CN110976866A - Integrated preparation method of gradient change component - Google Patents

Integrated preparation method of gradient change component Download PDF

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CN110976866A
CN110976866A CN201911326133.7A CN201911326133A CN110976866A CN 110976866 A CN110976866 A CN 110976866A CN 201911326133 A CN201911326133 A CN 201911326133A CN 110976866 A CN110976866 A CN 110976866A
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powder
gradient change
component
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CN110976866B (en
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杨晓珊
乐国敏
周昱昭
刘学
李晋锋
王斗
王小英
张玮
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Institute of Materials of CAEP
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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
    • 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
    • B22F10/32—Process control of the atmosphere, e.g. composition or pressure in a building chamber
    • 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
    • B22F10/25—Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
    • 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
    • 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
    • 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
    • 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
    • B22F10/34—Process control of powder characteristics, e.g. density, oxidation or flowability
    • 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
    • B22F10/36—Process control of energy beam parameters
    • 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
    • B22F10/36—Process control of energy beam parameters
    • B22F10/366—Scanning parameters, e.g. hatch distance or scanning strategy
    • 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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  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • Automation & Control Theory (AREA)
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Abstract

The invention relates to the technical field of high-energy beam rapid forming, and provides an integrated preparation method of a gradient change component, which comprises the following steps: s1, establishing a three-dimensional model of the member to be processed, wherein the three-dimensional model comprises at least two sub-models; s2, slicing and layering all the sub models according to the set layering thickness; s3, setting scanning paths of all slice layers in each sub-model, and setting technological parameters required by the preparation of each sub-model; s4, generating each layer of subcodes of each sub-model according to the scanning path and the process parameters; writing a total code; guiding all codes into a high-energy beam rapid prototyping system; s5, filling metal powder into a powder feeding barrel of the high-energy beam rapid prototyping system; and S6, starting the high-energy-beam rapid forming system, and operating the general code to continuously deposit the metal powder on the forming substrate. The method does not need to perform partition on each slice layer, is simpler to operate and higher in accuracy, and saves a large amount of time.

Description

Integrated preparation method of gradient change component
Technical Field
The invention relates to the technical field of high-energy beam rapid forming, in particular to an integrated preparation method of a gradient change component.
Background
In recent years, with the progress of science and technology and the rapid development of engineering technology, the application environment of high-end components is more and more severe, and in order to meet the use requirements of the high-end components, higher requirements are put forward on the organization structure, the performance and the like of materials.
The gradient material is a novel functional material which enables the organization structure and the performance of the material to present gradient change, the gradient performance of the material can be realized through the spatial layout of two or more material components in a component, and the gradient performance of the material can also be realized through the spatial layout of different organization forms of the same material. Therefore, the component gradient change component or the structural gradient change component prepared from the gradient material has important application prospects in the fields of national defense, military industry, aerospace and the like.
The common preparation methods of gradient change components mainly include powder metallurgy, plasma spraying, sintering, vapor deposition, electrodeposition, centrifugal casting and the like. The traditional preparation method has the following disadvantages: 1. only functional gradient material blocks or material rings with simple shapes and structures can be prepared; 2. the fitting gradient component with a complicated structure cannot be manufactured.
The high-energy beam rapid forming technology is very suitable for manufacturing gradient change components with complex spatial structures and spatial layout of tissue components due to the processing modes of layered manufacturing and layer-by-layer superposition.
At present, the most common high-energy beam rapid prototyping technology is laser rapid prototyping technology, and a plurality of researchers achieve the preparation of structural or composition gradient change components by using the laser rapid prototyping technology. However, most of the prior art is to build up gradient layers layer by layer in the vertical direction, and the structural or composition gradient is distributed in a single vertical direction. If a multi-dimensional gradient change component is to be prepared, process parameters need to be adjusted in time through external control in the preparation process, but the external control adjustment mode is not coupled with each layer of control path program, so that the automation degree is low, the operation difficulty is high, and the timely and accurate control of the structure and the components is difficult to realize by combining with a model accurate fixed-point control process.
At present, the existing commercial software for layered slicing can be adopted, each slicing layer of the model is separately partitioned according to the requirements of components or structures, forming process parameters are independently given to each area, and then the gradient change component is prepared by the high-energy beam rapid forming technology. However, this method is complicated in operation, and when the components or structures are embedded in a multi-dimensional complex manner, partitioning of each layer is very complicated, which further increases operation difficulty and operation time.
Disclosure of Invention
The technical problem to be solved by the invention is to provide an integrated preparation method of a gradient change component, which can be used for quickly preparing a gradient alloy and realizing the gradient distribution of structures or components in multiple directions.
The technical scheme adopted by the invention for solving the technical problems is as follows: the integrated preparation method of the gradient change component comprises the following steps:
s1, establishing a three-dimensional model of the member to be processed, wherein the three-dimensional model comprises at least two sub-models; wherein, the parts with the same structure or components in the component to be processed are built into the same sub-model;
s2, slicing and layering all the sub models according to the set layering thickness;
s3, setting scanning paths of all slice layers in each sub-model, and setting technological parameters required by the preparation of each sub-model;
s4, generating each layer of subcodes of each sub-model according to the scanning path and the process parameters in the step S3; compiling a total code, and sequentially calling the sub-codes of the layer in each sub-model in each slice layer by the total code; then all codes are led into a high-energy beam rapid forming system;
s5, filling the pretreated metal powder into a powder feeding barrel of a high-energy beam rapid forming system;
and S6, starting the high-energy beam rapid forming system, and operating the general code to continuously deposit the metal powder on the forming substrate to prepare the gradient change component.
Further, when the component to be processed is a component with a gradient change in composition, in step S3, the process parameters include output power, scanning speed, powder feeding channel, powder carrying airflow and overlapping ratio; when the component to be processed is a structural gradient change component, in step S3, the process parameters include output power, scanning speed, powder feeding speed, and powder carrying airflow.
Further, in step S6, during powder feeding, argon gas is used as the powder carrying gas and the shielding gas.
Further, in step S1, all the sub-models are established in the same coordinate system.
Further, in step S2, after the submodel slices are layered, the thicknesses of the slice layers are equal or different.
The invention has the beneficial effects that: according to the integrated preparation method of the gradient change component, the sub-models are respectively established according to the structure or component difference of the component, compared with the integrated modeling, the sub-models do not need to be partitioned in each slice layer of the sub-models, the operation is simpler, and a large amount of time is saved; realizing the coupling control of the path and the process parameters of each sliced layer through each layer of subcodes, sequentially calling corresponding subcodes through a total code, and realizing the timely and accurate control of the structure or the components through fixed-point control; compared with the prior art, the process parameters do not need to be regulated by external control in the forming process, the operation is simpler, and the accuracy is higher; the method is particularly suitable for complex embedding forming of various materials in three-dimensional space.
Drawings
FIG. 1 is a schematic representation of a tungsten alloy and a cross-sectional profile of a tungsten alloy prepared by an integrated method of making a gradient change member according to an embodiment of the present invention;
FIG. 2 is a schematic representation of a titanium alloy and a sample of a titanium alloy prepared by the integrated method of manufacturing a gradient change member according to an embodiment of the present invention.
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
The integrated preparation method of the gradient change component provided by the embodiment of the invention comprises the following steps:
s1, establishing a three-dimensional model of the member to be processed, wherein the three-dimensional model comprises at least two sub-models; wherein, the parts with the same structure or components in the component to be processed are built into the same sub-model;
s2, slicing and layering all the sub models according to the set layering thickness;
s3, setting scanning paths of all slice layers in each sub-model, and setting technological parameters required by the preparation of each sub-model;
s4, generating each layer of subcodes of each sub-model according to the scanning path and the process parameters in the step S3; compiling a total code, and sequentially calling the sub-codes of the layer in each sub-model in each slice layer by the total code; then all codes are led into a high-energy beam rapid forming system;
s5, filling the pretreated metal powder into a powder feeding barrel of a high-energy beam rapid forming system;
and S6, starting the high-energy beam rapid forming system, and operating the general code to continuously deposit the metal powder on the forming substrate to prepare the gradient change component.
The gradient change member of the embodiments of the present invention is mainly referred to as a composition gradient member or a structural gradient member.
In step S1, a three-dimensional model of the member to be machined is established using three-dimensional software such as UG and SolidWorks. When the model is established, an integral model of the component to be processed can be established, and then the integral model is divided into at least two sub-models according to the difference of the structure or the components; or at least two sub-models can be respectively established according to the difference of the structure or the composition of the member to be processed, and the plurality of sub-models jointly form the integral model of the member to be processed. Wherein, the parts with the same structure or the same composition in the component to be processed are built into the same sub-model. When building the model, all the sub-models may be built in the same coordinate system, or may be built in different coordinate systems, which is not limited herein.
In step S2, importing the file of the three-dimensional model created in step S1 into layered slicing software; and slicing and layering each sub-model according to the set layering thickness. After the sub-model slices are layered, the thicknesses of all slice layers can be equal or unequal.
In step S3, according to the shape of each slice layer, setting the scanning path of each slice layer in each sub-model, and simultaneously setting the technological parameters required by the preparation of each sub-model; when the component to be processed is a component with gradient change, the process parameters comprise output power, scanning speed, powder feeding channel, powder carrying airflow and overlapping rate. When the component to be processed is a structural gradient change component, the process parameters comprise output power, scanning speed, powder feeding speed and powder carrying airflow.
In step S4, generating each layer of subcodes of each submodel according to the scanning path and the process parameters in step S3; then writing a total code; the total code has the function of sequentially calling the layer of subcodes in each submodel when each sliced layer is prepared, so that the coupling control between the subcodes of the corresponding layers in each submodel is realized, and further the integrated forming of gradient change components with different structures or components is realized. After the writing of the subcodes and the total code is finished, the total code and all the subcodes are led into the high-energy beam rapid prototyping system together. The heat source of the high-energy beam rapid prototyping system may be a laser beam, an electron beam, a plasma beam, etc., and is not particularly limited herein.
Step S5, the metal powder after pretreatment is put into a powder feeding barrel of a high-energy beam rapid forming system for standby; the pretreatment process comprises the working procedures of screening, drying and the like. When the component to be processed is a component with gradient change of components, metal powder with different components can be respectively filled into different powder feeding charging barrels; the metal powders with different components can also be sequentially loaded into the same powder feeding barrel according to the deposition sequence. During powder feeding, inert gas is used as powder carrying gas and protective gas. Preferably, high-purity argon is used as the powder carrying gas and the shielding gas during powder feeding.
In step S6, the high-energy beam rapid prototyping system is started to run the total code, so that the metal powder is continuously deposited on the prototyping substrate under the action of the laser according to the set process parameters and paths, thereby realizing the integrated prototyping of the structural or component gradient change member.
According to the integrated preparation method of the gradient change component, the sub-models are respectively established according to the structure or component difference of the component, compared with the integrated modeling, the sub-models do not need to be partitioned in each slice layer of the sub-models, the operation is simpler, and a large amount of time is saved; the coupling control of the path and the process parameters of each sliced layer is realized through each layer of subcodes, corresponding subcodes are sequentially called through the total codes, and the timely and accurate control of the structure or the components is realized through fixed-point control; the method is particularly suitable for complex embedding forming of various materials in three-dimensional space.
Example 1:
the existing tungsten alloy sample piece with gradient change of components is formed by embedding two alloy components in the horizontal direction and the vertical direction. The conventional preparation method is to adjust the technological parameters of the powder feeder in time by external control in the forming process, but the external control adjusting mode is not coupled with each layer of control path program, so that the degree of automation is low and the operation difficulty is high.
The method for preparing the tungsten alloy sample piece comprises the following steps:
s1, as shown in a1 in a picture of a picture 1, establishing a three-dimensional model of the tungsten alloy sample piece, and dividing the model into a sub-model A and a sub-model B according to the gradient;
s2, performing preliminary process parameter search, and enabling the tungsten alloy to have good final formability when the layering thickness is 0.25mm, so that the layering thickness is set to be 0.25mm, and slicing and layering the sub-model A and the sub-model B according to the layering thickness;
s3, sub model A and sub model B all use serpentine scanning path; setting the technological parameters of the sub-model A as follows: the laser power is 700W, the scanning speed is 400mm/min, the powder feeding speed is 5-20 g/min, the powder feeding channel is a No. 1 channel, the powder carrying air flow is 5L/min, and the lap joint rate is 40%; setting the technological parameters of the sub-model B as follows: the laser power is 750W, the scanning speed is 400mm/min, the powder feeding speed is 5-20 g/min, the powder feeding channel is a No. 2 channel, the powder carrying air flow is 5L/min, and the lap joint rate is 40%.
S4, generating each layer of subcodes of each sub-model according to the scanning path and the process parameters in the step S3; then writing a total code for calling the subcodes; then all codes are led into a laser rapid prototyping system;
s5, sieving commercial tungsten powder, iron powder and nickel powder respectively to obtain tungsten powder with the average particle size of 10 microns, iron powder with the average particle size of 30 microns and nickel powder with the average particle size of 120 microns; the tungsten powder is polygonal, the iron powder and the nickel powder are spherical, and the mixed powder a 'for the forming sub-model a and the mixed powder B' for the forming sub-model B are disposed respectively. Wherein the mixed powder A' comprises the following components in percentage by weight: weighing the powder B' according to the weight ratio of tungsten, nickel and iron of 50: 35: 15: weighing tungsten, nickel and iron in a ratio of 83: 11.9: 5.1; then respectively loading the two mixed powders into a charging bucket of a three-dimensional mixer, and adding a stainless steel spring to promote stirring in the mixing process, wherein the mixing time is 1 hour; and then drying the mixed powder in a vacuum oven at 120 ℃ for 2 hours, then filling the mixed powder A 'into a powder feeding cylinder of a No. 1 powder feeder, filling the mixed powder B' into a powder feeding cylinder of a No. 2 powder feeder, and taking high-purity argon gas as a powder carrying gas and a shielding gas during powder feeding.
S6, starting a laser rapid forming system, operating a total code, coaxially outputting laser and powder, wherein the total code automatically calls the subcode of the submodel A and the submodel B in each slice layer, and the mixed powder A 'and the mixed powder B' are integrally fused and deposited on a forming substrate according to the parameters and the paths set in the step S3 to prepare the tungsten alloy with gradient change, wherein the cross-sectional morphology of the tungsten alloy is shown as a graph B1 in figure 1.
As can be seen from the graph a1 in fig. 1, the two alloy compositions in the submodel a and the submodel B are tightly combined in the model, and the gradient distribution is realized in the horizontal direction and the vertical direction; as can be seen from the graph b1 in FIG. 1, the tungsten alloy with the composition gradient in the horizontal direction and the vertical direction is successfully prepared in the embodiment, the alloy formability of the two components is good, the boundary presents good metallurgical bonding, and no obvious defect exists. Compared with the existing preparation method, the method of the embodiment can automatically perform continuous melting deposition of different tungsten alloy components on each sliced layer, can realize integrated preparation of the tungsten alloy sample pieces in multidirectional gradient distribution without externally controlling and timely adjusting process parameters, and has the advantages of simple preparation process, high automation degree and high production efficiency.
Example 2:
the existing titanium alloy sample piece with the structural gradient change consists of an annular inner wall, an annular outer wall and blades arranged between the inner wall and the outer wall, wherein the thickness of the circular wall is greater than that of the blades. The conventional preparation method is that the circular wall and the blade are formed by adopting the same technological parameters, and the blade adopts single-channel scanning, so that the circular wall needs to be lapped in multiple channels, and the mode can cause longer deposition path and lower efficiency; or the circular wall also adopts single-channel scanning, but the process parameters of each layer need to be adjusted by external control, the automation degree is low, and the operation difficulty is high.
The method for preparing the titanium alloy sample piece comprises the following steps:
and S1, as shown in a2 in a picture of figure 2, establishing a three-dimensional model of the titanium alloy sample piece, and dividing the model into a circular wall and a blade according to the gradient, wherein the circular wall comprises an inner wall and an outer wall.
S2, through earlier-stage process parameter exploration, the titanium alloy has better final formability when the layering thickness is 0.23mm, therefore, the layering thickness is set to be 0.23mm, and the circular wall and the blade are sliced and layered according to the layering thickness;
s3, setting a scanning path of the circular wall part by adopting an equal-thickness thin-wall circular line, wherein the number of the circular lines is 1; the blade portion is set to adopt a single-pass scanning path. The process parameters of the circular wall part are set as follows: the laser power is 400W, the scanning speed is 600mm/min, the powder feeding speed is 5-20 g/min, and the powder carrying air flow is 5L/min. The process parameters of the blade part are set as follows: the laser power is 700W, the scanning speed is 500mm/min, the powder feeding speed is 5-20 g/min, and the powder carrying air flow is 5L/min.
S4, generating each layer of subcodes of the circular wall part and the blade part according to the scanning path and the process parameters in the step S3; then writing a total code for calling the subcodes; then all codes are led into a laser rapid prototyping system;
s5, weighing the powder, and sieving the commercial titanium powder to obtain the titanium powder with the average particle size of 30-120 mu m, wherein the titanium powder is in a sphere-like shape; titanium powder is dried for 2 hours in a vacuum oven at 120 ℃ and then is put into a powder feeding charging barrel of a powder feeder, and high-purity argon is used as a powder carrying gas and a protective gas during powder feeding.
S6, starting the laser rapid forming system, operating the total code, coaxially outputting laser and powder, wherein the total code automatically calls the layer subcodes of the circular wall part and the blade part in each cutting layer, and according to the parameters and the path set in the step S3, the titanium powder is melted and deposited on the forming substrate to prepare the titanium alloy with the structural gradient change, and the titanium alloy sample is shown as a graph b2 in figure 2.
As can be seen from the b2 diagram in fig. 2, this example successfully produced a titanium alloy with a complex structural gradient, and it is apparent from the figure that the thickness of the circular wall portion is greater than the thickness of the blade portion. Compared with the existing preparation method, the method of the embodiment can automatically perform continuous melting deposition of the circular wall and the blade on each sliced layer, and can realize integrated preparation of the circular wall part and the blade part in the titanium alloy sample without externally controlling and timely adjusting process parameters, thereby greatly shortening the deposition path and improving the production efficiency.

Claims (5)

1. The integrated preparation method of the gradient change component is characterized by comprising the following steps:
s1, establishing a three-dimensional model of the member to be processed, wherein the three-dimensional model comprises at least two sub-models; wherein, the parts with the same structure or components in the component to be processed are built into the same sub-model;
s2, slicing and layering all the sub models according to the set layering thickness;
s3, setting scanning paths of all slice layers in each sub-model, and setting technological parameters required by the preparation of each sub-model;
s4, generating each layer of subcodes of each sub-model according to the scanning path and the process parameters in the step S3; compiling a total code, each slice layer, and sequentially calling the layer of subcodes in each sub-model by the total code; then all codes are led into a high-energy beam rapid forming system;
s5, filling the pretreated metal powder into a powder feeding barrel of a high-energy beam rapid forming system;
and S6, starting the high-energy beam rapid forming system, and operating the general code to continuously deposit the metal powder on the forming substrate to prepare the gradient change component.
2. The integrated manufacturing method of a gradient change member according to claim 1, wherein when the member to be processed is a component gradient change member, in step S3, the process parameters include output power, scanning speed, powder feeding channel, powder carrying airflow and overlapping ratio; when the component to be processed is a structural gradient change component, in step S3, the process parameters include output power, scanning speed, powder feeding speed, and powder carrying airflow.
3. The integrated manufacturing method of a gradient changing member according to claim 1, wherein in step S6, argon gas is used as the powder carrying gas and the shielding gas during powder feeding.
4. The integrated manufacturing method of gradient change member of claim 1, wherein in step S1, all sub-models are established in the same coordinate system.
5. The integrated manufacturing method of a gradient changing member according to claim 1, wherein in step S2, after the submodel slices are layered, the thicknesses of the slice layers are equal or different.
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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111774567A (en) * 2020-08-29 2020-10-16 沈阳工业大学 Method for manufacturing high-performance gradient alloy steel material through laser additive manufacturing
CN112317761A (en) * 2020-10-10 2021-02-05 北京隆源自动成型系统有限公司 Intelligent SLM (selective laser melting) forming process for linear gradient alloy
CN113021881A (en) * 2021-03-12 2021-06-25 湖南华曙高科技有限责任公司 Forming method and forming equipment for complex truss structure workpiece and readable storage medium
CN114713845A (en) * 2022-04-21 2022-07-08 中国工程物理研究院材料研究所 Laser rapid forming preparation method of metal high-flux sample

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6451082B1 (en) * 2000-01-07 2002-09-17 Kawasaki Steel Corporation Iron-based powder mixture for powder metallurgy, process for producing the same, and method of forming a molding from the same
CN109590472A (en) * 2018-12-27 2019-04-09 鑫精合激光科技发展（北京）有限公司 A kind of functionally gradient material (FGM) Method of printing based on coaxial powder-feeding
CN109967739A (en) * 2019-03-26 2019-07-05 上海工程技术大学 A method of gradient-structure metalwork is prepared based on increases material manufacturing technology
CN110523981A (en) * 2019-08-23 2019-12-03 广东省新材料研究所 The 3D printing method of more performance composite constructions

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BRPI0904605A2 (en) * 2009-11-16 2012-02-22 Calcados Bibi Ltda interactive sound module applied to general sports shoes

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6451082B1 (en) * 2000-01-07 2002-09-17 Kawasaki Steel Corporation Iron-based powder mixture for powder metallurgy, process for producing the same, and method of forming a molding from the same
CN109590472A (en) * 2018-12-27 2019-04-09 鑫精合激光科技发展（北京）有限公司 A kind of functionally gradient material (FGM) Method of printing based on coaxial powder-feeding
CN109967739A (en) * 2019-03-26 2019-07-05 上海工程技术大学 A method of gradient-structure metalwork is prepared based on increases material manufacturing technology
CN110523981A (en) * 2019-08-23 2019-12-03 广东省新材料研究所 The 3D printing method of more performance composite constructions

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111774567A (en) * 2020-08-29 2020-10-16 沈阳工业大学 Method for manufacturing high-performance gradient alloy steel material through laser additive manufacturing
CN112317761A (en) * 2020-10-10 2021-02-05 北京隆源自动成型系统有限公司 Intelligent SLM (selective laser melting) forming process for linear gradient alloy
CN112317761B (en) * 2020-10-10 2023-01-10 北京隆源自动成型系统有限公司 Intelligent process for forming linear gradient alloy by SLM (Selective laser melting)
CN113021881A (en) * 2021-03-12 2021-06-25 湖南华曙高科技有限责任公司 Forming method and forming equipment for complex truss structure workpiece and readable storage medium
CN114713845A (en) * 2022-04-21 2022-07-08 中国工程物理研究院材料研究所 Laser rapid forming preparation method of metal high-flux sample

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