium Substances 0.000 claims abstract description 10
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 5
- 229910052758 niobium Inorganic materials 0.000 claims abstract description 5
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 3
- 229910045601 alloy Inorganic materials 0.000 abstract description 12
- 239000000956 alloy Substances 0.000 abstract description 12
- 229910000765 intermetallic Inorganic materials 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 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
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 229910052720 vanadium Inorganic materials 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
Landscapes
- Forging (AREA)
- Manufacture And Refinement Of Metals (AREA)
Abstract
The invention discloses an ultrahigh-strength titanium alloy for an aviation structural member, which comprises the following components in percentage by mass: 4.0 to 6.0 percent of Al, 4.0 to 6.0 percent of Cr, (Mo + V)/Cr = (1 to 1.5): 1, 2.0 to 4.0 percent of Zr, 0.5 to 1.5 percent of Nb, and the balance of Ti and inevitable impurities. The ultrahigh-strength titanium alloy of the invention uses a fast eutectoid element Cr to ensure that the alloy obtains high strength and toughness, obviously improves the hardenability of the alloy by adding a beta stable element Mo + V with the content of 1-1.5 times of that of the Cr element, greatly inhibits the peritectic reaction or eutectoid reaction possibly generated after adding more elements such as Al, cr and the like, is difficult to form a brittle intermetallic compound, avoids the loss of the plasticity of the alloy, has the tensile strength of not less than 1500MPa after heat treatment, and is used for manufacturing key bearing parts in airplane fuselage, wings and undercarriage structural members.
Description
Technical Field
The invention belongs to the technical field of ultrahigh-strength titanium alloy, and particularly relates to ultrahigh-strength titanium alloy for an aviation structural part.
Background
High strength beta titanium alloys are one of the main directions in the development of titanium alloys. In the seventies of the last century, two typical high-strength beta titanium alloys BT22 and Ti-1023 are used for manufacturing airplane bearing members to reduce the weight of an airplane structure by more than 20% by replacing high-strength steel in succession.
With the development of aviation and aerospace technologies, high-strength titanium alloys with the strength level of 1000 MPa-1400 MPa are generally used, the strength is further improved, the plasticity and toughness of the alloys are sharply reduced, and the practical application is difficult. For many components with service strengths above 1500mpa, steel alloys are still being used. Therefore, the ultrahigh strength titanium alloy with tensile strength of more than 1500MPa and certain ductility and toughness is developed, and has great promotion effect on the development of aviation and aerospace industries in China.
Disclosure of Invention
The invention aims to solve the technical problem of providing the ultrahigh-strength titanium alloy for the aviation structural part aiming at the defects of the prior art. The ultrahigh-strength titanium alloy uses a rapid eutectoid element Cr to ensure that the alloy obtains high strength and toughness, simultaneously improves the hardenability of the alloy obviously by adding a beta stable element Mo + V with the content of 1-1.5 times of that of the Cr element, greatly inhibits the peritection or eutectoid reaction possibly generated after more elements such as Al, cr and the like are added, is difficult to form a brittle intermetallic compound, avoids the plasticity of the alloy from being lost, and has the tensile strength Rm of not less than 1500MPa after heat treatment.
In order to solve the technical problems, the invention adopts the technical scheme that: the ultrahigh-strength titanium alloy for the aviation structural member is characterized by comprising the following components in percentage by mass: 4.0 to 6.0 percent of Al, 4.0 to 6.0 percent of Cr, 2.0 to 4.0 percent of Zr, 0.5 to 1.5 percent of Nb, (Mo + V)/Cr = (1 to 1.5) = (1), 1/V =1, (0.5 to 1.3), and the balance of Ti and inevitable impurities.
The ultrahigh-strength titanium alloy for the aviation structural member 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 ZrC, 0.5 to 1.0 percent of Nb, (Mo + V)/Cr = (1 to 1.4): 1, 1 to 1.3 of Mo/V =1, and the balance of Ti and inevitable impurities.
The ultrahigh-strength titanium alloy for the aviation structural member is characterized by comprising the following components in percentage by mass: 5.0% of Al, 6.0% of Cr, 4.0% of Zr, 0.5% of nb0, (Mo + V)/Cr =1, mo/V =1:1, and the balance of Ti and unavoidable impurities.
The ultrahigh-strength titanium alloy for the aviation structural member is characterized in that the tensile strength Rm of the ultrahigh-strength titanium alloy after heat treatment is more than or equal to 1500MPa, the elongation A of the ultrahigh-strength titanium alloy is more than or equal to 6 percent, and the fracture toughness K of the ultrahigh-strength titanium alloy IC ≥45MPa·m 1/2 。
The ultrahigh-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;
step two, forging the ingot obtained in the step one to obtain the ultrahigh-strength titanium alloy;
and step three, carrying out heat treatment on the ultrahigh-strength titanium alloy obtained in the step two 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 rapid eutectoid element Cr to ensure that the alloy obtains high strength and toughness, simultaneously improves the hardenability of the alloy obviously by adding the isomorphous beta stable elements Mo and V with the content of 1-1.5 times of the Cr element, simultaneously greatly inhibits the possible peritection or eutectoid reaction after adding more elements such as Al, cr and the like, is not easy to form brittle intermetallic compounds, and avoids the loss of the plasticity of the alloy.
2. The tensile strength Rm of the ultrahigh-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 ultrahigh-strength titanium alloy still has certain plasticity and toughness at the level of 1500MPa, and can be used for manufacturing forged parts in structural members of airframes, wings and undercarriages of airplanes.
The technical solution of the present invention is further described in detail by examples below.
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;
step two, forging the ingot obtained in the step one to obtain the ultrahigh-strength titanium alloy with the diameter of 180 mm; the ultrahigh-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 inevitable impurities;
and step three, carrying out heat treatment on the ultrahigh-strength titanium alloy obtained in the step two to obtain the heat-treated ultrahigh-strength titanium alloy.
The ultrahigh-strength titanium alloy prepared in the embodiment after heat treatment has tensile strength Rm =1571MPa, elongation A =7.5%, and fracture toughness K 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;
step two, forging the ingot obtained in the step one to obtain the ultrahigh-strength titanium alloy with the diameter of 150 mm; the ultrahigh-strength titanium alloy comprises the following components in percentage by mass: 4.0% of Al, 2.0% of V, 4.0% of Mo, 4.0% of Cr, 2.0% of Zr, 1.5% of Nb and the balance of Ti and inevitable impurities;
and step three, carrying out heat treatment on the ultrahigh-strength titanium alloy obtained in the step two to obtain the heat-treated ultrahigh-strength titanium alloy.
The heat-treated ultrahigh-strength titanium alloy prepared in the embodiment has the tensile strength Rm =1511MPa, the elongation A =8% and the fracture toughness K 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;
step two, forging the ingot obtained in the step one to obtain an ultrahigh-strength titanium alloy with the diameter of 200 mm; the ultrahigh-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 inevitable impurities;
and step three, carrying out heat treatment on the ultrahigh-strength titanium alloy obtained in the step two to obtain the heat-treated ultrahigh-strength titanium alloy.
The heat-treated ultrahigh-strength titanium alloy prepared in the embodiment has the tensile strength Rm =1521MPa, the elongation A =6.5% and the fracture toughness K IC ＝48.6MPa·m 1/2 。
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention in any way. Any simple modification, change and equivalent changes of the above embodiments according to the technical essence of the invention are still within the protection scope of the technical solution of the invention.
Claims (4)
1. The ultrahigh-strength titanium alloy for the aviation structural part is characterized by comprising the following components in percentage by mass: 4.0 to 6.0 percent of Al, 4.0 to 6.0 percent of Cr, 0.0 to 4.0 percent of Zr2, 0.5 to 1.5 percent of Nb, (Mo + V)/Cr = (1 to 1.5) = (1), 1/Mo =1, (0.5 to 1.3), and the balance of Ti and inevitable impurities.
2. The ultrahigh-strength titanium alloy for the aviation structural member as recited in claim 1, wherein the ultrahigh-strength titanium alloy consists 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), (1 to 1.3) of Mo/V =1, and the balance of Ti and inevitable impurities.
3. The ultrahigh-strength titanium alloy for the aviation structural member as recited in claim 1, wherein the ultrahigh-strength titanium alloy consists of the following components in percentage by mass: 5.0% of Al, 6.0% of Cr, 4.0% of Zr, 0.5% of Nb, (Mo + V)/Cr =1, mo/V =1:1, and the balance being Ti and unavoidable impurities.
4. The ultrahigh-strength titanium alloy for aviation structural members as claimed in claim 1, wherein the ultrahigh-strength titanium alloy after heat treatment has a tensile strength Rm of 1500MPa or more, an elongation A of 6% or more, and a fracture toughness K IC ≥45MPa·m 1/2 。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211579352.8A CN115772616B (en) | 2022-12-06 | 2022-12-06 | Ultrahigh-strength titanium alloy for aviation structural part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211579352.8A CN115772616B (en) | 2022-12-06 | 2022-12-06 | Ultrahigh-strength titanium alloy for aviation structural part |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115772616A true CN115772616A (en) | 2023-03-10 |
| CN115772616B CN115772616B (en) | 2024-03-19 |
Family
ID=85391783
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211579352.8A Active CN115772616B (en) | 2022-12-06 | 2022-12-06 | Ultrahigh-strength titanium alloy for aviation structural part |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115772616B (en) |
Citations (8)
| 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 |
| US20220025488A1 (en) * | 2018-09-24 | 2022-01-27 | Alloyed Limited | A beta titanium alloy for additive manufacturing |
| 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 |
-
2022
- 2022-12-06 CN CN202211579352.8A patent/CN115772616B/en active Active
Patent Citations (8)
| 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 |
| US20220025488A1 (en) * | 2018-09-24 | 2022-01-27 | Alloyed Limited | A beta titanium alloy for additive manufacturing |
| 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 |
|---|
| 辛社伟 等: "1500MPa级新型超高强中韧钛合金", 《中国材料进展》, vol. 40, no. 6, pages 441 - 445 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115772616B (en) | 2024-03-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5442857B2 (en) | High-strength near β-type titanium alloy and method for producing the same | |
| US9828657B2 (en) | Ni-base super alloy | |
| CN103276242A (en) | Ultrahigh-strength titanium alloy and preparation method thereof | |
| CN109161727B (en) | Titanium alloy for manufacturing electric arc/electron beam fuse additive and preparation method thereof | |
| CN110257668B (en) | High-performance and low-cost titanium alloy | |
| CN109852845A (en) | Tough titanium alloy of a kind of nearly β type height and preparation method thereof | |
| CN111020414B (en) | Preparation method of short fiber reinforced high-temperature titanium alloy bar for 700-750 DEG C | |
| CN111270102B (en) | Near-beta ultrahigh-strength titanium alloy with tensile strength of more than 1450MPa and preparation method thereof | |
| CN104726746A (en) | High-strength metastable beta-type titanium alloy bar and production method thereof | |
| CN101775524A (en) | Titanium alloy material and preparation method thereof | |
| CA3110188C (en) | High strength fastener stock of wrought titanium alloy and method of manufacturing the same | |
| CN109930030A (en) | A kind of alpha-beta type is high-strength, high impact toughness titanium alloy and preparation method thereof | |
| CA2812347A1 (en) | Method for the manufacture of wrought articles of near-beta titanium alloys | |
| CN113355559B (en) | High-strength high-toughness high-damage-tolerance titanium alloy and preparation method thereof | |
| CN103114224B (en) | Multi-component alloy composite reinforced high-strength titanium alloy and preparation method thereof | |
| CN112538581A (en) | 1400 MPa-level low-cost high-strength titanium alloy | |
| CN106011537A (en) | Fine grain high-strength and high-toughness beta titanium alloy and manufacturing method thereof | |
| CN111349815A (en) | Ti-1300Z novel high-strength high-toughness titanium alloy and preparation method thereof | |
| CN103243235A (en) | High strength titanium alloy | |
| CN115772616B (en) | Ultrahigh-strength titanium alloy for aviation structural part | |
| CN112958784A (en) | Method for actively controlling uniform distribution and growth direction of reinforcing phase in particle-reinforced titanium-based composite material | |
| CN114592142A (en) | Medium-strength high-toughness titanium alloy with yield strength of 800MPa for ocean engineering and preparation process thereof | |
| CN114351066B (en) | Preparation method of TC11 forging with 1060MPa strength level | |
| CN109971999A (en) | A kind of 1500MPa grades of superelevation be strong, in tough titanium alloy | |
| CN111225989B (en) | Improved heat treatable titanium alloys |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |