CN114043169A - Micro-stress composite machining method for mortise of turbine disc of aircraft engine - Google Patents
Micro-stress composite machining method for mortise of turbine disc of aircraft engine Download PDFInfo
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- CN114043169A CN114043169A CN202111329624.4A CN202111329624A CN114043169A CN 114043169 A CN114043169 A CN 114043169A CN 202111329624 A CN202111329624 A CN 202111329624A CN 114043169 A CN114043169 A CN 114043169A
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- 238000003754 machining Methods 0.000 title claims abstract description 48
- 238000000034 method Methods 0.000 title claims abstract description 34
- 239000002131 composite material Substances 0.000 title claims abstract description 17
- 238000005520 cutting process Methods 0.000 claims abstract description 37
- 238000005498 polishing Methods 0.000 claims abstract description 7
- 230000003746 surface roughness Effects 0.000 claims abstract description 3
- 239000002245 particle Substances 0.000 claims description 21
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 8
- 238000003672 processing method Methods 0.000 claims description 8
- 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
- 238000003825 pressing Methods 0.000 claims description 3
- 229910052750 molybdenum Inorganic materials 0.000 claims description 2
- 239000011733 molybdenum Substances 0.000 claims description 2
- 238000009966 trimming Methods 0.000 claims description 2
- 239000000843 powder Substances 0.000 description 9
- 239000000463 material Substances 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 6
- 229910000601 superalloy Inorganic materials 0.000 description 6
- 229910045601 alloy Inorganic materials 0.000 description 5
- 239000000956 alloy Substances 0.000 description 5
- 230000000694 effects Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000005111 flow chemistry technique Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
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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
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- 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 composite machining method for a mortise of a turbine disc of an aero-engine, which comprises the steps of firstly carrying out linear cutting on a turbine disc blank (2) along a tooth crest datum line of the mortise to form the mortise with a preset finishing size, and then carrying out abrasive flow polishing on the mortise with the preset finishing size to obtain the mortise with the preset size and surface roughness. The machining precision of the turbine disc mortise combined machining process is high, a broaching process is omitted, no broaching tool is needed, the machining cost is greatly reduced, meanwhile, the linear cutting is stress-free machining, the problem that the final size of the tenon tooth is difficult to guarantee due to large stress generated during broaching is avoided, and the requirement on the machining size precision of the turbine disc mortise is met. Meanwhile, the abrasive flow is adopted to remove a recast layer and a heat affected zone left on the surface of the workpiece by linear cutting, so that the service life of the turbine disc is ensured.
Description
Technical Field
The invention discloses a micro-stress composite machining method for a mortise of a turbine disc of an aero-engine, and relates to the technical field of machining of turbine discs.
Background
The turbine disk is used as a core component of an engine, blades and a rotor of the turbine disk are connected with the tenon teeth in a matched mode through the tenon grooves in the high-temperature and high-pressure working process, and the tenon grooves and the tenon teeth are required to have extremely high precision and reliable mechanical performance in order to guarantee the working reliability of the turbine disk. Most of traditional turbine disc tongue-and-groove processing adopts the broaching method, but has that the broach design degree of difficulty is big, the maintenance is time-consuming, and broach wearing and tearing scheduling problem fast for the processing cost promotes greatly, and the broaching machine equipment that broaching technology used is imported basically, and the price is expensive, is difficult to independently ensure.
Disclosure of Invention
The invention provides a micro-stress composite machining method for a mortise of a turbine disc of an aero-engine, which is designed aiming at the prior art situation, and aims to machine the mortise of the turbine disc by wire cutting, avoid the use of a broach, solve the problem that the final size of a tenon tooth is difficult to ensure due to large stress generated during broaching, further remove a recasting layer and a heat affected zone left by the wire cutting by adopting an abrasive flow process, finally ensure the machining size precision requirement and the service life of the mortise of the turbine disc, improve the machining precision and reduce the machining cost.
In order to achieve the purpose, the technical scheme of the invention comprises the following steps:
the micro-stress composite machining method for the turbine disc mortise of the aero-engine is characterized by comprising the following steps of: the machining method comprises the steps of firstly carrying out linear cutting on a turbine disc blank (2) along the tooth top datum line of a mortise to form the mortise with the reserved finish dimension, and then carrying out abrasive flow polishing on the mortise with the reserved finish dimension to obtain the mortise with the preset dimension and surface roughness.
In practice, wire cutting leaves a recast layer of less than 0.01 mm.
In the implementation, the maximum reserved finishing size of the mortise is 0.01-0.02 mm.
In the implementation, the wire cutting processing in the processing method is completed by adopting numerical control wire cutting equipment and a molybdenum wire, 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 wheel disc blank 2 is fixed by a pressing block 3 and a screw 4.
Further, in the linear cutting machining in the machining method, the molybdenum wire 5 is vertically machined, when one mortise is machined, the C shaft is rotated by one degree, the angle is equal to 360 degrees/the total number of the mortises of the turbine disc, the next mortise is machined, and after the machining is finished, the size and the position degree of the mortise are detected by adopting three coordinates.
In the wire-electrode cutting process in this processing method, the rough size, the rough finishing first time, the semi-finishing second time, and the finishing third time are performed in this order.
In the wire cutting process in the processing method, the pulse width of the wire cutting process is 10 to 40 mus, the pulse stop is 60 to 200 mus, 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 combined machining process of 'linear cutting and abrasive particle flow', has the obvious advantages of high machining precision and low cost, can avoid the defects of mortise machining deformation and material hardening by applying the technology to the turbine disc mortise machining, ensures the machining precision requirement of the turbine disc mortise, simultaneously adopts linear cutting to replace broaching machining, does not need a broaching machine and a broach, and greatly reduces the cost. The process is used for processing and exploring the turbine disc mortise, and has great significance for realizing complete autonomous and controllable processing of the turbine disc. The characteristics and advantageous effects are further described as follows:
the turbine disk is an important core hot end part of an aircraft engine, the metallurgical quality and performance level of the turbine disk are decisive for improving the reliability, the safe service life and the performance of the engine, meanwhile, the turbine disk mortise is a key connection part for connecting turbine working blades, and the material organization and the surface quality of the mortise are very important for the safe service of the engine. The powder high-temperature alloy is the preferred material of the turbine disc of the high-performance aeroengine at present due to the good comprehensive performance of the powder high-temperature alloy. The low-stress composite process of linear cutting and abrasive particle flow is adopted to replace the traditional broaching machine broaching method to machine the turbine disc mortise, the problems that the broaching machine broaching tool is high in design difficulty, time-consuming to maintain, rapid in abrasion and the like can be solved, meanwhile, the machining cost of the turbine disc mortise can be greatly reduced, and broaching machine equipment used in the broaching process is basically imported, expensive and difficult to independently guarantee. However, the powder superalloy for the aircraft engine turbine disc is difficult to deform, the surface integrity and the structure stability of the powder superalloy need to be guaranteed in the processing process, the surface of the powder superalloy material removed by the abrasive particle flow process is limited and is difficult to exceed 0.02mm, so that the influence of linear cutting on the surface structure of the powder superalloy material needs to be reduced to the maximum extent, a recast layer generated by the linear cutting is guaranteed not to exceed 0.015mm, and the recast layer on each part of the surface of the material after the linear cutting is kept consistent. Therefore, the determination of the processing technology of the powder superalloy material linear cutting and the processing parameters of the abrasive particle flow processing is particularly important for ensuring the tissue and surface integrity of the processed material, and finally the turbine disc mortise after processing meets the use requirements of the engine and ensures the safe service of the aeroengine.
Through repeated process exploration, the parameters of the linear cutting machining process in the powder high-temperature alloy turbine disc mortise combined machining process are 10-40 mu s of pulse width, 60-200 mu s of pulse stop and 2-4A of current, silicon carbide is used 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 mortise of the processed powder superalloy turbine disc is completely removed, and the low stress and the integrity of the surface of the mortise are ensured.
The technical scheme of the invention overcomes the problems that an expensive imported broaching machine and a large number of broaches are needed for machining the turbine disc mortise, deformation and size deviation are easily caused in the broaching process, the machining cost of the turbine disc is greatly reduced, the machining quality of the turbine disc mortise is ensured, the turbine disc mortise is completely and independently controllable, and the economic and national defense effects are obvious.
Drawings
FIG. 1 is a schematic view of the assembly of a turbine disk and a tooling of the present invention.
FIG. 2 is a schematic view of the machining of a turbine disk according to the present invention.
FIG. 3 is a view showing the most area recast layer after the wire-cutting process of the FGH96 alloy is optimized.
FIG. 4 is a view of the optimized individual zone recast layer of the FGH96 alloy wire-cut process.
Detailed Description
The invention is described in further detail below with reference to the figures and specific examples.
In this embodiment, the steps of performing micro-stress composite processing on the turbine disc mortise by using the technical scheme of the present invention are as follows:
firstly, wire cutting processing in the processing method is completed by adopting numerical control wire cutting equipment and molybdenum wires, the clamping mode of the turbine disc 2 is determined according to the structural form and the size of the turbine disc 2 and is shown in figures 1 and 2, an installation seat 1 for installing a turbine disc blank 2 is connected to a turntable 6, the wheel disc blank 2 is fixed by a pressing block 3 and a screw 4, and the angle phi in the figure 2 is ensured to be complementary with the mortise and radial included angle of the turbine disc;
in the linear cutting machining in the machining method, the molybdenum wire 5 is vertically machined, when one mortise is machined, the C shaft is rotated by one degree, the angle is equal to 360 degrees/the total number of the mortises of the turbine disc, the next mortise is machined, and after the machining is finished, the size and the position degree of the mortise are detected by adopting three coordinates;
secondly, performing line cutting according to the graph shown in FIG. 2, vertically processing the molybdenum wire 5, rotating the shaft C by 8.78 degrees after each mortise is processed, wherein the angle is equal to 360 degrees/the total number of the mortises of the turbine disc, namely 360 degrees/41, then starting to process the next mortise, and after the processing is finished, detecting the size and the position degree of the mortises by adopting three coordinates;
in the linear cutting processing technology, the pulse width is 30 mus, the pulse stop is 100 mus, the current is 3A, after the processing is finished, most of the recast layer of the area under the linear cutting technology is less than 0.005mm, the recast layer of the individual area is about 0.012mm, as shown in figures 3 and 4, the turbine disc mortise formed by the final linear cutting technology is reserved with the fine trimming size of 0.02 mm;
and step three, polishing the turbine disc mortise reserved with the finishing size of 0.02mm in thickness in the step two by abrasive particle flow, wherein the abrasive particles are made of silicon carbide, the abrasive particles are cylindrical, and the abrasive particle speed is 80 m/s. And the abrasive particle speed is controlled, and the precise machining of the turbine disc mortise structure is realized.
Claims (8)
1. A micro-stress composite machining method for a mortise of a turbine disc of an aero-engine is characterized by comprising the following steps: the machining method comprises the steps of firstly carrying out linear cutting on a turbine disc blank (2) along the tooth top datum line of a mortise to form the mortise with the reserved finish dimension, and then carrying out abrasive flow polishing on the mortise with the reserved finish dimension to obtain the mortise with the preset dimension and surface roughness.
2. The micro-stress composite machining method for the mortise of the turbine disc of the aero-engine according to claim 1, characterized in that: wire cutting leaves a recast layer of less than 0.01 mm.
3. The micro-stress composite machining method for the mortise of the turbine disc of the aero-engine according to claim 1, characterized in that: the maximum reserved finishing size of the mortise is 0.01-0.02 mm.
4. The micro-stress composite machining method for the mortise of the turbine disc of the aero-engine according to claim 1, characterized in that: the 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 turbine disc blank (2) is fixed by a pressing block (3) and a screw (4).
5. The micro-stress composite machining method for the mortise of the turbine disk of the aero-engine according to claim 1 or 4, wherein: in the linear cutting machining in the machining method, the molybdenum wire (5) is vertically machined, when one mortise is machined, the C shaft is rotated by one degree, the angle is equal to 360 degrees/the total number of the mortises of the turbine disc, the next mortise is machined, and after the machining is finished, the size and the position degree of the mortise are detected by adopting three coordinates.
6. The micro-stress composite machining method for the mortise of the turbine disc of the aero-engine according to claim 1, characterized in that: in the wire cutting processing in the processing method, the rough processing size, the rough trimming for the first time, the semi-finishing for the second time and the finishing for the third time are sequentially carried out.
7. The micro-stress composite machining method for the mortise of the turbine disc of the aero-engine according to claim 1, characterized in that: in the wire cutting process in the processing method, the pulse width of the wire cutting process is 10-40 mus, the pulse stop is 60-200 mus, and the current is 2-4A.
8. The micro-stress composite machining method for the mortise of the turbine disc of the aero-engine according to claim 1, characterized in that: according to the abrasive particle flow polishing method, silicon carbide is used as abrasive particles, the abrasive particles are cylindrical, and the abrasive particle speed is 50-100 m/s.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| 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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| CN114043169A true CN114043169A (en) | 2022-02-15 |
| CN114043169B CN114043169B (en) | 2024-06-18 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109926894A (en) * | 2019-04-15 | 2019-06-25 | 南京航空航天大学 | Turbine disc mortise form grinding process equipment and its application method |
| 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 |
| CN111203603A (en) * | 2018-11-21 | 2020-05-29 | 中国航发商用航空发动机有限责任公司 | Interchange clamping device for turbine disc |
| 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 |
| CN112658735A (en) * | 2020-12-31 | 2021-04-16 | 北京航空航天大学 | Clamp for linear cutting and forming grinding of turbine disc inclined tenon groove and mounting method |
-
2021
- 2021-11-10 CN CN202111329624.4A patent/CN114043169B/en active Active
Patent Citations (5)
| 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 |
| CN111203603A (en) * | 2018-11-21 | 2020-05-29 | 中国航发商用航空发动机有限责任公司 | Interchange clamping device for turbine disc |
| CN109926894A (en) * | 2019-04-15 | 2019-06-25 | 南京航空航天大学 | Turbine disc mortise form grinding process equipment and its application method |
| 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 |
| CN112658735A (en) * | 2020-12-31 | 2021-04-16 | 北京航空航天大学 | Clamp for linear cutting and forming grinding of turbine disc inclined tenon groove and mounting method |
Non-Patent Citations (1)
| Title |
|---|
| 蒲一民: "《涡轮盘榫槽线切割加工工艺研究》", 《航天制造技术》, no. 2016, 30 April 2016 (2016-04-30), pages 37 - 40 * |
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| CN114043169B (en) | 2024-06-18 |
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