CN108788808A - A kind of quick-clamping of vertical lathe processing aircraft engine annular element device in place - Google Patents
A kind of quick-clamping of vertical lathe processing aircraft engine annular element device in place Download PDFInfo
- Publication number
- CN108788808A CN108788808A CN201811049892.9A CN201811049892A CN108788808A CN 108788808 A CN108788808 A CN 108788808A CN 201811049892 A CN201811049892 A CN 201811049892A CN 108788808 A CN108788808 A CN 108788808A
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- quick
- aircraft engine
- annular element
- place
- out against
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- 230000002787 reinforcement Effects 0.000 claims abstract description 14
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 11
- 238000003825 pressing Methods 0.000 claims description 42
- 230000000694 effects Effects 0.000 claims description 6
- 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 2
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
Abstract
The present invention provides a kind of quick-clamping device, including rotating disk in place of vertical lathe processing aircraft engine annular element, through-hole, movable plate, adjustment hole, fixing bolt, motion bar, swingle, mounting hole, connector, it is adjustable to hold out against holder structure, reinforce fastening harden structure, additional reinforcement rod structure, screw, non-slip mat and groove, the through-hole are opened in two up and down inside rotating disk respectively；The movable plate is plugged in through-hole, and is fixed by fixing bolt.Beneficial effects of the present invention are：Pass through the adjustable setting for holding out against holder structure, be conducive to more fasten fixes aircraft engine annular element, and more convenient use this adjustable hold out against holder structure, the setting of harden structure is fastened by reinforcing, be conducive to easily clamp aircraft engine annular element, and the tightness of quick-clamping device in place is increased, and then avoid the problem that quick-clamping device appearance in place falls off easily.
Description
Technical field
The invention belongs to clamping apparatus technical fields more particularly to a kind of vertical lathe to process aircraft engine annular element
Quick-clamping device in place.
Background technology
Aircraft engine annular element is extremely common workpiece in aircraft engine production, when the diameter of the annular workpieces of processing
It is larger, it when thickness is smaller, easily deforms in processing, it is therefore desirable to which a kind of device of clip-like, the prior art are Chinese patent
Technical solution is used by a kind of annular workpieces clamp for machining of Publication No. CN201610093787.X：It is pressed from both sides including three
Head, bottom plate and screw rod, the collet are sector, which is 120 °, it is characterised in that：Collet includes vertical fixture block and water
Flat supporting table, vertical fixture block are fixedly connected with level support platform, and the radius of vertical fixture block is less than the radius of level support platform, and two
The semidiameter of person is greater than or equal to the ring hem width degree of annular workpieces, and the height of vertical fixture block is more than the height of level support platform, and
The difference in height of the two is greater than or equal to the thickness of annular workpieces, and the level support platform bottom is equipped with sliding block, sliding block and the bottom of set on
Sliding slot on plate is slidably matched, and screw rod connect with base thread and puts in sliding slot and is fixedly connected with a slide block, the axis and cunning of screw rod
The axis of slot is consistent, have process radial dimension be much larger than axial dimension annular workpieces when, can reducing deformation, reach
The advantages of processing request.
But there is also be inconvenient to fix different size of aircraft engine ring for device in place for existing quick-clamping
Shape part, the device do not have the problem of playing the role of support and fastening effect difference and being inconvenient to increase fixed mode.
Therefore, inventing the quick-clamping of vertical lathe processing aircraft engine annular element a kind of, device seems and very must in place
It wants.
Invention content
In order to solve the above technical problem, the present invention provides a kind of vertical lathes to process the quick of aircraft engine annular element
Clamping device in place, to solve existing quick-clamping, device is inconvenient to fix different size of aircraft engine annular in place
Part, the device do not have the problem of playing the role of support and fastening effect difference and being inconvenient to increase fixed mode.One kind is vertical
The quick-clamping device, including rotating disk in place of formula lathe process aircraft engine annular element, through-hole, movable plate, adjustment hole, Gu
Determine bolt, motion bar, swingle, mounting hole, connector is adjustable to hold out against holder structure, reinforces fastening harden structure, additional reinforcement bar
Structure, screw, non-slip mat and groove, the through-hole are opened in two up and down inside rotating disk respectively；The movement
Plate is plugged in through-hole, and is fixed by fixing bolt；The adjustment hole is opened in the front surface of movable plate respectively, and with
Fixing bolt is threadedly coupled；The motion bar is threaded in the inside of movable plate；The swingle is respectively welded at work
The left and right ends of lever outer wall, while screw is welded on the outside of swingle；The mounting hole is opened in rotation respectively
Middle upside inside disk and middle downside；The connector is welded on the intermediate position of rotating disk left surface, while being opened in inside
Equipped with groove；The adjustable inside for holding out against holder structure and being mounted on motion bar；The reinforcing fastening harden structure is mounted on
In mounting hole；The additional reinforcement rod structure is mounted on the outer wall of connector；The non-slip mat is embedded in the rotating disk right side
The intermediate position on surface；The described adjustable holder structure that holds out against includes the first pressing tight plate, and first holds out against slot, swivel bearing, and second
Pressing tight plate, second holds out against slot and fastening bolt, and described first holds out against the lower surface that slot is opened in the first pressing tight plate；Described
Two pressing tight plates are socketed in the lower part of the first pressing tight plate outer wall, while the lower section inside the second pressing tight plate offers second and holds out against
Slot；The fastening bolt is threaded in the left and right sides on the second pressing tight plate front surface top respectively.
Preferably, reinforcing fastening harden structure includes threaded rod, movable plate, the first fastening nut, the second fastening spiral shell
Mother, accessory plate and auxiliary tank, the movable plate are socketed on the outer wall of threaded rod；First fastening nut and second is tightly
Gu nut is threaded in two up and down of threaded rod outer wall respectively；The accessory plate is welded on the upper right quarter of movable plate, together
When in internal top offer auxiliary tank.
Preferably, the additional reinforcement rod structure includes support column, lower covered joint seat, upper covered joint seat, assembles bearing, rotation
Seat, inclined seat and antiskid plate, the lower covered joint seat and upper covered joint seat are socketed in respectively on the outer wall of assembling bearing, and mutual spiral shell
It tethers and connects；The assembling bearing is socketed on the outer wall of connector；The rotating seat is welded on the lower end of lower covered joint seat；Institute
The antiskid plate stated is welded on the lower end of inclined seat.
Preferably, it described first holds out against slot and second and holds out against slot and be respectively set to arc.
Preferably, the fastening bolt of the second pressing tight plate outer wall is threadedly coupled with the first pressing tight plate.
Preferably, the swivel bearing is embedded in the intermediate position of the first pressing tight plate upper surface, and is socketed in motion bar
Inside.
Preferably, first fastening nut and the second fastening nut are in close contact with the outer wall of movable plate respectively.
Preferably, the auxiliary tank inside the accessory plate is set as arc.
Preferably, the threaded rod is welded on the inner wall of mounting hole, and there are two threaded rod settings.
Preferably, two insides are respectively welded rectangle piece of stainless steel before and after the lower covered joint seat and upper covered joint seat,
Simultaneously bolt is threaded in inside.
Preferably, the support column upper and lower ends are bolted with rotating seat and inclined seat respectively.
Compared with prior art, beneficial effects of the present invention are：
1. in the present invention, described first, which holds out against slot and second, holds out against slot and is respectively set to arc, and be conducive to more fasten consolidates
Surely live aircraft engine annular element, and more convenient use this adjustable hold out against holder structure.
2. in the present invention, the fastening bolt of the second pressing tight plate outer wall is threadedly coupled with the first pressing tight plate, is conducive to
Convenient the second pressing tight plate of assembly and disassembly and the first pressing tight plate, and easily fix different size of aircraft engine annular
Part.
3. in the present invention, the swivel bearing is embedded in the intermediate position of the first pressing tight plate upper surface, and is socketed in work
The inside of lever, be conducive to easily to install this it is adjustable hold out against holder structure, while the rotation being also convenient for is adjustable holds out against seat knot
Structure, and then this is more reasonably made adjustable to hold out against holder structure and fix aircraft engine annular element.
4. in the present invention, first fastening nut and the second fastening nut closely connect with the outer wall of movable plate respectively
It touches, is conducive to easily fix movable plate, and the position between more convenient socket movable plate and movable plate.
5. in the present invention, the auxiliary tank inside the accessory plate is set as arc, be conducive to easily clamp aircraft hair
Motivation annular element, and increase the tightness of quick-clamping device in place, so avoid quick-clamping in place device occur it is light
The problem of easily falling off.
6. in the present invention, the threaded rod is welded on the inner wall of mounting hole, there are two threaded rod settings, has
Harden structure is fastened conducive to more reasonably using or reconciling the reinforcing.
7. in the present invention, two insides are respectively welded rectangle stainless steel before and after the lower covered joint seat and upper covered joint seat
Block, while bolt is threaded in inside, be conducive to it is more convenient fix assembling bearing, and more reasonably use this auxiliary
Help reinforcing rod structure.
8. in the present invention, the support column upper and lower ends are bolted with rotating seat and inclined seat respectively, the side of being conducive to
Just the angle of inclined shore column, while the support that is also convenient for and using the additional reinforcement rod structure.
Description of the drawings
Fig. 1 is the structural schematic diagram of the present invention.
Fig. 2 is the adjustable structural schematic diagram for holding out against holder structure of the present invention.
Fig. 3 is the structural schematic diagram of the reinforcing fastening harden structure of the present invention.
Fig. 4 is the structural schematic diagram of the additional reinforcement rod structure of the present invention.
In figure：
1, rotating disk；2, through-hole；3, movable plate；4, adjustment hole；5, fixing bolt；6, motion bar；7, swingle；8, mounting hole；
9, connector；10, it is adjusted and holds out against holder structure；101, the first pressing tight plate；102, first slot is held out against；103, swivel bearing；104,
Second pressing tight plate；105, second slot is held out against；106, fastening bolt；11, fastening harden structure is reinforced；111, threaded rod；112, movable
Plate；113, the first fastening nut；114, the second fastening nut；115, accessory plate；116, auxiliary tank；12, additional reinforcement rod structure；
121, support column；122, lower covered joint seat；123, upper covered joint seat；124, bearing is assembled；125, rotating seat；126, inclined seat；127,
Antiskid plate；13, screw；14, non-slip mat；15, groove.
Specific implementation mode
The present invention is described further below in conjunction with attached drawing：
Embodiment：
As shown in Figure 1 and Figure 2, the quick-clamping of a kind of vertical lathe processing aircraft engine annular element device in place, packet
Rotating disk 1 is included, through-hole 2, movable plate 3, adjustment hole 4, fixing bolt 5, motion bar 6, swingle 7, mounting hole 8, connector 9 can
Adjusting holds out against holder structure 10, reinforces fastening harden structure 11, additional reinforcement rod structure 12, screw 13, non-slip mat 14 and groove 15,
The through-hole 2 is opened in two up and down inside rotating disk 1 respectively；The movable plate 3 is plugged in through-hole 2, and is passed through
Fixing bolt 5 is fixed；The adjustment hole 4 is opened in the front surface of movable plate 3 respectively, and is threadedly coupled with fixing bolt 5,
Movable plate 3 can easily be adjusted in the length on the right side of rotating disk 1, and more reasonably make the quick-clamping device is fixed in place
Firmly smaller aircraft engine annular element；The motion bar 6 is threaded in the inside of movable plate 3；The swingle 7 divides
It is not welded on the left and right ends of 6 outer wall of motion bar, while screw 13 is welded in the outside of swingle 7；The mounting hole 8
The middle upside and middle downside being opened in respectively inside rotating disk 1；The connector 9 is welded on the centre of 1 left surface of rotating disk
Position, while offering groove 15 in inside；And more convenient installation quick-clamping device in place；The adjustable top
Tight holder structure 10 is mounted on the inside of motion bar 6；The reinforcing fastening harden structure 11 is mounted in mounting hole 8；Described is auxiliary
It helps and reinforces rod structure 12 on the outer wall of connector 9；The non-slip mat 14 is embedded in the middle part on 1 right surface of rotating disk
Position, can play aircraft engine annular element anti-skidding effect；The adjustable holder structure 10 that holds out against is held out against including first
Plate 101, first holds out against slot 102, and swivel bearing 103, the second pressing tight plate 104, second holds out against slot 105 and fastening bolt 106, described
First hold out against the lower surface that slot 102 is opened in the first pressing tight plate 101；The swivel bearing 103 is embedded in the first pressing tight plate
The intermediate position of 101 upper surfaces, and be socketed in the inside of motion bar 6 is conducive to easily to install this and adjustable holds out against holder structure
10, while the rotation being also convenient for is adjusted and holds out against holder structure 10, and then more reasonably consolidate the adjustable holder structure 10 that holds out against
Surely aircraft engine annular element is lived；Second pressing tight plate 104 is socketed in the lower part of 101 outer wall of the first pressing tight plate, while
Lower section inside second pressing tight plate 104 offers second and holds out against slot 105；The fastening bolt of second pressing tight plate, 104 outer wall
106 are threadedly coupled with the first pressing tight plate 101, are conducive to convenient assembly and disassembly the second pressing tight plate 104 and the first pressing tight plate
101, and easily fix different size of aircraft engine annular element；The fastening bolt 106 is threaded in respectively
The left and right sides on 104 front surface top of the second pressing tight plate；When adjusting, loosen fastening bolt 106, then pulls the second pressing tight plate
104 can detach with the first pressing tight plate 101, be can be completed in this way to the adjustable adjusting for holding out against holder structure 10.
As shown in Fig. 3, in above-described embodiment, specifically, the reinforcing fastening harden structure 11 includes threaded rod 111,
Movable plate 112, the first fastening nut 113, the second fastening nut 114, accessory plate 115 and auxiliary tank 116, the threaded rod
111 are welded on the inner wall of mounting hole 8, and there are two the threaded rod 111 settings, is conducive to more reasonably use or reconcile
The reinforcing fastens harden structure 11；The movable plate 112 is socketed on the outer wall of threaded rod 111；First fastening nut
113 and second fastening nut 114 be threaded in two up and down of 111 outer wall of threaded rod respectively；The accessory plate 115 welds
Auxiliary tank 116 is offered in the upper right quarter of movable plate 112, while in internal top；Auxiliary inside the accessory plate 115
Slot 116 is set as arc, be conducive to easily clamp aircraft engine annular element, and increases quick-clamping device in place
Tightness, and then avoid the problem that quick-clamping device appearance in place falls off easily.
As shown in Fig. 4, in above-described embodiment, specifically, the additional reinforcement rod structure 12 includes support column 121,
Lower covered joint seat 122, upper covered joint seat 123 assemble bearing 124, rotating seat 125, inclined seat 126 and antiskid plate 127, the support
121 upper and lower ends of column are bolted with rotating seat 125 and inclined seat 126 respectively, are conducive to the angle of convenient inclined shore column 121
Degree, while the support that is also convenient for and using the additional reinforcement rod structure 12；The lower covered joint seat 122 and upper covered joint seat 123 divides
It is not socketed on the outer wall of assembling bearing 124, and is mutually bolted；The assembling bearing 124 is socketed in the outer of connector 9
On wall；The rotating seat 125 is welded on the lower end of lower covered joint seat 122；The antiskid plate 127 is welded on inclined seat 126
Lower end；In use, moving up and down movable plate 112 and the auxiliary tank 116 of accessory plate 115 being made to clamp aircraft engine annular element, so
It rotates the second fastening nut 114 respectively afterwards and the first fastening nut 113 fixes movable plate 112,.
In above-described embodiment, specifically, described first holds out against slot 102 and second and holds out against slot 105 and be respectively set to arc,
Be conducive to more fasten fixes aircraft engine annular element, and more convenient use this adjustable hold out against holder structure 10.
In above-described embodiment, specifically, first fastening nut 113 and the second fastening nut 114 respectively with activity
The outer wall of plate 112 is in close contact, and is conducive to easily fix movable plate 112, and more convenient socket movable plate 112 and work
Position between movable plate 112.
In above-described embodiment, specifically, two insides are distinguished before and after the lower covered joint seat 122 and upper covered joint seat 123
It is welded with rectangle piece of stainless steel, while bolt is threaded in inside, is conducive to more convenient fix and assembles bearing 124,
And more reasonably use the additional reinforcement rod structure 12.
Operation principle
The operation principle of the present invention：Connector 9 and groove 15 is set to be connect with specified equipment first, then by upper covered joint seat 123
It is sleeved on lower covered joint seat 122 on the outer wall of assembling bearing 124, while inclined shore column 121 therewith, and makes antiskid plate 127 and ground
Face or equipment contact, subsequently tighten the bolt in inclined seat 126 and rotating seat 125 and can support the quick-clamping and arrive respectively
Aircraft engine annular element is placed into first first and holds out against slot 102 and second and hold out against in slot 105 by position device when in use
Then side rotating rotary rods 7 and drives motion bar 6 to move inward can to hold out against 102 He of slot by the first of the first pressing tight plate 101
The second of second pressing tight plate 104 holds out against slot 105 and fixes aircraft engine annular element, after completing preliminary fix, moves up and down work
Movable plate 112 simultaneously makes the auxiliary tank 116 of accessory plate 115 clamp aircraft engine annular element, then rotates the second fastening nut respectively
114 and first fastening nut 113 fix movable plate 112, can be used in this way.
Using technical solutions according to the invention or those skilled in the art under the inspiration of technical solution of the present invention,
Similar technical solution is designed, and reaches above-mentioned technique effect, is to fall into protection scope of the present invention.
Claims (10)
1. a kind of quick-clamping of vertical lathe processing aircraft engine annular element device in place, which is characterized in that the vertical vehicle
The quick-clamping device, including rotating disk in place of bed processing aircraft engine annular element（1）, through-hole（2）, movable plate（3）, adjust
Hole（4）, fixing bolt（5）, motion bar（6）, swingle（7）, mounting hole（8）, connector（9）, adjustable to hold out against holder structure
（10）, reinforce fastening harden structure（11）, additional reinforcement rod structure（12）, screw（13）, non-slip mat（14）And groove（15）, institute
The through-hole stated（2）It is opened in rotating disk respectively（1）Internal two up and down；The movable plate（3）It is plugged on through-hole（2）It is interior,
And pass through fixing bolt（5）It fixes；The adjustment hole（4）It is opened in movable plate respectively（3）Front surface, and with fixed spiral shell
Bolt（5）It is threadedly coupled；The motion bar（6）It is threaded in movable plate（3）Inside；The swingle（7）It welds respectively
It is connected on motion bar（6）The left and right ends of outer wall, while in swingle（7）Outside be welded with screw（13）；The fixation
Hole（8）It is opened in rotating disk respectively（1）Internal middle upside and middle downside；The connector（9）It is welded on rotating disk（1）It is left
The intermediate position on surface, while offering groove in inside（15）；It is described adjustable to hold out against holder structure（10）Mounted on activity
Bar（6）Inside；The reinforcing fastens harden structure（11）Mounted on mounting hole（8）It is interior；The additional reinforcement rod structure
（12）Mounted on connector（9）Outer wall on；The non-slip mat（14）It is embedded in rotating disk（1）The intermediate position on right surface；
It is described adjustable to hold out against holder structure（10）Including the first pressing tight plate（101）, first holds out against slot（102）, swivel bearing（103）,
Second pressing tight plate（104）, second holds out against slot（105）And fastening bolt（106）, described first holds out against slot（102）It is opened in
One pressing tight plate（101）Lower surface；Second pressing tight plate（104）It is socketed in the first pressing tight plate（101）The lower part of outer wall, together
When in the second pressing tight plate（104）Internal lower section offers second and holds out against slot（105）；The fastening bolt（106）Spiral shell respectively
Line is connected to the second pressing tight plate（104）The left and right sides on front surface top.
2. the quick-clamping of vertical lathe as described in claim 1 processing aircraft engine annular element device in place, feature
It is, the reinforcing fastens harden structure（11）Including threaded rod（111）, movable plate（112）, the first fastening nut（113）, the
Two fastening nuts（114）, accessory plate（115）And auxiliary tank（116）, the movable plate（112）It is socketed in threaded rod（111）'s
On outer wall；First fastening nut（113）With the second fastening nut（114）It is threaded in threaded rod respectively（111）Outside
Two up and down of wall；The accessory plate（115）It is welded on movable plate（112）Upper right quarter, while being opened up in internal top
There is auxiliary tank（116）.
3. the quick-clamping of vertical lathe as described in claim 1 processing aircraft engine annular element device in place, feature
It is, the additional reinforcement rod structure（12）Including support column（121）, lower covered joint seat（122）, upper covered joint seat（123）, assembling
Bearing（124）, rotating seat（125）, inclined seat（126）And antiskid plate（127）, the lower covered joint seat（122）With upper covered joint seat
（123）It is socketed in assembling bearing respectively（124）Outer wall on, and be mutually bolted；The assembling bearing（124）It is socketed in
Connector（9）Outer wall on；The rotating seat（125）It is welded on lower covered joint seat（122）Lower end；The antiskid plate
（127）It is welded on inclined seat（126）Lower end.
4. the quick-clamping of vertical lathe as described in claim 1 processing aircraft engine annular element device in place, feature
It is, described first holds out against slot（102）Slot is held out against with second（105）It is respectively set to arc.
5. the quick-clamping of vertical lathe as described in claim 1 processing aircraft engine annular element device in place, feature
It is, second pressing tight plate（104）The fastening bolt of outer wall（106）With the first pressing tight plate（101）It is threadedly coupled.
6. the quick-clamping of vertical lathe as described in claim 1 processing aircraft engine annular element device in place, feature
It is, the swivel bearing（103）It is embedded in the first pressing tight plate（101）The intermediate position of upper surface, and it is socketed in motion bar
（6）Inside.
7. the quick-clamping of vertical lathe as claimed in claim 2 processing aircraft engine annular element device in place, feature
It is, first fastening nut（113）With the second fastening nut（114）Respectively with movable plate（112）Outer wall closely connect
It touches.
8. the quick-clamping of vertical lathe as claimed in claim 2 processing aircraft engine annular element device in place, feature
It is, the accessory plate（115）Internal auxiliary tank（116）It is set as arc.
9. the quick-clamping of vertical lathe as claimed in claim 2 processing aircraft engine annular element device in place, feature
It is, the threaded rod（111）It is welded on mounting hole（8）Inner wall on, the threaded rod（111）There are two settings.
10. the quick-clamping of vertical lathe as claimed in claim 3 processing aircraft engine annular element device in place, feature
It is, the lower covered joint seat（122）With upper covered joint seat（123）Front and back two insides are respectively welded rectangle piece of stainless steel,
Simultaneously bolt is threaded in inside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811049892.9A CN108788808A (en) | 2018-09-10 | 2018-09-10 | A kind of quick-clamping of vertical lathe processing aircraft engine annular element device in place |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811049892.9A CN108788808A (en) | 2018-09-10 | 2018-09-10 | A kind of quick-clamping of vertical lathe processing aircraft engine annular element device in place |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108788808A true CN108788808A (en) | 2018-11-13 |
Family
ID=64082210
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811049892.9A Pending CN108788808A (en) | 2018-09-10 | 2018-09-10 | A kind of quick-clamping of vertical lathe processing aircraft engine annular element device in place |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108788808A (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 |
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| 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 |
| US20180043439A1 (en) * | 2016-08-12 | 2018-02-15 | Robert James Suhling | Modular Tubing Notcher System |
| 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 |
-
2018
- 2018-09-10 CN CN201811049892.9A patent/CN108788808A/en active Pending
Patent Citations (7)
| 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 |
| US20180043439A1 (en) * | 2016-08-12 | 2018-02-15 | Robert James Suhling | Modular Tubing Notcher System |
| 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 |
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