CN108057997A - 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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- CN108057997A CN108057997A CN201711397870.7A CN201711397870A CN108057997A CN 108057997 A CN108057997 A CN 108057997A CN 201711397870 A CN201711397870 A CN 201711397870A CN 108057997 A CN108057997 A CN 108057997A
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- turbine
- cutter
- 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
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- Drilling And Boring (AREA)
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, 16 machines of Ф folder slotting cutter is selected in roughing, and finishing uses special Combined hard-alloy reamer；Diesel oil is cooled down；Reference plane and two dowel holes is selected to be positioned as positioning datum by the way of the additional top of plane and two pits；During roughing, programming coordinates origin is overlapped with turbine axis hole center, Z-direction, and turbine axis hole aperture face is arranged to zero point；Milling is carried out using 16 machines of Ф folder vertical milling cutter, F values take 100；Finishing by programming coordinates origin with turbine axis hole is centrally disposed overlaps, Z-direction, turbine axis hole aperture face is arranged to 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 positional 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 technology
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 passing power, the predetermined function for changing speed, completing machine or component.Box parts requirement has 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), Ф 23H9 holes and Ф
22H9 holes are connected by 10 ° of taper holes, and Ф 23H9 holes and Ф 22H9 holes hole wall surface roughness Ra are 1.6, and the surface of countersunk portion is thick
Rugosity Ra is 6.3.20 ° of Ф 23H9 holes orifice chamfer, surface roughness Ra 6.3.Ф 23H9 hole depths be 16mm, countersunk portion and
Ф 22H9 hole depths are 46mm, and the air line distance at the Ф 62H7 holes center in center and upright opening 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 and the distance of reference plane (such as Fig. 2) are
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 relation, process tool overall length is caused just to can guarantee up to 150mm or so and is not hitting the feelings of knife
Processing is completed under condition.The side turbine bore directly carries out milling using 16 machines of Ф folder slotting cutter at present, 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 machines of Ф folder
Milling cutter.Cutter is long, is susceptible to " allow knife " deformation in process.Cause it is processed after turbine bore occur it is upper big
Under it is small the phenomenon that, easily vibrate, cause it is processed after turbine hole wall there is chatter mark, make dimensional accuracy and surface roughness
All it is unable to reach technology requirement.So on clamping and machining accuracy control, there are great difficulties.
In conclusion problem existing in the prior art is：Since cutter is long, it is susceptible to " allows in process
Knife " deform, cause it is processed after turbine bore occur it is up big and down small the phenomenon that.Easily vibrate, 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 technology requirement.Furthermore due to front two because
Element will cause cutter life to shorten, and product qualification rate substantially reduces.Tool changing debug time greatly increases.
The content 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 present invention is achieved in that 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 comprises the following steps：
Step 1 selects vertical machining centre to be processed, and 16 machines of Ф folder slotting cutter is selected in roughing, and finishing is using special
Combined hard-alloy reamer processed；Diesel oil is cooled down；
Step 2 selects reference plane 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, reference plane and two locating and machining pin holes have machined.Cause
This, selects reference plane 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 degree of freedom.A top on one side limits 3 degree of freedom, moves along X, is rotated around Z, is rotated around Y.Two
A positioning pin must be a straight pin and a rhombus pin, otherwise can cross positioning, the centre-to-centre spacing of 2 location holes and two pin centers
Away from can not possibly be completely the same, both the effect of rhombus pin exactly " is got out of the way " centre-to-centre spacing error eliminates installation interference, limitation workpiece around
X is rotated, and 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 30 ° of installations counterclockwise along X-axis to be fixed, and ensures turbine centerline hole and machine tool chief axis axis parallel.
Step 3, during roughing, programming coordinates origin is overlapped with turbine axis hole center, Z-direction, turbine axis hole aperture face
It is arranged to zero point；Milling is carried out using the machine folder vertical milling cutter of Ф 16, F values take 100；Using UG softwares 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 on whirlpool
At axle hole center, the reset of Z-direction is in turbine axis hole whirlpool aperture face.Select the machine folder vertical milling cutter of Ф 16, feeding
Speed chooses F100, and plunge cut way cuts for spiral.It is unilateral to stay chipping allowance 0.2mm.
Step 4, finish by programming coordinates origin with turbine axis hole is centrally disposed overlaps, Z-direction, turbine axis hole hole
Mouth face is arranged to 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 ensure that cutter feeds downwardly into size positions along central axis during, cutting.Using side instrument is sought to knife, will program
Origin is arranged at turbine axis hole center, and the reset of Z direction of principal axis is in turbine axis hole aperture face.Manual programming.
Further, Set and Positioning limits 6 degree of freedom in the step 2, on one side a top, limits 3 degree of freedom, is moved along X
It moves, rotated around Z, rotated 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 frock
It is installed on the T-shaped workbench of machining center；Amesdial gauge stand is drawn onto on machine tool chief axis, amesdial contact head contact tooling base
Long side, indicator rotation 0.5mm, amesdial is returned to zero；Under lathe manual mode, move back and forth workbench along X-axis, according to thousand points
List index change conditions adjustment frock position, until amesdial pointer is changed within the scope of 0.02mm；
The extension box for adding reference plane is installed in frock；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 storehouse；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, 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, on computers using UG softwares peace according to 1:1 ratio draws extension box threedimensional model, in the automated programming module of UG softwares
It is processed lathe 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 turbine using the minicar gearbox
The automobile gearbox of hole forming method processing.
The present invention is processed turbine axis hole, can be to avoid cutter in existing scheme " allow knife " " vibration " phenomena such as, 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；Production
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 etc., can ensure the turbine wheel shaft completely
Existing " the allow knife " phenomenon of can't process for hole, and positional 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 machines 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 be integrated combined type reamer, cutter is along turbine axially bored line when finishing
Straight-line feed there is no " allow knife " deformation, just solves " allow knife " phenomenon in existing scheme, also there is no vibration, just
Solve the problems, such as that the precision caused by vibration in existing scheme 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 " in existing scheme etc.
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 assembling turbine and turbine wheel shaft, ensures turbine and the correct relative position of turbine wheel shaft, each other can
Co-ordination, while turbine bore coordinates with rubber seal on turbine wheel shaft, plays sealing function.So processing the turbine
When hole, it is necessary to ensure its technology acuracy.
Description of the drawings
Fig. 1 is the extension box side turbine hole forming method flow 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 center provided in an embodiment of the present invention and reference plane schematic diagram.
Specific embodiment
In order to make the purpose , technical scheme and advantage of the present invention be 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 near
The development of decades is either obtained for from scope of the enterprise, product technology, product quality and is significantly promoted very much, state
The competitiveness of production automobile mechanical component product is also constantly enhancing, and is progressively substituting import.
The application principle of the present invention is explained in detail below in conjunction with the accompanying drawings.
As shown in Figure 1, the extension box side turbine hole forming method of minicar gearbox provided in an embodiment of the present invention
Comprise the following steps：
S101：Selection vertical machining centre is processed, and 16 machines of Ф folder slotting cutter is selected in roughing, and finishing is using special
Combined hard-alloy reamer；Diesel oil is cooled down；
S102：Reference plane and two dowel holes are selected as positioning datum, in a manner that plane and two pits additional one push up into
Row positioning；
S103：During 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 values take 100；
S104：Finishing by programming coordinates origin with turbine axis hole is centrally disposed overlaps, Z-direction, turbine axis hole aperture
Face is arranged to 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
Frock is installed on the T-shaped workbench of machining center with 4 block pressur plates, mounting tool when to ensure frock long side parallel to
(mode that table is played using amesdial adjusts frock to the X-axis of lathe, and amesdial gauge stand is drawn onto on machine tool chief axis, amesdial contact
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, and frock position is adjusted according to amesdial pointer change conditions, until amesdial pointer changes
Within the scope of 0.02mm, think frock long side parallel to lathe X-axis at this time.).Then prolonging for reference plane will have been added again
It stretches case to be installed in frock, since the clamping power of the frock is to use pneumatic pinch, so to ensure to extend when installation
Case reference plane closely adheres to opens frock jettron, Clamp blocks again on frock vertical plane.The turbine hole machined uses two
Cutter, (No. 1 cutter presss from both sides slotting cutter for 16 machines of Ф that roughing is selected, and No. 2 cutters are hard for the special combined type that finishing is selected
Matter alloy reamer), No. 1 cutter is measured the offset of No. 2 cutters using tool setting gauge, No. 1 Cutting tool installation manner is arrived as basic-cutter
On main shaft and No. 2 Cutting tool installation manners are in 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, check that coolant, program are imitated
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, on computers using UG softwares peace according to 1:1 ratio draws extension box threedimensional model, in UG
Lathe model, Workpiece zero point, cutter parameters, cutter path track, feed side are processed 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 to derived program finely tune.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 connected by data cable with machining center numerical control device, can realize importing and exporting for data.)
The application principle of the present invention is further described with reference to specific embodiment.
First, 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 some positions also have " partition wall ", except being arranged on tank wall
Have outside parallel hole system, be arranged to upright opening system.Turbine axis hole turbine bore is a cone step blind hole, Ф 23H9 holes and Ф
22H9 holes are connected by 10 ° of taper holes, and Ф 23H9 holes and Ф 22H9 holes hole wall surface roughness Ra are 1.6, and the surface of countersunk portion is thick
Rugosity Ra is 6.3.20 ° of Ф 23H9 holes orifice chamfer, surface roughness Ra 6.3.Ф 23H9 hole depths be 16mm, countersunk portion and
Ф 22H9 hole depths are 46mm, and the air line distance at the Ф 62H7 holes center in turbine axis hole turbine bore center and upright opening 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 reference plane
Distance is 117.5 ± 0.1mm.(such as Fig. 2) axis both clockwise angle is 30 °.Turbine axis hole center and reference plane (such as Fig. 3).
2nd, the selection of machine tool, cutter and coolant
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 relation 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 long, " allow knife " deformation is susceptible in process.16 machines of Ф folder vertical milling is selected in roughing
Knife, finishing use special Combined hard-alloy reamer.
Coolant：Selection diesel oil is cooled down.Diesel oil has good cooling effect and lubricating action, can improve workpiece
Machining accuracy and finish, while also there is certain anti-rust action.
3rd, extension box Set and Positioning
When carrying out side turbine bore manufacturing procedure, reference plane and two locating and machining pin holes have machined.It selects
Reference plane and two dowel holes are as positioning datum.It is positioned by the way of the additional top of plane and two pits, which determines
Position mode limits 6 degree of freedom.A top on one side limits 3 degree of freedom, moves along X, is rotated around Z, is rotated around Y.Two fixed
Position pin must be a straight pin and a rhombus pin, otherwise can cross positioning, the centre-to-centre spacing of 2 location holes is with two pin centers away from not
May be completely the same, the effect of rhombus pin exactly " gets out of the way " the two centre-to-centre spacing error, eliminates 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 30 ° of installations counterclockwise along X-axis to be fixed, and ensures turbine centerline hole and machine tool chief axis axis parallel.
4th, side turbine bore roughing
During roughing, programming coordinates origin is overlapped with turbine axis hole center, Z-direction, and turbine axis hole aperture face is arranged to
Zero point.Milling is carried out using the machine folder vertical milling cutter of Ф 16, F values take 100.Due to a diameter of 20mm of blank hole, 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 into Ф 22.6 and Ф
21.6.Roughing program is as follows：
5th, side turbine bore finishes
Finishing by programming coordinates origin with turbine axis hole is centrally disposed overlaps, 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 Ф 23H9 holes is completed during 22H9 and Ф 23H9.During fraising, F values take 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, (causing it) processing
Degree-of-difficulty factor is big.By it was verified that improve its processing method and Cutting Process, reasonably selecting machine tool, cutting tool
With coolant etc., can ensure existing " the allow knife " phenomenon of can't process for the turbine axis hole completely, and positional 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 essences in the present invention
All any modification, equivalent and improvement made within refreshing and principle etc., should all be included in the protection scope of the present invention.
Claims (5)
1. the extension box side turbine hole forming method of a kind of minicar gearbox, which is characterized in that the minicar becomes
The extension box side turbine hole forming method of fast case comprises the following steps：
Step 1 selects vertical machining centre to be processed, and 16 machines of Ф folder slotting cutter is selected in roughing, and finishing uses special group
Box-like carbide-tipped reamer；Diesel oil is cooled down；
Step 2 selects reference plane and two dowel holes to be carried out as positioning datum by the way of the additional top of plane and two pits
Positioning；
Step 3, during roughing, programming coordinates origin is overlapped with turbine axis hole center, Z-direction, and turbine axis hole aperture face is set
For zero point；Milling is carried out using the machine folder vertical milling cutter of Ф 16, F values take 100；
Step 4, finish by programming coordinates origin with turbine axis hole is centrally disposed overlaps, Z-direction, turbine axis hole aperture face
It is arranged to zero point；Ream machining is carried out using special Combined hard-alloy reamer, and is one-pass molding.
2. the extension box side turbine hole forming method of minicar gearbox as described in claim 1, which is characterized in that institute
It states Set and Positioning in step 2 and limits 6 degree of freedom, a top, limits 3 degree of freedom on one side, moves along X, is rotated around Z, turns around Y
It is dynamic；Two positioning pins must be a straight pin and a rhombus pin；The long axis of rhombus pin must be perpendicular to connecting with the heart for two pin holes
Line；Straight pin limitation workpiece is moved along Z, Y；30 ° of installations are rotated counterclockwise along X-axis to fix.
3. the extension box side turbine hole forming method of minicar gearbox as described in claim 1, which is characterized in that institute
Frock 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 onto on machine tool chief axis, amesdial contact head contact tooling base long side, indicator rotation
0.5mm returns to zero amesdial；Under lathe manual mode, move back and forth workbench along X-axis, become emotionally according to amesdial pointer
Condition adjustment frock position, until amesdial pointer is changed within the scope of 0.02mm；
The extension box for adding reference plane is installed in frock；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, procedure simulation track, conditions of machine tool, it is ensured that after errorless, start good program prepared in advance, cut
Processing.
4. 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 softwares peace according to 1:1 ratio draw extension box threedimensional model, the automated programming module of UG softwares be processed lathe model,
Workpiece zero point, cutter parameters, cutter path track, feed mode；Analogue simulation is carried out, zero defect has been checked, and has modified
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.
5. a kind of extension box side turbine bore of minicar gearbox using as described in Claims 1 to 4 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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| 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 |
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| CN103949850A (en) * | 2014-04-16 | 2014-07-30 | 靖江市顺达模具厂 | Method for processing back box of automobile gearbox |
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| 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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2017
- 2017-12-21 CN CN201711397870.7A patent/CN108057997B/en active Active
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| 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 |
|---|---|
| CN108057997B (en) | 2019-09-20 |
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