CN115673443A - Machining method for square conical air film hole of turbine blade - Google Patents
Machining method for square conical air film hole of turbine blade Download PDFInfo
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- CN115673443A CN115673443A CN202211718579.6A CN202211718579A CN115673443A CN 115673443 A CN115673443 A CN 115673443A CN 202211718579 A CN202211718579 A CN 202211718579A CN 115673443 A CN115673443 A CN 115673443A
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- 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
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract
The invention relates to the technical field of electric discharge machining of turbine blades, and particularly discloses a method for machining a square conical air film hole of a turbine blade, wherein a correcting part is also arranged on a machining platform, and a correcting cavity is arranged on the correcting part, and the method comprises the following steps of: s1, operating a machining electrode to complete tool setting on a turbine blade and a correcting part; s2, operating the machining electrode to penetrate into the first length of the turbine blade, and performing electric discharge machining on the square conical air film hole in the turbine blade; s3, after square conical air film holes in a fixed number of turbine blades are machined, moving machining electrodes into the correction cavity; s4, discharging the machining electrode in the correction cavity and feeding the machining electrode with a second length; and S5, repeating the steps S2-S4 for a plurality of times, wherein in the repeating process, the next first length in the step S2 is the sum of the last first length and the last second length. The electrode is repaired in the machining process, the electrode replacement frequency is reduced, the machining precision is improved, and the workload of workers is reduced.
Description
Technical Field
The invention relates to the technical field of electric discharge machining of turbine blades, in particular to a machining method of a square conical air film hole of a turbine blade.
Background
In the production and manufacture of turbine blades, in order to meet the use environment and design premise of various blades, the shapes of the film holes are different, and the square conical film holes are one of the film holes. In production, the electric spark machining process is generally used for machining a plurality of film holes on a turbine blade, and hundreds of film holes can be formed on one turbine blade.
In the existing production, after the same electrode is used for machining a fixed number of air film holes, the electrode can be lost, the follow-up machining precision cannot be met, and the air film holes can be machined again only after the electrode is replaced and the tool is adjusted. According to the machining method, when the air film hole on the same turbine blade is machined, the electrode and the turbine blade need to be subjected to tool setting for many times, so that the machining precision is reduced; meanwhile, the electrodes need to be replaced for many times manually, so that the labor capacity of workers is increased.
Disclosure of Invention
The invention aims to provide a method for machining a square conical air film hole of a turbine blade, which is used for repairing an electrode in the machining process, reducing the replacement frequency of the electrode, improving the machining precision and reducing the workload of workers.
The embodiment of the invention is realized by the following technical scheme:
a method for machining a square conical film hole of a turbine blade, wherein the turbine blade is fixed on a machining platform of an electric discharge machine, a machining electrode is arranged on a movable main shaft, a correcting part is also arranged on the machining platform, and a correcting cavity is arranged on the correcting part, comprises the following steps: s1, operating a machining electrode to complete tool setting on a turbine blade and a correcting part; s2, operating the machining electrode to penetrate into the first length of the turbine blade, and performing electric discharge machining on the square conical air film hole in the turbine blade; s3, after square conical air film holes in a fixed number of turbine blades are machined, moving machining electrodes into the correction cavity; s4, discharging the machining electrode in the correction cavity, and feeding a second length; and S5, repeating the steps S2-S4 for a plurality of times, wherein in the repeating process, the next first length in the step S2 is the sum of the last first length and the last second length.
Further, the second length in S4 is greater than the sum of the theoretical loss lengths of the square tapered film holes of the machining electrode discharge machining a fixed number of turbine blades.
Further, the fixed number is 5.
Further, the turbine blade is made of a high temperature alloy.
Further, the machining electrode is made of red copper.
Further, the modified cavity is manufactured according to the theoretical size of the square conical film hole on the turbine blade.
Furthermore, the correction component at least comprises a first splicing piece and a second splicing piece, and the plurality of correction cavities are formed by splicing and combining the first splicing piece and the second splicing piece.
Further, the correction cavity is made of silver-tungsten alloy materials through milling.
The technical scheme of the embodiment of the invention at least has the following advantages and beneficial effects:
according to the invention, after the machining electrode machines a certain number of square conical gas film holes, the machining electrode is moved into the correction cavity, and compared with the electric spark machining of the square conical gas film holes, the machining electrode is subjected to discharge consumption and fed by a second length into the correction cavity. And correcting the worn machining electrode by correcting the inner surface of the cavity, restoring the worn machining electrode to the theoretical size again, and then machining the square conical air film hole of the next round. After clamping is completed, a large number of square conical air film holes can be machined by one-time tool setting, so that machining benchmarks of the process are unified; meanwhile, the times of manually clamping and processing the electrode are reduced, and the workload is reduced.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is an overall schematic view provided by the present invention;
FIG. 2 is a schematic diagram of a square conical gas film hole machined by the machining electrode according to the present invention;
FIG. 3 is a top view of a correction member provided by the present invention;
FIG. 4 is a schematic view of a machining electrode modification provided by the present invention;
icon: 1-turbine blade, 11-square conical air film hole, 2-processing platform, 3-processing electrode, 4-correcting part, 41-first splicing piece, 42-second splicing piece and 43-correcting cavity.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 and 3, the invention provides a method for machining a square-cone-shaped film hole of a turbine blade, which comprises the steps of fixing the turbine blade 1 on a machining platform 2 of an electric discharge machine, installing a machining electrode 3 on a movable main shaft, installing a correcting part 4 on the machining platform 2, arranging a correcting cavity 43 on the correcting part 4, wherein the correcting part 4 at least comprises a first splicing piece 41 and a second splicing piece 42, and a plurality of correcting cavities 43 are formed by splicing and combining the first splicing piece 41 and the second splicing piece 42.
Further, the modification cavity 43 is made of a silver-tungsten alloy material by milling (copper-tungsten alloy, etc. can be used, which has a higher melting point and better conductivity than the machining electrode 3), the turbine blade 1 is made of a high temperature alloy, and in this embodiment, the high temperature alloy is a nickel-based high temperature alloy brand: k417 and K438, the machining electrode 3 is made of red copper, and the correction cavity 43 is made in accordance with the theoretical size of the square tapered film hole 11 in the turbine blade 1.
Referring to fig. 2 and 4, the specific processing includes the following steps: s1, operating a machining electrode 3 to finish tool setting on a turbine blade 1 and a correcting part 4; s2, operating the machining electrode 3 to penetrate into the turbine blade 1 by a first length, and performing electric discharge machining on the square conical film hole 11 on the turbine blade 1; s3, after the square conical air film holes 11 in the fixed number of the turbine blades 1 are machined, the machining electrodes 3 are moved into the correction cavity 43; s4, discharging the machining electrode 3 in the correction cavity 43 and feeding the machining electrode with a second length; and S5, repeating the steps S2-S4 for a plurality of times, wherein in the repeating process, the next first length in the step S2 is the sum of the last first length and the last second length.
In the machining, the fixed number is 5, the machining electrode 3 is moved into the correction cavity 43 after the machining of 5 square-cone-shaped gas film holes 11 is completed, the correction part 4 is used for severely consuming the machining electrode 3 at the moment, the machining electrode 3 is discharged in the correction cavity 43 for correction, and when one correction cavity 43 is used for a certain number of times, the other correction cavity 43 is replaced and used. The machining electrode 3 is thereby simultaneously fed along the correction cavity 43 by a second length, which in S4 is greater than the sum of the theoretical lost lengths of the square-tapered film holes 11 in the fixed number of turbine blades 1 of the electric discharge machining by the machining electrode 3. After the machining electrode 3 is used for a certain time, correcting the machining electrode 3; after the correction cavity 43 is used for a certain time, the correction cavity 43 for performing the correction work is replaced, thereby ensuring the dimensional accuracy of the machining electrode 3 each time the square tapered gas film hole 11 is machined.
In the present invention, after the machining electrode 3 machines a certain number of square tapered gas film holes 11, the machining electrode 3 is moved into the correction cavity 43, and compared with the electric discharge machining of the square tapered gas film holes 11, the polarities of the machining electrode 3 and the work table are exchanged, and the machining electrode 3 is discharged and consumed, and at the same time, the machining electrode 3 is fed into the correction cavity 43 by a second length. The worn machining electrode 3 is subjected to the correction machining by correcting the inner surface of the cavity 43, the worn machining electrode 3 is restored to the theoretical size again, and the square conical gas film hole 11 of the next round is machined, so that the cycle is repeated. Meanwhile, in the repeated process of S5, the next first length in S2 is the sum of the previous first length and the previous second length, the depth of the square conical film hole 11 during machining is compensated, the depth of each electric spark machining penetrating into the turbine blade 1 is guaranteed to be consistent, and the machining precision is guaranteed.
Thus, when a turbine blade 1 is machined, the machining electrode 3 is corrected for fixed times, the machining electrode 3 after each correction is restored to the theoretical size, and the precision of the square conical air film hole 11 is guaranteed; after the initial clamping is completed, a large number of square conical air film holes 11 can be machined subsequently by carrying out tool setting once, so that the machining standard of the procedure is unified, and the precision between the relative positions of each square conical air film hole 11 is ensured; meanwhile, the times of manual replacement and clamping of the machining electrode 3 are reduced, and the workload is reduced.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to 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 (8)
1. A method for machining a square conical film hole of a turbine blade, wherein the turbine blade (1) is fixed on a machining platform (2) of an electric discharge machine, a machining electrode (3) is installed on a moving main shaft, a correcting part (4) is further installed on the machining platform (2), and a correcting cavity (43) is arranged on the correcting part (4), the method comprises the following steps:
s1, operating the machining electrode (3) to finish tool setting on the turbine blade (1) and the correcting part (4);
s2, operating the machining electrode (3) to penetrate into the turbine blade (1) by a first length, and performing electric discharge machining on a square conical film hole (11) in the turbine blade (1);
s3, after the square conical air film holes (11) in a fixed number of the turbine blades (1) are machined, the machining electrode (3) is moved into the correction cavity (43);
s4, discharging the machining electrode (3) in the correction cavity (43) and feeding the machining electrode to a second length;
and S5, repeating S2-S4 for a plurality of times, wherein in the repeating process, the first length in the S2 at the next time is the sum of the first length and the second length at the last time.
2. The method for machining a turbine blade square cone shaped film hole according to claim 1, characterized in that the second length in the S4 is larger than a sum of theoretical loss lengths of the square cone shaped film holes (11) on a fixed number of the turbine blades (1) by the machining electrode (3) through electric discharge machining.
3. The method for machining the square conical film hole of the turbine blade as claimed in claim 2, wherein the fixed number is 5.
4. The method for machining the square conical film hole of the turbine blade as claimed in claim 1, wherein the turbine blade (1) is made of a high temperature alloy.
5. The method for machining the square conical film hole of the turbine blade as claimed in claim 1, wherein the machining electrode (3) is made of red copper.
6. The method for machining the square conical film hole of the turbine blade as claimed in claim 1, wherein the correction cavity (43) is manufactured according to the theoretical size of the square conical film hole (11) on the turbine blade (1).
7. The method for machining the turbine blade square-cone-shaped film hole according to claim 1, wherein the correction part (4) at least comprises a first splicing piece (41) and a second splicing piece (42), and a plurality of correction cavities (43) are formed by splicing and combining the first splicing piece (41) and the second splicing piece (42).
8. The machining method of the square conical film hole of the turbine blade is characterized in that the correction cavity (43) is made of silver-tungsten alloy materials through milling.
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| CN202211718579.6A CN115673443B (en) | 2022-12-30 | 2022-12-30 | Machining method of turbine blade square conical air film hole |
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| CN202211718579.6A CN115673443B (en) | 2022-12-30 | 2022-12-30 | Machining method of turbine blade square conical air film hole |
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| CN115673443A true CN115673443A (en) | 2023-02-03 |
| CN115673443B CN115673443B (en) | 2023-04-21 |
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| CN1695862A (en) * | 2004-12-16 | 2005-11-16 | 江汉大学 | Method for carrying out trepanning through electric spark based on wire frame type electrode |
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| CN206550457U (en) * | 2016-12-27 | 2017-10-13 | 成都鑫胜太数控设备有限公司 | A kind of aeroturbine blade air film hole processing device of removable remelted layer |
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| CN110695475A (en) * | 2019-10-15 | 2020-01-17 | 东莞台一盈拓科技股份有限公司 | Method for protecting side wall of workpiece of fine hole discharge punching machine |
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| CN114043024A (en) * | 2021-11-30 | 2022-02-15 | 大连工业大学 | Digital twin electric spark machining based cavity morphology online monitoring system and online monitoring method |
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2022
- 2022-12-30 CN CN202211718579.6A patent/CN115673443B/en active Active
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| CN110695475A (en) * | 2019-10-15 | 2020-01-17 | 东莞台一盈拓科技股份有限公司 | Method for protecting side wall of workpiece of fine hole discharge punching machine |
| CN111822801A (en) * | 2020-07-31 | 2020-10-27 | 成都和鸿科技有限公司 | Method for milling turbine blade expansion hole by electric spark |
| CN114799383A (en) * | 2021-01-19 | 2022-07-29 | 中国航发商用航空发动机有限责任公司 | Method and device for trimming casting edge plate of single crystal turbine blade and single crystal turbine blade |
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Non-Patent Citations (1)
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