CN114043169B - Micro-stress composite machining method for turbine disc mortises of aero-engine - Google Patents
Micro-stress composite machining method for turbine disc mortises of aero-engine Download PDFInfo
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- CN114043169B CN114043169B CN202111329624.4A CN202111329624A CN114043169B CN 114043169 B CN114043169 B CN 114043169B CN 202111329624 A CN202111329624 A CN 202111329624A CN 114043169 B CN114043169 B CN 114043169B
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- turbine
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- 238000003754 machining Methods 0.000 title claims abstract description 42
- 238000000034 method Methods 0.000 title claims abstract description 28
- 239000002131 composite material Substances 0.000 title claims abstract description 13
- 238000005520 cutting process Methods 0.000 claims abstract description 36
- 239000002245 particle Substances 0.000 claims abstract description 24
- 238000005498 polishing Methods 0.000 claims abstract description 7
- 150000001875 compounds Chemical class 0.000 claims abstract description 3
- 230000003746 surface roughness Effects 0.000 claims abstract description 3
- 238000003672 processing method Methods 0.000 claims description 9
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 8
- 238000009966 trimming Methods 0.000 claims description 6
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 4
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 4
- 229910052750 molybdenum Inorganic materials 0.000 claims description 3
- 239000011733 molybdenum Substances 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 3
- 239000000843 powder Substances 0.000 description 8
- 239000000956 alloy Substances 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 229910045601 alloy Inorganic materials 0.000 description 4
- 229910000601 superalloy Inorganic materials 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P23/00—Machines or arrangements of machines for performing specified combinations of different metal-working operations not covered by a single other subclass
- B23P23/04—Machines or arrangements of machines for performing specified combinations of different metal-working operations not covered by a single other subclass for both machining and other metal-working operations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q17/00—Arrangements for observing, indicating or measuring on machine tools
- B23Q17/20—Arrangements for observing, indicating or measuring on machine tools for indicating or measuring workpiece characteristics, e.g. contour, dimension, hardness
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a micro-stress compound machining method of a turbine disc mortise of an aeroengine, which comprises the steps of firstly cutting lines on a turbine disc blank (2) along tooth crest datum lines of the mortise to form a mortise reserved with a finishing size, and then polishing abrasive particle flow of the mortise reserved with the finishing size to obtain the mortise with the preset size and surface roughness. The composite machining process for the turbine disc mortises has high machining precision, omits a broaching process, does not need a broaching tool, greatly reduces the machining cost, simultaneously adopts linear cutting to realize stress-free machining, avoids the problem that the final mortises are difficult to ensure due to large stress generated during broaching, and ensures the machining dimensional precision requirement of the turbine disc mortises. Meanwhile, the abrasive particle flow is adopted to remove the recast layer and the heat affected zone remained on the surface of the workpiece in the wire cutting process, so that the service life of the turbine disk is ensured.
Description
Technical Field
The invention discloses a micro-stress composite machining method for a turbine disc mortise of an aeroengine, and relates to the technical field of turbine disc machining.
Background
In high-temperature and high-pressure operation, the blades and the rotor of the turbine disk are connected in a matched manner through the mortises and the tenons, and in order to ensure the working reliability of the turbine disk, the mortises and the tenons are required to have extremely high precision and reliable mechanical properties. The traditional turbine disc mortises are processed mostly by adopting a broaching method, but the problems of high design difficulty, time-consuming maintenance, quick abrasion of the broaching tool and the like exist, so that the processing cost is greatly improved, broaching equipment used by the broaching process is basically imported, the broaching equipment is high in price and difficult to independently guarantee.
Disclosure of Invention
The invention provides a micro-stress compound machining method for a turbine disc mortise of an aeroengine, which aims to solve the problem that the final tenon tooth size is difficult to guarantee due to large stress generated during broaching by wire cutting through wire cutting machining of the turbine disc mortise, further adopts an abrasive particle flow process to remove a recast layer and a heat affected zone left by wire cutting, finally ensures the machining dimensional accuracy requirement and the service life of the turbine disc mortise, improves the machining accuracy and reduces the machining cost.
In order to achieve the above object, the technical scheme of the present invention comprises the following:
The micro-stress composite processing method for the turbine disc mortises of the aero-engine is characterized by comprising the following steps of: according to the machining method, firstly, linear cutting is carried out on a turbine disc blank (2) along a tooth crest datum line of a mortise to form the mortise reserved with the finishing size, and then abrasive particle flow polishing is carried out on the mortise reserved with the finishing size to obtain the mortise with the preset size and surface roughness.
In practice, the wire cut ends up with a recast layer of less than 0.01mm.
In practice, the finishing size of the mortise reservation is 0.01mm to 0.02mm at the most.
In implementation, wire cutting processing in the processing method is completed by adopting numerical control wire cutting equipment and molybdenum wires, the equipment comprises a rotary table 6, a mounting seat 1 for mounting a turbine disc blank 2 is connected to the rotary table 6, and the disc blank 2 is fixed through a pressing block 3 and a screw 4.
Further, in the wire cutting processing in the processing method, the molybdenum wire 5 is vertically processed, and every time one mortice is processed, the C shaft is rotated by one degree, the angle is equal to 360 degrees/the total number of mortises of the turbine disc, the next mortice is started to be processed, and after the finish, the size and the position of the mortises are detected by adopting three coordinates.
In the wire cutting process in this processing method, the rough machining size, the rough trimming first time, the semi-trimming second time, and the trimming third time are sequentially performed.
In the wire cutting process in this processing method, the pulse width of the wire cutting process is 10 to 40 μs, the pulse stop is 60 to 200 μs, and the current is 2 to 4A.
In the implementation, the abrasive particle flow polishing in the processing method adopts silicon carbide as abrasive particles, the abrasive particles are cylindrical, and the abrasive particle speed is 50-100 m/s.
The technical scheme of the invention adopts a composite machining process of linear cutting and abrasive flow, has the remarkable advantages of high machining precision and low cost, can avoid the defects of deformation and material hardening in machining the mortises in machining the turbine disc mortises, ensures the machining precision requirement of the turbine disc mortises, and simultaneously adopts linear cutting to replace broaching machining without using a broaching machine and a broach, thereby greatly reducing the cost. The process is used for processing and exploring the mortise of the turbine disk, and has great significance in realizing complete independent and controllable processing of the turbine disk. The characteristics and beneficial effects are further described as follows:
The turbine disk is an important core hot end component of the aeroengine, the metallurgical quality and performance level of the turbine disk have decisive effects on the improvement of the reliability, the safety life and the performance of the engine, and meanwhile, the turbine disk tongue-and-groove is a key connecting part for connecting turbine working blades, and the material structure and the surface quality of the tongue-and-groove are critical to the safety service of the engine. The powder superalloy has become the material of choice for the turbine disk of the current high-performance aero-engine because of its good comprehensive properties. The low-stress composite process of wire cutting and abrasive flow is adopted to replace the existing broaching method for machining the turbine disc mortises, so that the problems of high design difficulty, time-consuming maintenance, quick broaching wear and the like of the broaching tool can be solved, the machining cost of the turbine disc mortises can be greatly reduced, broaching equipment used by the broaching process is basically imported, the cost is high, and the independent guarantee is difficult. However, the powder high-temperature alloy for the turbine disk of the aeroengine is difficult to deform, the surface integrity and the tissue stability of the powder high-temperature alloy are required to be ensured in the processing process, the surface of the powder high-temperature alloy material is limited to be removed by an abrasive particle flow process, and the surface is difficult to exceed 0.02mm, so that the influence of wire cutting on the surface tissue of the powder high-temperature alloy material is required to be reduced to the greatest extent, the recast layer generated by the wire cutting is ensured not to exceed 0.015mm, and the recast layer on each part of the surface of the material after the wire cutting is kept consistent. Therefore, the process parameters of the powder superalloy material wire cutting process and the abrasive particle flow process are determined, the process parameters are particularly important to ensure the tissue and surface integrity of the processed material, and finally, the processed turbine disc mortises meet the use requirement of the engine and ensure the safe service of the aeroengine.
Through repeated technological groves, the linear cutting processing technological parameters in the powder superalloy turbine disc mortise composite processing technology are 10-40 mu s pulse width, 60-200 mu s pulse stop and 2-4A current, silicon carbide is adopted as abrasive particles for abrasive particle flow polishing, the abrasive particles are cylindrical, and the abrasive particle speed is 50-100 m/s. The matching of the composite technological parameters can ensure that the recast layer on the surface of the mortises of the processed powder superalloy turbine disk is completely removed, and the low stress and the integrity of the surfaces of the mortises are ensured.
The technical scheme of the invention solves the problems that an expensive imported broaching machine and a large number of broaches are needed to be adopted for machining the turbine disc mortises, deformation and deviation of the dimension are easy to occur in the broaching process, greatly reduces the machining cost of the turbine disc, ensures the machining quality of the turbine disc mortises, realizes complete independent and controllable machining of the turbine disc mortises, and has obvious economic and national defense effects.
Drawings
FIG. 1 is a schematic diagram of the assembly of a turbine disk and tooling of the present invention.
Fig. 2 is a schematic view of the processing of the turbine disc of the invention.
FIG. 3 illustrates a most area recast layer after optimization of the FGH96 alloy wire cutting process.
FIG. 4FGH96 alloy wire cut process optimized individual region recast layer.
Detailed Description
The invention will be described in further detail with reference to the drawings and the specific examples.
In the embodiment, the technical scheme of the invention is adopted to carry out the microstress composite processing on the turbine disk mortise as follows:
firstly, wire cutting machining in the machining method is completed by adopting numerical control wire cutting equipment and molybdenum wires, a clamping mode of the turbine disc 2 is determined according to the structural form and the size of the turbine disc 2, as shown in figures 1 and 2, a mounting seat 1 for mounting a turbine disc blank 2 is connected to a rotary table 6, the turbine disc blank 2 is fixed through a pressing block 3 and a screw 4, and the angle phi in figure 2 is ensured to be complementary with a radial included angle between a turbine disc mortice groove and a radial included angle;
In the linear cutting processing in the processing method, the molybdenum wire 5 is vertically processed, and every time one mortice is processed, the C shaft is rotated by one degree, the angle is equal to 360 degrees/the total number of mortises of the turbine disk, the next mortice is started to be processed, and after the finish, the size and the position of the mortises are detected by adopting three coordinates;
step two, performing wire cutting according to the diagram shown in the figure 2, vertically machining the molybdenum wire 5, rotating the C shaft by 8.78 degrees after finishing machining one mortice, wherein the angle is equal to 360 degrees/the total number of the mortises of the turbine disc, namely 360 degrees/41 degrees, then starting to machine the next mortises, and detecting the sizes and the positions of the mortises by adopting three coordinates after finishing;
In the wire cutting processing technology, the pulse width is 30 mu s, the pulse stop is 100 mu s, the current is 3A, after the processing is finished, the recast layer of most areas in the wire cutting processing technology is less than 0.005mm, the recast layer of each area is about 0.012mm, as shown in fig. 3 and 4, and the finished size of 0.02mm thick is reserved for forming a turbine disk tenon groove by final wire cutting;
And thirdly, polishing the turbine disc mortises reserved with the finishing size of 0.02mm in thickness in the second step by abrasive particle flow, wherein the abrasive particles are made of silicon carbide, the shapes of the abrasive particles are cylinders, and the abrasive particle speed is 80m/s. And controlling the speed of abrasive particles to realize the precise machining of the turbine disc mortise structure.
Claims (4)
1. A micro-stress compound machining method for a turbine disc mortise of an aeroengine is characterized by comprising the following steps of: according to the machining method, firstly, linear cutting is carried out on a turbine disc blank (2) along a tooth crest datum line of a tongue groove, pulse width of linear cutting machining is 10 mu s-40 mu s, pulse stop is 60 mu s-200 mu s, current is 2A-4A, a recast layer left by linear cutting is smaller than 0.01mm, a tongue groove reserved with a finishing size is formed, the finishing size reserved by the tongue groove is 0.01 mm-0.02 mm, abrasive particle flow polishing is carried out on the tongue groove reserved with the finishing size, silicon carbide is adopted as abrasive particles for abrasive particle flow polishing, abrasive particle shape is a cylinder, abrasive particle speed is 50 m/s-100 m/s, and the tongue groove with preset size and surface roughness is obtained.
2. The micro-stress composite machining method for the turbine disc mortise of the aeroengine according to claim 1, characterized by comprising the following steps of: the wire cutting machining in the machining method is completed by adopting numerical control wire cutting equipment and molybdenum wires, the equipment comprises a rotary table (6), a mounting seat (1) for mounting a turbine disc blank (2) is connected to the rotary table (6), and the turbine disc blank (2) is fixed through a pressing block (3) and a screw (4).
3. The micro-stress composite machining method of the turbine disc mortise of the aeroengine according to claim 1 or 2, characterized by comprising the following steps: in the linear cutting processing in the processing method, the molybdenum wire (5) is vertically processed, and every time one mortice is processed, the C shaft is rotated by one degree, the angle is equal to 360 degrees/the total number of the mortises of the turbine disk, the next mortice is started to be processed, and after the finish, the size and the position of the mortises are detected by adopting three coordinates.
4. The micro-stress composite machining method for the turbine disc mortise of the aeroengine according to claim 1, characterized by comprising the following steps of: in the wire cutting processing in the processing method, rough processing size, rough trimming first time, semi-trimming second time and fine trimming third time are sequentially carried out.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111329624.4A CN114043169B (en) | 2021-11-10 | 2021-11-10 | Micro-stress composite machining method for turbine disc mortises of aero-engine |
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|---|---|---|---|
| CN202111329624.4A CN114043169B (en) | 2021-11-10 | 2021-11-10 | Micro-stress composite machining method for turbine disc mortises of aero-engine |
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| CN114043169A CN114043169A (en) | 2022-02-15 |
| CN114043169B true CN114043169B (en) | 2024-06-18 |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110125497A (en) * | 2018-02-09 | 2019-08-16 | 中国航发商用航空发动机有限责任公司 | A kind of processing method of high temperature alloy diskware tongue-and-groove |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111203603B (en) * | 2018-11-21 | 2021-04-20 | 中国航发商用航空发动机有限责任公司 | Interchange clamping device for turbine disc |
| CN109926894B (en) * | 2019-04-15 | 2020-11-06 | 南京航空航天大学 | Turbine disc mortise forming and grinding processing equipment and using method thereof |
| CN112091539A (en) * | 2020-08-28 | 2020-12-18 | 陕西斯瑞新材料股份有限公司 | Turbine disc tenon and tooth composite machining process |
| CN112658735B (en) * | 2020-12-31 | 2022-04-29 | 北京航空航天大学 | Clamp for linear cutting and forming grinding of turbine disc inclined tenon groove and mounting method |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110125497A (en) * | 2018-02-09 | 2019-08-16 | 中国航发商用航空发动机有限责任公司 | A kind of processing method of high temperature alloy diskware tongue-and-groove |
Non-Patent Citations (1)
| Title |
|---|
| 《涡轮盘榫槽线切割加工工艺研究》;蒲一民;《航天制造技术》;20160430(第2016年02期期);第37-40页 * |
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