CN113977020A - Turbine disc mortise machining method - Google Patents
Turbine disc mortise machining method Download PDFInfo
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- CN113977020A CN113977020A CN202111387240.8A CN202111387240A CN113977020A CN 113977020 A CN113977020 A CN 113977020A CN 202111387240 A CN202111387240 A CN 202111387240A CN 113977020 A CN113977020 A CN 113977020A
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- 238000003754 machining Methods 0.000 title claims abstract description 30
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000005520 cutting process Methods 0.000 claims abstract description 104
- 230000006835 compression Effects 0.000 claims abstract description 6
- 238000007906 compression Methods 0.000 claims abstract description 6
- 229910001369 Brass Inorganic materials 0.000 claims description 3
- 239000010951 brass Substances 0.000 claims description 3
- 239000011162 core material Substances 0.000 claims description 3
- 238000007730 finishing process Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000009966 trimming Methods 0.000 description 3
- 238000009826 distribution Methods 0.000 description 2
- 241001391944 Commicarpus scandens Species 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H7/00—Processes or apparatus applicable to both electrical discharge machining and electrochemical machining
- B23H7/02—Wire-cutting
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
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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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- Engineering & Computer Science (AREA)
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- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
Abstract
A turbine disc mortise machining method comprises the following steps of S1: clamping a turbine disc workpiece by using an inner hole of the turbine disc in an axial compression mode; step S2: processing a cutting line at each mortise position by adopting linear cutting for releasing stress; step S3: carrying out linear cutting on the outline of the rough-cut mortise and leaving allowance; step S4: adopting multiple linear cutting to finish the contour of the mortise to reach the size, wherein the thickness of the remelted layer after finish cutting is less than or equal to 0.005 mm; step S5: and (4) performing finish machining on the mortise by adopting a broach to remove the remelted layer. According to the invention, the inner hole of the turbine disc is used for clamping the workpiece in an axial compression mode, so that the generation of clamping stress is reduced, and the influence of deformation on the processing precision of the mortise is eliminated by adopting axial clamping. By cutting the cutting lines on each mortise, most of stress is released and eliminated for the workpiece, stress generation in the subsequent linear cutting process is reduced, and workpiece deformation is avoided. And after the wire-electrode cutting rough cutting, arranging a plurality of times of wire-electrode cutting fine cutting to reduce the thickness of the remelted layer, and finally removing the remelted layer by broaching.
Description
Technical Field
The invention relates to the technical field of machining and manufacturing of turbine disks of aero-engines, in particular to a method for machining a mortise of a turbine disk.
Background
In the split turbine rotor of the engine turbine disc, the disc and the blades are connected with the tenon through the mortises in a matched mode. The material of the turbine disk must have high yield strength, tensile strength, good thermal stability and the like to meet the conditions of high-temperature, high-pressure and high-speed operation. Superalloys are the best materials for engines meeting high thrust-weight ratios. The dimensional tolerance and the geometric tolerance of the mortises on the disc are high. With the continuous improvement of the material performance of the turbine disc, the traditional machining process is difficult to meet the machining requirements. At present, the mortises of turbine discs are mainly finished by machining molded surfaces by using a broaching method through a forming cutter, on one hand, the structural characteristics and the shapes of parts are complex, the deformation is easily generated during thin-wall machining, great difficulty is brought to cutting, and the requirements on the dimensional tolerance and the geometric tolerance of the mortises are high and often out of tolerance. On the other hand, the problems of complex shape, small rigidity, easy loss, high design difficulty, high cutter cost and the like of the broach are solved. All can produce residual stress in the course of working, residual stress's existence can have very big influence to the part, because unstable residual stress's existence, in case receive the effect of external force, the part will produce local plastic deformation under the effect of external force and residual stress, redistribute the stress in the cross-section, get rid of the external force effect after, the part will receive the effect of inside residual stress and appear warping, can seriously influence processingquality.
The wire-electrode cutting process technology, as a special processing technology, cannot be replaced by a mechanical processing technology in many cases. The mortise is cut and processed by adopting a slow-moving wire, the axial force is clamped, the mortise is not influenced by the cutting force of a cutter like a machining method, the stress deformation generated by parts is small, and the good processing precision and the good surface quality can be ensured. The slow-moving wire can process conductive materials with any hardness, and has wide application range. However, when the number of the mortises is dozens or more, hundreds of mortises are formed in the circumference of the turbine disc, the removal of materials can cause the release and redistribution of internal stress of parts, the deformation of the parts is caused, the influence on machining is caused, and in addition, if the setting of linear cutting parameters is not reasonable, a remelted layer is generated, and the precision of the mortises is influenced.
Disclosure of Invention
The invention mainly aims to provide a turbine disc mortise machining method, and aims to solve the technical problems.
In order to achieve the purpose, the invention provides a turbine disc mortise machining method, which comprises the following steps:
step S1: clamping a workpiece: clamping a turbine disc workpiece by using an inner hole of the turbine disc in an axial compression mode;
step S2: processing one or more cutting lines at each mortise position by adopting linear cutting for releasing stress;
step S3: carrying out linear cutting on the outline of the rough-cut mortise and leaving allowance;
step S4: adopting multiple linear cutting to finish the contour of the mortise to reach the size, wherein the thickness of the remelted layer after finish cutting is less than or equal to 0.005 mm;
step S5: and (4) performing finish machining on the mortise by adopting a broach to remove the remelted layer.
Preferably, when the contour of the rough-cutting mortise is subjected to wire cutting, the single edge is left with a margin of 0.5 mm.
Preferably, in step S2, the number of the cutting lines on each mortise is 1, the cutting lines are located at the center of each mortise, and the distance from the bottom end of each cutting line to the bottom of each mortise is 0.5 mm.
Preferably, in step S4, in the wire-electrode cutting finishing process, a coated wire electrode is used, the core material of the wire electrode is Brass CuZn37, the diameter of the wire electrode is 0.25mm, the tensile strength of the wire electrode is 900N/mm2, and the elongation of the wire electrode is less than or equal to 2%.
Preferably, in step S4, a three-time wire cutting is adopted to finish-cut the contour of the mortise, and a margin of 0.2-0.3 mm is left on the first finish-cut single side; performing secondary fine cutting on the single side to leave a margin of 0.01-0.1 mm; and performing fine cutting to size for the third time.
Preferably, in the servo control parameters of step S4, the cutting speed of the first fine cut is set to 10.5mm2Min; the cutting speed of the second fine cutting is set to be 11.5mm2Min; the cutting speed of the third fine cutting is set to be 22mm2/min。
Preferably, in the servo control parameters of step S4, the compensation amount of the single blade for the first fine cut is set to 155 μm; the single-blade compensation amount of the second fine cutting is set to be 132 mu m; the single-blade compensation amount for the third fine cut was set to 131 μm.
Preferably, in the servo control parameter of step S4, the offset amount of the first fine cut is set to 219 μm; the offset of the second fine cutting is set to be 143 mu m; the offset of the third fine cut was set to 131 μm.
Preferably, in the servo control parameters of step S4: the ignition voltage of the first fine cutting is set to be 80V, the current slope is set to be 226V, and the peak current is set to be 5A; setting the ignition voltage of the third fine cutting to be 120V, setting the current slope to be 300V and setting the peak current to be 4A; the ignition voltage for the third fine cut was set to 120V, the current slope was set to 103V, and the peak current was set to 2A.
Preferably, in the servo control parameters of step S4: the roughness of the first time is set to be Ra2.8; the roughness of the second fine cut was set to ra1.8 and the roughness of the third fine cut was set to ra 0.55.
Due to the adoption of the technical scheme, the invention has the following beneficial effects:
according to the invention, the inner hole of the turbine disc is used for clamping the workpiece in an axial compression mode, so that the generation of clamping stress is reduced, and the influence of deformation on the processing precision of the mortise is eliminated by adopting axial clamping. By cutting the cutting lines on each mortise, most of stress is released and eliminated for the workpiece, stress generation in the subsequent linear cutting process is reduced, and workpiece deformation is avoided. After the wire cutting rough cutting, a plurality of times of wire cutting fine cutting are arranged, so that the stress generated by cutting force and clamping force and the residual stress of the part can be eliminated, the deformation is generated before the final broaching fine cutting, and the size precision and the form and position tolerance precision of the finished part can be ensured. When the contour of the fine-cutting mortise is cut by multiple linear cutting, the thickness of the remelted layer is less than or equal to 0.005mm by selecting reasonable parameters, and because a large amount of machining allowance is removed, the machining of the mortise can be completed only by removing the remelted layer with the thickness of 0.005mm by using the finishing broach, so that the machining cost can be reduced while the efficiency is improved. The processing mode of the invention mainly uses linear cutting, and the electrode wire is not directly contacted with a workpiece in the processing process and has no macroscopic cutting force.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic illustration of a turbine disk tongue and groove position distribution;
FIG. 2 is a schematic view of the present invention with a cut line machined at each mortise location on the turbine disk;
FIG. 3 is a schematic view of a cut line cut by a single mortise on a line according to the present invention;
fig. 4 is a schematic structural diagram of the present invention using one-cutting-one-trimming (one rough cutting, three fine cutting).
Detailed Description
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 only a part of the embodiments of the present invention, and not all of the embodiments. 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.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
As shown in FIG. 1, the distribution of the mortises of the turbine disk is schematically illustrated, a plurality of mortises are uniformly distributed on the circumferential surface of the turbine disk, and the turbine disk is made of FGH97 high-temperature alloy.
Referring to fig. 2 to 4, a method for processing a turbine disc mortise comprises the following steps:
step S1: clamping a workpiece: clamping a turbine disc workpiece by using an inner hole of the turbine disc in an axial compression mode;
step S2: processing one or more cutting lines at each mortise position by adopting linear cutting for releasing stress; specifically, as shown in fig. 2 and 3, the number of the cutting lines on each mortise is 1, the cutting lines are located at the center of each mortise, and the distance from the bottom end of each cutting line to the bottom of each mortise is 0.5 mm;
step S3: performing linear cutting on the outline of the rough-cut mortise, and keeping the allowance of 0.5mm on a single side;
step S4: adopting multiple linear cutting to finish the contour of the mortise to reach the size, wherein the thickness of the remelted layer after finish cutting is less than or equal to 0.005 mm;
step S5: and (4) performing finish machining on the mortise by adopting a broach to remove the remelted layer.
In this example, in step S4, a coated wire electrode was used in the wire-cut finishing process, the core material of the wire electrode was Brass CuZn37, the diameter of the wire electrode was 0.25mm, the tensile strength of the wire electrode was 900N/mm2, and the elongation of the wire electrode was 2% or less. The plating electrode wire is adopted, so that the cutting speed is high, the wire is not easy to break, the surface quality of a processed workpiece is favorably improved, copper accumulation is avoided, and the thickness of a remelted layer is favorably reduced.
In the present embodiment, the turbine disc mortise linear cutting is performed by "cutting one and trimming three", that is, "cutting one", that is, roughly cutting the contour of the mortise once in step S3, and "trimming three", that is, cutting the contour of the mortise finely in step S4 by using three times of linear cutting; the single edge is finely cut for the first time, and the allowance is 0.2-0.3 mm; performing secondary fine cutting on the single side to leave a margin of 0.01-0.1 mm; and performing fine cutting to size for the third time. In step S4, the thickness of the reflow layer is reduced by setting reasonable servo control parameters for the three-time fine cutting. The servo control parameters of the first fine cutting, the second fine cutting and the third fine cutting are shown in the following table:
by adopting the servo control parameters of the first fine cutting, the second fine cutting and the third fine cutting in the upper table, after the fine cutting of the mortise linear cutting is finished, a remelted layer generated during processing can be effectively controlled within 0.005mm, so that the processing of the mortise can be finished by removing the remelted layer within 0.005mm by adopting a fine broach. In this embodiment, adopt the tertiary essence to cut, the essence is cut every time and is got rid of some allowances, can not cause the deformation in the cutting process, consequently does not influence the size of tongue-and-groove.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. The turbine disc mortise machining method is characterized by comprising the following steps of:
step S1: clamping a workpiece: clamping a turbine disc workpiece by using an inner hole of the turbine disc in an axial compression mode;
step S2: processing one or more cutting lines at each mortise position by adopting linear cutting for releasing stress;
step S3: carrying out linear cutting on the outline of the rough-cut mortise and leaving allowance;
step S4: adopting multiple linear cutting to finish the contour of the mortise to reach the size, wherein the thickness of the remelted layer after finish cutting is less than or equal to 0.005 mm;
step S5: and (4) performing finish machining on the mortise by adopting a broach to remove the remelted layer.
2. The turbine disk mortise machining method according to claim 1, characterized in that: in step S3, when the rough-cut tongue-and-groove profile is wire-cut, a margin of 0.5mm is left on one side.
3. The turbine disk mortise machining method according to claim 1, characterized in that: in step S2, the number of the cutting lines on each mortise is 1, and the cutting lines are located at the center of each mortise, and the distance from the bottom end of each cutting line to the bottom of each mortise is 0.5 mm.
4. The turbine disk mortise machining method according to claim 1, characterized in that: in step S4, in the wire-electrode cutting finishing process, a coated wire electrode is used, the core material of the wire electrode is Brass CuZn37, the diameter of the wire electrode is 0.25mm, and the tensile strength of the wire electrode is 900N/mm2The elongation of the wire electrode is less than or equal to 2 percent.
5. The turbine disk mortise machining method according to claim 1, characterized in that: in step S4, a three-time linear cutting fine cutting mortise contour is adopted, and the allowance of a first fine cutting single side is 0.2-0.3 mm; performing secondary fine cutting on the single side to leave a margin of 0.01-0.1 mm; and performing fine cutting to size for the third time.
6. The turbine disk mortise machining method according to claim 5, characterized in that: in the servo control parameters of step S4, the cutting speed of the first finish cut was set to 10.5mm2Min; the cutting speed of the second fine cutting is set to be 11.5mm2Min; the cutting speed of the third fine cutting is set to be 22mm2/min。
7. The turbine disk mortise machining method according to claim 5, characterized in that: in the servo control parameters of step S4, the single-blade compensation amount for the first fine cut is set to 155 μm; the single-blade compensation amount of the second fine cutting is set to be 132 mu m; the single-blade compensation amount for the third fine cut was set to 131 μm.
8. The turbine disk mortise machining method according to claim 5, characterized in that: in the servo control parameter of step S4, the offset amount of the first fine cut is set to 219 μm; the offset of the second fine cutting is set to be 143 mu m; the offset of the third fine cut was set to 131 μm.
9. The turbine disk mortise machining method according to claim 5, characterized in that: in the servo control parameters of step S4:
the ignition voltage of the first fine cutting is set to be 80V, the current slope is set to be 226V, and the peak current is set to be 5A;
setting the ignition voltage of the third fine cutting to be 120V, setting the current slope to be 300V and setting the peak current to be 4A;
the ignition voltage for the third fine cut was set to 120V, the current slope was set to 103V, and the peak current was set to 2A.
10. The turbine disk mortise machining method according to claim 5, characterized in that: in the servo control parameters of step S4: the roughness of the first time is set to be Ra2.8; the roughness of the second fine cut was set to ra1.8 and the roughness of the third fine cut was set to ra 0.55.
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| CN202111387240.8A CN113977020A (en) | 2021-11-22 | 2021-11-22 | Turbine disc mortise machining method |
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Cited By (3)
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| CN114589363A (en) * | 2022-03-07 | 2022-06-07 | 山西电机制造有限公司 | Processing technology of female die in stator punching large-small groove single-punching die |
| CN114918482A (en) * | 2022-06-21 | 2022-08-19 | 中国航发贵州黎阳航空动力有限公司 | Machining method for wide and large mortise of turbine disc |
| CN115213642A (en) * | 2022-08-04 | 2022-10-21 | 松下压缩机(大连)有限公司 | Processing method of movable scroll |
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| CN114918482B (en) * | 2022-06-21 | 2024-07-09 | 中国航发贵州黎阳航空动力有限公司 | Machining method for large turbine disc width mortises |
| CN115213642A (en) * | 2022-08-04 | 2022-10-21 | 松下压缩机(大连)有限公司 | Processing method of movable scroll |
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