CN116748819A - Method for machining end face and inner circle of opening expansion ring for aviation - Google Patents
Method for machining end face and inner circle of opening expansion ring for aviation Download PDFInfo
- Publication number
- CN116748819A CN116748819A CN202311048501.2A CN202311048501A CN116748819A CN 116748819 A CN116748819 A CN 116748819A CN 202311048501 A CN202311048501 A CN 202311048501A CN 116748819 A CN116748819 A CN 116748819A
- Authority
- CN
- China
- Prior art keywords
- expansion ring
- clamping
- face
- machining
- ring blank
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000003754 machining Methods 0.000 title claims abstract description 34
- 238000000034 method Methods 0.000 title claims abstract description 24
- 210000001503 joint Anatomy 0.000 claims description 23
- 239000000463 material Substances 0.000 claims description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052802 copper Inorganic materials 0.000 claims description 4
- 239000010949 copper Substances 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 3
- 230000003746 surface roughness Effects 0.000 description 3
- 238000003032 molecular docking Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B21/00—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings
- F16B21/10—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings by separate parts
- F16B21/16—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings by separate parts with grooves or notches in the pin or shaft
- F16B21/18—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings by separate parts with grooves or notches in the pin or shaft with circlips or like resilient retaining devices, i.e. resilient in the plane of the ring or the like; Details
- F16B21/183—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings by separate parts with grooves or notches in the pin or shaft with circlips or like resilient retaining devices, i.e. resilient in the plane of the ring or the like; Details internal, i.e. with spreading action
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The invention relates to the technical field of aviation part processing, in particular to a method for processing an end face and an inner circle of an opening expansion ring for aviation, which comprises the following steps: s1, checking; s2, clamping and matching the guide sleeve with the clamping seat; s3, pushing the expansion ring blank into the clamping groove; s4, separating the guide sleeve from the clamping seat, and clamping the clamping part of the clamping seat on a three-jaw chuck of the machine tool; s5, machining a first end face of the expansion ring blank by using a machine tool; s6, pushing out the expansion ring blank with the first end face processed from the clamping groove; s7, repeating the steps S2-S4, and simultaneously enabling the other end face of the expansion ring blank to be located at a processing position; s8, machining a second end face of the expansion ring blank by using a machine tool; s9, directly processing the inner hole to the target size without taking down the clamping seat and the expansion ring blank with the second end face processed. The invention has the advantages that: the clamping times of product processing are reduced, alignment is not needed during clamping, clamping difficulty is reduced, and product processing efficiency is improved.
Description
Technical Field
The invention relates to the technical field of aviation part processing, in particular to an aviation opening expansion ring end face and inner circle processing method.
Background
As shown in fig. 1 and 2, the aviation opening expansion ring is provided with an opening, is thin (3.5 mm), has an outer diameter of 76mm and an inner diameter of 68mm, and is made of copper material.
Before machining, the split expander blank needs to be subjected to heat treatment, and the split expander blank after heat treatment forms tension, so that the split expander blank is in a state without external force (in a dotted line shape in fig. 2), an inner hole of the split expander blank is not a circular contour, and in a use state (in a solid line shape in fig. 2) of the split expander, the inner hole of the split expander is a circular contour, and therefore, when the inner circle is machined, the inner hole of the split expander blank needs to be machined in place in a state that the inner hole of the split expander blank is the circular contour.
When the end face is machined, the clamping can not be adsorbed by magnetic force due to the material reason, so that the end face can not be machined by a grinding machine, meanwhile, the clamping length of the three jaws of the machine tool is too small due to the fact that the workpiece is very thin, an opening exists, and alignment is not easy after clamping.
In addition, in the processing process of the opening expansion ring, the end face processing and the inner circle processing are processed step by step, the clamping times are more, the difficulty is high, the processing time is longer, and the processing efficiency of the product is low.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides a method for processing the end face and the inner circle of an opening expansion ring for aviation, which reduces the clamping frequency of product processing, does not need alignment during clamping, reduces the clamping difficulty and improves the product processing efficiency.
The aim of the invention is achieved by the following technical scheme:
the method for processing the end face and the inner circle of the opening expansion ring for aviation uses the clamping tool for processing the end face and the inner circle of the opening expansion ring for aviation, and comprises the following steps:
s1, checking the initial size of an expansion ring blank;
s2, clamping and matching the guide sleeve with the clamping seat to enable the docking station and the docking slot to be clamped into a whole;
s3, placing the expansion ring blank from the large end of the guide taper hole, pushing the expansion ring blank to the small end of the guide taper hole by using the core rod, and finally pushing the expansion ring blank into the clamping groove, wherein the expansion ring blank simulates the shape in the use state;
s4, separating the guide sleeve from the clamping seat, and clamping the clamping part of the clamping seat on a three-jaw chuck of the machine tool;
s5, machining a first end face of the expansion ring blank by using a machine tool;
s6, taking down the clamping seat from the three-jaw chuck, extending the core rod into the through hole, and pushing out the expansion ring blank with the first end face processed from the clamping groove;
s7, repeating the steps S2-S4, and simultaneously enabling the other end face of the expansion ring blank to be located at a processing position;
s8, machining a second end face of the expansion ring blank by using a machine tool;
s9, directly processing the inner hole to the target size without taking down the clamping seat and the expansion ring blank with the second end face processed.
Further, step S5 is followed by machining the orifice chamfer; step S8 is followed by machining the orifice chamfer.
The clamping fixture for machining the end face and the inner circle of the aviation opening expansion ring comprises a clamping seat, a guide sleeve and a core rod, wherein a clamping part is arranged at the outer side of one end of the clamping seat, and a butt joint table is arranged at the other end of the clamping seat; the inner side of the clamping seat is provided with a through hole, one end of the through hole, which is close to the butt joint table, is provided with a clamping groove capable of clamping the expansion ring blank, and the clamping part is coaxial with the clamping groove; the small end of the guide taper hole is positioned at one side of the butt joint groove, the hole diameter of the small end of the guide taper hole is equal to the diameter of the clamping groove, and the butt joint groove can be in clamping fit with the butt joint table; the core rod can extend into the guide taper hole, and the diameter of the core rod is not larger than the aperture of the small end of the guide taper hole.
Further, the clamping groove is a circular step groove, the depth of the clamping groove is smaller than the thickness of the expansion ring blank, the diameter of the clamping groove is not smaller than the outer diameter of the opening expansion ring in the use state, and the diameter of the through hole is larger than the inner diameter of the opening expansion ring in the use state.
Further, the difference a between the depth of the clamping groove and the thickness of the expansion ring blank is 0.1 mm-0.3 mm.
Further, the included angle beta between the hole wall of the guide taper hole and the axis is 0.5-3 degrees.
Further, the core rod is a copper rod.
Further, the clamping seat and the guide sleeve are both made of stainless steel materials.
The invention has the following advantages:
1. according to the invention, after the expansion ring blank is compressed through the guide taper hole in the guide sleeve and is led into the clamping groove, the clamping part of the clamping seat is clamped on the three-jaw chuck of the lathe, the end face of the expansion ring blank can be directly subjected to finish machining, after one end face is machined, the end face is taken out and turned over and then is led into the clamping groove again, the other end face is machined, after the two end faces are machined, the workpiece is not required to be taken down at the moment, the inner hole machining is directly performed, the expansion ring blank which is arranged in the clamping groove simulates the shape of the opening expansion ring in the use state, the inner hole machining is performed, the clamping times of product machining are reduced, alignment is not required during clamping, the clamping difficulty is reduced, and the product machining efficiency is improved.
2. The tool is of a split type structure, the processing difficulty of the tool is low, and if one part is damaged, only the damaged part is required to be replaced independently, so that the cost of the tool is reduced.
Drawings
FIG. 1 is a schematic cross-sectional view of an open expander of the present invention;
FIG. 2 is a schematic plan view of an open expander of the present invention (broken line is natural; solid line is in use);
FIG. 3 is a whole structure diagram of the clamping tool of the invention;
FIG. 4 is a schematic cross-sectional view of a clamping seat according to the present invention;
FIG. 5 is a schematic cross-sectional view of the guide sleeve of the present invention;
FIG. 6 is a schematic structural diagram of the clamping tool of the present invention when used in combination;
FIG. 7 is a schematic cross-sectional view of an expander blank of the present invention clamped in a clamping groove;
in the figure: the device comprises a 1-clamping seat, a 1 a-clamping part, a 1 b-through hole, a 1 c-butt joint table, a 1 d-clamping groove, a 2-guide sleeve, a 2 a-guide taper hole, a 2 b-butt joint groove, a 3-core rod and a 4-expansion ring blank.
Detailed Description
The present invention will be further described with reference to the accompanying drawings, but the scope of the present invention is not limited to the following.
As shown in FIG. 1, the thickness of the opening expansion ring is 3.5mm, the outer diameter is 76mm, the inner diameter is 68mm, and as shown in FIG. 2, the broken line is a schematic diagram of the opening expansion ring in a natural state; the solid line is a schematic diagram of the opening expansion ring in the use state. When the inner hole size is processed, the shape of the opening expansion ring in the use state needs to be simulated so as to ensure that the inner hole size of the opening expansion ring is the correct size in the use state.
As shown in fig. 3 to 7, the clamping fixture for machining the end face and the inner circle of the aviation opening expansion ring comprises a clamping seat 1, a guide sleeve 2 and a core rod 3, wherein a clamping part 1a is arranged at the outer side of one end of the clamping seat 1, the clamping part 1a can be clamped on a three-jaw chuck, and a butt joint table 1c is arranged at the other end of the clamping seat 1; the inner side of the clamping seat 1 is provided with a through hole 1b which penetrates through, the size of the through hole 1b is slightly larger than the inner diameter of the expansion ring blank 4, the inner ring of the expansion ring blank 4 is exposed, the subsequent inner hole processing is facilitated, the expansion ring blank 4 is taken out, one end, close to the butt joint table 1c, of the through hole 1b is provided with a clamping groove 1d which can clamp the expansion ring blank 4, the clamping groove 1d is used for clamping the expansion ring blank 4 and simulating the form of an opening expansion ring in use, the clamping part 1a is coaxial with the clamping groove 1d, and when a three-jaw chuck is clamped on the clamping part 1a, a machine tool main shaft is coaxial with the clamping groove 1 d; a butt joint groove 2b is formed in one end, facing the clamping seat 1, of the guide sleeve 2, a penetrating guide taper hole 2a is formed in the inner side of the guide sleeve 2, the inner diameter of the large end of the guide taper hole 2a is usually slightly larger than the size of the expansion ring blank 4 in a natural state, the inner diameter of the small end is equal to the outer diameter of the opening expansion ring in a use state, the small end of the guide taper hole 2a is positioned on one side of the butt joint groove 2b, the hole diameter of the small end of the guide taper hole 2a is equal to the diameter of the clamping groove 1d, and the butt joint groove 2b can be in clamping fit with the butt joint table 1c; the core rod 3 can extend into the guide taper hole 2a, the diameter of the core rod 3 is not larger than the small end aperture of the guide taper hole 2a, and the core rod 3 can smoothly push the expansion ring blank 4 into the clamping groove 1 d.
Further, the clamping groove 1d is a circular step groove, the depth of the clamping groove 1d is smaller than the thickness of the expansion ring blank 4, the diameter of the clamping groove 1d is not smaller than the outer diameter of the expansion ring blank 4 in the use state, and the diameter of the through hole 1b is larger than the inner diameter of the opening expansion ring in the use state.
Further, as shown in fig. 7, the difference a between the depth of the clamping groove 1d and the thickness of the expander blank 4 is 0.1mm to 0.3mm, and in this embodiment, preferably 0.2mm.
Further, as shown in fig. 5, the included angle β between the hole wall of the guide cone hole 2a and the axis is 0.5 ° to 3 °, and in this embodiment, it is preferably 2 °.
Further, the core rod 3 is a copper rod, and when the core rod 3 pushes the expansion ring blank 4 into the clamping groove 1d, the surface of the expansion ring blank 4 is not damaged.
Further, the clamping seat 1 and the guide sleeve 2 are made of stainless steel materials.
The method for processing the end face and the inner circle of the aviation opening expansion ring comprises the following steps:
s1, checking the initial size of the expansion ring blank 4, wherein the thickness of the expansion ring blank 4 is 3.6mm-3.8mm in the embodiment, and the surface roughness is Ra3.2;
s2, the guide sleeve 2 is matched with the clamping seat 1 in a clamping way, so that the butt joint table 1c and the butt joint groove 2b are integrally clamped, and at the moment, the small end of the guide taper hole 2a is aligned with the clamping groove 1 d;
s3, placing the expansion ring blank 4 from the large end of the guide taper hole 2a, pushing the expansion ring blank 4 to the small end of the guide taper hole 2a by using the core rod 3, and finally pushing the expansion ring blank 4 into the clamping groove 1d, wherein the expansion ring blank 4 simulates a shape in a use state;
s4, separating the guide sleeve 2 from the clamping seat 1, and clamping the clamping part 1a of the clamping seat 1 on a three-jaw chuck of the machine tool;
s5, machining a first end face of the expansion ring blank 4 by utilizing a machine tool, so that the surface roughness of the end face is Ra0.32;
s6, the clamping seat 1 is taken down from the three-jaw chuck, the core rod 3 stretches into the through hole 1b, and the expansion ring blank 4 with the first end face processed is pushed out of the clamping groove 1 d;
s7, repeating the steps S2-S4, and simultaneously enabling the other end face of the expansion ring blank 4 to be located at a processing position;
s8, machining a second end face of the expansion ring blank 4 by using a machine tool to ensure that the surface roughness of the end face is Ra0.32 and the thickness is 3.38-3.5 mm;
s9, directly processing the inner hole to the target size without taking down the clamping seat 1 and the expansion ring blank 4 with the second end face processed.
Further, step S5 further includes machining an orifice chamfer; and step S8, machining an orifice chamfer, wherein the orifice chamfer is R0.5mm+/-0.2 mm.
Through the special structure of this clamping frock, can directly process the hole after processing the terminal surface, in the internal hole course of working moreover, simulated the form of opening expander under the user state, avoided the deformation that expander body self leads to because of tension after the heat treatment.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The method for machining the end face and the inner circle of the opening expansion ring for aviation uses an tooling for machining the end face and the inner circle of the opening expansion ring for aviation to clamp, and is characterized in that: the method comprises the following steps:
s1, checking the initial size of an expansion ring blank (4);
s2, the guide sleeve (2) is matched with the clamping seat (1) in a clamping way, so that the butt joint table (1 c) and the butt joint groove (2 b) are clamped into a whole;
s3, placing the expansion ring blank (4) from the large end of the guide taper hole (2 a), pushing the expansion ring blank (4) to the small end of the guide taper hole (2 a) by using the core rod (3), and finally pushing the expansion ring blank into the clamping groove (1 d), wherein the expansion ring blank (4) simulates a shape in a use state;
s4, separating the guide sleeve (2) from the clamping seat (1), and clamping the clamping part (1 a) of the clamping seat (1) on a three-jaw chuck of the machine tool;
s5, machining a first end face of the expansion ring blank (4) by using a machine tool;
s6, taking down the clamping seat (1) from the three-jaw chuck, extending the core rod (3) from the through hole (1 b), and pushing out the expansion ring blank (4) with the first end face processed from the clamping groove (1 d);
s7, repeating the steps S2-S4, and simultaneously enabling the other end face of the expansion ring blank (4) to be located at a processing position;
s8, machining a second end face of the expansion ring blank (4) by using a machine tool;
s9, directly processing the inner hole to the target size without taking down the clamping seat (1) and the expansion ring blank (4) with the second end face processed.
2. The method for machining the end face and the inner circle of the open expansion ring for aviation according to claim 1, wherein the method comprises the following steps: step S5 is followed by machining an orifice chamfer; step S8 is followed by machining the orifice chamfer.
3. The method for machining the end face and the inner circle of the open expansion ring for aviation according to claim 1, wherein the method comprises the following steps: the aviation opening expansion ring end face and inner circle machining tool comprises a clamping seat (1), a guide sleeve (2) and a core rod (3), wherein a clamping part (1 a) is arranged at the outer side of one end of the clamping seat (1), and a butt joint table (1 c) is arranged at the other end of the clamping seat; a through hole (1 b) penetrating through the inner side of the clamping seat (1) is formed, a clamping groove (1 d) capable of clamping the expansion ring blank (4) is formed in one end, close to the butt joint table (1 c), of the through hole (1 b), and the clamping part (1 a) is coaxial with the clamping groove (1 d); a butt joint groove (2 b) is formed in one end, facing the clamping seat (1), of the guide sleeve (2), a penetrating guide taper hole (2 a) is formed in the inner side of the guide sleeve (2), the small end of the guide taper hole (2 a) is located on one side of the butt joint groove (2 b), the small end hole diameter of the guide taper hole (2 a) is equal to the diameter of the clamping groove (1 d), and the butt joint groove (2 b) can be in clamping fit with the butt joint table (1 c); the core rod (3) can extend into the guide taper hole (2 a), and the diameter of the core rod is not larger than the small end aperture of the guide taper hole (2 a).
4. The method for machining the end face and the inner circle of the open expansion ring for aviation according to claim 3, wherein the method comprises the following steps: the clamping groove (1 d) is a circular step groove, the depth of the clamping groove (1 d) is smaller than the thickness of the expansion ring blank (4), the diameter of the clamping groove (1 d) is not smaller than the outer diameter of the opening expansion ring in the use state, and the diameter of the through hole (1 b) is larger than the inner diameter of the opening expansion ring in the use state.
5. The method for machining the end face and the inner circle of the open expansion ring for aviation according to claim 4, wherein the method comprises the following steps: the difference a between the depth of the clamping groove (1 d) and the thickness of the expansion ring blank (4) is 0.1 mm-0.3 mm.
6. The method for machining the end face and the inner circle of the open expansion ring for aviation according to claim 3, wherein the method comprises the following steps: the included angle beta between the hole wall of the guide taper hole (2 a) and the axis is 0.5-3 degrees.
7. The method for machining the end face and the inner circle of the open expansion ring for aviation according to claim 3, wherein the method comprises the following steps: the core rod (3) is a copper rod.
8. The method for machining the end face and the inner circle of the open expansion ring for aviation according to claim 3, wherein the method comprises the following steps: the clamping seat (1) and the guide sleeve (2) are both made of stainless steel materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311048501.2A CN116748819B (en) | 2023-08-21 | 2023-08-21 | Method for machining end face and inner circle of opening expansion ring for aviation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311048501.2A CN116748819B (en) | 2023-08-21 | 2023-08-21 | Method for machining end face and inner circle of opening expansion ring for aviation |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116748819A true CN116748819A (en) | 2023-09-15 |
| CN116748819B CN116748819B (en) | 2023-10-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311048501.2A Active CN116748819B (en) | 2023-08-21 | 2023-08-21 | Method for machining end face and inner circle of opening expansion ring for aviation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116748819B (en) |
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| GB963793A (en) * | 1961-10-20 | 1964-07-15 | Hedwin Corp | Closure fitting |
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| CN103231074A (en) * | 2013-04-18 | 2013-08-07 | 哈尔滨汽轮机厂有限责任公司 | Machining method of inner circle and outer circle of elastic ring provided with opening and made of high temperature alloy |
| CN203236240U (en) * | 2013-05-22 | 2013-10-16 | 西北轴承股份有限公司 | Novel clamp for machining thin-wall bearing ring |
| CN103752919A (en) * | 2014-01-09 | 2014-04-30 | 大连理工大学 | Non-circular expanded ring type sealing ring machining method |
| CN105710392A (en) * | 2014-12-04 | 2016-06-29 | 苏州道森阀门有限公司 | Machining process for annular thin-wall part and tool thereof |
| JP2017019077A (en) * | 2015-07-14 | 2017-01-26 | 株式会社リコー | Gripping device |
| CN109482907A (en) * | 2018-11-13 | 2019-03-19 | 北京星航机电装备有限公司 | A kind of processing clamping and processing method of the weak hard parts of thin-walled |
| CN217749737U (en) * | 2022-07-19 | 2022-11-08 | 成立航空技术(成都)有限公司 | Clamping frock of elasticity expanded ring car processing |
| CN218693980U (en) * | 2022-09-28 | 2023-03-24 | 瓦房店轴承集团国家轴承工程技术研究中心有限公司 | Clamping tool for machining bearing spacer ring |
-
2023
- 2023-08-21 CN CN202311048501.2A patent/CN116748819B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB963793A (en) * | 1961-10-20 | 1964-07-15 | Hedwin Corp | Closure fitting |
| GB2076493A (en) * | 1981-05-18 | 1981-12-02 | Olympic Fastening Systems | Blind Fastener with Deformable Clamping Means |
| JP2000343365A (en) * | 1999-06-08 | 2000-12-12 | Dowa Mining Co Ltd | Workpiece holding jig and machining method for machine tool |
| CN202377796U (en) * | 2011-11-16 | 2012-08-15 | 天津职业技术师范大学 | Numerical control turning fixture for inner outline of focusing guide ring |
| CN103231074A (en) * | 2013-04-18 | 2013-08-07 | 哈尔滨汽轮机厂有限责任公司 | Machining method of inner circle and outer circle of elastic ring provided with opening and made of high temperature alloy |
| CN203236240U (en) * | 2013-05-22 | 2013-10-16 | 西北轴承股份有限公司 | Novel clamp for machining thin-wall bearing ring |
| CN103752919A (en) * | 2014-01-09 | 2014-04-30 | 大连理工大学 | Non-circular expanded ring type sealing ring machining method |
| CN105710392A (en) * | 2014-12-04 | 2016-06-29 | 苏州道森阀门有限公司 | Machining process for annular thin-wall part and tool thereof |
| JP2017019077A (en) * | 2015-07-14 | 2017-01-26 | 株式会社リコー | Gripping device |
| CN109482907A (en) * | 2018-11-13 | 2019-03-19 | 北京星航机电装备有限公司 | A kind of processing clamping and processing method of the weak hard parts of thin-walled |
| CN217749737U (en) * | 2022-07-19 | 2022-11-08 | 成立航空技术(成都)有限公司 | Clamping frock of elasticity expanded ring car processing |
| CN218693980U (en) * | 2022-09-28 | 2023-03-24 | 瓦房店轴承集团国家轴承工程技术研究中心有限公司 | Clamping tool for machining bearing spacer ring |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116748819B (en) | 2023-10-20 |
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