CN114102050A - Cutting method for cantilever mounting edge of high-temperature alloy part of aero-engine - Google Patents
Cutting method for cantilever mounting edge of high-temperature alloy part of aero-engine Download PDFInfo
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- CN114102050A CN114102050A CN202111488771.6A CN202111488771A CN114102050A CN 114102050 A CN114102050 A CN 114102050A CN 202111488771 A CN202111488771 A CN 202111488771A CN 114102050 A CN114102050 A CN 114102050A
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- 238000005520 cutting process Methods 0.000 title claims abstract description 216
- 239000000956 alloy Substances 0.000 title claims abstract description 30
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000009434 installation Methods 0.000 claims abstract description 21
- 238000012545 processing Methods 0.000 claims abstract description 20
- 239000000463 material Substances 0.000 claims abstract description 9
- 238000003754 machining Methods 0.000 claims description 41
- 230000003247 decreasing effect Effects 0.000 claims description 4
- 238000013461 design Methods 0.000 claims description 3
- 229910000601 superalloy Inorganic materials 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 238000005299 abrasion Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000725 suspension Substances 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
- B23P13/00—Making metal objects by operations essentially involving machining but not covered by a single other subclass
- B23P13/02—Making metal objects by operations essentially involving machining but not covered by a single other subclass in which only the machining operations are important
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Abstract
The invention discloses a cutting method of a cantilever mounting edge of a high-temperature alloy part of an aero-engine, which comprises the steps of firstly selecting a cutting linear speed according to a guide linear speed of a cutting material, then cutting the cantilever mounting edge by adopting the cutting linear speed and a positive and negative alternate cutting mode, wherein the positive and negative alternate cutting mode can prevent the mounting edge from deforming and chamfering, in the cutting process, the cutting depth is reduced along with the increase of the cutting times, and the cutting linear speed is increased along with the increase of the cutting times, so that the cutting force is gradually reduced, and the cutting performance is improved; this scheme is through adopting positive and negative alternative cutting mode and cutting linear velocity bigger than finger line speed to cantilever installation limit cutting to in cutting process, along with the increase of cutting number of times, corresponding increase cutting linear velocity reduces the depth of cut, with improving cutting performance, prevents that cantilever installation limit from adding the processing and warping and the too fast wearing and tearing of cutter, has shortened the cycle of processing on cantilever installation limit, has reduced manufacturing cost.
Description
Technical Field
The invention relates to the technical field of machining of parts of aero-engines, in particular to a method for cutting a cantilever mounting edge of a high-temperature alloy part of an aero-engine.
Background
China has the rapid development of aero-engines, the performance requirements of the aero-engines are higher and higher, and the hardness and the strength of the raw materials of the aero-engines are also higher and higher, so that the high-temperature alloy is widely applied to casing parts of the aero-engines. Because the high-temperature alloy has high hardness and strength, the high-temperature alloy has poor machining performance and large cutting resistance, vibration is easily generated in the machining process, the numerical control cutter is quickly abraded, the abraded numerical control cutter can extrude a part to cause deformation, and then the phenomenon of edge chamfering occurs when the edge is machined and installed. The existing aircraft engine is formed by connecting large engine casings through cantilever mounting edges. The mounting edge has the following characteristics: 1. the mounting edge is very thin, and the mounting edge of part of the casing is only 1.2 mm; 2. the radial dimension of the mounting edge is large, and the mounting edge overhang length is 31.5mm and the difference between the mounting edge overhang length and the mounting edge overhang length is large. 3. The size precision of the mounting edge is high, and the flatness requirement is 0.1 mu m; 4. the high-temperature alloy material is difficult to process, and the blade is seriously worn. Based on the characteristics, the mounting edge of the suspension arm in the existing aero-engine generally has the following problems: 1. the mounting edge is easy to be seriously deformed and has out-of-tolerance planeness due to larger cutting force in the cutting process; 2. the cutter easily wears and sharp not, and the cutter of not sharp extrudees the installation limit easily man-hour, leads to installing the limit chamfered edge, and then makes installation limit axial and radial dimension unqualified and scrap to seriously influence aeroengine scientific research production's progress.
Disclosure of Invention
The invention provides a method for cutting a cantilever mounting edge of a high-temperature alloy part of an aero-engine, which aims to solve the technical problems that the cantilever mounting edge of the aero-engine in the prior art is easy to deform during processing and a cutter is worn too fast during processing to extrude the part, so that the part is scrapped.
According to one aspect of the invention, the cutting method for the cantilever mounting edge of the high-temperature alloy part of the aircraft engine is provided, the thickness of the cantilever mounting edge of the high-temperature alloy part is 0.5mm-1.5mm, the overhang length of the cantilever mounting edge of the high-temperature alloy part is 25mm-40mm, and the flatness requirement of the cantilever mounting edge of the high-temperature alloy part is not more than 0.1 μm, and the cutting method comprises the following steps; a. selecting a cutting linear speed according to the speed of the guide line of the cutting material, wherein the cutting linear speed is greater than the guide linear speed; b. and cutting the cantilever mounting edge by adopting a cutting linear velocity and a positive and negative alternate cutting mode to obtain the qualified cantilever mounting edge, wherein the cutting depth is reduced along with the increase of the cutting times, and the cutting linear velocity is increased along with the increase of the cutting times.
Further, in the step b, the cantilever mounting edge is cut in sections along the radial direction of the cantilever mounting edge.
Further, the linear cutting speed in the step a is 30-40% higher than the guide linear speed.
Further, the linear cutting speed in the step a is more than 40% of the guiding linear speed.
Further, step b specifically comprises the following steps: b1, firstly, roughly machining the cantilever installation edge by adopting a cutting linear velocity and a positive and negative alternate cutting mode; b2, continuously adopting the cutting linear velocity and the positive and negative alternate cutting mode to perform semi-finishing on the cantilever mounting edge; b3, finally, performing finish machining on the cantilever mounting edge by adopting a cutting linear velocity and a positive and negative alternate cutting mode to obtain a qualified cantilever mounting edge.
Further, the cutting depths of the rough machining, the semi-finishing machining and the finishing machining are all decreased in a descending mode from 0.2mm to 0.05mm, and the minimum cutting depth is 0.05 mm.
Further, step b1 specifically includes the following steps: firstly, machining a first knife on the front side and the back side of a cantilever mounting edge respectively by adopting a proper cutting depth fz1 and a cutting linear speed v1, wherein fz1 is 0.20mm, and v1 is 85 m/min; and then processing a second cutter on the front side and the back side of the cantilever mounting edge respectively by adopting a proper cutting depth fz2 and a cutting linear speed v2, wherein fz2 is 0.15mm, and v2 is 85 m/min.
Further, step b2 specifically includes the following steps: firstly, machining a first knife on the front face of a cantilever mounting edge by adopting a proper cutting depth fz3 and a cutting linear speed v3, wherein fz3 is 0.10mm, and v3 is 95 m/min; and then processing a first knife on the reverse surface of the cantilever mounting edge by adopting a proper cutting depth fz4, a cutting linear speed v4 and a cutting length x1, wherein fz4 is 0.10mm, v4 is 95m/min, and x1 is 15 mm.
Further, step b3 specifically includes the following steps: firstly, processing a first knife on the front surface of the cantilever mounting edge by adopting a proper cutting depth fz5 and a cutting linear speed v5, wherein fz5 is 0.05mm, and v5 is 100 m/min; and then processing a first knife on the reverse surface of the cantilever mounting edge by adopting a proper cutting depth fz6, a cutting linear speed v6 and a cutting length x2, wherein fz6 is 0.05mm, v6 is 100m/min, and x2 is 30 mm.
Further, step b3 is followed by the steps of: and B4, measuring the parameters of the cantilever mounting edge after rough machining, semi-finish machining and finish machining, and comparing the parameters with the axial dimension, the planeness, the mounting edge thickness and the mounting edge excircle diameter required by design to confirm whether the part is qualified.
The invention has the following beneficial effects:
the cutting method of the cantilever mounting edge of the high-temperature alloy part of the aero-engine comprises the steps of firstly selecting a cutting linear speed according to the speed of a guide line of a cutting material, wherein the cutting linear speed is greater than the guide linear speed so as to improve the cutting performance, then cutting the cantilever mounting edge by adopting the cutting linear speed and a positive and negative alternative cutting mode, wherein the positive and negative alternative cutting mode can prevent the mounting edge from deforming and chamfering, and ensure that the flatness and the axial dimension of the mounting edge are qualified; this scheme is through adopting positive and negative alternative cutting mode and cutting linear velocity bigger than finger line speed to cantilever installation limit cutting to in cutting process, along with the increase of cutting number of times, corresponding increase cutting linear velocity reduces the depth of cut, with improving cutting performance, prevents that cantilever installation limit from adding the processing and warping and the too fast wearing and tearing of cutter, has shortened the cycle of processing on cantilever installation limit, has reduced manufacturing cost.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic representation of the steps of a preferred embodiment of the present invention.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
FIG. 1 is a schematic representation of the steps of a preferred embodiment of the present invention.
As shown in fig. 1, the method for cutting the cantilever mounting edge of the high-temperature alloy part of the aircraft engine of the embodiment includes the following steps, wherein the thickness of the cantilever mounting edge of the high-temperature alloy part is 0.5mm-1.5mm, the overhang length of the cantilever mounting edge of the high-temperature alloy part is 25mm-40mm, and the flatness requirement of the cantilever mounting edge of the high-temperature alloy part is not more than 0.1 μm; a. selecting a cutting linear speed according to the speed of the guide line of the cutting material, wherein the cutting linear speed is greater than the guide linear speed; b. and cutting the cantilever mounting edge by adopting a cutting linear velocity and a positive and negative alternate cutting mode to obtain the qualified cantilever mounting edge, wherein the cutting depth is reduced along with the increase of the cutting times, and the cutting linear velocity is increased along with the increase of the cutting times. The cutting method comprises the steps of firstly selecting a cutting linear speed according to the speed of a guide line of a cutting material, wherein the cutting linear speed is greater than the guide linear speed so as to improve the cutting performance, then cutting the cantilever mounting edge by adopting the cutting linear speed and a positive and negative alternative cutting mode, wherein the positive and negative alternative cutting mode can prevent the mounting edge from deforming and chamfering, and ensure that the flatness and the axial dimension of the mounting edge are qualified; this scheme is through adopting positive and negative alternative cutting mode and cutting linear velocity bigger than finger line speed to cantilever installation limit cutting to in cutting process, along with the increase of cutting number of times, corresponding increase cutting linear velocity reduces the depth of cut, with improving cutting performance, prevents that cantilever installation limit from adding the processing and warping and the too fast wearing and tearing of cutter, has shortened the cycle of processing on cantilever installation limit, has reduced manufacturing cost. It should be understood that in one embodiment, the tool is selected to be CNMG120404-TX3F40M, when the part material is cast superalloy K4169, the guide line speed is 35m/min, the cutting line speed is 45-60m/min, the cutting depth is 0.1-0.3mm, and the feed rate is 0.08-0.15 mm/r; when the part material is a forged high-temperature alloy GH4169, the guide linear speed is 65m/min, the cutting linear speed is 85-100m/min, the cutting depth is 0.1-0.3mm, and the feed rate is 0.1-0.15 mm/r; when the material of the part is titanium alloy TC4, the guide line speed is 45m/min, the cutting line speed is 60-75m/min, the cutting depth is 0.1-0.3mm, and the feeding quantity is 0.1-0.2 mm/r.
In this embodiment, the step b further includes performing segmented cutting on the cantilever mounting edge along the radial direction of the cantilever mounting edge. Specifically, the front and back alternate cutting is carried out while the segmented cutting is carried out, so that the thickness of the uncut part in the cutting process of the cantilever mounting edge is improved, the rigidity requirement in the machining process is further guaranteed, and the machining deformation is reduced.
In the embodiment, the linear cutting speed in the step a is 30-40% higher than the linear guide speed. Specifically, when the cutting linear velocity is greater than 30% -40% of the guide linear velocity, the cutting force applied to the cantilever mounting edge is reduced, the cutting performance in the cutting process is effectively improved, and further the mutual damage between the cutter and the cantilever mounting edge is reduced.
In this embodiment, the linear cutting speed in step a is 40% higher than the linear guide speed. Specifically, when the cutting linear velocity is greater than 40% of the guide linear velocity, the cutting force applied to the cantilever mounting edge is reduced to the maximum extent, and further mutual damage between the cutter and the cantilever mounting edge is reduced.
In this embodiment, step b specifically includes the following steps: b1, firstly, roughly machining the cantilever installation edge by adopting a cutting linear velocity and a positive and negative alternate cutting mode; b2, continuously adopting the cutting linear velocity and the positive and negative alternate cutting mode to perform semi-finishing on the cantilever mounting edge; b3, finally, performing finish machining on the cantilever mounting edge by adopting a cutting linear velocity and a positive and negative alternate cutting mode to obtain a qualified cantilever mounting edge. Specifically, through carrying out rough machining, semi-finishing and finish machining to cantilever installation limit in proper order to improve the machining precision, adopt cutting linear velocity and positive and negative alternative cutting mode to process simultaneously, reduce the cutting force, prevent that cantilever installation limit chamfered edge from warping and cutter wearing and tearing too fast.
In the embodiment, the cutting depths of the rough machining, the semi-finishing machining and the finishing machining are all decreased in a decreasing manner by 0.2-0.05mm, and the minimum cutting depth is 0.05 mm. Specifically, by gradually reducing the cutting depth, the cutting force is reduced, and the damage between the tool and the part during machining is reduced.
In this embodiment, step b1 specifically includes the following steps: firstly, machining a first knife on the front side and the back side of a cantilever mounting edge respectively by adopting a proper cutting depth fz1 and a cutting linear speed v1, wherein fz1 is 0.20mm, and v1 is 85 m/min; and then processing a second cutter on the front side and the back side of the cantilever mounting edge respectively by adopting a proper cutting depth fz2 and a cutting linear speed v2, wherein fz2 is 0.15mm, and v2 is 85 m/min. Specifically, the cutting force during cutting is reduced by selecting proper cutting depth and cutting linear speed and adopting a positive and negative alternative cutting mode, the cutting performance is improved, and deformation and chamfering of the cantilever installation edge and over-fast abrasion of a cutter are avoided.
In this embodiment, step b2 specifically includes the following steps: firstly, machining a first knife on the front face of a cantilever mounting edge by adopting a proper cutting depth fz3 and a cutting linear speed v3, wherein fz3 is 0.10mm, and v3 is 95 m/min; and then processing a first knife on the reverse surface of the cantilever mounting edge by adopting a proper cutting depth fz4, a cutting linear speed v4 and a cutting length x1, wherein fz4 is 0.10mm, v4 is 95m/min, and x1 is 15 mm. Specifically, the cutting force during cutting is reduced by selecting proper cutting depth and cutting linear speed and adopting a positive and negative alternative cutting mode, the cutting performance is improved, and deformation and chamfering of the cantilever installation edge and over-fast abrasion of a cutter are avoided. It will be appreciated that during this step, the reverse side of the cantilever mounting edge is cut in sections to ensure rigidity during further machining of the cantilever mounting edge and to reduce machining distortion.
In this embodiment, step b3 specifically includes the following steps: firstly, processing a first knife on the front surface of the cantilever mounting edge by adopting a proper cutting depth fz5 and a cutting linear speed v5, wherein fz5 is 0.05mm, and v5 is 100 m/min; and then processing a first knife on the reverse surface of the cantilever mounting edge by adopting a proper cutting depth fz6, a cutting linear speed v6 and a cutting length x2, wherein fz6 is 0.05mm, v6 is 100m/min, and x2 is 30 mm. Specifically, the cutting force during cutting is reduced by selecting proper cutting depth and cutting linear speed and adopting a positive and negative alternative cutting mode, the cutting performance is improved, and deformation and chamfering of the cantilever installation edge and over-fast abrasion of a cutter are avoided. It should be appreciated that step b2 leaves a 15mm allowance to be cut for ensuring the rigidity requirements of the step 3 process and reducing the machining distortion.
In this embodiment, step b3 is followed by the steps of: and B4, measuring the parameters of the cantilever mounting edge after rough machining, semi-finish machining and finish machining, and comparing the parameters with the axial dimension, the planeness, the mounting edge thickness and the mounting edge excircle diameter required by design to confirm whether the part is qualified. Specifically, whether the size of the cut part meets the production requirement is determined according to the axial size of the cut part, and whether the machining precision of the cut part meets the production requirement is judged according to the actual cutting size.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A cutting method of cantilever mounting edge of aeroengine high temperature alloy part, the thickness of the cantilever mounting edge of the high temperature alloy part is 0.5mm-1.5mm, the overhang length of the cantilever mounting edge of the high temperature alloy part is 25mm-40mm, the planeness requirement of the cantilever mounting edge of the high temperature alloy part is not more than 0.1 μm, characterized by comprising the following steps;
a. selecting a cutting linear speed according to the speed of the guide line of the cutting material, wherein the cutting linear speed is greater than the guide linear speed;
b. and cutting the cantilever mounting edge by adopting a cutting linear velocity and a positive and negative alternate cutting mode to obtain the qualified cantilever mounting edge, wherein the cutting depth is reduced along with the increase of the cutting times, and the cutting linear velocity is increased along with the increase of the cutting times.
2. The method for cutting the cantilever mounting edge of the high-temperature alloy part for the aircraft engine as claimed in claim 1, wherein the step b is further performed by cutting the cantilever mounting edge in sections along the radial direction of the cantilever mounting edge.
3. The method for cutting the cantilever installation edge of the high-temperature alloy part of the aircraft engine as claimed in claim 1, wherein the cutting linear speed in the step a is 30-40% higher than the guide linear speed.
4. The method for cutting the cantilever installation edge of the high-temperature alloy part of the aircraft engine as claimed in claim 3, wherein the linear cutting speed in the step a is more than 40% of the guiding linear speed.
5. The method for cutting the cantilever mounting edge of the high-temperature alloy part of the aircraft engine as claimed in any one of claims 1 to 4, wherein the step b specifically comprises the following steps:
b1, firstly, roughly machining the cantilever installation edge by adopting a cutting linear velocity and a positive and negative alternate cutting mode;
b2, continuously adopting the cutting linear velocity and the positive and negative alternate cutting mode to perform semi-finishing on the cantilever mounting edge;
b3, finally, performing finish machining on the cantilever mounting edge by adopting a cutting linear velocity and a positive and negative alternate cutting mode to obtain a qualified cantilever mounting edge.
6. The method for cutting the cantilever mounting edge of the superalloy component for an aircraft engine as in claim 5, wherein the cutting depths of the rough machining, the semi-finishing and the finishing are all decreased in a range of 0.2-0.05mm, and the minimum cutting depth is 0.05 mm.
7. The method for cutting the cantilever mounting edge of the high-temperature alloy part for the aircraft engine as claimed in claim 5, wherein the step b1 specifically comprises the following steps:
firstly, machining a first knife on the front side and the back side of a cantilever mounting edge respectively by adopting a proper cutting depth fz1 and a cutting linear speed v1, wherein fz1 is 0.20mm, and v1 is 85 m/min;
and then processing a second cutter on the front side and the back side of the cantilever mounting edge respectively by adopting a proper cutting depth fz2 and a cutting linear speed v2, wherein fz2 is 0.15mm, and v2 is 85 m/min.
8. The method for cutting the cantilever mounting edge of the high-temperature alloy part for the aircraft engine as claimed in claim 5, wherein the step b2 specifically comprises the following steps:
firstly, machining a first knife on the front face of a cantilever mounting edge by adopting a proper cutting depth fz3 and a cutting linear speed v3, wherein fz3 is 0.10mm, and v3 is 95 m/min;
and then processing a first knife on the reverse surface of the cantilever mounting edge by adopting a proper cutting depth fz4, a cutting linear speed v4 and a cutting length x1, wherein fz4 is 0.10mm, v4 is 95m/min, and x1 is 15 mm.
9. The method for cutting the cantilever mounting edge of the high-temperature alloy part for the aircraft engine as claimed in claim 5, wherein the step b3 specifically comprises the following steps:
firstly, processing a first knife on the front surface of the cantilever mounting edge by adopting a proper cutting depth fz5 and a cutting linear speed v5, wherein fz5 is 0.05mm, and v5 is 100 m/min;
and then processing a first knife on the reverse surface of the cantilever mounting edge by adopting a proper cutting depth fz6, a cutting linear speed v6 and a cutting length x2, wherein fz6 is 0.05mm, v6 is 100m/min, and x2 is 30 mm.
10. The method for cutting the cantilever mounting edge of the superalloy component of the aircraft engine as claimed in claim 5, wherein the step b3 is followed by the further step of:
and B4, measuring the parameters of the cantilever mounting edge after rough machining, semi-finish machining and finish machining, and comparing the parameters with the axial dimension, the planeness, the mounting edge thickness and the mounting edge excircle diameter required by design to confirm whether the part is qualified.
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| CN202111488771.6A CN114102050A (en) | 2021-12-08 | 2021-12-08 | Cutting method for cantilever mounting edge of high-temperature alloy part of aero-engine |
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| CN202111488771.6A CN114102050A (en) | 2021-12-08 | 2021-12-08 | Cutting method for cantilever mounting edge of high-temperature alloy part of aero-engine |
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Citations (5)
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|---|---|---|---|---|
| JPS58196934A (en) * | 1982-05-08 | 1983-11-16 | Utsunomiya Daigaku | Precision oscillation cutting method for ceramics |
| CN2144544Y (en) * | 1992-12-11 | 1993-10-27 | 范亚烔 | Cutting force fastening self-protection adjustable cutting tool |
| JP2011148016A (en) * | 2010-01-19 | 2011-08-04 | Kobe Steel Ltd | Method for efficiently cutting titanium and titanium alloy |
| CN102581362A (en) * | 2012-03-22 | 2012-07-18 | 沈阳飞机工业（集团）有限公司 | Method for processing part with thin wall and changed-angle curved surface appearance |
| CN102717115A (en) * | 2012-06-14 | 2012-10-10 | 北京航空航天大学 | High-speed intermittent ultrasonic vibration cutting method for low-rigidity parts |
-
2021
- 2021-12-08 CN CN202111488771.6A patent/CN114102050A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58196934A (en) * | 1982-05-08 | 1983-11-16 | Utsunomiya Daigaku | Precision oscillation cutting method for ceramics |
| CN2144544Y (en) * | 1992-12-11 | 1993-10-27 | 范亚烔 | Cutting force fastening self-protection adjustable cutting tool |
| JP2011148016A (en) * | 2010-01-19 | 2011-08-04 | Kobe Steel Ltd | Method for efficiently cutting titanium and titanium alloy |
| CN102581362A (en) * | 2012-03-22 | 2012-07-18 | 沈阳飞机工业（集团）有限公司 | Method for processing part with thin wall and changed-angle curved surface appearance |
| CN102717115A (en) * | 2012-06-14 | 2012-10-10 | 北京航空航天大学 | High-speed intermittent ultrasonic vibration cutting method for low-rigidity parts |
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| Title |
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Application publication date: 20220301 |