CN114713847A - Large-size structural part laser additive manufacturing method based on residual stress release - Google Patents
Large-size structural part laser additive manufacturing method based on residual stress release Download PDFInfo
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- CN114713847A CN114713847A CN202210034163.6A CN202210034163A CN114713847A CN 114713847 A CN114713847 A CN 114713847A CN 202210034163 A CN202210034163 A CN 202210034163A CN 114713847 A CN114713847 A CN 114713847A
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 34
- 239000000654 additive Substances 0.000 title claims abstract description 33
- 230000000996 additive effect Effects 0.000 title claims abstract description 33
- 238000007639 printing Methods 0.000 claims abstract description 32
- 239000000758 substrate Substances 0.000 claims abstract description 20
- 238000010438 heat treatment Methods 0.000 claims abstract description 17
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 10
- 238000001816 cooling Methods 0.000 claims description 8
- 239000000843 powder Substances 0.000 claims description 7
- 229910052786 argon Inorganic materials 0.000 claims description 5
- 238000010276 construction Methods 0.000 claims description 4
- 239000007789 gas Substances 0.000 claims 1
- 239000000463 material Substances 0.000 description 9
- 238000000034 method Methods 0.000 description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 229910000881 Cu alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- 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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
-
- 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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/64—Treatment of workpieces or articles after build-up by thermal means
-
- 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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/80—Data acquisition or data processing
- B22F10/85—Data acquisition or data processing for controlling or regulating additive manufacturing processes
-
- 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
-
- 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
- B33Y40/00—Auxiliary operations or equipment, e.g. for material handling
- B33Y40/20—Post-treatment, e.g. curing, coating or polishing
-
- 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
- B33Y50/00—Data acquisition or data processing for additive manufacturing
- B33Y50/02—Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Automation & Control Theory (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Powder Metallurgy (AREA)
Abstract
The invention provides a large-size structural member laser additive manufacturing method based on residual stress release, which comprises the steps of firstly, taking a clamping edge of a long edge of a structural member and a substrate as a rotating shaft, rotating a bottom edge of the structural member along an additive manufacturing and building direction to enable the bottom of a short edge to be lifted upwards, and filling the gap between the bottom of a model and the substrate; according to the length of the bottom edge, rounding the connecting part of the short edge and the substrate; the height of the intersection edge of the edge rounding and the short edge is taken as the height of the circle center of the first stress release hole; a second stress release hole is arranged in the direction of the first stress release hole downward close to the rotating shaft; guiding the model of the component into laser additive manufacturing equipment, and printing to obtain a structural component; and carrying out heat treatment on the printed mechanism to obtain the structural member without participating in stress. The invention can improve the yield of the printed products.
Description
Technical Field
The invention belongs to the technical field of additive manufacturing, and particularly relates to a laser additive manufacturing method of a large-size structural part based on residual stress release.
Background
The rudder wing structure is one of main bearing parts of an aircraft, the traditional preparation method is mainly to weld skin and a skeleton structure, the method needs to consume a large amount of manpower and material resources to complete machining and welding of parts, the development period is long, and the development cost is high. With the development of metal additive manufacturing technology, the size of a forming cabin of a printer is larger and larger, and the effective forming length of the device exceeds 600mm, which brings possibility for additive manufacturing of large-size structural members such as rudder wings. During the heating cycle of the laser additive manufacturing process, the thermal expansion of the material is limited by the surrounding material at lower temperatures, creating compressive stress in the heated region, and during the cooling cycle the heated region begins to cool, in which the shrinkage of the material is limited by the plastic strain created during the heating stage, creating tensile stress. If the magnitude of the stress exceeds the yield strength of the material during the hot-cold cycle, residual stresses can form and remain in the part even if the material cools to ambient temperature. For large-size structural members such as rudder wings, residual stress at the bottom in the cooling process is large, and particularly, due to the lack of material constraint at the short edge, the risks of breakage and deformation are multiplied.
Disclosure of Invention
The invention aims to provide a laser additive manufacturing method of a large-size structural part based on residual stress release, aiming at the large-size metal structural part of a rudder wing, in particular to materials with higher strength, such as titanium alloy, high-strength steel and the like, the probability of occurrence of printing cracks can be effectively reduced, and one-step forming of a structural complex copper alloy part is realized.
The technical solution for realizing the purpose of the invention is as follows:
a large-size structural part laser additive manufacturing method based on residual stress release comprises the following steps:
constructing a model:
taking the long edge of the structural member and the clamping edge of the substrate as a rotating shaft, rotating the bottom edge of the structural member along the additive manufacturing construction direction to lift the bottom of the short edge upwards, and filling the gap between the bottom of the model and the substrate;
according to the length of the bottom edge, rounding the connecting part of the short edge and the substrate;
the height of the intersection edge of the edge rounding and the short edge is taken as the height of the circle center of the first stress release hole;
a second stress release hole is arranged in the direction of the first stress release hole downward close to the rotating shaft;
printing a structural part:
guiding the model of the component into laser additive manufacturing equipment, and printing to obtain a structural component;
and (3) heat treatment: and carrying out heat treatment on the printed mechanism to obtain the structural member without participating in stress.
Compared with the prior art, the invention has the remarkable advantages that:
(1) according to the laser additive manufacturing method for the large-size structural part based on residual stress release, the diameter, the rotation angle and the number of stress holes of the structure are determined according to the length of the bottom edge of the model, then the stress holes are rearranged to obtain the required stress release structure, the printing success rate of the product can be increased to 95% for the product with the length size of less than 500mm, and the printing success rate of the product can be increased to 90% for the product with the size of more than 500 mm.
(2) The success rate of printing multiple products in one cabin is greatly improved, for the printing of two products in one cabin, the length size of the products is less than 500mm, the printing success rate of the products can be improved to 95 percent (except for the stress release holes and the supporting structure, the part body is not cracked, the printing success rate of the products can be improved to 90 percent for the products with the size of more than 500 mm).
Drawings
Fig. 1 is a schematic diagram of a rudder wing model.
Fig. 2 is a top view of fig. 1.
Detailed Description
The invention is further described with reference to the following figures and embodiments.
According to the laser additive manufacturing method of the large-size structural member based on residual stress release, the diameter, the rotation angle and the number of stress holes of the structure are determined according to the length of the bottom edge of the model, and then the stress holes are rearranged to obtain the required stress release structure (the specific relation is shown in table 1).
TABLE 1
| Length of bottom edge (mm) | Diameter of stress hole (mm) | Angle of rotation (°) | Number of stress holes |
| 100-200 | 3-4 | 2 | 1-2 |
| 200-300 | 3-5 | 2 | 1-2 |
| 300-400 | 4-6 | 1-2 | 2-3 |
| Over 500A | 5-8 | 1-2 | 2-3 |
Two examples are described in detail below in Table 1:
example 1
According to the laser additive manufacturing method for the large-size structural part based on residual stress release, when the length of the bottom edge of the model is 300mm, two pieces in one cabin are adopted for printing, the model is firstly constructed, then 3D printing is carried out,
A model construction step:
step one, on the premise of meeting the structural size requirement, the clamping edge of the long edge of the structural member and the substrate is used as a rotating shaft, the bottom edge of the structural member is rotated by 2 degrees along the additive manufacturing and building direction, the bottom of the short edge is lifted by about 10mm, and the gap between the bottom of the model and the substrate is filled. As shown in fig. 1 and 2.
And secondly, according to the length of the bottom edge, rounding the edge at the joint of the short edge and the substrate, wherein the radius is 8 mm.
And step three, taking the height of the edge rounding and the short edge as the height of the circle center of the first stress release hole, and taking the height as the diameter of the stress release hole, wherein the diameter of the stress release hole is 3 mm.
And step four, using the left lower part of the first stress release hole as a second stress release hole with the diameter of 3 mm.
And fifthly, copying the model at the position 30mm away from the right side of the structural model to serve as a second product model.
The printing process comprises the following steps:
TC4 powder is used as a raw material, and selective laser melting equipment is adopted for printing. Argon is introduced before printing, so that the oxygen content in the forming chamber is lower than 1000ppm, and the substrate is preheated to 80 ℃. Printing was carried out at a scanning speed of 1200mm/s and a printing power of 350W, with a powder diameter of 15 to 53 μm and a printing layer thickness of 50 μm. And after printing is finished, when the temperature in the forming cabin is reduced to below 70 ℃, taking out the substrate, removing residual powder, and observing the forming condition of the part.
A heat treatment step:
the heat treatment furnace is vacuumized to 10 DEG-3And Pa, heating to 800 ℃, preserving heat for 2 hours, cooling the furnace to 500 ℃, introducing argon for cooling, taking out the sample after the heat treatment is finished, removing the support, and observing part cracks.
The first stress release hole is highly fractured along the edge rounding circle center, the second stress release hole is not fractured, and the success rate of the product of the structural member obtained by the laser material increase manufacturing equipment after multiple tests is 95%. Through set up stress release hole at the filling position, the fracture position can not take place on the structure body, and wisdom takes place in filling position department, provides the yield.
Example 2
In the laser additive manufacturing method for the large-size structural member based on residual stress release of the embodiment, when the length of the bottom edge of the model is 500mm, one cabin is adopted for printing:
Model construction:
step one, on the premise of meeting the structural size requirement, the clamping edge of the long edge of the structural member and the substrate is used as a rotating shaft, the bottom edge of the structural member is rotated by 2 degrees along the additive manufacturing and building direction, the bottom of the short edge is lifted by about 20mm, and the gap between the bottom of the model and the substrate is filled.
And secondly, according to the length of the bottom edge, rounding the edge at the joint of the short edge and the substrate, wherein the radius is 20 mm.
And step three, taking the height of the edge rounding and the short edge as the height of the circle center of the first stress release hole, and taking the height as the height of the circle center of the first stress release hole, wherein the diameter of the stress release hole is 8 mm.
And step four, using the left lower part of the first stress release hole as a second stress release hole with the diameter of 8mm, and using the right lower part of the first stress release hole as a third stress release hole with the diameter of 8mm according to the size of the model.
The printing process comprises the following steps:
and (3) importing the model into software for slicing, and finally obtaining a structural part through laser additive manufacturing equipment: TC4 powder is used as a raw material, and selective laser melting equipment is adopted for printing. Argon is introduced for protection before printing is started, the oxygen content of the forming cabin is enabled to be lower than 1000ppm, and the substrate is preheated to 80 ℃. Printing was carried out at a scanning speed of 1200mm/s and a printing power of 350W, with a powder diameter of 15 to 53 μm and a printing layer thickness of 50 μm. And after printing is finished, when the temperature in the forming cabin is reduced to below 70 ℃, taking out the substrate, removing residual powder, and observing the forming condition of the part.
A heat treatment step:
the heat treatment furnace is vacuumized to 10 DEG-3And Pa, heating to 800 ℃, preserving heat for 2 hours, cooling the furnace to 500 ℃, introducing argon for cooling, taking out the sample after the heat treatment is finished, removing the support, and observing part cracks.
Through tests, the first stress release hole is fractured along the height of the edge rounding circle center, the second stress release hole is not fractured, the third stress release hole is fractured, and the success rate of the product of the structural part obtained through the laser additive manufacturing equipment after multiple tests is 90%.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. A large-size structural part laser additive manufacturing method based on residual stress release is characterized by comprising the following steps:
constructing a model:
taking the long edge of the structural member and the clamping edge of the substrate as a rotating shaft, rotating the bottom edge of the structural member along the additive manufacturing construction direction to lift the bottom of the short edge upwards, and filling the gap between the bottom of the model and the substrate;
According to the length of the bottom edge, rounding the connecting part of the short edge and the substrate;
the height of the intersection edge of the edge rounding and the short edge is taken as the height of the circle center of the first stress release hole;
a second stress release hole is arranged in the direction of the first stress release hole which is downward close to the rotating shaft;
printing a structural part:
guiding the model of the component into laser additive manufacturing equipment, and printing to obtain a structural component;
and (3) heat treatment: and carrying out heat treatment on the printed mechanism to obtain the structural member without participating in stress.
2. The laser additive manufacturing method for large-size structural members based on residual stress relief according to claim 1, wherein the bottom edge is rotated by an angle of 1-2 ° in the additive manufacturing building direction.
3. The laser additive manufacturing method for large-size structural members based on residual stress relief according to claim 1, wherein the bottom of the short edge is raised by 10-20 mm.
4. The laser additive manufacturing method for large-size structural members based on residual stress relief according to claim 1, wherein the radius of the edge rounding is 8-20mm in size.
5. The laser additive manufacturing method for large-size structural members based on residual stress relief as claimed in claim 1, wherein when the length of the bottom edge is not less than 300mm, a third stress relief hole is further provided at the filling position, and the third stress relief hole is close to the edge rounding.
6. The laser additive manufacturing method for large-size structural members based on residual stress relief according to any of claims 1-5, wherein the diameter of the stress relief holes is 3-8 mm.
7. The laser additive manufacturing method of the large-size structural member based on residual stress release according to any one of claims 1 to 5, wherein a shielding gas is introduced during printing to preheat the substrate, and the scanning speed, the printing power and the printing layer thickness are set, and the powder diameter is 15 to 53 μm, so that printing is performed.
8. The laser additive manufacturing method of large-size structural members based on residual stress relief according to any one of claims 1-5, wherein the heat treatment furnace is evacuated to 10 degrees-3Pa, heating to 800 ℃, preserving heat for 2h, cooling the furnace to 500 ℃, and introducing argon for cooling.
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Cited By (1)
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| CN115740501A (en) * | 2022-12-14 | 2023-03-07 | 南京中科神光科技有限公司 | Laser additive manufacturing method for eliminating formation cracks of large-width structural part |
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