CN115055696A - Composite manufacturing method for titanium alloy blisk of aircraft engine - Google Patents
Composite manufacturing method for titanium alloy blisk of aircraft engine Download PDFInfo
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- CN115055696A CN115055696A CN202210886553.6A CN202210886553A CN115055696A CN 115055696 A CN115055696 A CN 115055696A CN 202210886553 A CN202210886553 A CN 202210886553A CN 115055696 A CN115055696 A CN 115055696A
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 33
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 23
- 239000002131 composite material Substances 0.000 title claims abstract description 15
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- 230000000996 additive effect Effects 0.000 claims abstract description 37
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- 238000010438 heat treatment Methods 0.000 claims abstract description 14
- 238000005242 forging Methods 0.000 claims abstract description 6
- 239000000843 powder Substances 0.000 claims description 76
- 239000002994 raw material Substances 0.000 claims description 22
- 238000011049 filling Methods 0.000 claims description 18
- 238000003892 spreading Methods 0.000 claims description 8
- 230000007480 spreading Effects 0.000 claims description 8
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/20—Direct sintering or melting
- 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
- B22F10/60—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
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/66—Treatment of workpieces or articles after build-up by mechanical 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
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y40/00—Auxiliary operations or equipment, e.g. for material handling
- B33Y40/20—Post-treatment, e.g. curing, coating or polishing
-
- 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
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention discloses a composite manufacturing method of a titanium alloy blisk of an aircraft engine, which is characterized by comprising the following steps of: 1) respectively preparing a wheel disc semi-finished product and a blade additive matrix semi-finished product through a forging forming process; 2) machining the wheel disc semi-finished product to obtain a wheel disc finished product; 3) machining the blade additive matrix semi-finished product, and then carrying out heat treatment to obtain a blade additive matrix finished product; 4) carrying out selective laser melting on the finished product of the blade additive substrate, and then carrying out heat treatment to obtain a finished product of the blade; 5) fixedly connecting a wheel disc finished product and a blade finished product into a whole through linear friction welding connection to obtain a blisk semi-finished product; 6) and machining the semi-finished blisk to obtain a finished blisk. The titanium alloy blisk for the aircraft engine is compositely manufactured by multiple processing modes, the advantages of multiple technologies are exerted, the cost is low, the forming efficiency is high, and the quality of the obtained blisk product is high.
Description
Technical Field
The invention relates to the technical field of titanium alloy for high temperature, in particular to a composite manufacturing method of a titanium alloy blisk of an aircraft engine.
Background
The excellent flight performance of modern aircraft depends on the application of advanced high thrust-to-weight ratio aircraft engines, and the design goal of ever-decreasing engine weight needs to be achieved by using light-weight, high-temperature-resistant materials and light-weight overall structures. The non-integral blade disc of the aviation gas turbine engine usually adopts a tenon-tooth connection structure, namely, tenons (mostly in a dovetail shape) under blade bodies of fan working blades (namely rotor blades) are arranged in mortises on the rim of the wheel disc, and then the blades are locked in the wheel disc by a locking device. The blisk integrates and designs parts such as blades, a wheel disc and the like into an integral component, compared with a traditional tenon tooth connecting structure, the blisk is reduced by about 30%, contact stress between the parts caused by connection and assembly is eliminated, the potential risk of fatigue failure between a blade tenon and a wheel disc mortise caused by fretting wear is avoided, leakage of airflow between the tenon and the mortise is eliminated, the radial temperature gradient of a blade and a wheel disc rotor assembly is reduced, the thermal mechanical fatigue risk is effectively reduced, the stability of a pneumatic compressor is improved, and the use reliability of the blisk is improved.
At present, the machining method of the large blisk is summarized into milling machining, electrochemical machining, linear friction welding and the like of a numerical control milling machine. However, these techniques have different advantages and disadvantages: the numerical control milling machine can mill parts with extremely complex outline shapes, the machining precision is high, but in the manufacturing process from the blisk blank to the blisk part, the material cutting rate exceeds 90%, and the material utilization rate is extremely low. Electrolytic machining can reduce the machining time, machining residual stress and a large stress concentration area cannot exist, but the method is only limited to machining of a straight line-expandable curved surface, and the material utilization rate is low. As a solid-state connecting technology, the linear friction welding does not have the phenomenon of easy-to-occur desoldering in common welding, and the strength and the elasticity of a welding seam at the connecting part are superior to those of a body material.
The selective laser melting repair technology is a novel rapid forming repair technology for obtaining parts in required shapes by laying a powder layer in advance, and controlling laser to scan and melt a selected area of the metal powder layer through software in a computer. Compared with the traditional laser melting deposition repair technology, the technology has smaller light spot and smaller heat influence, and hardly causes deformation.
Disclosure of Invention
The invention aims to design the idea and the preparation technology of the dual performance of the blisk, namely, respectively producing the blisk and the blades by adopting different manufacturing methods, so that the blisk and the blades are most suitable for the organization state required by the actual use working condition of an aircraft engine, and the integration of material performance and structural design is realized.
The technical scheme of the invention is specifically that the composite manufacturing method of the titanium alloy blisk of the aircraft engine is characterized by comprising the following steps:
1) respectively preparing a wheel disc semi-finished product and a blade additive matrix semi-finished product through a forging forming process;
2) machining the wheel disc semi-finished product to obtain a wheel disc finished product;
3) machining the blade additive matrix semi-finished product, and then carrying out heat treatment to obtain a blade additive matrix finished product;
4) carrying out selective laser melting on the finished product of the blade additive substrate, and then carrying out heat treatment to obtain a finished product of the blade;
5) fixedly connecting a wheel disc finished product and a blade finished product into a whole through linear friction welding connection to obtain a blisk semi-finished product;
6) and machining the semi-finished blisk to obtain a finished blisk.
Preferably, the selective laser melting includes designing a three-dimensional model of a blade entity, slicing and layering the three-dimensional model to obtain profile data of each section, generating a filling scanning path according to the profile data, and introducing the filling scanning path into a laser, where the filling scanning path is formed by dividing a scanning plane into multiple grids which are identical in size and spliced with each other, each grid is formed by splicing multiple rectangular strips which are identical in size and arranged in parallel, the side length of each grid is 2-10mm, the rectangular strips of two adjacent grids are perpendicular to each other, and all the rectangular strips in the scanning plane are the filling scanning path.
It is further preferable that the projections of the squares of two adjacent layers on the horizontal plane are correspondingly overlapped, but two groups of rectangular bars forming the two correspondingly overlapped squares are perpendicular to each other.
More preferably, the laser power is 800W or more when the selective laser melting is performed.
Further preferably, when the selective area is subjected to laser melting, the laser power is 900-1100W, the scanning speed is 900-1100mm/s, the powder spreading thickness is 0.03mm, the spot diameter is 3-5mm, the defocusing amount is 40-60mm, and the scanning interval is 0.1 mm.
Preferably, the selective laser melting includes placing raw material powder into a powder cylinder of the processing chamber, placing the finished blade additive substrate into a forming cylinder of the processing chamber, pushing the raw material powder onto the surface of the finished blade additive substrate by using a powder spreading device to form the raw material powder with the powder spreading thickness, starting a laser to enable a laser beam to melt the raw material powder on the surface of the finished blade additive substrate according to a filling scanning path of a current layer, and processing the current layer; and then, controlling the finished blade additive substrate to descend by a distance of one processing layer thickness, raising the raw material powder in the powder cylinder by a certain distance, forming the raw material powder with the powder laying thickness on the processed current layer by the powder laying device, starting a laser to enable a laser beam to press a filling scanning path of one layer, selectively melting the raw material powder on the surface of the finished blade additive substrate, and processing layer by layer until the whole blade is processed.
More preferably, the heat treatment in the step 4) is carried out by raising the temperature to 580-620 ℃ at a speed of 10 ℃/min and then preserving the heat for 1.5-2.5 h.
Further preferably, the raw material powder is dried at 120 ℃ for 3 hours before being placed in a powder cylinder of the processing chamber.
Further preferably, the finished blade additive substrate is preheated to 80 ℃ before being placed in a forming cylinder of the processing chamber.
Further preferably, the friction frequency of the linear friction welding is 30-40Hz, the upsetting pressure is 3.5-4.3kN, the acting time is 25-35 seconds, and the friction amplitude is 4-4.5 mm.
Compared with the prior art, the invention designs the thought and the preparation technology of the dual performance of the blisk, namely, the blisk and the blades are respectively produced by adopting different manufacturing methods, so that the blisk and the blades are most suitable for the organization state required by the actual use working condition of the aero-engine, and the integration of the material performance and the structural design is realized. The working conditions of different parts of the blisk are different greatly, the blisk mainly bears the action of great centrifugal stress and thermal stress, and low-cycle fatigue and creep property are the first factors for ensuring the use reliability of the blisk, so that the blisk is produced by adopting a forging mode; the blade mainly bears the action of high-frequency low-amplitude vibration stress, and the high-cycle fatigue performance is the first factor influencing the use reliability of the blade, so that the blade is produced by adopting a selective laser melting method; then, the wheel disc and the blade are connected together in a linear friction welding connection mode to obtain excellent connection strength, so that the wheel disc and the blade are integrated; and finally milling redundant materials by a numerical control milling machine to finally obtain a finished blisk.
In conclusion, the titanium alloy blisk for the aircraft engine is compositely manufactured by using various processing modes, and the advantages of various technologies are exerted: the wheel disc produced by forging has excellent fatigue and creep properties and short processing period; the blade manufactured by selective laser melting has high flexibility and high material utilization rate; the linear friction welding has excellent performance of the connecting weld joint, and can realize welding of different materials; the milling of the numerical control milling machine can process various complex surfaces and has high processing precision.
Drawings
FIG. 1 is a flow chart of the manufacturing process of the titanium alloy blisk of the present invention.
Fig. 2 is a schematic structural design diagram of the blade additive substrate according to the present invention.
FIG. 3 is a schematic structural view of a selective laser melting and forming apparatus according to the present invention.
Fig. 4A and 4B are schematic diagrams of scanning paths of the selective laser melting nth layer and the N +1 th layer, respectively.
Detailed Description
The technical solutions in the embodiments of the present invention will be described below with reference to the drawings in the embodiments of the present invention.
The flow chart of the invention for manufacturing the titanium alloy blisk is shown in figure 1,
1) respectively preparing a wheel disc semi-finished product and a blade additive matrix semi-finished product through a forging forming process;
2) machining the wheel disc semi-finished product to obtain a wheel disc finished product;
3) machining the blade additive matrix semi-finished product, and then carrying out heat treatment to obtain a blade additive matrix finished product;
4) carrying out selective laser melting on the finished product of the blade additive substrate, and then carrying out heat treatment to obtain a finished product of the blade;
5) fixedly connecting a wheel disc finished product and a blade finished product into a whole through linear friction welding connection to obtain a blisk semi-finished product;
6) and machining the semi-finished blisk to obtain a finished blisk.
The following mainly describes a selective laser melting method of the blade in the step 4), which mainly comprises the following steps: 1. preparing an additive matrix; 2. selecting raw materials; 3. and (4) selective laser melting process.
1. Preparation of additive matrix
The blade disc prepared by the invention is formed by connecting the blades and the wheel disc through linear friction welding, so that a structure meeting the linear friction welding work needs to be designed during blade preparation. Fig. 2 shows that the vane additive substrate designed by the invention is different from a common rectangular plate-shaped substrate, two skirt edges are added at one end of the rectangular plate-shaped substrate, and a boss is correspondingly arranged on a wheel disc, so that the pressure applying condition can be met, the substrate is forged and formed by adopting TC17 titanium alloy, then the substrate is subjected to heat treatment (under the vacuum condition, the temperature is kept at 820 ℃ for 4 hours) to enable the performance to meet the required requirements, and the selective laser melting forming process of the vane is carried out on the vane additive substrate.
2. Raw material selection
The TC17 titanium alloy powder prepared by the plasma rotary electrode atomization method is adopted, the cooling speed is high when the plasma rotary electrode atomization powder is prepared, the powder cleanliness is high, the particle shape is very close to a sphere, the surface is smooth and clean, the fluidity is good, and the titanium alloy powder is suitable for selective laser melting forming of the titanium alloy powder, and the chemical components of the titanium alloy powder are shown in Table 1. The invention selects the titanium alloy powder of the above type prepared by the above method, but is not limited to the method.
TABLE 1 chemical composition of TC17 titanium alloy powder raw material used in the present invention
| Element(s) | Al | Sn | Zr | Mo | Cr | H | O | Ti |
| Content (wt.%) | 5.23 | 1.97 | 1.80 | 4.06 | 4.04 | 0.01 | 0.14 | Bal. |
3. Selective laser melting process
As shown in fig. 3, the selective laser melting and forming apparatus (SLM) used in the present invention mainly comprises a fiber laser 1, an optical path transmission unit 2, a sealed forming chamber 3 (including a powder spreading device), a control system 4, and process software (not shown). Firstly, a three-dimensional model of a blade entity is designed on a computer by using three-dimensional modeling software (the size of a blade additive substrate is considered when the three-dimensional model of the blade is designed), then the three-dimensional model is sliced and layered by using slicing software to obtain profile data of each single-layer section, and a filling scanning path is generated according to the profile data. The method comprises the following steps of drying the TC17 titanium alloy powder in an oven for 3 hours at the drying parameter of 120 ℃, so that impurities such as water vapor and the like attached to the powder can be effectively removed, and hot cracking caused by too high heating speed in subsequent additive manufacturing can be prevented. And then the processed powder 11 is put into a powder cylinder 5 of a sealed forming chamber 3, wherein the powder cylinder 5 consists of a powder cylinder sleeve and a plunger type powder placing platform matched with the powder cylinder sleeve, and the raw material powder is stacked on the powder placing platform until the raw material powder is flush with the top opening of the powder cylinder sleeve. Leading in a filling scanning path generated before in a laser, preheating to 80 ℃ (a matrix needs to be polished before material increase to remove surface oxides and oil stains, then cleaning with organic solvents such as acetone, meanwhile, laser energy input is fast in the material increase process, heat is high, the matrix is likely to be subjected to heat crack, the material increase blade matrix 6 which is preheated to 80 ℃ can remove the acetone, can raise the temperature of a base plate without changing the matrix structure and prevent heat crack is placed in a forming cylinder 7 of a sealed forming chamber 3, the forming cylinder 7 consists of a forming cylinder sleeve and a plunger type objective table matched with the forming cylinder sleeve, and the material increase blade matrix 6 is placed on the objective table and controls the surface of the material increase blade matrix to be flush with the top opening of the forming cylinder sleeve. The top of the cylinder sleeve of the forming cylinder and the top of the cylinder sleeve of the powder cylinder are the same in height and are both positioned on a processing plane of selective laser melting, a powder placing table is firstly lifted for a certain distance, titanium alloy powder is flatly pushed onto a material adding substrate to achieve the powder laying thickness through a powder laying device 8, a laser is started to enable a laser beam to follow a filling scanning line of a current layer, the powder on the substrate is selectively melted to process the current layer, then the forming cylinder is lowered for a distance of one processing layer thickness, the powder cylinder is lifted for a certain distance, the powder laying device is used for laying powder raw materials on the processed current layer, before actual processing, the distance of the lifting amount of the powder cylinder can be determined through a pre-experiment mode, the powder laying device can be used for flatly pushing the titanium alloy powder onto the material adding substrate to achieve the powder laying thickness through one-time operation, of course, the powder laying thickness can be detected through an infrared measuring device in the powder laying process of the powder laying device, if the required powder spreading thickness is not accurately achieved, the powder spreading device can be used for adjusting until the required powder spreading thickness is achieved. And (5) transferring the data of the next layer of the outline into the equipment for processing, and processing layer by layer until the whole blade 9 is processed. The whole process is carried out in a sealed forming chamber which is protected by argon inert gas 10 to avoid the metal reacting with other gases at high temperature. And after the processed blade is cooled to room temperature, taking the blade out of the selective laser melting forming equipment. And placing the test piece in an acetone solution, carrying out ultrasonic cleaning for 10 minutes, and carrying out stress relief annealing after blow-drying so as to eliminate residual stress in the test piece.
Designing a specific scanning path and parameters:
in the SLM process of the present invention, the laser scanning path adopts checkerboard scanning, as shown in fig. 4A and 4B, the filling scanning path generated according to the profile data is a filling scanning path that divides the scanning plane into a plurality of grids that are identical in size and are spliced with each other, each grid is formed by splicing a plurality of rectangular bars that are identical in size and are arranged in parallel, the side length of each grid is 2-10mm, if the size of the grid is smaller, the advantage of the scanning path set in the present invention cannot be exerted, if the size of the grid is larger, the forming efficiency is affected, the rectangular bars of two adjacent grids are perpendicular to each other (that is, the scanning trace between adjacent grids rotates 90 °), and all the rectangular bars in the scanning plane are the filling scanning path of the current layer. It is particularly preferred that the projections of the squares of two adjacent layers (e.g. the nth layer and the N +1 th layer) on the horizontal plane are correspondingly coincident, but that the two sets of rectangular strips making up the two correspondingly coincident squares are perpendicular to each other (i.e. the entire board between adjacent layers is rotated 90 °), as shown in fig. 4A (the nth layer) and 4B (the N +1 th layer). Compared with the conventional continuous long-line scanning, the checkerboard scanning is adopted, the surface of the sample is flat, obvious warping deformation is avoided, the holes are few, the molten pools are periodically arranged along the checkerboard grid scanning direction and are vertically arranged in a crossed manner, the molten pools are regularly and uniformly distributed and have small sizes, the obtained tissue uniformity is better, the interlayer combination on the side surface of the sample is good, and obvious cracks and interlayer combination defects do not exist.
The power selection of the laser is also extremely important, the laser power in the process is more than 800W and higher than the power for forming common titanium alloy, and the laser fuse additive manufacturing is carried out in a positive defocusing large-spot mode in the additive manufacturing process. Because the defocusing light spot is larger, the laser energy density acting on the material is smaller than that of the focusing light spot, and is in a thermal conduction mode (conduction molten pool), the process is relatively stable, the keyhole phenomenon is avoided, the defect of air holes generated by the closing of common deep melting small holes is reduced, the molten pool is smoother, and the surface quality is higher. The power adopted by the invention is larger, so that the forming efficiency can be obviously improved, the efficiency of the conventional low-power uniform scanning SLM titanium alloy is about 50g/h, and the efficiency of the high-power checkerboard type scanning adopted by the invention can be improved to 100 g/h.
And finally, fixedly connecting the finished wheel disc and the finished blade into a whole by adopting linear friction welding, wherein the friction frequency of the linear friction welding is 35Hz, the upsetting pressure is 4kN, the action time is 30 seconds, and the friction amplitude is 4.3 mm.
Example (b):
the forming is carried out by referring to the technological parameters of selective laser melting of the blade, the technological parameters of selective laser melting and the technological parameters of heat treatment after forming of the embodiment are respectively shown in the following tables 2 and 3, and the parameters of sample of the embodiment obtained after forming are shown in the following table 4.
TABLE 2 Process parameters for selective laser melting of examples
| Parameter (Unit) | Value of |
| Laser power (W) | 1000 |
| Scanning speed (mm/s) | 1000 |
| Powder thickness (mm) | 0.03 |
| Spot diameter (mm) | 4 |
| Defocus (mm) | 50 |
| Scanning interval (mm) | 0.1 |
Table 3 annealing process parameters of the examples
| Parameter (Unit) | Value of |
| Annealing temperature (. degree.C.) | 600 |
| Rate of temperature rise (. degree. C./min) | 10 |
| Incubation time (h) | 2 |
TABLE 4 parameters of the samples of the examples
| Parameter (Unit) | Value of |
| Density (%) | 99.938 |
| Shaping efficiency (g/h) | 102.4 |
Comparative example:
the comparative example adopts low-power continuous long-line scanning selective laser to melt TC17 titanium alloy, the technological parameters of selective laser melting are shown in the following table 5, the technological parameters of heat treatment are consistent with those of the example, and the parameters of the sample of the example obtained after forming are shown in the following table 6.
TABLE 5 Process parameters for selective laser melting of comparative examples
| Parameter (Unit) | Value of |
| Laser power (W) | 300 |
| Scanning speed (mm/s) | 1000 |
| Powder thickness (mm) | 0.03 |
| Spot diameter (mm) | 0.1 |
| Defocus (mm) | 0 |
| Scanning interval (mm) | 0.1 |
TABLE 6 comparative example sample parameters
| Parameter (Unit) | Value of |
| Density (%) | 99.6 |
| Shaping efficiency (g/h) | 48.6 |
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. The composite manufacturing method of the titanium alloy blisk of the aircraft engine is characterized by comprising the following steps:
1) respectively preparing a wheel disc semi-finished product and a blade additive matrix semi-finished product through a forging forming process;
2) machining the wheel disc semi-finished product to obtain a wheel disc finished product;
3) machining the blade additive matrix semi-finished product, and then carrying out heat treatment to obtain a blade additive matrix finished product;
4) carrying out selective laser melting on the finished product of the blade additive substrate, and then carrying out heat treatment to obtain a finished product of the blade;
5) fixedly connecting a wheel disc finished product and a blade finished product into a whole through linear friction welding connection to obtain a blisk semi-finished product;
6) and machining the semi-finished blisk to obtain a finished blisk.
2. The composite manufacturing method of the titanium alloy blisk of the aircraft engine according to claim 1, wherein the selective laser melting comprises the steps of firstly designing a three-dimensional model of a blade entity, then slicing and layering the three-dimensional model to obtain profile data of each section, generating a filling scanning path according to the profile data, and guiding the filling scanning path into a laser, wherein the filling scanning path is formed by dividing a scanning plane into a plurality of grids which are identical in size and are spliced with each other, each grid is formed by splicing a plurality of rectangular strips which are identical in size and are arranged in parallel, the side length of each grid is 2-10mm, the rectangular strips of two adjacent grids are perpendicular to each other, and all the rectangular strips in the scanning plane are the filling scanning path.
3. The composite manufacturing method of the titanium alloy blisk according to claim 2, characterized in that the projections of the squares of two adjacent layers on the horizontal plane are correspondingly overlapped, but the two sets of rectangular strips forming the two squares correspondingly overlapped are perpendicular to each other.
4. The composite manufacturing method of the titanium alloy blisk of the aircraft engine as claimed in claim 1, wherein laser power is above 800W when the selected area is melted by laser.
5. The composite manufacturing method of the titanium alloy blisk of the aircraft engine as claimed in claim 4, wherein during the selective laser melting, the laser power is 900-1100W, the scanning speed is 900-1100mm/s, the powder spreading thickness is 0.03mm, the spot diameter is 3-5mm, the defocusing amount is 40-60mm, and the scanning distance is 0.1 mm.
6. The aircraft engine titanium alloy blisk composite manufacturing method according to claim 1, wherein the selective laser melting comprises placing raw material powder into a powder cylinder of a processing chamber, placing the finished blade additive substrate into a forming cylinder of the processing chamber, pushing the raw material powder to the surface of the finished blade additive substrate by a powder laying device to form the raw material powder with a powder laying thickness, starting a laser to enable a laser beam to follow a filling scanning path of a current layer, and selectively melting the raw material powder on the surface of the finished blade additive substrate to process the current layer; and then, controlling the finished blade additive substrate to descend by a distance of one processing layer thickness, raising the raw material powder in the powder cylinder by a certain distance, forming the raw material powder with the powder laying thickness on the processed current layer by the powder laying device, starting a laser to enable a laser beam to press a filling scanning path of one layer, selectively melting the raw material powder on the surface of the finished blade additive substrate, and processing layer by layer until the whole blade is processed.
7. The composite manufacturing method of the titanium alloy blisk of the aircraft engine according to claim 6, characterized in that the raw material powder is dried at 120 ℃ for 3h before being put into a powder cylinder of a processing chamber.
8. The composite manufacturing method of the titanium alloy blisk of the aircraft engine as claimed in claim 7, wherein the finished blade additive substrate is preheated to 80 ℃ before being placed in a forming cylinder of a processing chamber.
9. The composite manufacturing method of the titanium alloy blisk of the aircraft engine as claimed in claim 1, wherein the heat treatment in the step 4) is performed by raising the temperature to 580-620 ℃ at a rate of 10 ℃/min and then preserving the heat for 1.5-2.5 h.
10. The composite manufacturing method of the titanium alloy blisk of the aircraft engine as claimed in claim 1, wherein the friction frequency of the linear friction welding is 30-40Hz, the upsetting pressure is 3.5-4.3kN, the acting time is 25-35 seconds, and the friction amplitude is 4-4.5 mm.
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