CN112846229B - Laser material increase and decrease manufacturing method for large-size interlayer straight-groove annular component - Google Patents
Laser material increase and decrease manufacturing method for large-size interlayer straight-groove annular component Download PDFInfo
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- CN112846229B CN112846229B CN202110003700.6A CN202110003700A CN112846229B CN 112846229 B CN112846229 B CN 112846229B CN 202110003700 A CN202110003700 A CN 202110003700A CN 112846229 B CN112846229 B CN 112846229B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
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- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/36—Removing material
- B23K26/38—Removing material by boring or cutting
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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
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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
- B33Y40/00—Auxiliary operations or equipment, e.g. for material handling
- B33Y40/20—Post-treatment, e.g. curing, coating or polishing
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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
- B33Y50/00—Data acquisition or data processing for additive manufacturing
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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
- B33Y80/00—Products made by additive manufacturing
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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
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
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- Y02P10/25—Process efficiency
Abstract
The invention discloses a laser material increase and decrease manufacturing method of a large-size interlayer straight-groove annular component. Establishing a three-dimensional model of a large-size interlayer straight-groove annular component suitable for laser melting deposition forming and laser cutting material reduction manufacturing; setting laser melting deposition forming process parameters and laser cutting material reduction manufacturing process parameters in a slicing software platform; after the growth direction is determined, placing a large-size interlayer straight-groove annular component three-dimensional model, and guiding the model into a set slicing software platform for slicing; under the protection of inert gas, material increase and decrease manufacturing is carried out; after the forming is finished, recovering powder in the cabin, and annealing the unseparated annular component and the substrate; separating the substrate and the annular member using wire cutting; and performing final heat treatment on the annular member. The large-size interlayer straight-groove annular component obtained by the invention has high performance, low surface roughness and high forming precision, and provides a brand new method for final manufacturing of the large-size interlayer straight-groove annular component.
Description
Technical Field
The invention relates to a laser material-increasing and material-decreasing manufacturing method for a large-size interlayer straight-groove annular component, belongs to the technical field of material-increasing manufacturing, and particularly relates to an integral manufacturing method for the large-size interlayer straight-groove annular component, in particular to a manufacturing method for obtaining the large-size interlayer straight-groove annular component with the breadth size of more than 600mm multiplied by 600mm by adopting a laser melting deposition forming technology and a laser cutting material-decreasing manufacturing technology.
Background
The laser melting deposition forming is an advanced manufacturing technology integrating a digitization technology, a manufacturing technology and a laser technology, and compared with the traditional manufacturing technology, the laser melting deposition forming has the advantages of no mould, high material utilization rate, excellent comprehensive mechanical property, short processing period and the like, and has wide application in the field of aerospace. However, the surface of the formed part is rough, the dimensional accuracy is low, and the direct use requirement is difficult to meet, and particularly, the large-size interlayer straight-groove annular formed part is easy to form processing defects at the interlayer straight-groove structure and cannot be subjected to subsequent treatment. Therefore, the large-size interlayer straight groove annular member is integrally manufactured by adopting the laser melting deposition forming and laser cutting material reducing composite manufacturing technology, and the application prospect is great.
The large-size interlayer straight-groove annular component is manufactured by adopting a forging piece, machining and welding method at present, the forging piece is used as a blank, a flow channel structure is formed by adopting a machining and milling mode, and the large-size interlayer straight-groove annular component is manufactured by tailor-welding after being manufactured.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method for integrally manufacturing the large-size interlayer straight-groove annular member has the advantages of high performance, high size precision and low surface roughness, and provides a brand new method for manufacturing the large-size interlayer straight-groove annular member.
The purpose of the invention is realized by the following technical scheme:
a high-strength stainless steel large-size interlayer straight groove annular member material increase and decrease integral manufacturing method is characterized in that a prepared member is a hollow cylinder, the material of the member is 03Cr13Ni5Co9Mo5 stainless steel, the large size means that the height of the member is not less than 600mm, the outer diameter of the member is not less than 600mm, the wall thickness is controlled within 15-30mm, axial through holes are circumferentially and uniformly distributed in the inner portion of the side wall of the member, the profile of the cross section of each through hole is a part of a circular ring, the radial size of each through hole is within 4-8mm, the circumferential angle is 6-30 degrees, and the number of the through holes is within 6-30 degrees; the base plate used in the method is a hollow cylinder, the bottom end of the hollow cylinder is provided with a notch, the number of the notches is consistent with that of the member through holes, the positions of the notches correspond to those of the member through holes, and the notches are used for discharging metal powder falling in the forming process out of the base plate; the inner diameter and the outer diameter of the substrate are matched with those of a member to be molded;
comprises the following steps:
(1) Establishing a three-dimensional model of a member to be molded by using modeling software Pro/engineer or UG, and preparing a substrate; wherein, the outer surfaces of the three-dimensional models are added with 2-4mm of allowance along the normal direction, and 6-15mm of allowance is added at the bottom of the part. And after modeling is finished, exporting the three-dimensional model into an STL format, wherein the exporting precision is not less than 0.005mm.
(2) Slicing the three-dimensional model established in the step (1) along the axial direction to obtain N slices, wherein the first slice is the lowest end of the member to be molded, and the Nth slice is the topmost end of the member to be molded; the thickness of each slice is 0.5-1mm;
(3) Performing laser melting deposition forming on the first slice on the substrate prepared in the step (1), performing laser melting deposition forming on a second slice on the first slice after the first slice is formed, performing laser melting deposition forming on a third slice on the second slice after the second slice is formed, and repeating the steps until the total thickness of the formed slices is not less than 1mm and not more than 3mm, and completing forming of the ith slice, wherein i =1,2, 3' \ 8230, N;
(4) Performing laser cutting material reduction forming on the slice obtained in the step (3) (because the size of the through hole formed in the slice is smaller than that of the through hole of the member to be formed), namely performing laser cutting material reduction processing on the through hole of the member to be formed, so that the size of the through hole in the slice is consistent with that of the through hole of the member to be formed;
(5) Performing laser melting deposition forming on the i +1 th slice obtained in the step (4);
(6) Performing laser cutting and material reducing forming on the slices obtained in the step (5) to enable the sizes of through holes in the slices to be consistent with those of through holes of the members to be formed;
(7) Performing laser melting deposition forming on the (i + 2) th slice obtained in the step (6);
(8) Performing laser cutting and material reducing forming on the slices obtained in the step (7) to enable the sizes of the through holes in the slices to be consistent with those of the through holes of the members to be formed;
by the way of analogy, the method can be used,
(9) Performing laser melting deposition forming on the N slice obtained in the step (8);
(10) Performing laser cutting and material reducing forming on the slice obtained in the step (9) to enable the size of the through hole in the slice to be consistent with that of the through hole of the member to be formed;
(11) Annealing the slices and the substrate obtained in the step (10), and separating the substrate from the slices after the annealing;
the annealing temperature is 450-560 ℃, the temperature is kept for 4-6 h, and then air cooling is carried out;
use linear cutting when separating the base plate and section, the linear cutting parameter is: the pulse waveform is rectangular, the pulse width is 25-50 mus, the pulse interval is 15-250 mus, and the current is 3-6A;
(12) And (4) carrying out heat treatment on the slices separated in the step (11) to finish the integral manufacture of the member to be molded.
The laser melting deposition forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 3-6 mm, the scanning speed is 800-1100 mm/min, the scanning interval is 2-2.5 mm, the powder feeding amount is 20-30 g/min, and the layering thickness is 0.5-1mm;
the laser material reduction forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 0.2-0.8 mm, the scanning speed is 600-1500 mm/min, the auxiliary gas pressure is 0.6-1.8 MPa, inert gas such as argon is used for protection in the laser material reduction forming process, and the oxygen content is required to be less than 1000PPM;
the heat treatment comprises the steps of carrying out solution treatment, then carrying out cold treatment and finally carrying out tempering treatment, wherein:
pressure intensity is not more than 10 during solution treatment -3 Pa, the temperature is 1050 ℃ to 1130 ℃, the heat preservation time is 2h to 4h, and inert gas is backfilled for cooling;
the temperature during cold treatment is-70 ℃ to-80 ℃, the temperature is kept for 3.5 to 4.5 hours, and the temperature is returned to the room temperature;
the temperature of the tempering treatment is 250-320 ℃, the heat preservation time is 3-6 h, and the tempering treatment is carried out by air cooling to the room temperature.
Compared with the prior art, the invention has the following beneficial effects:
(1) The large-size interlayer straight-groove annular component is integrally manufactured by adopting laser material increase and decrease, near-net high-precision forming of the large-size interlayer straight-groove annular component can be realized through a three-dimensional model, the application range of laser melting deposition forming is greatly expanded, the period is reduced by more than half compared with a forge piece, machining and welding method, the whole forming process can be completed by only one laser material increase and decrease device, and the cost of manpower and material resources is greatly reduced.
(2) The annular component integrally manufactured by increasing and decreasing the laser additive has no macrosegregation inside, no obvious difference in the tissue structures of different parts, fine internal structure crystal grains and excellent mechanical property, and completely meets the standard requirement of a forged piece.
(3) The invention discloses a laser material increase and decrease manufacturing method of a large-size interlayer straight-groove annular component, which comprises the following steps of: establishing a large-size interlayer straight groove annular component three-dimensional model suitable for laser melting deposition forming and laser cutting material reduction manufacturing; setting laser melting deposition forming process parameters and laser cutting material reduction manufacturing process parameters in a slicing software platform according to the characteristics of the component material; after the growth direction is determined, placing a large-size interlayer straight-groove annular component three-dimensional model, and guiding the model into a set slicing software platform for slicing; under the protection of inert gas, material increase and decrease manufacturing is carried out; after the forming is finished, recovering powder in the cabin, and annealing the unseparated annular member and the substrate; separating the substrate and the annular member using wire cutting; and performing final heat treatment on the annular component. The large-size interlayer straight-groove annular component obtained by the invention has high performance, low surface roughness and high forming precision, and provides a brand new method for final manufacturing of the large-size interlayer straight-groove annular component.
Drawings
Various additional advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 (a) is a schematic diagram of a three-dimensional model of a large-sized sandwich straight-grooved annular member according to an embodiment of the present invention;
FIG. 1 (b) is another schematic diagram of a three-dimensional model of a large-sized sandwich straight-grooved annular member provided by an embodiment of the invention;
FIG. 2 (a) is a schematic diagram of a large-sized sandwich straight-grooved ring member forming scheme provided by an embodiment of the present invention;
FIG. 2 (b) is another schematic diagram of a large-sized sandwich straight-grooved ring member forming scheme provided by an embodiment of the invention;
FIG. 3 (a) is a schematic view of a substrate for forming a large-sized sandwich straight-grooved ring member according to an embodiment of the present invention;
FIG. 3 (b) is another schematic diagram of a substrate for forming a large-sized sandwich straight-grooved ring member according to an embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments of the present invention may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The embodiment provides an integral manufacturing method of a large-size interlayer straight-groove annular member, as shown in fig. 1 (a), fig. 1 (b), fig. 2 (a), fig. 2 (b), fig. 3 (a) and fig. 3 (b), the method comprises the following steps:
(1) Establishing a three-dimensional model of a large-size gimbal member suitable for laser melting deposition forming;
(2) Setting laser melting deposition forming process parameters and laser cutting material reduction manufacturing process parameters in a slicing software platform;
(3) After the growing direction is determined, placing a three-dimensional model of the large-size interlayer straight-groove annular component, and guiding the three-dimensional model into a slicing software platform which is set to perform slicing processing;
(4) Adding and reducing materials under the protection of inert gas for forming;
(5) After the forming is finished, recovering powder in the cabin, and annealing the unseparated interlayer straight groove annular member and the substrate;
(6) Separating the substrate and the interlayer straight groove annular member using wire cutting;
(7) And carrying out final heat treatment on the interlayer straight-groove annular member.
In the step (1), a three-dimensional model of the large-size interlayer straight-groove annular member is designed by using modeling software Pro/engineer or UG. And after modeling is finished, the three-dimensional model is exported into an STL format, and the export precision is not less than 0.005mm. Specifically, a large-size interlayer straight groove annular component shown in fig. 2 (a) and 2 (b) is drawn, the thickness of the annular wall is 17mm, the thickness of the interlayer straight groove is 4mm, the overall dimension of the breadth is 600mm × 600mm, and the height in the growth direction is 606mm.
In the step (2), when the slicing software platform is set, according to the characteristics of the high-strength stainless steel material, setting laser melting deposition forming process parameters and laser cutting material reduction process parameters in the slicing software platform, wherein the laser melting deposition forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 4-6 mm, the scanning speed is 800-1100 mm/min, the scanning interval is 2-2.5 mm, the powder feeding amount is 20-30 g/min, the layering thickness is 0.5-1mm, and the laser material reduction manufacturing process parameters are as follows: laser power 2600W to 3000W, laser spot size: 0.2-0.8 mm, a scanning speed of 600-1500 mm/min, and an auxiliary gas pressure of 0.6-1.8 MPa. During scanning, firstly scanning the outline part of a slice area, then scanning an inner filling area in a zigzag scanning mode, wherein the phase angle between layers is 90 degrees, after scanning of each layer area is finished, closing a powder feeder for laser melting deposition, opening an auxiliary gas switch, starting laser cutting of an interlayer straight groove, after cutting is finished, closing the auxiliary gas switch, then opening the powder feeder, and continuing laser melting deposition forming of a lower layer. And at the initial forming stage of the part, the straight groove is not cut by laser, and when the forming height of the part reaches 1mm or more, the straight groove is cut by the laser and is combined with laser melting deposition forming.
In step (3), the annular member model with the added allowance is imported into three-dimensional model processing software, and the growth direction of the model is adjusted (the Z direction is the growth direction) as shown in fig. 2 (a) and 2 (b), the model placement position is overlapped with the actual substrate placement position, and the accuracy of the overlap of the model, the substrate in the X-axis direction and the Y-axis direction is controlled to be +/-0.15. And importing the cutting program into a cutting software platform for cutting to obtain the processing program.
In the step (4), the inert gas is argon, and the oxygen content of the atmosphere in the forming process is required to be less than 1000PPM. And (3) opening the cleaning function of the equipment, starting laser energy when the oxygen content of the atmosphere in the forming cabin is less than 1000PPM, starting to increase and decrease the material and form, and keeping the continuous delivery of argon in the forming process to ensure that the oxygen content in the forming cabin is always within 1000PPM.
In the step (5), after the laser material increase and decrease manufacturing of the large-size interlayer straight groove annular component is completed, the cabin door can be opened after the part is cooled for more than 4 hours to take out the part; after the parts are taken out, recovering the powder on the parts and the substrate; the annular member which is not separated and the substrate are subjected to annealing heat treatment, and the annealing treatment method comprises the following steps: keeping the temperature of 450-560 ℃ for 4-6 h, and cooling in air.
In the step (6), the substrate and the interlayer straight-groove annular component are separated by adopting high-speed reciprocating wire-feeding electrospark wire-electrode cutting, the separation process ensures that a wire-electrode cutting wire is tightly attached to the plane of the substrate, and the wire-electrode cutting parameters are as follows: pulse waveform: a rectangle shape; pulse width: 25-50 mus; pulse interval: 15-250 mus; current: 3A to 6A. .
In the step (7), the annular member is subjected to final heat treatment by (1) solution treatment: preserving the heat for 2 to 4 hours in a vacuum environment with the pressure not more than 10 < -3 > Pa and at the temperature of 1050 to 1130 ℃, and refilling inert gas for cooling; (2) and (3) cold treatment: keeping the temperature at-70 ℃ to-80 ℃ for 4h +/-30 min, and recovering to the room temperature; (3) tempering treatment: the temperature is 250-320 ℃, the temperature is kept for 3-6 h, and the air is cooled to the room temperature.
Examples
A high-strength stainless steel large-size interlayer straight groove annular member material increase and decrease integral manufacturing method is characterized in that a prepared member is a hollow cylinder, the material of the member is 03Cr13Ni5Co9Mo5 stainless steel, the member size height is 600mm, the outer diameter is 600mm, the wall thickness is 15mm, axial through holes are circumferentially and uniformly distributed in the side wall, the cross section of each through hole is a part of a circular ring, the radial size of each through hole is within 4mm, the circumferential angle is 6 degrees, and the number of the through holes is 30; the base plate used in the method is a hollow cylinder, the bottom end of the hollow cylinder is provided with a notch, the number of the notches is consistent with that of the member through holes, the positions of the notches correspond to those of the member through holes, and the notches are used for discharging metal powder falling in the forming process out of the base plate; the inner diameter and the outer diameter of the base plate are matched with those of the member to be molded;
comprises the following steps:
(1) Establishing a three-dimensional model of a member to be formed by using modeling software Pro/engineer, and preparing a substrate; and 2mm allowance is added on the outer surface of the three-dimensional model along the normal direction of the three-dimensional model, and 6mm allowance is added at the bottom of the part. And after modeling is finished, exporting the three-dimensional model into an STL format, wherein the exporting precision is not less than 0.005mm.
(2) Slicing the three-dimensional model established in the step (1) along the axial direction to obtain 100 slices, wherein the first slice is the lowest end of the member to be molded, the 100 th slice is the topmost end of the member to be molded, and the thickness of each slice is 0.5mm;
(3) Performing laser melting deposition forming on the first slice on the substrate prepared in the step (1), and performing laser melting deposition forming on a second slice on the first slice after the first slice is formed, wherein the total thickness of the formed slices is 1mm;
(4) Performing laser cutting and material reducing forming on the slice obtained in the step (3), namely performing laser cutting and material reducing treatment on the through hole of the member to be formed to enable the size of the through hole on the slice to be consistent with that of the through hole of the member to be formed;
(5) Performing laser melting deposition forming on the slice obtained in the step (4) for a third slice;
(6) Performing laser cutting and material reducing forming on the slice obtained in the step (5) to enable the size of the through hole in the slice to be consistent with that of the through hole of the member to be formed;
(7) Performing laser melting deposition forming on the fourth slice obtained in the step (6);
(8) Performing laser cutting and material reducing forming on the slice obtained in the step (7) to enable the size of the through hole in the slice to be consistent with that of the through hole of the member to be formed;
by the way of analogy, the method can be used,
(9) Performing laser melting deposition forming on the 100 th slice obtained in the step (8);
(10) Performing laser cutting and material reducing forming on the slice obtained in the step (9) to enable the size of the through hole in the slice to be consistent with that of the through hole of the member to be formed;
(11) Annealing the slices and the substrate obtained in the step (10), and separating the substrate from the slices after the annealing is finished;
the annealing temperature is 450 ℃, the temperature is kept for 6 hours, and then air cooling is carried out;
use linear cutting when separating the base plate and section, the linear cutting parameter is: the pulse waveform is rectangular, the pulse width is 25 mus, the pulse interval is 15 mus, and the current is 3A;
(12) And (4) carrying out heat treatment on the slices separated in the step (11) to finish the integral manufacture of the member to be molded.
The laser melting deposition forming process parameters are as follows: laser power 2600W, laser spot size: 3mm, the scanning speed is 800mm/min, the scanning distance is 2mm, the powder feeding amount is 20g/min, and the layering thickness is 0.5mm;
the laser material reduction forming process parameters are as follows: laser power 2600W, laser spot size: 0.2mm, scanning speed of 600mm/min, auxiliary gas pressure of 0.6Mpa, and inert gas such as argon for protection in the laser material reduction forming process, wherein the oxygen content is required to be less than 1000PPM;
during heat treatment, firstly solid solution treatment, then cold treatment and finally tempering treatment are carried out, wherein:
pressure intensity is not more than 10 during solution treatment -3 Pa, 1050 ℃ and 2h of heat preservation time, and refilling inert gas for cooling;
the temperature during cold treatment is-70 ℃, the temperature is kept for 4.5 hours, and the temperature is returned to the room temperature;
tempering at 250 deg.C for 3 hr, and air cooling to room temperature.
In the embodiment, the large-size interlayer straight groove annular component is manufactured by adopting a laser material increasing and decreasing method, near-net forming of the large-size interlayer straight groove annular component can be realized through the three-dimensional model, the large-size interlayer straight groove annular component can be directly put into service, the material utilization rate is greatly improved, compared with a forge piece processing cycle, the processing cycle is reduced by more than half, the whole forming process can be completed by only one laser material increasing and decreasing device, and the cost of manpower and material resources is greatly reduced. In addition, the laser melting deposition forming gimbal ring component has no macrosegregation inside, no significant difference of tissue structures of different parts, fine internal structure crystal grains and excellent mechanical property, and completely meets the standard requirements of forgings. The large-size interlayer straight-groove annular component is manufactured by increasing and decreasing materials through laser, and the application range of the laser melting deposition forming technology is greatly expanded.
The above-described embodiments are merely preferred embodiments of the present invention, and those skilled in the art should be able to make various changes and substitutions within the scope of the present invention.
Claims (10)
1. A large-size interlayer straight-groove annular component laser material increase and decrease manufacturing method is characterized in that:
the component prepared in the method is a hollow cylinder, the material of the component is 03Cr13Ni5Co9Mo5 stainless steel, the height of the component is not less than 600mm, the outer diameter of the component is not less than 600mm, the wall thickness is 15-30mm, and a plurality of axial through holes are circumferentially and uniformly distributed in the side wall of the component;
the base plate used in the method is a hollow cylinder, the bottom end of the hollow cylinder is provided with openings, the number of the openings is consistent with that of the member through holes, the positions of the openings correspond to those of the member through holes, and the inner diameter and the outer diameter of the base plate are matched with those of a member to be molded;
the method comprises the following steps:
(1) Establishing a three-dimensional model of a member to be molded, then increasing the outer surface of the three-dimensional model by 2-4mm along the normal direction of the three-dimensional model, adding 6-15mm at the bottom of the three-dimensional model, and preparing a substrate;
(2) Slicing the three-dimensional model established in the step (1) along the axial direction to obtain N slices, wherein the first slice is the lowest end of the member to be molded, and the Nth slice is the topmost end of the member to be molded;
(3) Performing laser melting deposition forming on a first slice on the substrate prepared in the step (1), performing laser melting deposition forming on a second slice on the first slice after the first slice is formed, performing laser melting deposition forming on a third slice on the second slice after the second slice is formed, and repeating the steps until the total thickness of the formed slices is not less than 1mm and not more than 3mm, and completing forming of the ith slice at the moment, wherein i =1,2, 3' \ 8230n;
the laser melting deposition forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 3-6 mm, the scanning speed is 800-1100 mm/min, the scanning interval is 2-2.5 mm, the powder feeding amount is 20-30 g/min, and the layering thickness is 0.5-1mm;
(4) Performing laser cutting and material reducing forming on the through holes on the slices obtained in the step (3) to enable the sizes of the through holes on the slices to be consistent with those of the through holes of the members to be formed; the laser material reduction forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 0.2-0.8 mm, the scanning speed is 600-1500 mm/min, the auxiliary gas pressure is 0.6-1.8 Mpa, inert gas argon is used for protection in the laser material reduction forming process, and the oxygen content is required to be less than 1000PPM;
(5) Performing laser melting deposition forming on the (i + 1) th slice obtained in the step (4); the laser melting deposition forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 3-6 mm, the scanning speed is 800-1100 mm/min, the scanning interval is 2-2.5 mm, the powder feeding amount is 20-30 g/min, and the layering thickness is 0.5-1mm;
(6) Performing laser cutting and material reducing forming on the through holes on the slices obtained in the step (5) to enable the sizes of the through holes on the slices to be consistent with those of the through holes of the members to be formed; the laser material reduction forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 0.2-0.8 mm, the scanning speed is 600-1500 mm/min, the auxiliary gas pressure is 0.6-1.8 MPa, the inert gas argon is used for protection in the laser material reduction forming process, and the oxygen content is required to be less than 1000PPM;
(7) Performing laser melting deposition forming on the (i + 2) th slice obtained in the step (6); the laser melting deposition forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 3-6 mm, the scanning speed is 800-1100 mm/min, the scanning interval is 2-2.5 mm, the powder feeding amount is 20-30 g/min, and the layering thickness is 0.5-1mm;
(8) Performing laser cutting and material reducing forming on the through hole on the slice obtained in the step (7) to enable the size of the through hole on the slice to be consistent with that of the through hole of the member to be formed; the laser material reduction forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 0.2-0.8 mm, the scanning speed is 600-1500 mm/min, the auxiliary gas pressure is 0.6-1.8 Mpa, inert gas argon is used for protection in the laser material reduction forming process, and the oxygen content is required to be less than 1000PPM;
by the same way, the operation is carried out,
(9) Performing laser melting deposition forming on the N slice on the slice obtained in the step (8); the laser melting deposition forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 3-6 mm, the scanning speed is 800-1100 mm/min, the scanning interval is 2-2.5 mm, the powder feeding amount is 20-30 g/min, and the layering thickness is 0.5-1mm;
(10) Performing laser cutting and material reducing forming on the through hole on the slice obtained in the step (9) to enable the size of the through hole on the slice to be consistent with that of the through hole of the member to be formed; the laser material reduction forming process parameters are as follows: laser power 2600W to 3000W, laser spot size: 0.2-0.8 mm, the scanning speed is 600-1500 mm/min, the auxiliary gas pressure is 0.6-1.8 Mpa, inert gas argon is used for protection in the laser material reduction forming process, and the oxygen content is required to be less than 1000PPM;
(11) Annealing the slices and the substrate obtained in the step (10), and separating the substrate from the slices after the annealing is finished;
(12) And (5) carrying out heat treatment on the slices obtained by separation in the step (11) to finish the integral manufacture of the member to be molded.
2. The method for manufacturing large-size sandwich straight-groove annular component by laser addition and subtraction of materials according to claim 1, wherein the method comprises the following steps: the cross section of the through hole in the side wall of the member is an arc, the arc is concentric with the member, the radial size of the through hole is within 4-8mm, the circumferential angle is 6-30 degrees, and the number of the through holes is within 6-30 degrees.
3. The method for manufacturing large-size sandwich straight-groove annular component by laser addition and subtraction of materials according to claim 1, wherein the method comprises the following steps: the thickness of each slice is 0.5-1mm.
4. The method for manufacturing large-size sandwich straight-groove annular member according to claim 1, wherein the method comprises the following steps: in the step (11), the annealing temperature is 450-560 ℃, the temperature is kept for 4-6 h, and then air cooling is carried out.
5. The method for manufacturing large-size sandwich straight-groove annular member according to claim 1, wherein the method comprises the following steps: wire cutting is used to separate the substrate and the cut sheet.
6. The method for manufacturing large-size sandwich straight-groove annular component by laser addition and subtraction of materials according to claim 5, wherein the method comprises the following steps: the linear cutting parameters are as follows: the pulse waveform is rectangular, the pulse width is 25-50 mu s, the pulse interval is 15-250 mu s, and the current is 3-6A.
7. The method for manufacturing large-size sandwich straight-groove annular member according to claim 1, wherein the method comprises the following steps: in the step (12), the solution treatment is firstly carried out during the heat treatment, then the cold treatment is carried out, and finally the tempering treatment is carried out.
8. The method for manufacturing large-size sandwich straight-groove annular member according to claim 7, wherein the method comprises the following steps: pressure intensity is not more than 10 during solution treatment -3 Pa, 1050-1130 ℃ of temperature, 2-4 h of heat preservation time, and back filling inert gas for cooling.
9. The method for manufacturing large-size sandwich straight-groove annular member according to claim 7, wherein the method comprises the following steps: the temperature of the cold treatment is-70 ℃ to-80 ℃, the heat preservation is carried out for 3.5 to 4.5 hours, and the temperature is returned to the room temperature.
10. The method for manufacturing large-size sandwich straight-groove annular member according to claim 7, wherein the method comprises the following steps: the temperature for tempering treatment is 250-320 ℃, the heat preservation time is 3-6 h, and the air cooling is carried out to the room temperature.
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| CN114131042A (en) * | 2021-11-02 | 2022-03-04 | 西安航天发动机有限公司 | Method and device for preparing sandwich runner structural member |
| CN114570940B (en) * | 2022-01-25 | 2024-04-02 | 广东增减材科技有限公司 | Valve core material increasing and decreasing method and valve core structure |
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