CN111188000B - Ti2Stress-relief annealing heat treatment process of AlNb alloy member - Google Patents
Ti2Stress-relief annealing heat treatment process of AlNb alloy member Download PDFInfo
- Publication number
- CN111188000B CN111188000B CN202010160709.3A CN202010160709A CN111188000B CN 111188000 B CN111188000 B CN 111188000B CN 202010160709 A CN202010160709 A CN 202010160709A CN 111188000 B CN111188000 B CN 111188000B
- Authority
- CN
- China
- Prior art keywords
- heat treatment
- furnace
- stress
- alnb alloy
- relief annealing
- 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.)
- Active
Links
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 58
- 239000000956 alloy Substances 0.000 title claims abstract description 58
- 238000010438 heat treatment Methods 0.000 title claims abstract description 51
- 238000000034 method Methods 0.000 title claims abstract description 43
- 230000008569 process Effects 0.000 title claims abstract description 41
- 238000000137 annealing Methods 0.000 title claims abstract description 34
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims abstract description 16
- 239000000843 powder Substances 0.000 claims abstract description 15
- 238000004321 preservation Methods 0.000 claims abstract description 12
- 238000001816 cooling Methods 0.000 claims abstract description 11
- 229910052786 argon Inorganic materials 0.000 claims abstract description 8
- 238000005336 cracking Methods 0.000 claims abstract description 7
- 230000035882 stress Effects 0.000 claims description 33
- 238000001513 hot isostatic pressing Methods 0.000 claims description 9
- 238000003754 machining Methods 0.000 claims description 9
- 239000007789 gas Substances 0.000 claims description 5
- 230000032683 aging Effects 0.000 claims description 4
- 239000000243 solution Substances 0.000 claims description 4
- 229910000975 Carbon steel Inorganic materials 0.000 claims description 2
- 238000000889 atomisation Methods 0.000 claims description 2
- 239000010962 carbon steel Substances 0.000 claims description 2
- 239000006104 solid solution Substances 0.000 claims description 2
- 238000009849 vacuum degassing Methods 0.000 claims description 2
- 238000002360 preparation method Methods 0.000 claims 1
- 239000010936 titanium Substances 0.000 abstract description 27
- 238000004663 powder metallurgy Methods 0.000 abstract description 9
- 229910001069 Ti alloy Inorganic materials 0.000 abstract description 3
- 230000000052 comparative effect Effects 0.000 description 9
- 238000005516 engineering process Methods 0.000 description 5
- 230000009467 reduction Effects 0.000 description 4
- 238000005495 investment casting Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 229910004349 Ti-Al Inorganic materials 0.000 description 2
- 229910004692 Ti—Al Inorganic materials 0.000 description 2
- 229910000905 alloy phase Inorganic materials 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 229910000765 intermetallic Inorganic materials 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 229910021330 Ti3Al Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
-
- 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
-
- 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
- B22F3/12—Both compacting and sintering
- B22F3/14—Both compacting and sintering simultaneously
- B22F3/15—Hot isostatic pressing
-
- 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
-
- 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
- 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
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Manufacturing & Machinery (AREA)
- Powder Metallurgy (AREA)
Abstract
The invention discloses a Ti2A stress-relief annealing heat treatment process of an AlNb alloy component belongs to the field of powder metallurgy titanium alloy. The process comprises the following steps: (1) ti after mechanical processing2Placing the AlNb alloy component in a vacuum annealing furnace; (2) stress relief annealing heat treatment: the heat treatment temperature is 575-625 ℃, and the heat preservation time is 2-4 h; (3) and after the heat treatment and heat preservation stage is finished, stopping heating, cooling to 150-200 ℃ along with the furnace, and then introducing argon into the furnace to cool to room temperature. The invention can reduce powder Ti2The residual stress of the AlNb alloy complex component after mechanical processing reduces the risk of component cracking.
Description
Technical Field
The invention relates to the technical field of powder metallurgy titanium alloy, in particular to powder Ti2And (3) a stress relief annealing heat treatment process after AlNb alloy machining.
Background
Ti2The AlNb alloy is a Ti-Al series intermetallic compound alloy which takes an O phase with an orthogonal structure as a main component phase, has excellent strength, fracture toughness and creep resistance at 650-750 ℃, and has lower density and good oxidation resistance, so that Ti2The AlNb alloy has strong application potential in hot end components of aircraft engines. Ti2The AlNb alloy complex component is mainly adopted at presentBy using a forming process of welding after precision casting or split forging, the precision casting has casting defects of shrinkage cavity, looseness, component segregation and the like which are difficult to thoroughly solve, so that the rejection rate is high, and the out-of-tolerance use is common; the forging and welding combined method has the defects of low material utilization rate and cracking risk of a welding joint, and the requirements of high reliability and weight reduction of a modern aeroengine are difficult to meet.
The powder metallurgy near-net forming technology is a direct forming technology combining a hot isostatic pressing technology and computer-aided mold design and manufacture, and compared with a precision casting technology, the powder metallurgy near-net forming technology has the advantages of uniform components, no macrosegregation, fine and uniform tissue, high performance reliability, isotropy, easiness in ultrasonic detection and the like, is particularly suitable for preparing components with complex cavities, has the material utilization rate close to 100 percent, and has the performance similar to or even superior to that of wrought alloys.
But powder Ti produced by powder metallurgy process2AlNb alloys also have their own disadvantages, Ti2The AlNb alloy belongs to a brittle intermetallic compound, and is easy to crack under the action of residual stress in a machined component, so that the subsequent service of the component is influenced.
Disclosure of Invention
The invention aims to provide powder Ti2The stress relief annealing heat treatment process after machining of AlNb alloy can reduce powder Ti2The risk of cracking of the AlNb alloy after machining is characterized in that: the technological parameters of the vacuum annealing heat treatment are as follows: keeping the temperature at 575-625 ℃ for 2-4 h, and preferably selecting the vacuum degree of vacuum annealing heat treatment to be 10-2～10-4Pa; and after the heat treatment and heat preservation stage is finished, stopping heating, cooling to 150-200 ℃ along with the furnace, and introducing argon to cool to room temperature. The invention can reduce powder Ti2The residual stress of the AlNb alloy complex component after mechanical processing reduces the risk of component cracking.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
ti2The stress-relief annealing heat treatment process of the AlNb alloy component comprises the following steps:
(1) will be provided withMachined Ti2Placing the AlNb alloy component in a vacuum annealing furnace;
(2) stress relief annealing heat treatment: the heat treatment temperature is 575-625 ℃, preferably 595-605 ℃, and the heat preservation time is 2-4 hours, preferably 2-3 hours;
(3) and after the heat treatment and heat preservation stage is finished, stopping heating, cooling to 150-200 ℃ along with the furnace, and then introducing argon into the furnace to cool to room temperature.
The Ti2The AlNb alloy component is manufactured by a powder metallurgy process (e.g., a hot isostatic pressing process, as described in the' 201910773601.9 patent application), machined, and then placed in a vacuum annealing furnace for heat treatment.
In the stress relief annealing heat treatment process in the step (2), the vacuum degree in the furnace is 10-2～10-4Pa。
And (3) in the stress-relief annealing heat treatment process in the step (2), the heating rate is less than 8 ℃ per minute.
The process of the invention can reduce Ti2Residual stress after machining of the AlNb alloy component reduces the risk of cracking of the component.
The invention has the advantages and beneficial effects that:
1. the process can be realized on the traditional vacuum heat treatment furnace, and the process has the application range of Ti-Al alloy (Ti)2AlNb and Ti3Al) powder alloy is subjected to stress relief annealing heat treatment after machining.
2. The function of introducing argon gas to cool to room temperature in the process of the invention is to place the powder alloy component in protective atmosphere to prevent the surface of the component from being oxidized and colored.
3. The invention has simple and practical process, and can improve the overall metallurgical quality of the powder alloy and prolong the service life of the powder alloy, thereby reducing the manufacturing cost of the powder alloy.
4. The process is suitable for stress relief annealing after mechanical processing of the powder metallurgy titanium alloy component formed by direct hot isostatic pressing.
Drawings
FIG. 1 is a graph of the stress relief annealing heat treatment process of example 1.
Detailed Description
The following description of the preferred embodiments of the present invention is provided for the purpose of illustration and description, and is in no way intended to limit the invention.
The present invention will be described in further detail below with reference to the drawings, comparative examples and examples.
The compositions of the following comparative and example alloys are shown in table 1:
TABLE 1.Ti2AlNb alloy composition (wt.%)
Powder Ti2AlNb alloy main transformation point:
α2+ B2 → B2, alloy phase transition point TB2＝1055°C；
O+B2+α2→B2+α2Alloy phase transition point
Powdered Ti in the mechanically added state in the following examples and comparative examples2The AlNb alloy component is prepared by adopting a hot isostatic pressing process and a solution aging heat treatment process, and the specific process comprises the following steps:
preparing alloy powder by argon atomization, filling the powder with the size of below 250 microns into a carbon steel sheath, performing vacuum degassing, performing low-temperature pressure maintaining treatment, performing hot isostatic pressing treatment, and finally performing Ti2And the AlNb alloy component is delivered after solid solution and time-efficient heat treatment.
A first-stage low-temperature pressure maintaining process: the temperature rises and the pressure rises along with the furnace, and the heat preservation temperature is selected
The gas pressure should be greater than or equal to 100MPa, the time is greater than or equal to 30 minutes and less than or equal to 2 hours。
And (3) a second stage hot isostatic pressing process: after the first step is finished, continuously heating and pressurizing, and selecting the heat preservation temperature (T)B2-25°C)～(TB2-5 ℃) the gas pressure should be greater than or equal to 100MPa for a time greater than or equal to 30 minutes and less than or equal to 2 hours.
The third stage solution aging heat treatment process: 980 ℃/2 hours, and cooling to room temperature along with the furnace; 890 deg.C/4 hr, and cooling to room temperature.
Obtaining Ti after machining2AlNb alloy structural member, machine-processed powder metallurgy Ti2The mechanical properties and residual stress values of the AlNb alloy are shown in table 2.
TABLE 2 mechanically processed powder metallurgy Ti2Mechanical property and residual stress of AlNb alloy
Remarking: in the table RmIs tensile strength; rp0.2Is the yield strength; a is elongation; z is the reduction of area; residual stress is the Residual stress.
Comparative example 1
To mechanically-added Ti2Carrying out vacuum annealing heat treatment on the AlNb alloy component, wherein the process parameters are as follows: keeping the temperature at 500 ℃ for 2h, cooling along with the furnace, and keeping the vacuum degree at 10-3Pa. The mechanical properties and residual stress values of the alloy member obtained in this example are shown in Table 3.
TABLE 3 Ti after annealing treatment of comparative example 12Mechanical property and residual stress of AlNb alloy (500 ℃/2h)
Remarking: in the table RmIs tensile strength; rp0.2Is the yield strength; a is elongation; z is the reduction of area; residual stress is the Residual stress.
Comparative example 2
To machine-added stateTi2Carrying out vacuum annealing heat treatment on the AlNb alloy component, wherein the process parameters are as follows: keeping the temperature at 550 ℃ for 2h, cooling along with the furnace, and keeping the vacuum degree at 10-3Pa. The mechanical properties and residual stress values of the alloy member obtained in this example are shown in Table 4.
TABLE 4 Ti after annealing treatment of comparative example 22Mechanical property and residual stress of AlNb alloy (550 ℃/2h)
Remarking: in the table RmIs tensile strength; rp0.2Is the yield strength; a is elongation; z is the reduction of area; residual stress is the Residual stress.
Example 1
To mechanically-added Ti2Carrying out vacuum annealing heat treatment on the AlNb alloy component, wherein the process parameters are as follows: keeping the temperature at 600 ℃ for 2h, cooling along with the furnace, and keeping the vacuum degree at 10-3Pa; when the temperature is cooled to 150 ℃ along with the furnace, argon is introduced into the furnace to cool the furnace to room temperature.
The mechanical properties and residual stress values of the alloy member obtained in this example are shown in table 5.
TABLE 5 Ti after annealing Heat treatment of example 12Mechanical properties of AlNb alloy (600 ℃/2h)
Remarking: in the table RmIs tensile strength; rp0.2Is the yield strength; a is elongation; z is the reduction of area; residual stress is the Residual stress.
The results of the examples show that Ti in the as-machined state is obtained by machining2The AlNb alloy member is subjected to stress relief annealing heat treatment, the residual stress is converted into a compressive stress state from tensile stress, and the compressive stress of the alloy member subjected to 600 ℃ per 2h annealing heat treatment reaches the maximum value of-245 MPa compared with that of the alloy member subjected to comparative example 1 and comparative example 22Residual stress after mechanical processing of the AlNb alloy complex member,thereby reducing the risk of cracking of the component.
Claims (4)
1.Ti2The stress-relief annealing heat treatment process of the AlNb alloy component is characterized by comprising the following steps of: the process comprises the following steps:
(1) ti after mechanical processing2Placing the AlNb alloy component in a vacuum annealing furnace; the Ti2The AlNb alloy component is prepared by adopting a hot isostatic pressing process and a solution aging heat treatment process, firstly, argon atomization is adopted to prepare alloy powder, the powder with the size below 250 microns is filled into a carbon steel sheath, low-temperature pressure maintaining treatment is firstly carried out after vacuum degassing, then hot isostatic pressing treatment is carried out, and finally Ti is carried out2The AlNb alloy component is delivered after solid solution and time-efficient heat treatment, and the specific preparation process comprises the following steps:
a first-stage low-temperature pressure maintaining process: raising the temperature and boosting the pressure along with the furnace, and selecting the heat preservation temperature to be T (B α2+2)～(T (B α2+2)+20 ℃ and a gas pressure greater than or equal to 100MPa for a time greater than or equal to 30 minutes and less than or equal to 2 hours;
and (3) a second stage hot isostatic pressing process: after the first step is finished, continuously heating and pressurizing, and selecting the heat preservation temperature (T) B2-25℃ )～(T B2-5 ℃) at a gas pressure greater than or equal to 100MPa for a time greater than or equal to 30 minutes and less than or equal to 2 hours;
the third stage solution aging heat treatment process: processing at 980 ℃ for 2 hours, and cooling to room temperature along with the furnace; treating at 890 ℃ for 4 hours, and cooling to room temperature along with the furnace; obtaining Ti after machining2An AlNb alloy member;
(2) stress relief annealing heat treatment: the heat treatment temperature is 575-625 ℃, the heat preservation time is 2-4 h, the vacuum degree in the furnace is 10-2~10-4 Pa；
(3) And after the heat treatment and heat preservation stage is finished, stopping heating, cooling to 150-200 ℃ along with the furnace, and then introducing argon into the furnace to cool to room temperature.
2. The Ti of claim 12AlNb alloy structureThe stress-relief annealing heat treatment process of the part is characterized by comprising the following steps of: in the stress-relief annealing heat treatment process in the step (2), the heat treatment temperature is 595-605 ℃, and the heat preservation time is 2-3 hours.
3. The Ti of claim 12The stress-relief annealing heat treatment process of the AlNb alloy component is characterized by comprising the following steps of: and (3) in the stress-relief annealing heat treatment process in the step (2), the heating rate is less than 8 ℃/min.
4. The Ti of claim 12The stress-relief annealing heat treatment process of the AlNb alloy component is characterized by comprising the following steps of: the process can reduce Ti2Residual stress after machining of the AlNb alloy component reduces the risk of cracking of the component.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2019112592794 | 2019-12-10 | ||
| CN201911259279.4A CN110777311A (en) | 2019-12-10 | 2019-12-10 | Ti 2Stress-relief annealing heat treatment process of AlNb alloy member |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111188000A CN111188000A (en) | 2020-05-22 |
| CN111188000B true CN111188000B (en) | 2021-08-31 |
Family
ID=69394374
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911259279.4A Pending CN110777311A (en) | 2019-12-10 | 2019-12-10 | Ti 2Stress-relief annealing heat treatment process of AlNb alloy member |
| CN202010160709.3A Active CN111188000B (en) | 2019-12-10 | 2020-03-10 | Ti2Stress-relief annealing heat treatment process of AlNb alloy member |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911259279.4A Pending CN110777311A (en) | 2019-12-10 | 2019-12-10 | Ti 2Stress-relief annealing heat treatment process of AlNb alloy member |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN110777311A (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111235430B (en) * | 2020-03-02 | 2021-01-15 | 北京理工大学 | Ti-Al alloy shaped charge liner material and powder metallurgy preparation method thereof |
| CN112921259A (en) * | 2021-01-28 | 2021-06-08 | 西安泰金工业电化学技术有限公司 | Residual stress eliminating method for titanium part subjected to powerful spinning deformation |
| CN112958784A (en) * | 2021-02-01 | 2021-06-15 | 中国科学院金属研究所 | Method for actively controlling uniform distribution and growth direction of reinforcing phase in particle-reinforced titanium-based composite material |
| CN113981348A (en) * | 2021-10-19 | 2022-01-28 | 宝鸡钛业股份有限公司 | Method for reducing residual stress of titanium alloy plate |
| CN114774819B (en) * | 2022-04-11 | 2023-05-12 | 中国科学院金属研究所 | Heat treatment process of TC4 alloy castings |
| CN115612879A (en) * | 2022-09-13 | 2023-01-17 | 南昌航空大学 | Ti containing Ta element 2 AlNb alloy and preparation method thereof |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2760469B1 (en) * | 1997-03-05 | 1999-10-22 | Onera (Off Nat Aerospatiale) | TITANIUM ALUMINUM FOR USE AT HIGH TEMPERATURES |
| CN105839039B (en) * | 2016-04-26 | 2017-08-25 | 哈尔滨工业大学 | A kind of preparation method of the TiAl alloy sheet material of uniform formation |
| CN110195172B (en) * | 2019-07-15 | 2021-03-23 | 哈尔滨工业大学 | Ti2AlNb-based alloy material and preparation method thereof |
| CN110252918B (en) * | 2019-07-25 | 2020-05-08 | 西北有色金属研究院 | Ti for 3D printing powder2Preparation method of AlNb-based alloy bar |
-
2019
- 2019-12-10 CN CN201911259279.4A patent/CN110777311A/en active Pending
-
2020
- 2020-03-10 CN CN202010160709.3A patent/CN111188000B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110777311A (en) | 2020-02-11 |
| CN111188000A (en) | 2020-05-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111188000B (en) | Ti2Stress-relief annealing heat treatment process of AlNb alloy member | |
| CN110607464B (en) | Hot isostatic pressing process of Ti2AlNb alloy powder | |
| US4612066A (en) | Method for refining microstructures of titanium alloy castings | |
| US10737314B2 (en) | Method for producing forged TiAl components | |
| CN108950303B (en) | Tough titanium alloy and preparation method thereof | |
| JP5155668B2 (en) | Titanium alloy casting method | |
| JP6176425B1 (en) | α + β type titanium alloy extrusion | |
| JP5855435B2 (en) | α + β-type or β-type titanium alloy and method for producing the same | |
| CN105665729A (en) | High-density Ti2AlNb powder alloy near-net forming technology | |
| CN111304476A (en) | Preparation method of fine-grain powder superalloy for inhibiting formation of original grain boundary | |
| CN113996812A (en) | Heat treatment method for improving fatigue performance of laser selective melting alpha-beta type titanium alloy | |
| EP2807282A2 (en) | Oxygen-enriched ti-6ai-4v alloy and process for manufacture | |
| RU2550459C2 (en) | METHOD OF PARTS MANUFACTURING BY SINTERING OF Co-Cr-Mo ALLOYS HAVING IMPROVED PLASTICITY AT HIGH TEMPERATURES | |
| CN113634767A (en) | Heat treatment method for manufacturing double-phase titanium alloy through laser material increase | |
| CN113862499A (en) | Processing and manufacturing method of novel titanium-based composite material with two-state tissue | |
| JP7233659B2 (en) | Titanium aluminide alloy material for hot forging, method for forging titanium aluminide alloy material, and forged body | |
| CN112958784A (en) | Method for actively controlling uniform distribution and growth direction of reinforcing phase in particle-reinforced titanium-based composite material | |
| CN114645230A (en) | Powder Ti capable of avoiding medium-temperature low plasticity2AlNb alloy member heat treatment process | |
| Sago et al. | METAL INJECTION MOLDING OF ALLOYS FOR IMPLANTABLE MEDICAL DEVICES. | |
| KR101346808B1 (en) | The Titanium alloy improved mechanical properties and the manufacturing method thereof | |
| CN112708788B (en) | Method for improving plasticity of K403 alloy, die material and product | |
| KR101626122B1 (en) | Ferritic oxide dispersion strengthened alloy with excellent high temperature strength and long-term thermal stability and manufacturing method thereof | |
| JP7233658B2 (en) | Titanium aluminide alloy material for hot forging and method for forging titanium aluminide alloy material | |
| CN114959358B (en) | Titanium-aluminum-based intermetallic compound material and preparation method thereof | |
| JPH07150316A (en) | Manufacture of (alpha+beta) type ti alloy forged material |
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 |