CN113369728B - Method for manufacturing titanium alloy large-scale complex structure component - Google Patents
Method for manufacturing titanium alloy large-scale complex structure component Download PDFInfo
- Publication number
- CN113369728B CN113369728B CN202110553595.3A CN202110553595A CN113369728B CN 113369728 B CN113369728 B CN 113369728B CN 202110553595 A CN202110553595 A CN 202110553595A CN 113369728 B CN113369728 B CN 113369728B
- Authority
- CN
- China
- Prior art keywords
- titanium alloy
- welding
- manufacturing
- equal
- component
- 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
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K28/00—Welding or cutting not covered by any of the preceding groups, e.g. electrolytic welding
- B23K28/02—Combined welding or cutting procedures or apparatus
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2103/00—Materials to be soldered, welded or cut
- B23K2103/08—Non-ferrous metals or alloys
- B23K2103/14—Titanium or alloys thereof
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laser Beam Processing (AREA)
- Welding Or Cutting Using Electron Beams (AREA)
Abstract
The invention provides a manufacturing method of a titanium alloy large-scale complex structure component, which comprises the following steps: taking a plurality of titanium alloy base materials with equal section thicknesses; wherein the content of the first and second substances,the thickness H of the cross section is less than or equal to 100 mm; under a vacuum environment, sequentially welding the titanium alloy base materials end to end on two sides by using electron beams to obtain a welding part; wherein the process conditions during the electron beam welding are as follows: the voltage is 150kV, the speed is 4-10 mm/s, the beam current is 50-150 mA, the focusing current is 2050-2120 mA, and the working pressure in the cavity is less than or equal to 6.7 multiplied by 10 ‑2 Pa; in an inert atmosphere, carrying out laser melting deposition on the surface of the welding part close to the welding area to obtain a component with a complex shape, and realizing the connection and the forming of a large-scale complex structural component of the titanium alloy, thereby greatly improving the material utilization rate, shortening the manufacturing period and reducing the cost.
Description
Technical Field
The invention relates to the technical field of electron beam welding and laser additive manufacturing composite connection methods, in particular to a manufacturing method of a titanium alloy large-scale complex structural component.
Background
With the development of the industries in the field of mechanical delivery such as aerospace, weapons, ships and warships and the like, various advanced equipment and components gradually develop towards large-scale, integration and light weight, wherein the traditional manufacturing process of high-performance large-scale complex structural components faces the problems of high manufacturing difficulty, low material utilization rate and high cost. The titanium alloy has the advantages of high specific strength, good heat resistance, corrosion resistance and the like, is widely applied to the aerospace and large equipment manufacturing industry, and for large complex titanium alloy components, the efficient and low-cost connection manufacturing technology becomes one of the core technologies of the major advanced equipment manufacturing industry.
The titanium alloy large frame beam structure is difficult to form by direct forging and subsequent machining, the equipment requirement is high, and particularly, the preparation period is long and the cost is high when the titanium alloy large frame beam structure is used for components with special shapes and complex structures. Because the electron beam welding titanium alloy process is mature, and the performance of the related welding joint can be controlled to meet the structural requirement, the equal-section plate parts in the large-sized titanium alloy complex structural component can be directly connected by adopting an electron beam butt welding mode, and the large-sized requirement for forming the titanium alloy complex structural component is preliminarily realized.
However, for the efficient manufacturing of large-scale complex structural components made of titanium alloy, the electron beam butt welding method can only solve the connection requirement of simple structures such as an inner uniform section of the component, and the preparation of complex structural areas needs to be realized by other manufacturing technologies. For example, the prior art typically assisted with machining a material reduction to form a complex structure external to the component, but this method is prone to substantial material waste and may face the problem of the cross-sectional thickness of the weld exceeding the maximum thickness (about 100mm) that the electron beam can weld, resulting in an unachievable joining process.
Disclosure of Invention
In order to solve the problems, the invention provides a method for manufacturing a titanium alloy large-scale complex structural component, which initially realizes the manufacture of the whole size of the component by electron beam butt welding of a sheet material piece with equal section thickness, carries out external laser material increase manufacturing of a complex structure on the basis of an equal section welding piece, and realizes the connection and the forming of the titanium alloy large-scale complex structural component.
In order to achieve the above object, the present invention provides a method for manufacturing a large complex structural member of titanium alloy.
The manufacturing method of the titanium alloy large-scale complex structure component comprises the following steps:
taking a plurality of titanium alloy base materials with equal section thickness; wherein the section thickness H is less than or equal to 100 mm;
under a vacuum environment, sequentially welding the titanium alloy base materials end to end on two sides by using electron beams to obtain a welding part; wherein the process conditions during the electron beam welding are as follows: the voltage is 150kV, the speed is 4-10 mm/s, the beam current is 50-150 mA, the focusing current is 2050-2120 mA, the working pressure in the cavity is less than or equal to 6.7 multiplied by 10- 2 Pa；
And carrying out laser melting deposition on the surface of the welding part close to the welding area in an inert atmosphere to obtain the component.
Further, the inert atmosphere is argon atmosphere, and the oxygen content is less than or equal to 50 ppm.
Further, the process conditions of the laser melting deposition are as follows: the power is 4-6 kW, the scanning speed is 600-1200 mm/min, and the diameter of a laser spot is 5-8 mm.
Further, the raw material adopted by the laser melting deposition is titanium alloy pre-alloy powder with the granularity of 70-250 mu m, and the chemical composition of the titanium alloy pre-alloy powder is consistent with that of the titanium alloy base material.
Further, a first annealing treatment is carried out on the welding part before the laser melting deposition;
and a second annealing process of the component is required after the laser melting deposition.
Further, the process conditions of the first annealing treatment are as follows: and (4) heating to 500-600 ℃, preserving the heat for 4-6 hours, and then air cooling.
Further, the process conditions of the second annealing treatment are as follows: and (4) heating to 500-600 ℃, preserving the heat for 4-6 hours, and then air cooling.
Furthermore, before the welding, the surfaces to be welded of the base materials are respectively required to be polished, degreased, cleaned and dried.
Furthermore, after the first annealing treatment, the area of the welding part to be subjected to laser melting deposition needs to be polished, cleaned and dried.
Furthermore, the flatness tolerance of the surface to be welded of the base material is 0.015-0.025 mm, the surface roughness is 3.0-3.2 microns, and the parallelism is 0.04-0.05 mm.
According to the invention, on the basis of electron beam butt welding of sheet materials with equal section thickness, laser additive manufacturing is carried out on the surface of the welding part to form the required external complex shape of the component, so that the manufacturing of the titanium alloy large complex structural component can be finally realized. The section thickness of the titanium alloy plate with the equal section thickness only needs to meet the thickness of a simple section structure in complex structural components such as a titanium alloy large frame beam structure and the like, and on the basis, the external complex shape of the component formed by additive manufacturing is also in a near-shape state, so that the whole component only needs to be subjected to a small amount of mechanical processing subsequently, the material utilization rate is greatly improved, the manufacturing period is shortened, and the cost is reduced.
Compared with the traditional manufacturing mode, the large-scale complex structure member connecting method can realize the near-shape rapid manufacturing of the large-scale complex structure titanium alloy member in different structure combination forms through the cooperation mode of the electron beam welding of the uniform-section simple-shape plate member and the laser additive manufacturing of the external complex structure of the forming welding member, and has the advantages of high manufacturing efficiency, high material utilization rate and low cost.
The connecting method of the large-scale complex structural member can be used for the near-shape quick connection manufacturing of the titanium alloy large-scale member with the complex external characteristic structure, and compared with the traditional manufacturing process, the connecting method has the advantages of short period and high material utilization rate; in addition, the force transmission form of the component connecting area can be promoted to be changed from the force transmission form characteristic of the internal uniform-section welding area to the large-section force transmission form characteristic of the internal uniform-section welding area and the external additive manufacturing area in cooperation with the additive manufacturing area/the substrate interface area, and the service safety of the component connecting area is improved.
The electron beam welding process and the laser melting deposition process supplement each other, and under the specific welding process condition and the laser melting deposition process condition, an electron beam connecting area is compact, the defects of oxidation, cracks and the like are avoided, the stress is low, and the mechanical property of a large member is improved.
Drawings
Various additional advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic flow chart of a method for manufacturing a large complex structural member made of titanium alloy according to an embodiment of the present invention.
In the figure:
(a) the schematic diagram is shown as the titanium alloy uniform-section deformed plate with the thickness H less than or equal to 100 mm;
(b) the schematic diagram of the titanium alloy uniform-section deformed plate with the thickness H less than or equal to 100mm in electron beam butt welding is shown;
(c) the surface laser forming complex appearance structure of the electron beam welding piece of the titanium alloy deformed material uniform section plate is shown as a schematic diagram.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
According to an embodiment of the present invention, there is provided a method of manufacturing a titanium alloy large complex structural member, as shown in fig. 1, the method including the steps of:
firstly, according to typical geometric dimension characteristics of titanium alloy components with complex structures such as large frame beams, the titanium alloy components are divided into different areas such as titanium alloy plate structures with equal section thicknesses and external complex structures, and an electron beam welding position and an external laser additive manufacturing area are designed.
And secondly, machining the titanium alloy plate with the equal section thickness, cutting the titanium alloy plate into parts with the size required by electron beam welding, and polishing, deoiling, degreasing, cleaning and drying the to-be-welded surfaces of the parts. The titanium alloy plate with the uniform cross-section thickness is a rolled or forged plate, the cross-section thickness H of the titanium alloy plate is less than or equal to 100mm, the cross section of a part to be welded is obtained by processing through a milling machine, the flatness tolerance is 0.015-0.025 mm, the surface roughness Ra3.0-3.2 mu m, and the parallelism is 0.04-0.05 mm.
It should be noted that the grinding, degreasing, cleaning and drying processes of the surfaces to be welded of the parts in the present invention are all conventional operation techniques in the field.
Thirdly, fixing the part on a platform of the electron beam welding equipment, and vacuumizing to 10- 2 After Pa, performing electron beam welding on the workpiece to obtain a welding part with an electron beam connection area; the electron beam welding is single-side forming or double-side forming butt welding, a tool fixture is adopted to butt-joint and clamp the sections to be welded of the parts with equal sections before welding, and the process conditions of the electron beam butt welding are as follows: the voltage is 150kV, the speed is 4-10 mm/s, the beam current is 50-150 mA, and the focusing current is 2050 to 2120mA, working pressure intensity in the cavity less than or equal to 6.7 x 10- 2 Pa。
Thirdly, performing stress relief annealing treatment on a welding piece obtained after the electron beam welding in a heat treatment furnace; wherein the process conditions of the stress relief annealing treatment are as follows: heating to 500-600 ℃, preserving heat for 4-6 h, and then air cooling.
Thirdly, performing surface polishing, cleaning and drying treatment on the laser additive area with the complex structure in the welding part after the stress relief annealing treatment; different metallurgical interface areas are respectively formed between the complex structure laser additive area and an electron beam connecting area (electron beam welding seam area) and between the complex structure laser additive area and the equal-section titanium alloy base material area, the electron beam welding seam area is covered by the complex structure laser additive area, and the complex structure laser additive area is formed outside the electron beam welding seam area and the equal-section titanium alloy base material.
It should be noted that the grinding, cleaning and drying treatment of the laser additive area with a complex structure in the welding part of the invention are all conventional operation techniques in the field.
And thirdly, fixing the welding part subjected to stress relief annealing treatment in laser additive manufacturing equipment, and performing laser melting deposition outside the electron beam connection area according to the requirement of a complex structure to obtain the component. The laser additive manufacturing method comprises the following processing steps of: firstly, titanium alloy powder with the granularity of 70-250 mu m is put into a powder feeder, wherein the content of interstitial element powder is (wt%): fe <0.25, O <0.15, C <0.08, N <0.05, H < 0.012; secondly, fixing the titanium alloy substrate in an additive manufacturing cavity, introducing argon with the purity of more than 99.99% for protection, and keeping the oxygen content not higher than 50 ppm; and finally, continuously melting and depositing the synchronously fed powder by taking laser as a heat source to nearly net manufacture the shape of a complex structure. The laser additive manufacturing method comprises the following process parameters: the power is 4-6 kW, the scanning speed is 600-1200 mm/min, and the diameter of a laser spot is 5-8 mm.
The main alloy composition of the titanium alloy prealloyed powder is identical to the main alloy composition of the base material.
And finally, performing stress relief annealing treatment on the component obtained by laser melting deposition in a heat treatment furnace. Wherein the process conditions of the stress relief annealing treatment are as follows: heating to 500-600 ℃, preserving heat for 4-6 h, and then air cooling.
The method for manufacturing a large complex structural member of titanium alloy using internal welding in cooperation with external additive manufacturing in the present invention will be described in detail below with specific examples.
Example 1:
first, a TC11 titanium alloy plate-shaped deformation material piece with the equal section thickness of 40mm is cut and processed (see attached drawing a), the surface is polished and cleaned, the flatness tolerance of the surface to be welded of the sample is 0.02mm, the surface roughness Ra3.2 μm, and the parallelism is controlled at 0.05 mm.
And then carrying out electron beam butt welding on the sample piece in a vacuum environment (see the attached drawing b), wherein the process parameters of the electron beam butt welding are as follows: voltage 150kV, speed 10mm/s, beam current 150mA, focusing current 2120mA, working pressure in cavity less than or equal to 6.7X 10- 2 Pa。
And (3) putting the electron beam butt welding sample into a heat treatment furnace, heating to 600 ℃, performing stress relief annealing, and cooling in air after treating for 4 hours.
And then, mechanically processing and cleaning the weld part surface excess height and relevant surface defects such as oxide scales, adhered powder particles and the like by using a milling machine.
And after the surface of the workpiece to be welded is polished to be smooth, wiping out fingerprints, oil stains, water stains and other pollution traces on the surface of the joint by using acetone.
And (3) transferring the cleaned to-be-welded part into a laser additive manufacturing system, clamping by using a tool clamp, introducing argon with the purity of more than 99.99% for protection, and keeping the oxygen content not higher than 50ppm to prepare for laser additive manufacturing (see attached figure c).
Putting TC11 titanium alloy prealloying powder with the granularity of 70-250 mu m into a powder feeder, and carrying out coaxial powder feeding, laser melting deposition and near-net forming to manufacture the shape of the external complex structure of the component. The laser additive manufacturing method comprises the following process parameters: the power is 6kW, the scanning speed is 1200mm/min, and the laser spot diameter is 8 mm.
Before deposition, a low-power laser beam is needed to preheat the welding area and the surface of the titanium alloy deformation material so as to obtain good interface quality during subsequent continuous melting deposition and reduce the formation probability of metallurgical defects such as air holes or non-fusion in an interface area; in the deposition process, under the protection of argon atmosphere, according to the characteristics of the external shape of the large-scale component with the titanium alloy complex structure, the scanning path and the scanning speed can be changed strategically, and finally, the additive manufacturing area with ideal shape and quality is obtained.
After laser additive manufacturing, the whole component is placed into a heat treatment furnace, the temperature is raised to 600 ℃, stress relief annealing is carried out again, and air cooling is carried out after treatment for 4 hours.
Example 2:
firstly, a TC11 titanium alloy plate-shaped deformation material piece with the equal section thickness of 60mm is cut and processed (see attached drawing a), the surface is polished and cleaned, the flatness tolerance of the surface to be welded of the sample is 0.02mm, the surface roughness Ra3.2 μm, and the parallelism is controlled to be 0.05 mm.
And then carrying out electron beam butt welding on the sample piece in a vacuum environment (see the attached drawing b), wherein the process parameters of the electron beam butt welding are as follows: the voltage is 150kV, the speed is 6mm/s, the beam current is 100mA, the focusing current is 2100mA, the working pressure in the cavity is less than or equal to 6.7 multiplied by 10- 2 Pa。
And (3) putting the electron beam butt welding sample into a heat treatment furnace, heating to 500 ℃ for stress relief annealing, and cooling in air after 6 hours of treatment.
And then, mechanically processing and cleaning the excess height of the surface of the welding part and surface defects such as related oxide scales, adhered powder particles and the like by using a milling machine.
And after the surface of the workpiece to be welded is polished to be smooth, wiping fingerprints, oil stains, water stains and other pollution traces on the surface of the joint by using acetone.
And (3) transferring the cleaned to-be-welded part into a laser additive manufacturing system, clamping by using a tool clamp, introducing argon with the purity of more than 99.99% for protection and keeping the oxygen content not higher than 50ppm, and preparing for laser additive manufacturing (see attached drawing c).
Putting TC11 titanium alloy prealloying powder with the granularity of 70-250 mu m into a powder feeder, and carrying out coaxial powder feeding, laser melting deposition and near-net forming to manufacture the shape of the external complex structure of the component. The laser additive manufacturing method comprises the following process parameters: the power is 5kW, the scanning speed is 1000mm/min, and the laser spot diameter is 6 mm.
Before deposition, a low-power laser beam is needed to preheat the welding area and the surface of the titanium alloy deformation material so as to obtain good interface quality during subsequent continuous melting deposition and reduce the formation probability of metallurgical defects such as air holes or non-fusion in an interface area; in the deposition process, under the protection of argon atmosphere, according to the characteristics of the external shape of the large-scale component with the titanium alloy complex structure, the scanning path and the scanning speed can be changed strategically, and finally, the additive manufacturing area with ideal shape and quality is obtained.
After laser additive manufacturing, the whole component is put into a heat treatment furnace, heated to 600 ℃ for stress relief annealing again, and air-cooled after treatment for 4 hours.
The titanium alloy large-scale component manufactured by the cooperation of internal welding and external additive in the embodiment of the invention can have a complex appearance structure, and the titanium alloy large-scale component with the complex appearance structure can be manufactured efficiently at low cost.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (6)
1. A manufacturing method of a titanium alloy large-scale complex structural component is characterized by comprising the following steps:
taking a plurality of titanium alloy base materials with equal section thickness; wherein the section thickness H is less than or equal to 100 mm; the flatness tolerance of the surface to be welded of the titanium alloy base material is 0.015-0.025 mm, the surface roughness is 3.0-3.2 mu m, and the parallelism is 0.04-0.05 mm;
under a vacuum environment, sequentially welding the titanium alloy base materials end to end on two sides by using electron beams to obtain a welding part; wherein, the process strip during the electron beam weldingThe parts are as follows: the voltage is 150kV, the speed is 4-10 mm/s, the beam current is 50-150 mA, the focusing current is 2050-2120 mA, and the working pressure in the cavity is less than or equal to 6.7 multiplied by 10 -2 Pa；
Carrying out first annealing treatment on the welding part; the process conditions are as follows: heating to 500-600 ℃, preserving the heat for 4-6 h, and then air cooling;
in an inert atmosphere, carrying out laser melting deposition on the surface of the welding part close to the welding area to obtain a component;
carrying out secondary annealing treatment on the component; the process conditions are as follows: heating to 500-600 ℃, preserving heat for 4-6 h, and then air cooling.
2. The method for manufacturing a large-sized complicated structural member of titanium alloy according to claim 1, wherein the inert atmosphere is an argon atmosphere and the oxygen content is 50ppm or less.
3. The method for manufacturing the large-scale complex structural member of titanium alloy according to claim 1, wherein the process conditions of the laser melting deposition are as follows: the power is 4-6 kW, the scanning speed is 600-1200 mm/min, and the diameter of a laser spot is 5-8 mm.
4. The method for manufacturing the large-scale complex structural member of titanium alloy according to claim 1, wherein the raw material adopted by the laser melting deposition is titanium alloy pre-alloyed powder with the grain size of 70-250 μm, and the chemical composition of the titanium alloy pre-alloyed powder is consistent with that of the titanium alloy base material.
5. The method for manufacturing large-scale complex structural member of titanium alloy according to claim 1, wherein before the welding, the surfaces to be welded of the base material are further subjected to polishing, degreasing, cleaning and drying respectively.
6. The method for manufacturing the large-scale complex structural component made of the titanium alloy as claimed in claim 1, wherein after the first annealing treatment, the areas to be subjected to laser melting deposition of the welded parts are further subjected to grinding, cleaning and drying treatment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110553595.3A CN113369728B (en) | 2021-05-20 | 2021-05-20 | Method for manufacturing titanium alloy large-scale complex structure component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110553595.3A CN113369728B (en) | 2021-05-20 | 2021-05-20 | Method for manufacturing titanium alloy large-scale complex structure component |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113369728A CN113369728A (en) | 2021-09-10 |
| CN113369728B true CN113369728B (en) | 2022-08-19 |
Family
ID=77571417
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110553595.3A Active CN113369728B (en) | 2021-05-20 | 2021-05-20 | Method for manufacturing titanium alloy large-scale complex structure component |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113369728B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114043109B (en) * | 2021-12-15 | 2024-07-23 | 中国航发动力股份有限公司 | Composite connection method of large-size round-square 3D printer cartridge |
| CN114570944B (en) * | 2022-03-07 | 2023-07-14 | 西北工业大学 | High-energy beam manufacturing method of complex component made of dissimilar metal materials difficult to be compatible |
| CN117852352B (en) * | 2024-01-09 | 2024-09-24 | 北京航空航天大学宁波创新研究院 | Rapid finite element modeling method for additive manufacturing of large complex structure |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016511697A (en) * | 2013-01-31 | 2016-04-21 | シーメンス エナジー インコーポレイテッド | Selective laser melting / sintering using powdered flux |
| CN108202142A (en) * | 2016-12-16 | 2018-06-26 | 北京有色金属研究总院 | A kind of laser substep increasing material manufacturing method |
| CN107498203B (en) * | 2017-08-10 | 2019-06-14 | 北京煜鼎增材制造研究院有限公司 | A kind of electron beam welding and laser gain material manufacture composite connecting method |
| CN107775194A (en) * | 2017-10-16 | 2018-03-09 | 北京煜鼎增材制造研究院有限公司 | A kind of laser gain material manufacture extension and electron beam welding composite connecting method |
| CN107755882A (en) * | 2017-10-17 | 2018-03-06 | 西安飞机工业（集团）有限责任公司 | A kind of large titanium alloy component laser gain material connection method |
-
2021
- 2021-05-20 CN CN202110553595.3A patent/CN113369728B/en active Active
Non-Patent Citations (1)
| Title |
|---|
| 航空航天钛合金结构件增材制造技术;唐洪奎 等;《金属加工（热加工）》;20200831(第8期);14-17 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113369728A (en) | 2021-09-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113369728B (en) | Method for manufacturing titanium alloy large-scale complex structure component | |
| KR20200083312A (en) | Method for controlling deformation and precision of parts in parallel in additive manufacturing process | |
| CN114101888B (en) | Zirconium alloy low-temperature diffusion connection method | |
| CN114434086B (en) | Surface crack repairing method for titanium alloy thin-wall part | |
| CN112775431B (en) | Laser additive manufacturing method of titanium alloy/stainless steel dissimilar metal member | |
| CN108637447B (en) | Electron beam welding method for dissimilar metals of titanium alloy and kovar alloy | |
| CN105414764A (en) | TIG (tungsten inert gas welding) arc synchronous preheating assisted connection method based on laser additive manufacturing | |
| CN111218684B (en) | Method for preparing high-melting-point coating through laser-assisted ultrahigh-speed laser cladding | |
| CN108213713B (en) | Thin-wall part composite repairing method based on pulse laser and continuous laser additive | |
| CN103008869B (en) | Electron beam pressurizing connection method for aluminum alloy and particle-reinforced aluminum matrix composite material | |
| WO2019156168A1 (en) | Method for reclaiming tool material and tool material | |
| TW201718119A (en) | Titanium composite material, and titanium material for hot rolling | |
| CN108857034B (en) | Electron beam welding method of BTi6431S high-temperature titanium alloy material | |
| CN113478063B (en) | Titanium-zirconium-molybdenum alloy vacuum diffusion bonding method taking refractory metal as intermediate layer | |
| WO2022222590A1 (en) | Additive manufacturing process, additive layer, additive product, and composite laser | |
| CN115091022B (en) | Crack repairing and micro-additive method based on friction stir welding | |
| CN111299833A (en) | Dissimilar metal pulse laser welding method for titanium alloy and stainless steel | |
| CN115261870A (en) | Short-process composite ultra-high-speed laser cladding processing method based on Haokeng technology | |
| CN113953670A (en) | Welding method of dissimilar metal tailor-welded blank | |
| CN116809680A (en) | Preparation method of titanium-aluminum composite sheet material | |
| CN113481448A (en) | Titanium alloy member and heat treatment method for titanium alloy member | |
| CN114083132A (en) | Friction-stir-assisted arc fuse additive manufacturing method suitable for magnesium alloy | |
| CN113084197A (en) | Inching repair method for thin-wall structural part based on laser additive manufacturing | |
| CN109848643B (en) | Method for improving corrosion resistance of 7075 aluminum alloy friction stir welding joint | |
| CN109604586B (en) | 3D printing repairing ink material and method suitable for rolled steel |
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 |