CN112453426A - 3D printing enhancement process for titanium alloy for aviation - Google Patents
3D printing enhancement process for titanium alloy for aviation Download PDFInfo
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- CN112453426A CN112453426A CN202011434093.0A CN202011434093A CN112453426A CN 112453426 A CN112453426 A CN 112453426A CN 202011434093 A CN202011434093 A CN 202011434093A CN 112453426 A CN112453426 A CN 112453426A
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- 238000000034 method Methods 0.000 title claims abstract description 41
- 230000008569 process Effects 0.000 title claims abstract description 38
- 238000010146 3D printing Methods 0.000 title claims abstract description 32
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 29
- 239000000843 powder Substances 0.000 claims abstract description 85
- 229910052751 metal Inorganic materials 0.000 claims abstract description 62
- 239000002184 metal Substances 0.000 claims abstract description 62
- 238000001816 cooling Methods 0.000 claims abstract description 12
- 239000002994 raw material Substances 0.000 claims abstract description 12
- 239000000047 product Substances 0.000 claims abstract description 11
- 238000005520 cutting process Methods 0.000 claims abstract description 7
- 239000011265 semifinished product Substances 0.000 claims abstract description 6
- 238000003892 spreading Methods 0.000 claims abstract description 6
- 230000007480 spreading Effects 0.000 claims abstract description 6
- 238000005728 strengthening Methods 0.000 claims description 12
- 238000000137 annealing Methods 0.000 claims description 8
- 230000008859 change Effects 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 7
- 238000002844 melting Methods 0.000 claims description 6
- 230000008018 melting Effects 0.000 claims description 6
- 238000002156 mixing Methods 0.000 claims description 5
- 230000002708 enhancing effect Effects 0.000 abstract description 7
- 230000003746 surface roughness Effects 0.000 abstract description 3
- 230000003014 reinforcing effect Effects 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 10
- 230000007547 defect Effects 0.000 description 7
- 238000007639 printing Methods 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000000630 rising effect Effects 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000000149 argon plasma sintering Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000007709 nanocrystallization Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
- B22F3/10—Sintering only
- B22F3/105—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- 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
Abstract
The invention discloses a 3D printing enhancing process for an aviation titanium alloy, which comprises the following steps of: s1, outputting the raw materials to be spread by a mixer, and flatly spreading the raw materials on a powder bed by a scraper bar and a powder leakage groove; s2, performing first laser scanning on the metal powder on the powder bed until the temperature of the metal powder paved on the powder bed is raised to a preset temperature; s3, planning a scanning path for the preheated metal powder layer according to a set scanning strategy, and performing secondary laser scanning; s4, cooling and forming to obtain a solidified metal sheet; s5, carrying out third laser scanning on the solidified metal sheet to obtain a semi-finished product; and S6, performing fourth laser scanning on the surface of the metal cutting layer of the finished product, and finishing the 3D printing and reinforcing process of the titanium alloy for aviation. The process provided by the invention can reduce cracks and bubbles in the finished product, and the finished product has high mechanical strength, dimensional accuracy and density and low surface roughness Ra value.
Description
Technical Field
The invention relates to the technical field of aviation part machining processes, in particular to a 3D printing strengthening process for an aviation titanium alloy.
Background
The titanium alloy is used in large amount on an air force machine type due to excellent mechanical property and lower density, but the titanium alloy is extremely difficult to process, the finished product rate of parts is greatly reduced, and the production cycle is prolonged. In addition, the air force has higher and higher requirements on the reliability of the airplane, in order to improve the reliability, parts of key parts of the airplane are greatly fused, and the parts are gradually integrated, so that the size is larger and larger, and the shape is more and more complex. In addition, with the wide application of some advanced technologies such as topology optimization and lightweight design in the design of aviation products, a plurality of highly complex parts are formed. Conventional cast-forge welding cannot process highly complex parts, and increasingly restricts the application of advanced design technologies.
Metal 3D printing technology has changed the manufacturing process and has grown more mature in recent years. Currently, metal 3D printing is mainly developed into three major categories, SLM (selective laser melting), EBM (electron beam forming), and LENS (simultaneous powder feeding). The SLM technology has the significant advantages of high forming precision, strong complex structure construction capability, and the like, and thus becomes the mainstream technology of the current metal 3D printing. In the processing process, the SLM technology uses laser to completely melt the powder, does not need an adhesive, and has better molding precision and mechanical property than the laser sintering technology. Therefore, the SLM technology is very important for aerospace researchers. Compared with the traditional process, the SLM metal 3D printing technology does not need a tool clamp or a die, has the advantages of wide forming materials, high complexity of a finished part and the like, and is particularly suitable for production of parts such as titanium alloy and the like which are difficult to machine and parts with high complexity.
Although the domestic SLM metal 3D printing technical field has achieved certain achievements, a larger gap still exists compared with the developed countries. In the existing 3D printing process, because a part area is selected by a laser to be melted, an unmelted area is still powder, the heat conductivity of a melt-formed solid is good, the heat conductivity of a powder material is poor, heat concentration is easily formed in an area with large section change in the Z-axis direction, the heat dissipation difference is large, and the residual stress is large. The defects of cracks, deformation and the like are easily generated on thin walls and special-shaped components of the aircraft, and the requirement on the mechanical performance of parts by the aircraft is strict, so that how to improve the printing process, reduce heat concentration, eliminate residual stress and reduce the printing defect is a problem to be solved urgently in the field. Based on the defects in the prior art, the invention provides a 3D printing enhancing process for an aviation titanium alloy.
Disclosure of Invention
The invention aims to solve the problems of heat concentration, large residual stress and easy formation of printing defects in the existing 3D printing process, and provides a 3D printing enhancing process for titanium alloy for aviation.
The 3D printing enhancing process for the titanium alloy for aviation comprises the following steps:
s1, flexible powder spreading: mixing the powder paving raw materials in a required proportion by a mixer, outputting the mixed raw materials through an output end of the mixer, and flatly paving the mixed sample on a powder bed through a scraper strip and a powder leakage groove to finish flexible powder paving;
s2, preheating metal powder: after the flexible powder laying in the step S1, carrying out first laser scanning on the metal powder on the powder bed until the temperature of the metal powder laid on the powder bed rises to 120-140 ℃, keeping for 3-5 min, and then raising the temperature to 180-220 ℃ to finish the preheating of the metal powder;
s3, laser forming: planning a scanning path for the metal powder layer preheated in the step S2 according to a set scanning strategy, ensuring that the lower seal is firstly melted, and performing secondary laser scanning;
s4, cooling and forming: cooling and forming the sample subjected to the second laser scanning to obtain a solidified metal sheet;
s5, stress relief annealing: carrying out third laser scanning on the surface of the solidified metal sheet, and controlling the temperature to be reduced to 30-40 ℃ below the melting point of the material to obtain a semi-finished product;
s6, laser surface phase change strengthening: and performing fourth laser scanning on the surface of the metal cutting layer of the finished product to finish the 3D printing enhancement process of the titanium alloy for aviation.
Preferably, in step S2, the temperature of the metal powder laid on the powder bed is raised to 130 ℃, maintained for 4min, and then raised to 200 ℃.
Preferably, in step S3, the power of the second laser scanning is 1 to 1.5kW, and the scanning speed is 350 to 500 mm/min.
Preferably, in step S5, the power of the third laser scanning is 30-60 mW, and the scanning speed is 200-260 mm/min.
Preferably, in step S6, the power of the fourth laser scanning is 1000 to 1200W, and the scanning speed is 400 to 500 mm/min.
Compared with the prior art, the invention has the beneficial effects that:
the 3D printing enhancement process for the titanium alloy for aviation mainly aims at special structures such as aviation thin walls and special-shaped parts, and provides a time-sharing collaborative forming technology based on four main stages of variable power laser beam composite scanning, namely metal powder preheating, forming, stress relief annealing and surface strengthening, so that internal cracks and bubbles of products are reduced. In the preheating process of the metal powder, low-power laser scanning is adopted, so that the temperature of the metal powder is raised to about 200 ℃, and further, water vapor in the metal powder overflows to reduce the bubble defects; in the laser forming process, high-power laser scanning is applied to the preheated metal powder layer according to a set scanning strategy, so that the forming speed and the forming capacity of the equipment are improved; in the stress relief annealing, low-power laser scanning is applied to the surface of the solidified metal slice layer, so that the cooling speed is reduced, and on the other hand, the stress relief annealing is realized, so that the residual stress is effectively reduced, and the cracking defect is reduced; and (3) performing laser surface phase change strengthening, namely performing high-intensity laser scanning on the surface of the solidified and formed metal cutting layer, promoting the nanocrystallization of metal grains, adjusting internal stress, welding cracks, and improving the fatigue fracture strength of the formed part layer by layer. Experiments prove that the machining process provided by the invention can obviously reduce the SLM metal 3D printing forming defects, realize 50% reduction of cracks and bubbles of a formed part at the same ratio, improve the mechanical strength, the dimensional precision and the density of the formed part by more than 15%, and lower the surface roughness Ra value of the part than 12.5 um.
Detailed Description
The present invention will be further illustrated with reference to the following specific examples.
Example 1
The invention provides a 3D printing enhancing process for an aviation titanium alloy, which comprises the following steps:
s1, flexible powder spreading: mixing the powder paving raw materials in a required proportion by a mixer, outputting the mixed raw materials through an output end of the mixer, and flatly paving the mixed sample on a powder bed through a scraper strip and a powder leakage groove to finish flexible powder paving;
s2, preheating metal powder: after the flexible powder paving in the step S1, carrying out first laser scanning on the metal powder on the powder bed until the temperature of the metal powder paved on the powder bed rises to 120 ℃, the power is 60mW, the scanning speed is 500mm/min, keeping for 5min, and then rising to 180 ℃ to finish the preheating of the metal powder;
s3, laser forming: planning a scanning path of the metal powder layer preheated in the step S2 according to a set scanning strategy, ensuring that the lower seal is firstly melted, and performing secondary laser scanning, wherein the power is 1.5kW, and the scanning speed is 350 mm/min;
s4, cooling and forming: cooling and forming the sample subjected to the second laser scanning to obtain a solidified metal sheet;
s5, stress relief annealing: carrying out third laser scanning on the surface of the solidified metal sheet, wherein the power is 30mW, the scanning speed is 260mm/min, and the temperature is controlled to be reduced to 40 ℃ below the melting point of the material, so that a semi-finished product is obtained;
s6, laser surface phase change strengthening: and (4) performing fourth laser scanning on the surface of the metal cutting layer of the finished product, wherein the power is 1200W, and the scanning speed is 400mm/min, so that the 3D printing strengthening process of the titanium alloy for aviation is completed.
Example 2
The invention provides a 3D printing enhancing process for an aviation titanium alloy, which comprises the following steps:
s1, flexible powder spreading: mixing the powder paving raw materials in a required proportion by a mixer, outputting the mixed raw materials through an output end of the mixer, and flatly paving the mixed sample on a powder bed through a scraper strip and a powder leakage groove to finish flexible powder paving;
s2, preheating metal powder: after the flexible powder laying in the step S1, carrying out first laser scanning on the metal powder on the powder bed until the temperature of the metal powder laid on the powder bed rises to 130 ℃, the power is 50mW, the scanning speed is 550mm/min, keeping for 4min, and then rising to 200 ℃ to finish the preheating of the metal powder;
s3, laser forming: planning a scanning path of the metal powder layer preheated in the step S2 according to a set scanning strategy, ensuring that the lower seal is firstly melted, and performing secondary laser scanning, wherein the power is 1.2kW, and the scanning speed is 400 mm/min;
s4, cooling and forming: cooling and forming the sample subjected to the second laser scanning to obtain a solidified metal sheet;
s5, stress relief annealing: carrying out third laser scanning on the surface of the solidified metal sheet, wherein the power is 50mW, the scanning speed is 230mm/min, and the temperature is controlled to be reduced to 35 ℃ below the melting point of the material, so as to obtain a semi-finished product;
s6, laser surface phase change strengthening: and (4) performing fourth laser scanning on the surface of the metal cutting layer of the finished product, wherein the power is 1100W, and the scanning speed is 450mm/min, so that the 3D printing strengthening process of the titanium alloy for aviation is completed.
Example 3
The invention provides a 3D printing enhancing process for an aviation titanium alloy, which comprises the following steps:
s1, flexible powder spreading: mixing the powder paving raw materials in a required proportion by a mixer, outputting the mixed raw materials through an output end of the mixer, and flatly paving the mixed sample on a powder bed through a scraper strip and a powder leakage groove to finish flexible powder paving;
s2, preheating metal powder: after the flexible powder laying in the step S1, carrying out first laser scanning on the metal powder on the powder bed until the temperature of the metal powder laid on the powder bed rises to 140 ℃, the power is 30mW, the scanning speed is 600mm/min, keeping for 3min, and then rising to 220 ℃ to finish the preheating of the metal powder;
s3, laser forming: planning a scanning path for the metal powder layer preheated in the step S2 according to a set scanning strategy, ensuring that the lower seal is firstly melted, and performing secondary laser scanning, wherein the power is 1kW, and the scanning speed is 500 mm/min;
s4, cooling and forming: cooling and forming the sample subjected to the second laser scanning to obtain a solidified metal sheet;
s5, stress relief annealing: carrying out third laser scanning on the surface of the solidified metal sheet, wherein the power is 60mW, the scanning speed is 200mm/min, and the temperature is controlled to be reduced to 30 ℃ below the melting point of the material, so as to obtain a semi-finished product;
s6, laser surface phase change strengthening: and (3) performing fourth laser scanning on the surface of the metal cutting layer of the finished product, wherein the power is 1000W, and the scanning speed is 500mm/min, so that the 3D printing enhancement process of the titanium alloy for aviation is completed.
The method provided by the embodiment 1 to the embodiment 3 and the conventional titanium alloy 3D printing process are used for carrying out experiments, and the experimental results show that compared with the conventional titanium alloy 4D printing process, the process method provided by the embodiment 1 to the embodiment 3 of the invention has the advantages that the cracks and the bubbles of the obtained ready-made part are reduced by more than 50% in proportion, the mechanical strength, the dimensional precision and the density of the formed part are improved by more than 15%, the surface roughness Ra value of the part is lower than 12.5um, and the process method is obviously lower than the conventional titanium alloy 4D printing process.
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 person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (6)
1. The 3D printing strengthening process for the titanium alloy for aviation is characterized by comprising the following steps of:
s1, flexible powder spreading: mixing the powder paving raw materials in a required proportion by a mixer, outputting the mixed raw materials through an output end of the mixer, and flatly paving the mixed sample on a powder bed through a scraper strip and a powder leakage groove to finish flexible powder paving;
s2, preheating metal powder: after the flexible powder laying in the step S1, carrying out first laser scanning on the metal powder on the powder bed until the temperature of the metal powder laid on the powder bed rises to 120-140 ℃, keeping for 3-5 min, and then raising the temperature to 180-220 ℃ to finish the preheating of the metal powder;
s3, laser forming: planning a scanning path for the metal powder layer preheated in the step S2 according to a set scanning strategy, ensuring that the lower seal is firstly melted, and performing secondary laser scanning;
s4, cooling and forming: cooling and forming the sample subjected to the second laser scanning to obtain a solidified metal sheet;
s5, stress relief annealing: carrying out third laser scanning on the surface of the solidified metal sheet, and controlling the temperature to be reduced to 30-40 ℃ below the melting point of the material to obtain a semi-finished product;
s6, laser surface phase change strengthening: and performing fourth laser scanning on the surface of the metal cutting layer of the finished product to finish the 3D printing enhancement process of the titanium alloy for aviation.
2. The 3D printing enhancement process for the titanium alloy for aviation according to claim 1, wherein in the step S2, the power of the first laser scanning is 30-60 mW, and the scanning speed is 500-600 mm/min.
3. The 3D printing enhancement process for the titanium alloy for aviation according to claim 1, wherein in the step S2, the temperature of the metal powder laid on the powder bed is raised to 130 ℃, kept for 4min and then raised to 200 ℃.
4. The 3D printing strengthening process for the titanium alloy for aviation as claimed in claim 3, wherein in the step S3, the power of the second laser scanning is 1-1.5 kW, and the scanning speed is 350-500 mm/min.
5. The 3D printing enhancement process for the titanium alloy for aviation according to claim 1, wherein in the step S5, the power of the third laser scanning is 30-60 mW, and the scanning speed is 200-260 mm/min.
6. The 3D printing enhancement process for the titanium alloy for aviation as claimed in claim 1, wherein in step S6, the power of the fourth laser scanning is 1000-1200W, and the scanning speed is 400-500 mm/min.
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| CN115178750A (en) * | 2022-05-16 | 2022-10-14 | 航材国创(青岛)高铁材料研究院有限公司 | Titanium alloy metal phased array standard test block and preparation method thereof |
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Application publication date: 20210309 |