CN113664218A - Composite manufacturing method of ultra-large metal structure - Google Patents
Composite manufacturing method of ultra-large metal structure Download PDFInfo
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- CN113664218A CN113664218A CN202111014344.4A CN202111014344A CN113664218A CN 113664218 A CN113664218 A CN 113664218A CN 202111014344 A CN202111014344 A CN 202111014344A CN 113664218 A CN113664218 A CN 113664218A
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- 239000002184 metal Substances 0.000 title claims abstract description 32
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 24
- 239000002131 composite material Substances 0.000 title claims abstract description 8
- 239000000843 powder Substances 0.000 claims abstract description 45
- 238000010438 heat treatment Methods 0.000 claims abstract description 36
- 238000000034 method Methods 0.000 claims abstract description 35
- 239000000463 material Substances 0.000 claims abstract description 29
- 238000003754 machining Methods 0.000 claims abstract description 6
- 239000000654 additive Substances 0.000 claims description 25
- 230000000996 additive effect Effects 0.000 claims description 25
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 12
- 239000010445 mica Substances 0.000 claims description 6
- 229910052618 mica group Inorganic materials 0.000 claims description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- 238000005266 casting Methods 0.000 claims description 4
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- 238000009413 insulation Methods 0.000 claims description 4
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- 230000008646 thermal stress Effects 0.000 abstract description 7
- 238000005516 engineering process Methods 0.000 description 7
- 230000002457 bidirectional effect Effects 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
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- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
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Classifications
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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
- B22F10/20—Direct sintering or melting
-
- 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
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
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- 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
-
- 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 composite manufacturing method of an ultra-large metal structure, which comprises the following steps of 1) processing split parts, wherein the ultra-large metal structure to be manufactured is divided into a plurality of split parts to be respectively molded; 2) the method comprises the following steps of (1) groove machining, wherein a groove is formed on each split part so as to realize that the grooves on the split parts to be connected with each other are integrally formed into an X-shaped groove; 3) the material increase connection is carried out, and metal powder is adopted for laser material increase connection so as to connect the plurality of split parts into an ultra-large metal structure; 4) and local heat treatment, namely performing local heat treatment on the ultra-large metal structure by adopting a local heat treatment device. According to the invention, through a novel X-shaped connection groove design mode, the difference of the performance of the connection area and the base material and the high thermal stress of the connection area are solved; the local heat treatment device and the local heat treatment method are designed, and the influence on other parts of the frame is reduced to the maximum extent under the condition of ensuring the performance requirement of the connection area.
Description
Technical Field
The invention relates to the technical field of metal structure manufacturing, in particular to a composite manufacturing method of an ultra-large metal structural part such as an airplane integral frame.
Background
The rear fuselage of the airplane mainly comprises a central cabin, a left cabin and a right cabin, and a transverse bearing component of the rear fuselage comprises a plurality of frames, wherein the whole frame is used as one of important bearing reinforcing frames of the rear fuselage and has very important influence on the stability of the fuselage.
The whole frame is composed of an outer frame section, an upper frame section and a lower frame section respectively, the whole frame is very complex in structure, poor in processing manufacturability and large in size, manufacturing difficulty is very high, an ordinary machine tool is difficult to integrally process, and after the outer frame section, the upper frame section and the lower frame section are forged or cast respectively, the problems that connection difficulty is large, and performance of a joint is poor exist, and requirements of the aerospace industry are difficult to meet.
The laser additive manufacturing technology is a rapid forming technology, the principle of 'dispersion + accumulation + lamination' is utilized, on the basis of the slicing data of a three-dimensional solid model of a part CAD, high-power laser melting synchronously-conveyed metal powder is controlled through computer programming, partial material is melted on the surface of a base material, the high-power laser melting synchronously-conveyed metal powder and the high-power laser melting synchronously-conveyed metal powder are mixed to form a molten pool, and the molten pool is rapidly solidified after a laser beam sweeps over the molten pool, so that the laser beam is deposited on the solidified base material and is accumulated layer by layer, and finally the three-dimensional part is obtained. The technology can realize the rapid and mold-free near-net forming of the large-scale compact metal parts with complex structures. This technique can also be used to connect parts, and compared to welding, it has the following advantages: (1) the heat input quantity can be reduced to be very low, the range of a heat affected zone is small, and deformation caused by heat conduction is little; (2) no electrode is needed, and no electrode pollution is caused; (3) the laser beam is easily focused, aligned, placed at a suitable distance from the workpiece, and can work between tools or obstacles around the workpiece; (4) the high-speed welding can be automatically carried out easily and is controlled by a computer; (5) when thin materials or small-diameter wires are connected, the problem of melt-back of the thin materials or the small-diameter wires in arc welding is solved; (6) the magnetic field is not influenced, and the parts can be accurately connected.
Therefore, the additive manufacturing technology provides a new thought for the connection of the whole frame, and a more reliable method with a shorter period is hopefully provided for the preparation of the whole frame of the airplane.
Disclosure of Invention
The invention provides a composite manufacturing method of an ultra-large metal structure by using a laser additive manufacturing technology, which aims to solve the connection problem of the whole frame of the large metal structure such as an airplane.
A composite manufacturing method of an ultra-large metal structure is characterized in that: comprises the following steps of (a) carrying out,
1) the method comprises the following steps of (1) processing split parts, namely dividing the ultra-large metal structure to be manufactured into a plurality of split parts to be respectively molded;
2) the method comprises the following steps of (1) groove machining, wherein a groove is formed on each split part so as to realize that the grooves on the split parts to be connected with each other are integrally formed into an X-shaped groove;
3) the material increase connection is carried out, and metal powder is adopted for laser material increase connection so as to connect the plurality of split parts into an ultra-large metal structure;
4) and local heat treatment, namely performing local heat treatment on the ultra-large metal structure by adopting a local heat treatment device.
Further preferably, the angle of the X-shaped groove is 55-75 degrees.
Further preferably, the thickness of the split connecting area is increased to 90mm or more during molding and processing, and the split connecting area is reduced to a proper size through machining after local heat treatment.
Preferably, the laser additive connection adopts a long-focus laser head, a lengthened powder feeding pipe is combined to extend into the X-shaped groove for powder feeding, and the lengthened powder feeding pipe extends out of the bottom of the long-focus laser head by 15-25 mm.
Further preferably, the laser additive connection adopts a bidirectional scanning process.
Further preferably, the laser additive connection process parameters are that the laser power is 1500-1800W, the scanning speed is 7-8mm/s, and the powder feeding speed is 70-80 g/min.
Preferably, the local heat treatment device is a tubular furnace with two open ends, the tubular furnace comprises a support base and an upper semi-cylindrical furnace shell and a lower semi-cylindrical furnace shell which are positioned on the support base and can be hinged, a mica heat insulation sheet is arranged on the inner wall of the shell, a heating wire controlled and adjusted by PID is arranged on the mica sheet, and a thermocouple extends into the furnace body; and during heat treatment, the additive manufacturing connection area of the ultra-large metal structure is placed inside the tube furnace, other areas except the connection area are placed outside the tube furnace, and the other areas are subjected to water cooling.
Further preferably, the ultra-large metal structure is an integral frame component of an airplane afterbody, and the metal is a TC4DT titanium alloy.
Further preferably, the forming process of the separate piece is casting, forging or additive manufacturing.
Further preferably, the heat treatment process parameters are a heating temperature of 600-.
Compared with the prior art, the invention has the beneficial effects that:
first, a special X-groove was designed. A groove of about 65 degrees is formed on the split parts at the two sides through mechanical processing, and under the protective atmosphere, powder and a base material are melted by means of a specially designed extended powder feeding pipe and high heat input of laser, so that the effective connection of large alloy components is realized.
Secondly, a novel local heat treatment furnace is designed, local heat treatment is carried out on the connecting area, other parts of the large-scale component cannot be influenced, and the connecting area can meet the performance requirement.
Thirdly, by adopting bidirectional scanning and combining with proper laser additive process parameters, the effective control of internal microstructure, residual stress, deformation and cracking can be realized so as to meet the requirements of various performances.
Fourthly, in order to overcome the defect that the connecting area is easy to deform or even break, the wall thickness of the connecting area is thickened to be more than 90mm through research and design, so that the heat dissipation performance of the connecting area is enhanced, the influence of heat input on a base body is reduced, the heat stress is reduced, meanwhile, the structural strength of the connecting area is also improved, and the connecting area is ensured not to deform.
Drawings
Fig. 1 is a schematic structural view of an airplane tail integral frame component.
Fig. 2 is a schematic perspective view of laser additive connection processing according to an embodiment of the present invention.
Fig. 3 is a perspective view of a closed use state of a special tube furnace structure according to an embodiment of the present invention.
Fig. 4 is a perspective view of the special tube furnace structure in an open idle state according to the embodiment of the invention.
Fig. 5 is a photograph of a macrostructure of a large titanium alloy structure connecting region according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be described below with reference to the drawings in the embodiments of the present invention.
The invention discloses a laser material-increasing connecting method of an oversized titanium alloy integral frame component structure by taking an integral frame component of a rear body of an airplane as an example and adopting titanium alloy as a material, and the method comprises the following specific steps:
the manufacturing method comprises the steps of (I) respectively manufacturing an outer frame section 2, an upper frame section 1 and a lower frame section 3 of a titanium alloy integral frame (shown in figure 1) as prefabricated split parts through forging, casting or laser material increase technology, prefabricating and thickening the joints to about 96mm, then preparing an X-shaped groove (shown in figure 2) with the angle of about 65 degrees at the joints through a machining mode, polishing the groove and the surrounding area by using a rotary filing tool, cleaning the groove and the surrounding area by using clean water after polishing, then cleaning the groove by using absolute ethyl alcohol, then cleaning by using absolute acetone, and finally cleaning by using clean water to ensure that the surface of the groove is free of oil stains and other impurities.
And (II) fixedly mounting the to-be-connected split parts (the outer side frame section, the upper frame section and the lower frame section) of the titanium alloy integral frame on a laser material increase connecting tool fixture, and placing the to-be-connected split parts in an argon environment.
Thirdly, laser forming adopts long-focus laser, adopts a variable-section copper pipe as a powder feeding pipe, extends the powder feeding pipe by 15-25mm, uses TC4DT titanium alloy powder to carry out laser additive connection, the titanium alloy powder is prepared in an argon atomization mode, the powder granularity is 250-300 meshes, laser beams and the powder synchronously swing and advance in an X-shaped gap, the powder and base materials of connecting pieces at two sides form a multi-layer mutually fused welding seam through the heat of the laser beams, each layer adopts a bidirectional scanning mode, the main process parameters are that the laser power is 1500-1800W, the scanning speed is 7-8mm/s and the powder feeding speed is 70-80g/min, if the power is too small, or the scanning speed and the powder feeding speed are too large, the base materials and the fed powder are difficult to be fully melted due to low heat input, the formability is poor, and the performance is seriously influenced, on the contrary, the performance is also seriously deteriorated due to the large heat input, the large size of the molten pool, the severe internal thermal cycle, and the coarse internal structure.
And (IV) carrying out local stress relief annealing treatment on the joint by adopting a specially designed tubular furnace for local heat treatment, wherein the annealing temperature range is 600-800 ℃, the heat preservation time is 2-5h, and the furnace is cooled.
More specifically, as shown in fig. 1, for the overall frame, since the thickness of the web at each position is not uniform, the thinnest position is only 3mm, the thickest position can reach 10mm, the minimum thickness at the edge strip is 5mm, and the maximum thickness is 18mm, when the connection is performed at the thin-walled position, the connection area is easily deformed or even broken due to the reasons of large heat input, high thermal stress, low structural strength, and the like. Therefore, in order to prevent the connecting area from deforming or even breaking after the frame is connected, the wall thickness of the connecting area is thickened to 96mm in research and design, and then an interface is processed into an X-shaped groove of 65 degrees for connection. The V-shaped groove adopted by the traditional connection mode has thermal stress in a one-way vertical direction and is easy to deform or even break, and the X-shaped groove introduces a reverse stress compared with the V-shaped groove, so that the bending deformation caused by the thermal stress possibly generated after connection is inhibited. Meanwhile, the design of the groove angle of 65 degrees is the optimal choice, when the groove angle is less than 55 degrees, the groove is larger, and the needed additive area is correspondingly overlarge, so that on one hand, the needed processing time is overlong, the preparation period is prolonged, on the other hand, the interface is overlong, the probability of introducing defects is greatly increased, and the performance of the interface is reduced; however, if the groove angle is too large, for example, greater than 75 °, although the required additive area is small, the angle of the additive area is small, at this time, because the groove angle is too large, the angle between the laser light path and the normal direction of the groove is too large due to the slope of the laser during processing, and further the laser spot is deformed, so that the difference of laser energy density is large, and because the angle is too large, melt flow is easily caused in the molten pool due to the influence of gravity, the stability of the molten pool is very poor, and further the formability is seriously influenced, and the interface performance is seriously influenced. The heat dissipation performance of the connecting area is improved to the maximum extent after the wall thickness of the connecting area is increased to 96mm, the influence of large heat input introduced by laser processing on a base body is reduced, the heat stress is reduced, the structural strength of the connecting area is improved, and the connecting area is ensured not to deform. At the same time, this prefabricated thickening of the connection region is thinned in subsequent machining to the appropriate dimensions.
On the laser vibration material disk device, laser head 4 adopts long burnt laser, because need carry out vibration material disk to in the groove, the depth of working is great, and the laser head volume is great, and is far away for making it from the machined surface to avoid the laser head to contact the sample, reserve the space that send the powder pipe to stretch into to send the powder simultaneously, so need the focus to be greater than 240mm long burnt laser. The powder feeding mode adopts a lengthened variable cross-section copper tube powder feeding method and adopts a lengthened conical powder feeding tube 5 with variable aperture, because the processing area of the X-shaped groove is deeper, the powder feeding tube is deep into the groove to feed powder, the powder is ensured not to splash and is fully and uniformly fed into the molten pool, meanwhile, the variable cross-section powder feeding tube can ensure that the flow velocity of the powder is uniform, the variable cross-section powder feeding tube can also ensure that the powder is fully fed into the molten pool, and the powder feeding tube extends out 15-25mm compared with the bottom of the long-focus laser to meet the requirements.
In the laser material increasing process, laser beams and powder synchronously swing and advance in an X-shaped gap, in a groove, each layer adopts a bidirectional scanning mode (namely scanning by end-to-end broken lines), the thermal deformation of the bidirectional scanning mode is small, and the low-degree thermal stress in a sample can be ensured; meanwhile, the next layer is scanned along the scanning path of the previous layer, so that the scanning requirement of the special groove shape is met, and if other scanning modes are adopted, for example, the mode that the next layer is rotated by 90 degrees compared with the previous layer is adopted, the forming shape is poor, and even the forming cannot be smoothly carried out. The specially designed laser power, scanning speed and powder feeding speed can ensure that the powder is fully melted, and meanwhile, the influence on the base material and the generation of cracks during laser material increase connection are reduced, so that the effective connection of a large-scale structural part is realized. Under the condition of the X-shaped groove angle, if the power is less than 1500W, the scanning speed is more than 8mm/s, and the powder feeding speed is more than 80g/min, the heat input is low, the base material and the fed powder are difficult to be fully melted, the formability is poor, and the performance is seriously influenced; and if the power is more than 1800W, the scanning speed is less than 7mm/s, and the powder feeding rate is less than 70g/min, the performance of the powder feeding device is seriously influenced because the heat input is large, the size of a molten pool is large, the internal thermal circulation is serious, and the internal structure is thick. At the same time, large bath sizes also affect the quality of the formation.
The apparatus of the partial heat treatment furnace is shown in fig. 3-4. The tubular furnace is in a tubular furnace form with two open sides, the tubular furnace comprises a ceramic support base 8 and an upper semi-cylindrical furnace shell 12 and a lower semi-cylindrical furnace shell 12, one end of the upper semi-cylindrical furnace shell is hinged with the other end of the lower semi-cylindrical furnace shell, a mortise and tenon structure 10 is connected with the other end of the lower semi-cylindrical furnace shell, a mica heat insulation plate 11 is arranged on the inner wall of the shell, a heating wire 13 controlled and adjusted by a PID current controller 9 through a wire 6 is arranged on the mica plate, a thermocouple and a temperature display 7 are arranged outside the furnace body, and a thermocouple temperature measuring end 14 extends into the furnace body; during heat treatment, the additive manufacturing connection area of the ultra-large metal structure subjected to laser additive connection is arranged inside the tube furnace, other areas outside the connection area are arranged outside the tube furnace, and the other areas are cooled in a water cooling mode, so that the influence of the heat treatment temperature of the connection area on the whole frame is reduced as much as possible. The specially designed local heat treatment can achieve the effect of heat treatment on the connecting area without influencing the frame. The heat treatment temperature is designed to be 600-800 ℃, and the time is 2-5h, so that the thermal stress can be fully removed, and the structural strength is improved. The heat treatment furnace adopts a PID adjusting mode, and the temperature can be fully ensured to be accurately controlled.
Fig. 5 shows a macroscopic structure photograph of the connecting region of a large titanium alloy structure prepared by applying TC4 DT. It was found that the structure had no macrocracks and no deformation, and that the formability was good. Meanwhile, the base material and the connecting area form good metallurgical bonding, and the bonding property is good. The mechanical properties of the connecting area and the base material are almost not different when the mechanical properties of the connecting area and the base material are tested.
The specially designed composite preparation method of the ultra-large alloy integral frame based on the laser additive manufacturing technology can connect the frames after forging, casting or additive manufacturing in a laser additive manufacturing mode, solves the problem of difference between the performance of a connecting area and a base material and high thermal stress of the connecting area through a novel X-shaped connecting groove design mode and an additive manufacturing process, and designs a local heat treatment device and a local heat treatment method to furthest reduce the influence on other parts of the frame under the condition of ensuring the performance requirement of the connecting area.
Although the embodiment of the invention adopts the titanium alloy to prepare the integral frame of the airplane afterbody, the method is not only suitable for the titanium alloy, but also can be applied to the manufacturing mode of large-scale structures made of materials such as steel, aluminum alloy and the like.
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 appended claims.
Claims (10)
1. A composite manufacturing method of an ultra-large metal structure is characterized in that: comprises the following steps of (a) carrying out,
1) the method comprises the following steps of (1) processing split parts, namely dividing the ultra-large metal structure to be manufactured into a plurality of split parts to be respectively molded;
2) the method comprises the following steps of (1) groove machining, wherein a groove is formed on each split part so as to realize that the grooves on the split parts to be connected with each other are integrally formed into an X-shaped groove;
3) the material increase connection is carried out, and metal powder is adopted for laser material increase connection so as to connect the plurality of split parts into an ultra-large metal structure;
4) and local heat treatment, namely performing local heat treatment on the ultra-large metal structure by adopting a local heat treatment device.
2. The method of claim 1, wherein the angle of the "X" groove is 55-75 °.
3. Method according to claim 1, characterized in that the separate piece connecting area is thickened to more than 90mm during the forming process and is machined down to the desired size after the local heat treatment.
4. The method of claim 1, wherein the laser additive connection uses a long-focus laser head, and an elongated powder feeding pipe is combined to extend into the X-shaped groove for powder feeding, and the elongated powder feeding pipe extends 15-25mm from the bottom of the long-focus laser head.
5. The method of claim 1, wherein the laser additive connection employs a bi-directional scanning process.
6. The method as claimed in claim 1, wherein the laser additive connection process parameters include laser power of 1500-.
7. The method according to claim 1, wherein the local heat treatment device is a tubular furnace with two open ends, the tubular furnace comprises a supporting base and an upper semi-cylindrical furnace shell and a lower semi-cylindrical furnace shell which are positioned on the supporting base and can be hinged, the inner wall of the shell is provided with a mica heat insulation sheet, the mica heat insulation sheet is provided with a heating wire controlled and adjusted by PID, and a thermocouple extends into the interior of the furnace body; and during heat treatment, the additive manufacturing connection area of the ultra-large metal structure is placed inside the tube furnace, other areas except the connection area are placed outside the tube furnace, and the other areas are subjected to water cooling.
8. The method of claim 1, wherein the oversized metal structure is a monolithic frame member of an aircraft tail, and the metal is a TC4DT titanium alloy.
9. The method of claim 1, wherein the forming process of the separate piece is casting, forging, or additive manufacturing.
10. The method as claimed in claim 1, wherein the heat treatment process parameter is a heating temperature of 600 ℃ and 800 ℃ for 2-5 h.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114211001A (en) * | 2021-11-29 | 2022-03-22 | 北京航星机器制造有限公司 | Method and device for controlling material increase manufacturing deformation of large thin-wall structural part |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114211001B (en) * | 2021-11-29 | 2023-12-08 | 北京航星机器制造有限公司 | Method and device for controlling additive manufacturing deformation of large thin-wall structural part |
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