CN108057997B - A kind of extension box side turbine hole forming method of minicar gearbox - Google Patents
A kind of extension box side turbine hole forming method of minicar gearbox Download PDFInfo
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- CN108057997B CN108057997B CN201711397870.7A CN201711397870A CN108057997B CN 108057997 B CN108057997 B CN 108057997B CN 201711397870 A CN201711397870 A CN 201711397870A CN 108057997 B CN108057997 B CN 108057997B
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- turbine
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- extension box
- minicar
- gearbox
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- 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
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/50—Other automobile vehicle parts, i.e. manufactured in assembly lines
Abstract
The invention belongs to technical fields of mechanical processing, disclose a kind of extension box side turbine hole forming method of minicar gearbox, select vertical processing, and roughing selects 16 machine of Ф to press from both sides slotting cutter, and finishing uses special Combined hard-alloy reamer；Diesel oil is cooled down；It selects datum level and two dowel holes as positioning datum, is positioned by the way of the additional top of plane and two pits；When roughing, programming coordinates origin is overlapped with turbine axis hole center, Z-direction, and turbine axis hole aperture face is set as zero point；Milling is carried out using 16 machine of Ф folder vertical milling cutter, F value takes 100；Programming coordinates origin is overlapped by finishing with the setting of turbine axis hole center, and Z-direction, turbine axis hole aperture face is set as zero point；Ream machining is carried out using special Combined hard-alloy reamer, and is one-pass molding.Present invention can ensure that existing " the allow knife " phenomenon of can't process for the turbine axis hole, and position precision, dimensional accuracy, finish etc. are attained by requirement.
Description
Technical field
The invention belongs to technical field of mechanical processing more particularly to a kind of extension box side turbines of minicar gearbox
Hole forming method.
Background technique
The gearbox of minicar is an indispensable important component of automobile, the effect of gear box casing be by
The related parts such as axis, set, gear in machine and component are unified into an entirety, and are allowed to keep correct relative position, each other
Co-ordination, with the predetermined function for transmitting power, changing speed, completing machine or component.Box parts require to have enough strong
Degree and rigidity, good leakproofness and thermal diffusivity.Therefore, the processing quality of box parts directly affects the performance of machine, precision
And the service life.The existing processing scheme of side turbine bore: the turbine axis hole is a cone step blind hole (such as Fig. 1), the hole Ф 23H9 and Ф
The hole 22H9 is connected by 10 ° of taper holes, and the hole Ф 23H9 and the hole Ф 22H9 hole wall surface roughness Ra are 1.6, and the surface of countersunk portion is thick
Rugosity Ra is 6.3.20 ° of orifice chamfer of the hole Ф 23H9, surface roughness Ra 6.3.Ф 23H9 hole depth be 16mm, countersunk portion and
Ф 22H9 hole depth is 46mm, and the linear distance at the hole the Ф 62H7 center in center and vertical hole system is 28.5+0.150mm.Turbine
Axis hole center line and Y-axis (such as Fig. 1) axis both clockwise angle are 30 °.Turbine axis hole center is at a distance from datum level (such as Fig. 2)
117.5±0.1mm.Since the workpiece is cast blank part, the surplus of turbine axis hole is in 2-3mm, total depth 62mm, Er Qieyou
In the hole the location of on part relationship, cause process tool overall length just to can guarantee up to 150mm or so in the feelings for not hitting knife
Processing is completed under condition.The side turbine bore directlys adopt 16 machine of Ф folder slotting cutter at present and carries out milling, and feed mode is under spiral
Knife is divided into roughing and finishes the processing that two procedures complete entire hole, and roughing and finishing are all vertical using 16 machine of Ф folder
Milling cutter.Cutter is long, is easy to appear " allow knife " deformation in process.Cause it is processed after turbine bore occur it is upper big
Under small phenomenon, be easy to happen vibration, cause it is processed after turbine hole wall there is chatter mark, make dimensional accuracy and surface roughness
All it is unable to reach technical requirements.So on clamping and machining accuracy control, there are great difficulties.
In conclusion problem of the existing technology is: since cutter is long, being easy to appear " allow in process
Knife " deformation, cause it is processed after turbine bore there is up big and down small phenomenon.Be easy to happen vibration, cause it is processed after
There is chatter mark in turbine hole wall, and dimensional accuracy and surface roughness is made all to be unable to reach technical requirements.Furthermore due to front two because
Element, will lead to cutter life shortening, and product qualification rate substantially reduces.Tool changing debug time greatly increases.
Summary of the invention
In view of the problems of the existing technology, the present invention provides a kind of extension box side turbines of minicar gearbox
Hole forming method.
The invention is realized in this way a kind of extension box side turbine hole forming method of minicar gearbox, described
The extension box side turbine hole forming method of minicar gearbox the following steps are included:
Step 1 selects vertical machining centre to be processed, and roughing selects 16 machine of Ф to press from both sides slotting cutter, and finishing is using special
Combined hard-alloy reamer processed；Diesel oil is cooled down；
Step 2 selects datum level and two dowel holes as positioning datum, by the way of the additional top of plane and two pits
It is positioned；When carrying out side turbine bore manufacturing procedure, datum level and two processing dowel holes have been completed the process.Cause
This, selects datum level and two dowel holes as positioning datum.Positioned by the way of the additional top of plane and two pits, it should
Set and Positioning mode limits 6 freedom degrees.A top on one side, limits 3 freedom degrees, moves along X, rotates around Z rotation, around Y.Two
A positioning pin must be a straight pin and a rhombus pin, otherwise can cross positioning, the centers of 2 location holes away from two pin centers
Away from can not be completely the same, the effect of rhombus pin both exactly " get out of the way " center away from error, eliminate installation interference, limitation workpiece around
X rotation, the long axis of rhombus pin must be perpendicular to the line of centres of two pin holes；Straight pin limitation workpiece is moved along Z, Y.Meanwhile the dress
Folder fixture must rotate counterclockwise 30 ° of installations along X-axis to be fixed, and guarantees that turbine centerline hole is parallel with machine tool chief axis axial line.
Step 3, when roughing, programming coordinates origin is overlapped with turbine axis hole center, Z-direction, turbine axis hole aperture face
It is set as zero point；Milling is carried out using the machine folder vertical milling cutter of Ф 16, F value takes 100；Using UG software by the three-dimensional mould of the part
Type is drawn, and then carries out program composition using software automatic programming function itself.Before programming, workpiece origin is arranged in whirlpool
At axle hole center, the reset of Z-direction is in turbine axis hole whirlpool aperture face.The machine of Ф 16 is selected to press from both sides vertical milling cutter, feeding
Speed chooses F100, and plunge cut way cuts for spiral.It is unilateral to stay chipping allowance 0.2mm.
Programming coordinates origin is overlapped by step 4, finishing with the setting of turbine axis hole center, Z-direction, turbine axis hole hole
Mouth face is set as zero point；Ream machining is carried out using special Combined hard-alloy reamer, and is one-pass molding.Finishing
When, due to using integrated combination reamer, the cutter be it is special according to technology acuracy requirement, can be with one-pass molding.Institute
Only to need to guarantee that cutter feeds downwardly into size positions along central axis when, cutting.Using side instrument is sought to knife, will program
Origin is arranged at turbine axis hole center, and the reset of Z axis direction is in turbine axis hole aperture face.Manual programming.
Further, Set and Positioning limits 6 freedom degrees in the step 2, and a top, limits 3 freedom degrees on one side, moves along X
It moves, rotated around Z rotation, around Y；Two positioning pins must be a straight pin and a rhombus pin；The long axis of rhombus pin must hang down
Directly in the line of centres of two pin holes；Straight pin limitation workpiece is moved along Z, Y；30 ° of installations are rotated counterclockwise along X-axis to fix.
Further, the extension box side turbine hole forming method of the minicar gearbox uses 4 block pressur plates by tooling
It is installed on the T-type workbench of machining center；Amesdial gauge stand is drawn on machine tool chief axis, and amesdial contact head contacts tooling base
Long side, indicator rotate 0.5mm, amesdial are returned to zero；Under lathe manual mode, move back and forth workbench along X-axis, according to thousand points
List index change conditions adjust tooling position, until amesdial pointer changes within the scope of 0.02mm；
The extension box of datum level out will be added to be installed in tooling；Turbine hole machined uses two cutters, No. 1 cutter conduct
Basic-cutter measures the offset of No. 2 cutters using tool setting gauge, will be on No. 1 Cutting tool installation manner to main shaft and No. 2 Cutting tool installation manners are to knife
In library；Start lathe, No. 1 cutter is carried out to knife, and will be to knife parameter typing lathe numerical control device；No. 1 cutter finishes knife
Afterwards, cutter compensation parameter setting is carried out to No. 2 cutters；
Check coolant liquid, procedure simulation track, conditions of machine tool, it is ensured that after errorless, start good program prepared in advance, carry out
Machining.
Further, the extension box side turbine hole forming method of the minicar gearbox is according to extension box drawing technology
Parameter draws extension box threedimensional model according to 1:1 ratio using UG software peace on computers, in the automated programming module of UG software
Carry out machining tool model, Workpiece zero point, cutter parameters, cutter path track, feed mode；Analogue simulation is carried out, has been checked
Zero defect, and adjustment of modifying, derivation program；Derived program finely tune further according to actual conditions；It will be complete
In the machining center digital control systems to be processed such as program importing.
Another object of the present invention is to provide a kind of extension box side turbines using the minicar gearbox
The automobile gearbox of hole forming method processing.
Phenomena such as present invention carries out processing turbine axis hole, can be to avoid cutter in existing scheme " allow knife " " vibration ", completely
It can guarantee the requirement on machining accuracy such as turbine pore size, surface roughness, verticality；The single-piece work time can shorten 2 minutes；It produces
Product qualification rate improves 20%；The turbine aperture knife tool service life extends 17 hours.By it was verified that improving it
Processing method and Cutting Process reasonably select machine tool, cutting tool and coolant liquid etc., can guarantee the turbine wheel shaft completely
Existing " the allow knife " phenomenon of can't process for hole, and position precision, dimensional accuracy, finish etc. are attained by requirement.It is equally applicable to
The processing in like parts hole.
The present invention using 16 machine of Ф press from both sides slotting cutter and special Combined hard-alloy reamer cooperation processing mode into
The Milling Process of the row side turbine bore, and when finishing, it is integrated combined type reamer, cutter is along turbine axially bored line
Straight-line feed just solves " allow knife " phenomenon in existing scheme, also there is no vibrations, just there is no " allow knife " deformation
Solve the problems, such as in existing scheme vibration caused by precision it is not up to standard.Present invention program in finishing is more existing
Scheme is more brief, so, substantially reduce process time.Simultaneously as without " allow knife " and " vibration " etc. in existing scheme
Phenomenon, cutter life are also extended, and product qualification rate is also increased dramatically.It is then the extension box of gear box casing
Important component, effect is assembly turbine and turbine wheel shaft, guarantees turbine and the correct relative position of turbine wheel shaft, each other can
Co-ordination, while rubber seal cooperates on turbine bore and turbine wheel shaft, plays sealing function.So processing the turbine
When hole, it is necessary to guarantee its technology acuracy.
Detailed description of the invention
Fig. 1 is the extension box side turbine hole forming method process of minicar gearbox provided in an embodiment of the present invention
Figure.
Fig. 2 is that axis both clockwise angle provided in an embodiment of the present invention is 30 ° of schematic diagrames.
Fig. 3 is turbine axis hole provided in an embodiment of the present invention center and datum level schematic diagram.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to embodiments, to the present invention
It is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, it is not used to
Limit the present invention.
With the continuous development of China's economy, the continuous improvement of quality of life, the pursuit that the people live to high-quality is more next
It is more urgent, it is especially even more growing day by day to the demand of minicar this vehicles.And Chinese Automobile Industry ' is by close
The development of decades either has all obtained significantly being promoted very much, state from scope of the enterprise, product technology, product quality
The competitiveness for producing automobile mechanical component product is also constantly enhancing, and is gradually substituting import.
Application principle of the invention is explained in detail with reference to the accompanying drawing.
As shown in Figure 1, the extension box side turbine hole forming method of minicar gearbox provided in an embodiment of the present invention
The following steps are included:
S101: selection vertical machining centre is processed, and roughing selects 16 machine of Ф to press from both sides slotting cutter, and finishing is using special
Combined hard-alloy reamer；Diesel oil is cooled down；
S102: selecting datum level and two dowel holes to be used as positioning datum, in such a way that plane and two pits additional one push up into
Row positioning；
S103: when roughing, programming coordinates origin is overlapped with turbine axis hole center, Z-direction, and turbine axis hole aperture face is set
It is set to zero point；Milling is carried out using the machine folder vertical milling cutter of Ф 16, F value takes 100；
S104: programming coordinates origin is overlapped by finishing with the setting of turbine axis hole center, Z-direction, turbine axis hole aperture
Face is set as zero point；Ream machining is carried out using special Combined hard-alloy reamer, and is one-pass molding.
The extension box side turbine hole forming method hardware aspect of minicar gearbox provided in an embodiment of the present invention: it adopts
Tooling is installed on the T-type workbench of machining center with 4 block pressur plates, mounting tool when will guarantee that tooling long side is parallel to
The X-axis of lathe (adjusts tooling using the mode that amesdial plays table, amesdial gauge stand is drawn on machine tool chief axis, amesdial contacts
Head contact tooling base long side, allows indicator to rotate 0.5mm or so, and amesdial is returned to zero, then under lathe manual mode, edge
X-axis moves back and forth workbench, adjusts tooling position according to amesdial pointer change conditions, until amesdial pointer changes
Within the scope of 0.02mm, think that tooling long side is parallel to lathe X-axis at this time.).Then prolonging for datum level will have been added again
It stretches case to be installed in tooling, since the clamping power of the tooling is to use pneumatic pinch, so to guarantee to extend when installation
Case datum level closely adheres to opens tooling jettron, Clamp blocks again on tooling vertical plane.The turbine hole machined uses two
Cutter, (No. 1 cutter is that 16 machine of Ф that roughing is selected presss from both sides slotting cutter, and No. 2 cutters are that the special combined type that finishing is selected is hard
Matter alloy reamer), No. 1 cutter measures the offset of No. 2 cutters using tool setting gauge as basic-cutter, and No. 1 Cutting tool installation manner is arrived
On main shaft and in No. 2 Cutting tool installation manners to tool magazine.Start lathe, No. 1 cutter is carried out to knife, and will be to knife parameter typing lathe number
Control device.After No. 1 cutter is to knife, cutter compensation parameter setting is carried out to No. 2 cutters.Finally, checking that coolant liquid, program are imitative
True track, conditions of machine tool etc., it is ensured that after errorless, start good program prepared in advance, carry out machining.
The software aspects of the extension box side turbine hole forming method of minicar gearbox provided in an embodiment of the present invention:
According to extension box drawing technical parameter, extension box threedimensional model is drawn according to 1:1 ratio using UG software peace on computers, in UG
Machining tool model, Workpiece zero point, cutter parameters, cutter path track, feed side are carried out in the automated programming module youngster of software
The parameter settings such as formula.Analogue simulation is carried out again, has checked zero defect, and adjustment of modifying, last derivation program.Further according to reality
Border situation finely tune to derived program.It will be in the machining center digital control systems to be processed such as complete program importing.It (compiles
Computer used in processing procedure sequence is connect by data line with machining center numerical control device, and importing and exporting for data may be implemented.)
Application principle of the invention is further described combined with specific embodiments below.
One, detail drawing industrial analysis
Gear box casing extension box drawing is kept off by certain model minicar five, the extension box of the model is thin-wall case zero
Part, planform is more complicated, and inside is irregular cavity shape, and certain positions are there are also " partition wall ", in addition to being arranged on tank wall
Have except parallel hole system, has been arranged to vertical hole system.Turbine axis hole turbine bore is a cone step blind hole, the hole Ф 23H9 and Ф
The hole 22H9 is connected by 10 ° of taper holes, and the hole Ф 23H9 and the hole Ф 22H9 hole wall surface roughness Ra are 1.6, and the surface of countersunk portion is thick
Rugosity Ra is 6.3.20 ° of orifice chamfer of the hole Ф 23H9, surface roughness Ra 6.3.Ф 23H9 hole depth be 16mm, countersunk portion and
Ф 22H9 hole depth is 46mm, and the linear distance at the hole the Ф 62H7 center in turbine axis hole turbine bore center and vertical hole system is 28.5
+0.15 0mm.Turbine wheel shaft centerline hole and Y-axis axis both clockwise angle are 30 °.Turbine axis hole turbine bore center and datum level
Distance is 117.5 ± 0.1mm.(such as Fig. 2) axis both clockwise angle is 30 °.Turbine axis hole center and datum level (such as Fig. 3).
Two, the selection of machine tool, cutter and coolant liquid
Lathe: selection vertical machining centre is processed --- Nantong V850, Siemens System.
Cutter: the workpiece is cast blank part, and the surplus of turbine axis hole is in 2-3mm, total depth 62mm, and due to this
Hole relationship the location of on part, causes process tool overall length just to can guarantee up to 150mm or so in the case where not hitting knife
Complete processing.Since cutter is too long, it is easy to appear " allow knife " deformation in process.Roughing selects 16 machine of Ф to press from both sides vertical milling
Knife, finishing use special Combined hard-alloy reamer.
Coolant liquid: selection diesel oil is cooled down.Diesel oil has good cooling effect and lubricating action, and workpiece can be improved
Machining accuracy and finish, while also there is certain anti-rust action.
Three, extension box Set and Positioning
When carrying out side turbine bore manufacturing procedure, datum level and two processing dowel holes have been completed the process.It selects
Datum level and two dowel holes are as positioning datum.It is positioned by the way of the additional top of plane and two pits, the clamping is fixed
Position mode limits 6 freedom degrees.A top on one side, limits 3 freedom degrees, moves along X, rotates around Z rotation, around Y.Two fixed
Position pin must be a straight pin and a rhombus pin, otherwise can cross positioning, and the centers of 2 location holes is away from selling centers away from not with two
May be completely the same, the effect of rhombus pin exactly " gets out of the way " the two center away from error, elimination installation interference, and limitation workpiece is around X turns
Dynamic, the long axis of rhombus pin must be perpendicular to the line of centres of two pin holes；Straight pin limitation workpiece is moved along Z, Y.Meanwhile the clamping presss from both sides
Tool must rotate counterclockwise 30 ° of installations along X-axis to be fixed, and guarantees that turbine centerline hole is parallel with machine tool chief axis axial line.
Four, side turbine bore roughing
When roughing, programming coordinates origin is overlapped with turbine axis hole center, Z-direction, and turbine axis hole aperture face is set as
Zero point.Milling is carried out using the machine folder vertical milling cutter of Ф 16, F value takes 100.Since blank bore dia is 20mm, unilateral surplus is
1-1.5mm, so rough milling using cutting at one time, unilateral surplus stays 0.2mm.I.e. after roughing, hole machined is at Ф 22.6 and Ф
21.6.Roughing program is as follows:
Five, side turbine bore finishes
Programming coordinates origin is overlapped by finishing with the setting of turbine axis hole center, Z-direction, the setting of turbine axis hole aperture face
For zero point.The process carries out ream machining using special Combined hard-alloy reamer, and is one-pass molding, i.e. ream Ф
Also the orifice chamfer in the hole Ф 23H9 is completed when 22H9 and Ф 23H9.During fraising, F value takes 100.Finishing procedures are such as
Under:
The part of the embodiment of the present invention is thin-walled aluminum component, and the position of side turbine axis hole is more special, (leading to it) processing
Degree-of-difficulty factor is big.By reasonably selecting machine tool, cutting tool it was verified that improve its processing method and Cutting Process
With coolant liquid etc., can guarantee existing " the allow knife " phenomenon of can't process for the turbine axis hole completely, and position precision, dimensional accuracy,
Finish etc. is attained by requirement.It is equally applicable to the processing in like parts hole.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (4)
1. a kind of extension box side turbine hole forming method of minicar gearbox, which is characterized in that the minicar becomes
The extension box side turbine hole forming method of fast case the following steps are included:
Step 1 selects vertical machining centre to be processed, and roughing selects 16 machine of Ф to press from both sides slotting cutter, and finishing uses special group
Box-like carbide-tipped reamer；Diesel oil is cooled down；
Step 2 is selected datum level and two dowel holes as positioning datum, is carried out by the way of the additional top of plane and two pits
Positioning；
Step 3, when roughing, programming coordinates origin is overlapped with turbine axis hole center, Z-direction, the setting of turbine axis hole aperture face
For zero point；Milling is carried out using the machine folder vertical milling cutter of Ф 16, F value takes 100；
Programming coordinates origin is overlapped by step 4, finishing with the setting of turbine axis hole center, Z-direction, turbine axis hole aperture face
It is set as zero point；Ream machining is carried out using special Combined hard-alloy reamer, and is one-pass molding；
Set and Positioning limits 6 freedom degrees in the step 2, and a top, limits 3 freedom degrees on one side, move along X, rotated around Z,
It is rotated around Y；Two positioning pins must be a straight pin and a rhombus pin；The long axis of rhombus pin must be perpendicular to two pin holes
Line of centres；Straight pin limitation workpiece is moved along Z, Y；30 ° of installations are rotated counterclockwise along X-axis to fix.
2. the extension box side turbine hole forming method of minicar gearbox as described in claim 1, which is characterized in that institute
Tooling is installed to the T of machining center using 4 block pressur plates by the extension box side turbine hole forming method for stating minicar gearbox
On type workbench；Amesdial gauge stand is drawn on machine tool chief axis, and amesdial contact head contacts tooling base long side, indicator rotation
0.5mm returns to zero amesdial；Under lathe manual mode, move back and forth workbench along X-axis, feelings are changed according to amesdial pointer
Condition adjusts tooling position, until amesdial pointer changes within the scope of 0.02mm；
The extension box of datum level out will be added to be installed in tooling；Turbine hole machined uses two cutters, and No. 1 cutter is as benchmark
Cutter measures the offset of No. 2 cutters using tool setting gauge, will be on No. 1 Cutting tool installation manner to main shaft and No. 2 Cutting tool installation manners are to tool magazine
In；
Start lathe, No. 1 cutter is carried out to knife, and will be to knife parameter typing lathe numerical control device；No. 1 cutter finishes knife
Afterwards, cutter compensation parameter setting is carried out to No. 2 cutters；
Check coolant liquid, procedure simulation track, conditions of machine tool, it is ensured that after errorless, start good program prepared in advance, cut
Processing.
3. the extension box side turbine hole forming method of minicar gearbox as described in claim 1, which is characterized in that institute
The extension box side turbine hole forming method of minicar gearbox is stated according to extension box drawing technical parameter, is made on computers
With UG software peace according to 1:1 ratio draw extension box threedimensional model, UG software automated programming module carry out machining tool model,
Workpiece zero point, cutter parameters, cutter path track, feed mode；Analogue simulation is carried out, has checked zero defect, and modify
Adjustment, derivation program；Derived program is finely adjusted further according to actual conditions；By complete program import etc. it is to be processed plus
In the digital control system of work center.
4. a kind of extension box side turbine bore using the minicar gearbox as described in claims 1 to 3 any one adds
The automobile gearbox of work method processing.
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| CN201711397870.7A CN108057997B (en) | 2017-12-21 | 2017-12-21 | A kind of extension box side turbine hole forming method of minicar gearbox |
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| CN201711397870.7A CN108057997B (en) | 2017-12-21 | 2017-12-21 | A kind of extension box side turbine hole forming method of minicar gearbox |
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| CN108057997B true CN108057997B (en) | 2019-09-20 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103567487A (en) * | 2013-11-11 | 2014-02-12 | 中国南方航空工业(集团)有限公司 | Method for machining small-diameter inclined hole |
| CN103607857A (en) * | 2013-11-28 | 2014-02-26 | 吴冬梅 | Blind hole machining method |
| CN103949850A (en) * | 2014-04-16 | 2014-07-30 | 靖江市顺达模具厂 | Method for processing back box of automobile gearbox |
| CN104801935A (en) * | 2015-04-28 | 2015-07-29 | 什邡市明日宇航工业股份有限公司 | Method for processing aircraft aluminum alloy special-shaped cabin |
| CN106736332A (en) * | 2016-12-23 | 2017-05-31 | 贵州黎阳航空动力有限公司 | A kind of High Pressure Turbine Rotor combination is with the numerical-control processing method for boring tapered hole |
| CN107186228A (en) * | 2017-06-30 | 2017-09-22 | 贵州凯星液力传动机械有限公司 | A kind of accurate cutting tool for boring of superdeep holes |
-
2017
- 2017-12-21 CN CN201711397870.7A patent/CN108057997B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103567487A (en) * | 2013-11-11 | 2014-02-12 | 中国南方航空工业(集团)有限公司 | Method for machining small-diameter inclined hole |
| CN103607857A (en) * | 2013-11-28 | 2014-02-26 | 吴冬梅 | Blind hole machining method |
| CN103949850A (en) * | 2014-04-16 | 2014-07-30 | 靖江市顺达模具厂 | Method for processing back box of automobile gearbox |
| CN104801935A (en) * | 2015-04-28 | 2015-07-29 | 什邡市明日宇航工业股份有限公司 | Method for processing aircraft aluminum alloy special-shaped cabin |
| CN106736332A (en) * | 2016-12-23 | 2017-05-31 | 贵州黎阳航空动力有限公司 | A kind of High Pressure Turbine Rotor combination is with the numerical-control processing method for boring tapered hole |
| CN107186228A (en) * | 2017-06-30 | 2017-09-22 | 贵州凯星液力传动机械有限公司 | A kind of accurate cutting tool for boring of superdeep holes |
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| Publication number | Publication date |
|---|---|
| CN108057997A (en) | 2018-05-22 |
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