CN116921700A - Laser selective melting forming anti-deformation method for high-temperature alloy - Google Patents
Laser selective melting forming anti-deformation method for high-temperature alloy Download PDFInfo
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- CN116921700A CN116921700A CN202311189400.7A CN202311189400A CN116921700A CN 116921700 A CN116921700 A CN 116921700A CN 202311189400 A CN202311189400 A CN 202311189400A CN 116921700 A CN116921700 A CN 116921700A
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 70
- 239000000956 alloy Substances 0.000 title claims abstract description 70
- 238000000034 method Methods 0.000 title claims abstract description 55
- 238000002844 melting Methods 0.000 title claims abstract description 24
- 230000008018 melting Effects 0.000 title claims abstract description 24
- 239000007787 solid Substances 0.000 claims abstract description 101
- 229910000601 superalloy Inorganic materials 0.000 claims abstract description 69
- 238000004458 analytical method Methods 0.000 claims abstract description 38
- 238000004088 simulation Methods 0.000 claims abstract description 21
- 238000010438 heat treatment Methods 0.000 claims abstract description 17
- 238000004381 surface treatment Methods 0.000 claims abstract description 7
- 239000000843 powder Substances 0.000 claims description 34
- 230000008093 supporting effect Effects 0.000 claims description 17
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 10
- 239000000758 substrate Substances 0.000 claims description 10
- 238000005520 cutting process Methods 0.000 claims description 6
- 239000007789 gas Substances 0.000 claims description 6
- 238000003801 milling Methods 0.000 claims description 6
- 229910052786 argon Inorganic materials 0.000 claims description 5
- 230000001681 protective effect Effects 0.000 claims description 5
- 239000000203 mixture Substances 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 239000000654 additive Substances 0.000 abstract description 2
- 230000000996 additive effect Effects 0.000 abstract description 2
- 238000012545 processing Methods 0.000 description 5
- 239000000725 suspension Substances 0.000 description 5
- 230000002265 prevention Effects 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003779 heat-resistant material Substances 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 229910052758 niobium Inorganic materials 0.000 description 1
- 239000010955 niobium Substances 0.000 description 1
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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
- B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
-
- 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
- B22F10/40—Structures for supporting workpieces or articles during manufacture and removed afterwards
- B22F10/47—Structures for supporting workpieces or articles during manufacture and removed afterwards characterised by structural features
-
- 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
-
- 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
-
- 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)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Thermal Sciences (AREA)
- Laser Beam Processing (AREA)
Abstract
The application discloses a laser selective melting forming anti-deformation method of a superalloy, and relates to the technical field of superalloy additive manufacturing. The method comprises the following steps: performing simulation analysis on the high-temperature alloy part model to obtain an analysis result; according to the analysis result, adding a support design at the easily deformable part of the high-temperature alloy part model by adopting a sheet-shaped solid support and column support mode to obtain a model to be printed; printing by adopting a laser selective melting forming method according to a model to be printed to obtain a printing piece, and performing heat treatment on the printing piece to obtain a forming piece; and carrying out surface treatment on the formed piece to remove the support, and obtaining the finished high-temperature alloy part. According to the application, through the manner of the lamellar solid support and the column support, the solid force can be increased, the residual stress deformation risk is reduced, and the problems that the solid support is excessive and the solid support is difficult to remove in the later stage can be avoided, so that the shape control of the superalloy part can be accurately supported in the printing process.
Description
Technical Field
The application relates to the technical field of high-temperature alloy additive manufacturing, in particular to a laser selective melting forming anti-deformation method of a high-temperature alloy.
Background
The high-temperature alloy is mainly a nickel-based deformation face-centered cubic alloy with molybdenum and niobium added as main strengthening elements, and has excellent strength and toughness in the temperature range from low temperature to 980 ℃. Therefore, the heat-resistant material is widely applied to hot-end components of aviation jet engines and various industrial gas turbines. But is limited by the accessibility of the traditional process, the processing cost is very high and the processing efficiency is low in the process of manufacturing aero-engine components and aerospace structural components, and the laser selective area melt forming (SLM) has the advantages of higher precision, high manufacturing applicability to special complex structures (such as a suspension structure, a complex curved surface and the like), low production cost, short period and the like, and becomes a novel process technology for manufacturing high-performance metal structural components in the fields of aviation and aerospace and the like at home and abroad.
When the small inclination angle or the overhang structure of the high-temperature alloy part stretches out to be longer and thicker, the forming end face cannot be pulled by the block support at the outer end part, the SLM is formed very easily to generate buckling deformation, printing is affected, deformation can be prevented only through the additional solid support, the solid support can increase the solid force on one hand, heat can be conducted rapidly on the other hand, and the deformation risk of residual stress is reduced. However, the existing solid support is difficult to achieve the aims of supporting, removing and preventing deformation, the forming end face cannot be pulled when the solid support is insufficient in design, the deformation preventing aim cannot be achieved, and the solid support is difficult to remove in later stage due to excessive design, so that the later-stage processing amount is increased. Therefore, the application provides a laser selective melting forming anti-deformation method of a superalloy to solve the technical problems.
Disclosure of Invention
The application mainly aims to provide a deformation preventing method for laser selective fusion forming of a high-temperature alloy, which aims to solve the technical problems of easy deformation or difficult removal caused by insufficient support or excessive support in the laser selective fusion forming process of the high-temperature alloy part.
In order to achieve the above purpose, the application provides a laser selective melting forming anti-deformation method of a superalloy, which comprises the following steps:
performing simulation analysis on the high-temperature alloy part model to obtain an analysis result;
according to the analysis result, adding a support design at the easily deformable part of the high-temperature alloy part model by adopting a sheet solid support and column support mode to obtain a model to be printed;
printing by adopting a laser selective melting forming method according to the model to be printed to obtain a printing piece, and performing heat treatment on the printing piece to obtain a forming piece;
and carrying out surface treatment on the formed part to remove the support, and obtaining the finished high-temperature alloy part.
Optionally, the step of performing simulation analysis on the superalloy component model to obtain an analysis result includes:
and adopting simulation software to perform stress-strain simulation analysis on the high-temperature alloy part model, determining stress-strain conditions of all parts, and obtaining an analysis result.
Optionally, the step of adding a support design to the easily deformable portion of the superalloy component model by adopting a sheet solid support and a column support includes:
adding a lamellar solid support to the outer end part of the easily deformable part of the superalloy part model in three-dimensional software;
then a plurality of powder holes are formed on the lamellar solid support;
and a plurality of column supports are added inside the lamellar solid support.
Optionally, in the step of adding a sheet-shaped solid support to the outer end part of the easy-to-deform part of the superalloy part model in three-dimensional software, the thickness of the sheet-shaped solid support is obtained by the following relation:
wherein delta is the thickness of the lamellar solid support, alpha is the included angle between the local overhang direction and the vertical direction of the high-temperature alloy part model, and is more than 45 degrees and less than 135 degrees, and delta is less than 135 degrees 1 And the thickness of the local overhang of the superalloy part model is equal to or less than 0.5 time of the height of the superalloy part model at the position where w is equal to or less than the extension length of the local overhang of the superalloy part model.
Optionally, in the step of adding a sheet-shaped solid support to the outer end of the deformable portion of the superalloy part model in three-dimensional software, the height position of the lower end point of the sheet-shaped solid support is obtained by the following relation:
wherein H is the height of the lower end point of the lamellar solid support, H is the length of the upper end of the position where the high-temperature alloy part model partially overhangs, and w is the length of the upper end where the high-temperature alloy part model partially overhangsLength delta 1 And (5) locally suspending the high-temperature alloy part model to a thickness.
Optionally, in the step of forming a plurality of powder holes on the sheet solid support, the distance between two adjacent powder holes is 12mm-15mm, and the diameter of the powder holes is obtained by the following relation:
wherein d is the diameter of the powder hole, and delta is the thickness of the lamellar solid support.
Optionally, in the step of adding a plurality of column supports inside the sheet solid support, the diameter of each column support is 1mm, and the distance between two adjacent column supports is obtained by the following relation:
wherein L is the distance between two adjacent column supports, delta 1 And (5) locally suspending the high-temperature alloy part model to a thickness.
Optionally, in the step of printing by using a laser selective melt forming method according to the model to be printed, the parameters of printing are set as follows:
the layer thickness is 0.04mm, the laser power is 280W-300W, the scanning speed is 900mm/s-1000mm/s, and the scanning interval is 0.1mm-0.12mm.
Optionally, the step of performing heat treatment on the printed piece includes:
heating the printing piece to 590-610 ℃, preserving heat for 20-40 min, continuously heating to 1090-1110 ℃, preserving heat for 50-70 min, and keeping the working pressure not to exceed 7.27×10 in the heat treatment process -2 Pa, argon is used as a protective gas, and after the completion, the mixture is cooled to below 90 ℃.
Optionally, the step of surface treating the shaped piece to remove support includes:
and removing the substrate on the formed piece through linear cutting, and removing the supporting part on the formed piece by adopting a milling method.
According to the application, simulation analysis is carried out on the high-temperature alloy part model, according to the simulation analysis result, stress conditions, forming difficulty and the like of different parts of the high-temperature alloy part model, a sheet-shaped solid support and column support mode is adopted to add a support design to the easily-deformed part of the high-temperature alloy part model, parameters of the sheet-shaped solid support and the column support are reasonably determined, so that the forming process of the high-temperature alloy part is accurately controlled, then a laser selective melting forming method is adopted to print according to the model to be printed after the support design is added, the printing quality of the high-temperature alloy part can be improved, and when the high-temperature alloy part extends out of a small inclination angle or a suspension structure to be thicker, the support design can be accurately carried out to prevent the high-temperature alloy part from buckling deformation in the laser selective melting forming process, the printing time is saved, the workload in the later support removing process is reduced, and the finished high-temperature alloy part with higher printing precision is obtained after the support is removed through surface treatment. According to the application, through the manner of sheet solid support and column support, the solid force can be increased, the risk of residual stress deformation is reduced, the problems of excessive solid support and difficult removal in the later stage can be avoided, the purposes of supporting, easy removal and deformation prevention of the support design can be achieved, and the shape control of the superalloy part can be accurately supported in the printing process.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow chart of a laser selective melt forming deformation prevention method for superalloy according to an embodiment of the present application;
FIG. 2 is a schematic illustration of the structure of a ductile portion support design of a superalloy part model in accordance with an embodiment of the present application;
FIG. 3 is a schematic illustration of a superalloy part model in accordance with an embodiment of the present application;
FIG. 4 is a schematic illustration of a superalloy part model with a conventional solid support added;
FIG. 5 is a schematic illustration of a superalloy part model incorporating a physical support in accordance with the present application.
Reference numerals:
1-lamellar solid support; 2-column support; 3-powder holes; 4-easily deformable portion.
The achievement of the objects, functional features and advantages of the present application will be further described with reference to the accompanying drawings, in conjunction with the embodiments.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
When the small inclination angle or the overhang structure of the high-temperature alloy part stretches out to be longer and thicker, as shown in fig. 3, the forming end face cannot be pulled by the block-shaped support, the SLM is very easy to warp and deform to influence printing, deformation can be prevented only through the additional solid support, the solid support can increase the solid force on one hand, and on the other hand, heat can be conducted rapidly, and the deformation risk of residual stress is reduced. However, the existing solid support is difficult to achieve the aims of supporting, removing and preventing deformation, the forming end face cannot be pulled when the solid support is insufficient in design, the deformation preventing aim cannot be achieved, and the solid support is difficult to remove in later stage due to excessive design, so that the later-stage processing amount is increased.
Aiming at the technical problems existing in the laser selective melting forming process of the existing high-temperature alloy part, the embodiment of the application provides a laser selective melting forming anti-deformation method of a high-temperature alloy, which comprises the following steps:
performing simulation analysis on the high-temperature alloy part model to obtain an analysis result;
according to the analysis result, adding a support design at the easily deformable part 4 of the superalloy part model by adopting a sheet-shaped solid support 1 and a column support 2 to obtain a model to be printed;
printing by adopting a laser selective melting forming method according to the model to be printed to obtain a printing piece, and performing heat treatment on the printing piece to obtain a forming piece;
and carrying out surface treatment on the formed part to remove the support, and obtaining the finished high-temperature alloy part.
According to the application, simulation analysis is carried out on the high-temperature alloy part model, and according to the simulation analysis result, stress conditions, forming difficulty and the like of different parts of the high-temperature alloy part model, a supporting design is added to the easily-deformed part 4 of the high-temperature alloy part model in a sheet solid support 1 and column support 2 mode, so that the forming process of the high-temperature alloy part is accurately controlled, then according to the model to be printed after the supporting design is added, a laser selective melting forming method is adopted for printing, the printing quality of the high-temperature alloy part can be improved, and when the high-temperature alloy part extends out of a small inclination angle or a suspension structure for a long time, the supporting design can be accurately carried out so as to prevent the high-temperature alloy part from buckling deformation in the laser selective melting forming process, the printing time is saved, the workload in the later support removal process is reduced, and after the support is removed through surface treatment, the finished high-temperature alloy part with higher printing precision is obtained. According to the application, through the manner of the sheet solid support 1 and the column support 2, the solid force can be increased, the residual stress deformation risk is reduced, the problems of excessive solid support and difficult removal in the later stage can be avoided, the purposes of supporting, easy removal and deformation prevention of the support design can be achieved, and the shape control of the superalloy part can be accurately supported in the printing process.
As an implementation manner of the application, the step of performing simulation analysis on the high-temperature alloy part model to obtain an analysis result comprises the following steps:
and adopting simulation software to perform stress-strain simulation analysis on the high-temperature alloy part model, determining stress-strain conditions of all parts, and obtaining an analysis result.
The simulation analysis is to adopt the simulation software of the simulation to carry out the simulation analysis of the stress field on the high-temperature alloy part model, and the stress and strain conditions of each part are determined. By carrying out simulation analysis on the high-temperature alloy part model, the stress condition of each part of the high-temperature alloy part model is convenient to determine, and the deformation-prone part 4 of the high-temperature alloy part is analyzed according to the stress condition of each part, so that the reasonable support design of the high-temperature alloy part model is facilitated.
As an embodiment of the present application, the step of adding a support design to the deformable portion 4 of the superalloy component model by adopting the sheet solid support 1 and the column support 2 includes:
adding a lamellar solid support 1 to the outer end part of the easy-to-deform part 4 of the superalloy part model in three-dimensional software;
a plurality of powder holes 3 are formed in the lamellar solid support 1;
a plurality of column supports 2 are added inside the sheet-shaped solid support 1.
As shown in fig. 2, in order to avoid the problem of insufficient or excessive solid support added to the easily deformable part 4 of the superalloy part model, according to the simulation analysis result, a sheet-shaped solid support 1 is added to the outer end part of the easily deformable part 4 of the superalloy part model so as to achieve the effect of supporting a small inclination angle or a suspension structure of the superalloy part, and meanwhile, a plurality of powder holes 3 are formed in the sheet-shaped solid support 1, so that powder in the sheet-shaped solid support 1 is beneficial to flowing out of the powder holes 3 after printing, printing time can be saved, printing materials can be saved, and a plurality of column supports 2 are added in the sheet-shaped solid support 1, so that the easily deformable part 4 of the superalloy part model can be further supported and controlled, and the longer small inclination angle or thicker suspension structure of the superalloy part can be prevented from buckling deformation in the laser selective melt forming process, and printing quality is influenced. As shown in fig. 4-5, by adding the sheet-shaped solid support 1 and the column support 2 to the deformable part 4 of the high-temperature alloy part model and providing the powder holes 3, compared with the traditional solid support, the design can solve the problem that the deformation or excessive support of the high-temperature alloy part is difficult to remove due to insufficient support in the laser selective melting forming process.
As an embodiment of the present application, in the step of adding a sheet-like solid support 1 to the outer end portion of the deformable portion 4 of the superalloy component model in three-dimensional software, the thickness of the sheet-like solid support 1 is obtained by the following relation:
wherein delta is the thickness of the lamellar solid support 1, alpha is the included angle between the local overhang direction and the vertical direction of the high-temperature alloy part model, and is more than 45 degrees and less than 135 degrees, and delta is less than 135 degrees 1 And the thickness of the local overhang of the superalloy part model is equal to or less than 0.5 time of the height of the superalloy part model at the position where w is equal to or less than the extension length of the local overhang of the superalloy part model.
The application further limits the thickness of the lamellar solid support 1, and a mathematical relation of the thickness of the lamellar solid support 1 is obtained through verification, the thickness of the lamellar solid support 1 is accurately limited through the extending length and the thickness of the local overhang of the superalloy part model and the included angle between the local overhang direction and the vertical direction of the superalloy part model, the precise support of the lamellar solid support 1 on the overhang structure of the superalloy part is realized, and the phenomenon that the lamellar solid support 1 is too little to support the easily deformed part 4 or the lamellar solid support 1 is excessive and difficult to remove in post-processing is avoided.
As an embodiment of the present application, in the step of adding the sheet-shaped solid support 1 to the outer end portion of the deformable portion 4 of the superalloy part model in three-dimensional software, the height position of the lower end point of the sheet-shaped solid support 1 is obtained by the following relation:
wherein H is the height of the lower end point of the sheet-shaped solid support 1, H is the length of the upper end of the position where the superalloy part model partially overhangs, w is the extension length of the superalloy part model partially overhangs, delta 1 And (5) locally suspending the high-temperature alloy part model to a thickness.
The application further limits the position of the sheet solid support 1, and the height position H of the lower end point of the sheet solid support 1, the length H of the upper end of the position where the superalloy part model partially overhangs, the extending length w of the superalloy part model partially overhangs and the thickness delta of the superalloy part model partially overhangs are used for controlling the position of the sheet solid support 1 1 The height position of the lower end point of the sheet-shaped solid support 1 is calculated according to the mathematical relation formula of the table, so that the sheet-shaped solid support 1 can accurately support the easily deformed part 4 of the high-temperature alloy part, and the purpose of supporting and controlling the shape is achieved.
As an embodiment of the present application, in the step of forming a plurality of powder holes 3 on the sheet-shaped solid support 1, a distance between two adjacent powder holes 3 is 12mm-15mm, and a diameter of the powder hole 3 is obtained by the following relation:
wherein d is the diameter of the powder hole 3, and delta is the thickness of the lamellar solid support 1.
The application limits the diameter of the powder hole 3 by the mathematical relation between the diameter of the powder hole 3 and the thickness of the sheet solid support 1, if the diameter of the powder hole 3 is too small, the outflow of internal powder after printing is not facilitated, and if the diameter of the powder hole 3 is too large, the support of the sheet solid support 1 on the easily deformed part 4 is not facilitated.
As an embodiment of the present application, in the step of adding a plurality of post supports 2 inside the sheet-shaped solid support 1, the diameter of the post supports 2 is 1mm, and the distance between two adjacent post supports 2 is obtained by the following relationship:
wherein L is the distance between two adjacent column supports, delta 1 And (5) locally suspending the high-temperature alloy part model to a thickness.
The application aims to ensure that the column support 2 can accurately control the deformation-prone part 4 of a superalloy part, and the diameter of the column support 2 is calculated by determining the relation between the diameter of the column support 2 and the thickness of the local overhang of a superalloy part model, so that the column support 2 can further support the deformation-prone part 4 of the superalloy part, and meanwhile, the diameter of the column support 2 is determined, thereby avoiding the problems that the diameter of the column support 2 is too small, the supporting effect is poor, or the diameter of the column support 2 is too large, and the column support 2 is difficult to remove by processing in the later period.
As an embodiment of the present application, in the step of printing by using a laser selective melt forming method according to the model to be printed, parameters of the printing are set as follows:
the layer thickness is 0.04mm, the laser power is 280W-300W, the scanning speed is 900mm/s-1000mm/s, and the scanning interval is 0.1mm-0.12mm.
The application reasonably sets the layer thickness, laser power, scanning speed, scanning interval and the like in the printing process to improve the printing forming quality of the high-temperature alloy part, and effectively controls the accuracy of the printed part.
As an embodiment of the present application, the step of heat-treating the printing member includes:
heating the printing piece to 590-610 ℃, preserving heat for 20-40 min, continuously heating to 1090-1110 ℃, preserving heat for 50-70 min, and keeping the working pressure not to exceed 7.27×10 in the heat treatment process -2 Pa, argon is used as a protective gas, and after the completion, the mixture is cooled to below 90 ℃.
In order to improve the performance of the formed part, the printed part is subjected to heat treatment after printing, preferably, the printed part is heated to 600 ℃, then is kept for 30min, and is kept for 60min after being continuously heated to 1100 ℃, so that the mechanical performance of the part is further improved, and the forming performance of the part is good.
As an embodiment of the present application, the step of performing surface treatment on the formed article to remove the support includes:
and removing the substrate on the formed piece through linear cutting, and removing the supporting part on the formed piece by adopting a milling method.
In the process of laser selective melting, a substrate of the same or similar material as a part to be formed is required to be selected, the substrate is fixed on a lifting workbench, the SLM equipment is leveled, a layer of powder is uniformly paved on the surface of the substrate, then a high-energy laser beam is controlled to scan according to a planned path, molten metal powder is solidified and a current layer is processed, the substrate is moved down to start a new round of powder paving and scanning, the process is performed layer by layer until the whole part is manufactured, after the laser selective melting forming is finished, the substrate on the formed part is separated and removed from the formed part through linear cutting, and a rest supporting part is removed through milling when the supporting design is carried out, so that the formed part is obtained.
The above technical scheme of the present application will be described in detail with reference to specific embodiments.
Example 1
A laser selective melting forming anti-deformation method of a superalloy, as shown in figure 1, comprises the following steps:
adopting simulation software to perform stress-strain simulation analysis on the high-temperature alloy part model, determining stress-strain conditions of all parts, and obtaining analysis results;
according to the analysis result, adding a lamellar solid support 1 to the outer end part of the easy-to-deform part 4 of the superalloy part model in three-dimensional software;
the thickness of the sheet-like solid support 1 is obtained by the following relation:
wherein alpha is an included angle between a local overhang direction and a vertical direction of the high-temperature alloy part model, and alpha=60°, delta 1 Thickness delta of local overhang for the superalloy part model 1 =30mm, w is the extension of the local overhang of the superalloy part model, w=50mm;
delta = 1.8mm;
the height position of the lower end point of the lamellar solid support 1 is obtained by the following relation:
h is the height of the lower end point of the sheet-shaped solid support 1, and H is the length of the upper end of the position where the high-temperature alloy part model partially overhangs, wherein H=120 mm;
h=40 mm;
a plurality of powder holes 3 are formed in the lamellar solid support 1;
the distance between two adjacent powder holes 3 is 12mm, and the diameter of the powder holes 3 is equal to=3×1.8=5.4mm；
Then adding a plurality of column supports 2 into the sheet solid support 1 to obtain a model to be printed;
wherein the diameter of the column supports 2 is 1mm, and the distance between two adjacent column supports 2=120/30=4mm；
The model to be printed is guided into magics slicing software to set the layer thickness to be 0.04mm, the laser power to be 290W, the scanning speed to be 960mm/s and the scanning interval to be 0.12mm, slicing is carried out, laser selective melting forming is carried out, the printed piece is obtained, after the printed piece is heated to 590 ℃, the temperature is kept for 40min, after the temperature is continuously raised to 1090 ℃, the temperature is kept for 70min, and the working pressure is kept to be not more than 7.27 multiplied by 10 in the heat treatment process -2 Pa，Argon is used as protective gas, and after the completion, the mixture is cooled to below 90 ℃ to obtain a formed piece;
and removing the substrate on the formed piece through linear cutting, and removing the supporting part on the formed piece by adopting a milling method to obtain the finished high-temperature alloy part.
Example 2
A laser selective melting forming anti-deformation method of a superalloy, as shown in figure 1, comprises the following steps:
adopting simulation software to perform stress-strain simulation analysis on the high-temperature alloy part model, determining stress-strain conditions of all parts, and obtaining analysis results;
according to the analysis result, adding a lamellar solid support 1 to the outer end part of the easy-to-deform part 4 of the superalloy part model in three-dimensional software;
the thickness of the sheet-like solid support 1 is obtained by the following relation:
wherein alpha is an included angle between a local overhang direction and a vertical direction of the high-temperature alloy part model, and alpha=90°, delta 1 Thickness delta of local overhang for the superalloy part model 1 =20mm, w is the extension of the local overhang of the superalloy part model, w=60 mm;
delta = 2mm;
the height position of the lower end point of the lamellar solid support 1 is obtained by the following relation:
h is the height of the lower end point of the sheet-shaped solid support 1, H is the length of the upper end of the position where the high-temperature alloy part model partially overhangs, and H=150mm;
h=70 mm;
a plurality of powder holes 3 are formed in the lamellar solid support 1;
the distance between two adjacent powder holes 3 is 15mm, and the diameter of the powder holes 3=3×2=6mm；
Then adding a plurality of column supports 2 into the sheet solid support 1 to obtain a model to be printed;
wherein the diameter of the column supports 2 is 1mm, and the distance between two adjacent column supports 2=120/20=6mm；
The model to be printed is guided into magics slicing software to set the layer thickness to be 0.04mm, the laser power to be 280W, the scanning speed to be 1000mm/s and the scanning interval to be 0.1mm, slicing is carried out, laser selective melting forming is carried out, the printed piece is obtained, after the printed piece is heated to 610 ℃, the temperature is kept for 20min, after the temperature is continuously raised to 1110 ℃, the temperature is kept for 50min, and the working pressure is kept to be not more than 7.27 multiplied by 10 in the heat treatment process -2 Pa, taking argon as a protective gas, and cooling to below 90 ℃ after finishing to obtain a formed piece;
and removing the substrate on the formed piece through linear cutting, and removing the supporting part on the formed piece by adopting a milling method to obtain the finished high-temperature alloy part.
The foregoing description is only of the optional embodiments of the present application, and is not intended to limit the scope of the application, and all the equivalent structural changes made by the description of the present application and the accompanying drawings or the direct/indirect application in other related technical fields are included in the scope of the application.
Claims (10)
1. The laser selective melting forming anti-deformation method of the superalloy is characterized by comprising the following steps of:
performing simulation analysis on the high-temperature alloy part model to obtain an analysis result;
according to the analysis result, adding a support design at the easily deformable part of the high-temperature alloy part model by adopting a sheet solid support and column support mode to obtain a model to be printed;
printing by adopting a laser selective melting forming method according to the model to be printed to obtain a printing piece, and performing heat treatment on the printing piece to obtain a forming piece;
and carrying out surface treatment on the formed part to remove the support, and obtaining the finished high-temperature alloy part.
2. The method for preventing deformation of a superalloy by laser selective melt forming according to claim 1, wherein the step of performing simulation analysis on the superalloy component model to obtain an analysis result comprises:
and adopting simulation software to perform stress-strain simulation analysis on the high-temperature alloy part model, determining stress-strain conditions of all parts, and obtaining an analysis result.
3. The method for preventing deformation of a superalloy by laser selective melt forming according to claim 1, wherein the step of adding a support design to the deformable portion of the superalloy component model by using a sheet-like solid support and a column support comprises:
adding a lamellar solid support to the outer end part of the easily deformable part of the superalloy part model in three-dimensional software;
then a plurality of powder holes are formed on the lamellar solid support;
and a plurality of column supports are added inside the lamellar solid support.
4. The method for preventing deformation of a superalloy by laser selective melt forming according to claim 3, wherein in the step of adding a sheet-like solid support to the outer end of the deformable portion of the superalloy component model in three-dimensional software, the thickness of the sheet-like solid support is obtained by the following relation:
wherein delta is the thickness of the lamellar solid support, alpha is the included angle between the local overhang direction and the vertical direction of the high-temperature alloy part model, and is more than 45 degrees and less than 135 degrees, and delta is less than 135 degrees 1 And the thickness of the local overhang of the superalloy part model is equal to or less than 0.5 time of the height of the superalloy part model at the position where w is equal to or less than the extension length of the local overhang of the superalloy part model.
5. The method for preventing deformation of a superalloy by laser selective melt forming according to claim 4, wherein in the step of adding a sheet-like solid support to the outer end of the deformable portion of the superalloy component model in three-dimensional software, the height position of the lower end point of the sheet-like solid support is obtained by the following relation:
h is the height of the lower end point of the sheet-shaped solid support, and H is the length of the upper end of the position where the high-temperature alloy part model partially overhangs.
6. The method for preventing deformation of a superalloy by laser selective melt forming according to claim 5, wherein in the step of forming a plurality of powder holes in the sheet-like solid support, the distance between two adjacent powder holes is 12mm to 15mm, and the diameter of the powder holes is obtained by the following relation:
wherein d is the diameter of the powder hole.
7. The method for preventing deformation of a superalloy by laser selective melt forming according to claim 4, wherein in the step of adding a plurality of column supports inside the sheet-like solid support, the diameter of the column support is 1mm, and the distance between two adjacent column supports is obtained by the following relation:
wherein L is the distance between two adjacent column supports.
8. The method for preventing deformation of superalloy by laser selective melt forming according to claim 1, wherein in the step of printing by using the laser selective melt forming method according to the model to be printed, the parameters for printing are set as follows:
the layer thickness is 0.04mm, the laser power is 280W-300W, the scanning speed is 900mm/s-1000mm/s, and the scanning interval is 0.1mm-0.12mm.
9. The method of preventing deformation of a superalloy by laser selective melt forming according to claim 1, wherein the step of heat treating the print comprises:
heating the printing piece to 590-610 ℃, preserving heat for 20-40 min, continuously heating to 1090-1110 ℃, preserving heat for 50-70 min, and keeping the working pressure not to exceed 7.27×10 in the heat treatment process -2 Pa, argon is used as a protective gas, and after the completion, the mixture is cooled to below 90 ℃.
10. The method of claim 1, wherein the step of surface treating the shaped part to remove support comprises:
and removing the substrate on the formed piece through linear cutting, and removing the supporting part on the formed piece by adopting a milling method.
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