CN108788808B - Quick clamping device for machining annular part of aircraft engine by vertical lathe - Google Patents
Quick clamping device for machining annular part of aircraft engine by vertical lathe Download PDFInfo
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- CN108788808B CN108788808B CN201811049892.9A CN201811049892A CN108788808B CN 108788808 B CN108788808 B CN 108788808B CN 201811049892 A CN201811049892 A CN 201811049892A CN 108788808 B CN108788808 B CN 108788808B
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- 238000003754 machining Methods 0.000 title claims description 9
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 28
- 230000008093 supporting effect Effects 0.000 claims description 11
- 229910001220 stainless steel Inorganic materials 0.000 claims description 4
- 239000010935 stainless steel Substances 0.000 claims description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 8
- 230000002349 favourable effect Effects 0.000 abstract description 5
- 230000000694 effects Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q2703/00—Work clamping
- B23Q2703/02—Work clamping means
- B23Q2703/10—Devices for clamping workpieces of a particular form or made from a particular material
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Clamps And Clips (AREA)
Abstract
The invention provides a quick clamping in-place device for processing an aircraft engine annular part by a vertical lathe, which comprises a rotating disc, a through hole, a moving plate, an adjusting hole, a fixed bolt, a movable rod, a rotating rod, a fixed hole, a connector, an adjustable jacking seat structure, a reinforcing fastening plate structure, an auxiliary reinforcing rod structure, a rotating ball, an anti-skid pad and a groove, wherein the through hole is respectively formed in the upper part and the lower part of the rotating disc; the movable plate is inserted into the through hole and is fixed through the fixing bolt. The beneficial effects of the invention are as follows: through the setting of adjustable tight seat structure in top, be favorable to the fixed aircraft engine ring spare of fastening more, and this adjustable tight seat structure in top of convenient use more is favorable to convenient centre gripping aircraft engine ring spare through the setting of consolidating the fastening plate structure, and has increased the tightness of this quick clamping device in place, and then avoids quick clamping device in place to appear appearing the problem that drops easily.
Description
Technical Field
The invention belongs to the technical field of clamping devices, and particularly relates to a rapid clamping in-place device for machining an annular part of an aircraft engine by a vertical lathe.
Background
The annular part of the aircraft engine is a very common workpiece in the production of the aircraft engine, when the diameter of the processed annular workpiece is larger and the thickness is smaller, the annular workpiece is very easy to deform in the processing, so a clamp-shaped device is needed, and the technical scheme adopted by the annular workpiece processing clamp with the Chinese patent publication number of CN201610093787.X in the prior art is as follows: the clamping head is fan-shaped, the radian of the fan is 120 degrees, and the clamping head is characterized in that: the chuck comprises a vertical clamping block and a horizontal supporting table, wherein the vertical clamping block is fixedly connected with the horizontal supporting table, the radius of the vertical clamping block is smaller than that of the horizontal supporting table, the radius difference of the vertical clamping block and the radius of the vertical clamping block is larger than or equal to the width of the annular edge of the annular workpiece, the height of the vertical clamping block is larger than that of the horizontal supporting table, the height difference of the vertical clamping block and the vertical clamping block is larger than or equal to the thickness of the annular workpiece, a sliding block is arranged at the bottom of the horizontal supporting table and is in sliding fit with a sliding groove arranged on a bottom plate, the screw is in threaded connection with the bottom plate and extends into the sliding groove to be fixedly connected with the sliding block, the axis of the screw is consistent with the axis of the sliding groove, and the radial deformation can be reduced when the radial dimension of the annular workpiece is far larger than the axial dimension of the annular workpiece is processed, so that the processing requirements are met.
But the existing quick clamping device in place also has the problems that the airplane engine annular parts with different sizes are inconvenient to fix, the device does not have the functions of supporting and fastening, the effect is poor, and the fixing mode is inconvenient to increase.
Therefore, the invention provides a quick clamping and positioning device for machining an aircraft engine ring-shaped part by a vertical lathe.
Disclosure of Invention
In order to solve the technical problems, the invention provides a quick clamping in-place device for processing an aircraft engine annular part by a vertical lathe, which aims to solve the problems that the existing quick clamping in-place device is inconvenient to fix the aircraft engine annular parts with different sizes, the device does not have the supporting effect, the fastening effect is poor and the fixing mode is inconvenient to increase. The quick clamping in-place device for the annular part of the aircraft engine of the vertical lathe processing comprises a rotating disc, a through hole, a moving plate, an adjusting hole, a fixing bolt, a movable rod, a rotating rod, a fixing hole and a connector, wherein the adjustable jacking seat structure, the reinforcing fastening plate structure, the auxiliary reinforcing rod structure, a rotating ball, an anti-skid pad and a groove are respectively arranged at the upper part and the lower part inside the rotating disc; the movable plate is inserted into the through hole and is fixed by the fixing bolt; the adjusting holes are respectively formed in the front surface of the moving plate and are in threaded connection with the fixing bolts; the movable rod is connected with the inside of the movable plate in a threaded manner; the rotary rods are respectively welded at the left end and the right end of the outer wall of the movable rod, and meanwhile, rotary balls are welded at the outer sides of the rotary rods; the fixing holes are respectively formed in the upper side and the lower side of the inside of the rotary disk; the connector is welded at the middle part of the left surface of the rotary disc, and a groove is formed in the connector; the adjustable jacking seat structure is arranged on the inner side of the movable rod; the reinforcing fastening plate structure is arranged in the fixing hole; the auxiliary reinforcing rod structure is arranged on the outer wall of the connector; the anti-slip pad is embedded in the middle part of the right surface of the rotating disc; the adjustable jacking seat structure comprises a first jacking plate, a first jacking groove, a rotating bearing, a second jacking plate, a second jacking groove and a fastening bolt, wherein the first jacking groove is formed in the lower surface of the first jacking plate; the second propping plate is sleeved on the lower part of the outer wall of the first propping plate, and a second propping groove is formed below the inner part of the second propping plate; the fastening bolts are respectively connected with the left side and the right side of the upper part of the front surface of the second jacking plate in a threaded manner.
Preferably, the reinforcing fastening plate structure comprises a threaded rod, a movable plate, a first fastening nut, a second fastening nut, an auxiliary plate and an auxiliary groove, wherein the movable plate is sleeved on the outer wall of the threaded rod; the first fastening nut and the second fastening nut are respectively in threaded connection with the upper part and the lower part of the outer wall of the threaded rod; the auxiliary plate is welded at the right upper part of the movable plate, and an auxiliary groove is formed in the upper part of the inner part.
Preferably, the auxiliary reinforcing rod structure comprises a supporting column, a lower sleeve seat, an upper sleeve seat, an assembly bearing, a rotating seat, an inclined seat and a antiskid plate, wherein the lower sleeve seat and the upper sleeve seat are respectively sleeved on the outer wall of the assembly bearing and are connected with each other through bolts; the assembly bearing is sleeved on the outer wall of the connector; the rotating seat is welded at the lower end of the lower sleeve seat; the antiskid plate is welded at the lower end of the inclined seat.
Preferably, the first propping groove and the second propping groove are respectively arranged in an arc shape.
Preferably, the fastening bolt of the outer wall of the second propping plate is in threaded connection with the first propping plate.
Preferably, the rotary bearing is embedded in the middle of the upper surface of the first jacking plate and sleeved on the inner side of the movable rod.
Preferably, the first fastening nut and the second fastening nut are respectively in close contact with the outer wall of the movable plate.
Preferably, the auxiliary groove in the auxiliary plate is arc-shaped.
Preferably, the threaded rods are welded on the inner wall of the fixing hole, and two threaded rods are arranged.
Preferably, the inner sides of the front and rear parts of the lower sleeve joint seat and the upper sleeve joint seat are respectively welded with rectangular stainless steel blocks, and are internally connected with bolts in a threaded manner.
Preferably, the upper end and the lower end of the support column are respectively connected with the rotating seat and the inclined seat through bolts.
Compared with the prior art, the invention has the beneficial effects that:
1. in the invention, the first propping groove and the second propping groove are respectively arranged in an arc shape, which is beneficial to more firmly fixing the annular part of the aircraft engine and is more convenient to use the adjustable propping seat structure.
2. In the invention, the fastening bolt on the outer wall of the second propping plate is in threaded connection with the first propping plate, which is favorable for conveniently assembling or disassembling the second propping plate and the first propping plate and conveniently fixing the annular parts of the aircraft engines with different sizes.
3. In the invention, the rotary bearing is embedded in the middle part of the upper surface of the first jacking plate and sleeved on the inner side of the movable rod, thereby being beneficial to conveniently installing the adjustable jacking seat structure, and simultaneously conveniently rotating the adjustable jacking seat structure, so that the adjustable jacking seat structure is more reasonably used for fixing the annular part of the aircraft engine.
4. In the invention, the first fastening nut and the second fastening nut are respectively in close contact with the outer wall of the movable plate, which is beneficial to conveniently fixing the movable plate and more conveniently sleeving the position between the movable plate and the movable plate.
5. According to the invention, the auxiliary groove in the auxiliary plate is arc-shaped, so that the annular part of the aircraft engine can be conveniently clamped, the tightness of the quick clamping in-place device is improved, and the problem that the quick clamping in-place device is easy to fall off is avoided.
6. In the invention, the threaded rods are welded on the inner wall of the fixing hole, and the threaded rods are provided with two threaded rods, so that the reinforcing fastening plate structure can be used or regulated more reasonably.
7. In the invention, the inner sides of the front and rear parts of the lower sleeve joint seat and the upper sleeve joint seat are respectively welded with rectangular stainless steel blocks, and are connected with bolts in internal threads, so that the assembly bearing can be more conveniently fixed, and the auxiliary reinforcing rod structure can be more reasonably used.
8. In the invention, the upper end and the lower end of the support column are respectively connected with the rotating seat and the inclined seat through bolts, which is favorable for conveniently inclining the angle of the support column and simultaneously conveniently supporting and using the auxiliary reinforcing rod structure.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Fig. 2 is a schematic structural view of an adjustable jack structure of the present invention.
Fig. 3 is a schematic structural view of the reinforced fastening-plate structure of the present invention.
Fig. 4 is a schematic structural view of the auxiliary reinforcing rod structure of the present invention.
In the figure:
1. A rotating disc; 2. a through hole; 3. a moving plate; 4. an adjustment aperture; 5. a fixing bolt; 6. a movable rod; 7. a rotating rod; 8. a fixing hole; 9. a connector; 10. an adjustable jack structure; 101. a first tightening plate; 102. a first tightening groove; 103. a rotating bearing; 104. a second tightening plate; 105. a second tightening groove; 106. a fastening bolt; 11. reinforcing the fastening plate structure; 111. a threaded rod; 112. a movable plate; 113. a first fastening nut; 114. a second fastening nut; 115. an auxiliary plate; 116. an auxiliary groove; 12. an auxiliary reinforcing rod structure; 121. a support column; 122. a lower sleeve joint seat; 123. an upper sleeve joint seat; 124. assembling a bearing; 125. a rotating seat; 126. an inclined seat; 127. a cleat; 13. a spin ball; 14. an anti-slip pad; 15. a groove.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
Examples:
As shown in fig. 1 and fig. 2, a quick clamping and positioning device for vertical lathe processing of an aircraft engine ring part comprises a rotary disc 1, a through hole 2, a movable plate 3, an adjusting hole 4, a fixed bolt 5, a movable rod 6, a rotary rod 7, a fixed hole 8, a connector 9, an adjustable jacking seat structure 10, a reinforced fastening plate structure 11, an auxiliary reinforcing rod structure 12, a rotary ball 13, an anti-slip pad 14 and a groove 15, wherein the through hole 2 is respectively formed in the upper part and the lower part of the rotary disc 1; the movable plate 3 is inserted into the through hole 2 and is fixed by a fixing bolt 5; the adjusting holes 4 are respectively formed in the front surface of the moving plate 3 and are in threaded connection with the fixing bolts 5, so that the length of the moving plate 3 on the right side of the rotating disc 1 can be conveniently adjusted, and the quick clamping in-place device can be more reasonably used for fixing smaller aircraft engine annular parts; the movable rod 6 is in threaded connection with the inside of the movable plate 3; the rotating rods 7 are respectively welded at the left end and the right end of the outer wall of the movable rod 6, and meanwhile, rotating balls 13 are welded at the outer sides of the rotating rods 7; the fixing holes 8 are respectively formed in the middle upper side and the middle lower side of the inside of the rotary disk 1; the connector 9 is welded at the middle part of the left surface of the rotary disk 1, and a groove 15 is formed in the connector; the quick clamping device is more convenient to install; the adjustable jacking seat structure 10 is arranged on the inner side of the movable rod 6; the reinforcing fastening plate structure 11 is arranged in the fixing hole 8; the auxiliary reinforcing rod structure 12 is arranged on the outer wall of the connector 9; the anti-skid pad 14 is embedded in the middle part of the right surface of the rotary disk 1, and can play an anti-skid role on an aircraft engine annular part; the adjustable jacking seat structure 10 comprises a first jacking plate 101, a first jacking groove 102, a rotary bearing 103, a second jacking plate 104, a second jacking groove 105 and a fastening bolt 106, wherein the first jacking groove 102 is formed in the lower surface of the first jacking plate 101; the rotary bearing 103 is embedded in the middle part of the upper surface of the first jacking plate 101 and sleeved on the inner side of the movable rod 6, so that the adjustable jacking seat structure 10 can be conveniently installed, and meanwhile, the adjustable jacking seat structure 10 can be conveniently rotated, and further, the adjustable jacking seat structure 10 can be more reasonably fixed on an aircraft engine annular part; the second tightening plate 104 is sleeved on the lower part of the outer wall of the first tightening plate 101, and a second tightening groove 105 is formed below the inside of the second tightening plate 104; the fastening bolts 106 on the outer wall of the second propping plate 104 are in threaded connection with the first propping plate 101, so that the second propping plate 104 and the first propping plate 101 can be conveniently assembled or disassembled, and aircraft engine annular parts with different sizes can be conveniently fixed; the fastening bolts 106 are respectively connected with the left side and the right side of the upper part of the front surface of the second jacking plate 104 in a threaded manner; during adjustment, the fastening bolts 106 are loosened, and then the second tightening plate 104 is pulled to separate from the first tightening plate 101, so that the adjustment of the adjustable tightening seat structure 10 can be completed.
As shown in fig. 3, in the foregoing embodiment, specifically, the reinforcing fastening plate structure 11 includes a threaded rod 111, a movable plate 112, a first fastening nut 113, a second fastening nut 114, an auxiliary plate 115 and an auxiliary groove 116, where the threaded rod 111 is welded on the inner wall of the fixing hole 8, and two threaded rods 111 are provided, so that it is advantageous to use or adjust the reinforcing fastening plate structure 11 more reasonably; the movable plate 112 is sleeved on the outer wall of the threaded rod 111; the first fastening nut 113 and the second fastening nut 114 are respectively in threaded connection with the upper and lower parts of the outer wall of the threaded rod 111; the auxiliary plate 115 is welded at the upper right part of the movable plate 112, and an auxiliary groove 116 is formed at the upper part of the inner part; the auxiliary groove 116 in the auxiliary plate 115 is arc-shaped, which is favorable for conveniently clamping the annular part of the aircraft engine, and increases the tightness of the quick clamping in-place device, thereby avoiding the problem that the quick clamping in-place device easily falls off.
As shown in fig. 4, in the above embodiment, specifically, the auxiliary reinforcing rod structure 12 includes a support column 121, a lower socket 122, an upper socket 123, an assembly bearing 124, a rotating seat 125, an inclined seat 126 and a cleat 127, where the upper and lower ends of the support column 121 are respectively connected with the rotating seat 125 and the inclined seat 126 by bolts, which is beneficial to the convenient angle of the inclined support column 121, and also convenient to support and use the auxiliary reinforcing rod structure 12; the lower sleeve joint seat 122 and the upper sleeve joint seat 123 are respectively sleeved on the outer wall of the assembled bearing 124 and are connected with each other through bolts; the assembly bearing 124 is sleeved on the outer wall of the connector 9; the rotating seat 125 is welded at the lower end of the lower sleeve seat 122; the antiskid plate 127 is welded at the lower end of the inclined seat 126; in use, the movable plate 112 is moved up and down and the auxiliary groove 116 of the auxiliary plate 115 is caused to clamp the aircraft engine ring, and then the second fastening nut 114 and the first fastening nut 113 are rotated to fix the movable plate 112, respectively.
In the above embodiment, specifically, the first propping groove 102 and the second propping groove 105 are respectively configured in an arc shape, which is beneficial to more tightly fixing the annular part of the aircraft engine, and is more convenient to use the adjustable propping seat structure 10.
In the above embodiment, specifically, the first fastening nut 113 and the second fastening nut 114 are respectively in close contact with the outer wall of the movable plate 112, which is beneficial to conveniently fixing the movable plate 112 and more conveniently sleeving the movable plate 112 and the position between the movable plates 112.
In the above embodiment, specifically, the inner sides of the front and rear parts of the lower sleeve seat 122 and the upper sleeve seat 123 are respectively welded with rectangular stainless steel blocks, and are simultaneously connected with bolts in an internal threaded manner, so that the assembly bearing 124 is more conveniently fixed, and the auxiliary reinforcing rod structure 12 is more reasonably used.
Principle of operation
The working principle of the invention is as follows: the connector 9 and the groove 15 are firstly connected with a specified device, then the upper sleeve joint seat 123 and the lower sleeve joint seat 122 are sleeved on the outer wall of the assembly bearing 124, the supporting column 121 is inclined along with the upper sleeve joint seat, the antiskid plate 127 is contacted with the ground or the device, then bolts in the inclined seat 126 and the rotating seat 125 are respectively screwed down to support the quick clamping device, when the quick clamping device is used, firstly, an aircraft engine annular part is placed inside the first tightening groove 102 and the second tightening groove 105, then the rotating rod 7 is rotated to drive the movable rod 6 to move inwards, the aircraft engine annular part can be fixed through the first tightening groove 102 of the first tightening plate 101 and the second tightening groove 105 of the second tightening plate 104, after preliminary fixing is completed, the movable plate 112 is moved up and down, the auxiliary groove 116 of the auxiliary plate 115 clamps the aircraft engine annular part, and then the second tightening nut 114 and the first tightening nut 113 are respectively rotated to fix the movable plate 112, so that the quick clamping device can be used.
By using the technical scheme of the invention or under the inspired by the technical scheme of the invention, a similar technical scheme is designed by a person skilled in the art, so that the technical effects are achieved, and the technical effects fall into the protection scope of the invention.
Claims (8)
1. The quick clamping in-place device for the vertical lathe machining of the annular part of the aircraft engine is characterized by comprising a rotary disc (1), a through hole (2), a moving plate (3), an adjusting hole (4), a fixing bolt (5), a movable rod (6), a rotary rod (7), a fixing hole (8), a connector (9), an adjustable jacking seat structure (10), a reinforcing and fastening plate structure (11), an auxiliary reinforcing rod structure (12), a rotary ball (13), an anti-slip pad (14) and a groove (15); the through holes (2) are respectively arranged on the upper side and the lower side of the interior of the rotary disk (1); the movable plate (3) is inserted into the through hole (2) and is fixed by the fixing bolt (5); the adjusting holes (4) are respectively formed in the front surface of the moving plate (3) and are in threaded connection with the fixing bolts (5); the movable rod (6) is in threaded connection with the inside of the movable plate (3); the rotating rods (7) are respectively welded at the left end and the right end of the outer wall of the movable rod (6), and meanwhile, rotating balls (13) are welded at the outer sides of the rotating rods (7); the fixing holes (8) are respectively formed in the middle upper side and the middle lower side in the rotary disc (1); the connector (9) is welded at the middle part of the left surface of the rotary disk (1), and a groove (15) is formed in the connector; the adjustable jacking seat structure (10) is arranged on one side of the movable rod (6) opposite to the rotary rod (7); the reinforcing fastening plate structure (11) is arranged in the fixing hole (8) and is used for clamping an aircraft engine annular piece; the reinforcing fastening plate structure (11) comprises a threaded rod (111), a movable plate (112), a first fastening nut (113), a second fastening nut (114), an auxiliary plate (115) and an auxiliary groove (116), wherein the movable plate (112) is sleeved on the outer wall of the threaded rod (111); the first fastening nut (113) and the second fastening nut (114) are respectively in threaded connection with the upper side and the lower side of the outer wall of the threaded rod (111); the auxiliary plate (115) is welded at one side of the right end of the movable plate (112) facing the rotary disk (1), and an auxiliary groove (116) is formed in one side of the inner part facing the rotary disk (1); the auxiliary reinforcing rod structure (12) is arranged on the outer wall of the connector (9); the auxiliary reinforcing rod structure (12) comprises a supporting column (121), a lower sleeve joint seat (122), an upper sleeve joint seat (123), an assembled bearing (124), a rotating seat (125), an inclined seat (126) and a antiskid plate (127); the lower sleeve joint seat (122) and the upper sleeve joint seat (123) are respectively sleeved on the outer wall of the assembled bearing (124) and are connected with each other through bolts; the assembly bearing (124) is sleeved on the outer wall of the connector (9); the rotating seat (125) is welded at the lower end of the lower sleeve seat (122); the antiskid plate (127) is welded at the lower end of the inclined seat (126); the anti-slip pad (14) is inlaid in the middle of the right surface of the rotary disc (1); the adjustable jacking seat structure (10) comprises a first jacking plate (101), a first jacking groove (102), a rotary bearing (103), a second jacking plate (104), a second jacking groove (105) and a fastening bolt (106); the first propping groove (102) is formed in the surface, far away from the movable rod (6), of the first propping plate (101); the second propping plate (104) is sleeved on the outer wall of one side, far away from the movable rod (6), of the first propping plate (101), and meanwhile, a second propping groove (105) is formed in one side, far away from the first propping plate (101), of the second propping plate (104); the fastening bolts (106) are respectively connected with the left side and the right side of the front surface of the second jacking plate (104) close to one side of the first jacking plate (101) in a threaded mode.
2. The quick clamping in place device for vertical lathe machining of an aircraft engine ring according to claim 1, wherein the first tightening groove (102) and the second tightening groove (105) are respectively arranged in an arc shape.
3. The quick clamping in-place device for the vertical lathe machining of the annular part of the aircraft engine according to claim 1, wherein the fastening bolt (106) on the outer wall of the second propping plate (104) is in threaded connection with the first propping plate (101).
4. The quick clamping in-place device for the vertical lathe processing aircraft engine annular piece according to claim 1, wherein the rotary bearing (103) is embedded in the middle part of the first jacking plate (101) close to one side surface of the movable rod (6) and sleeved on the inner side of the movable rod (6).
5. The quick clamping in place device for vertical lathe working of an aircraft engine ring according to claim 1, characterized in that said first fastening nut (113) and second fastening nut (114) are in close contact with the outer wall of the mobile plate (112), respectively.
6. A quick clamping in place device for vertical lathe machining an aircraft engine ring according to claim 1, characterized in that the auxiliary groove (116) inside the auxiliary plate (115) is arranged in an arc shape.
7. The quick clamping in-place device for the vertical lathe machining of the annular part of the aircraft engine according to claim 1, wherein the threaded rod (111) is welded on the inner wall of the fixing hole (8), and the threaded rod (111) is provided with two threaded rods.
8. The quick clamping in-place device for the vertical lathe processing of the annular part of the aircraft engine according to claim 1, wherein the inner sides of the front part and the rear part of the lower sleeve joint seat (122) and the upper sleeve joint seat (123) are respectively welded with rectangular stainless steel blocks, and simultaneously are internally connected with bolts in a threaded manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811049892.9A CN108788808B (en) | 2018-09-10 | 2018-09-10 | Quick clamping device for machining annular part of aircraft engine by vertical lathe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811049892.9A CN108788808B (en) | 2018-09-10 | 2018-09-10 | Quick clamping device for machining annular part of aircraft engine by vertical lathe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108788808A CN108788808A (en) | 2018-11-13 |
| CN108788808B true CN108788808B (en) | 2024-06-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811049892.9A Active CN108788808B (en) | 2018-09-10 | 2018-09-10 | Quick clamping device for machining annular part of aircraft engine by vertical lathe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108788808B (en) |
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| EP1810791A2 (en) * | 2006-01-23 | 2007-07-25 | Klann Spezial-Werkzeugbau GmbH | Device for compressing a coil spring of a suspension strut |
| TWM471956U (en) * | 2013-11-01 | 2014-02-11 | Chuan-Mao Huang | Tool for detaching vehicle pulley |
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| CN104552075A (en) * | 2015-01-26 | 2015-04-29 | 张世云 | Frame mounting clamp and using method thereof |
| CN108340173A (en) * | 2018-03-02 | 2018-07-31 | 苏州市昌星模具机械有限公司 | A kind of efficient high-precision fixture and its clamping method of undercarriage holder |
| CN209110577U (en) * | 2018-09-10 | 2019-07-16 | 贵州欣佰亿实业有限公司 | A kind of quick-clamping of vertical lathe processing aircraft engine annular element device in place |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10245653B2 (en) * | 2016-08-12 | 2019-04-02 | Robert James Suhling | Modular tubing notcher system |
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2018
- 2018-09-10 CN CN201811049892.9A patent/CN108788808B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1810791A2 (en) * | 2006-01-23 | 2007-07-25 | Klann Spezial-Werkzeugbau GmbH | Device for compressing a coil spring of a suspension strut |
| TWM471956U (en) * | 2013-11-01 | 2014-02-11 | Chuan-Mao Huang | Tool for detaching vehicle pulley |
| CN104260042A (en) * | 2014-09-23 | 2015-01-07 | 安徽六国化工股份有限公司 | Device for online replacing speed-regulation type hydraulic coupler execution mechanism |
| CN104552075A (en) * | 2015-01-26 | 2015-04-29 | 张世云 | Frame mounting clamp and using method thereof |
| CN108340173A (en) * | 2018-03-02 | 2018-07-31 | 苏州市昌星模具机械有限公司 | A kind of efficient high-precision fixture and its clamping method of undercarriage holder |
| CN209110577U (en) * | 2018-09-10 | 2019-07-16 | 贵州欣佰亿实业有限公司 | A kind of quick-clamping of vertical lathe processing aircraft engine annular element device in place |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108788808A (en) | 2018-11-13 |
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