CN105215968B - The profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting - Google Patents
The profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting Download PDFInfo
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- CN105215968B CN105215968B CN201510745242.8A CN201510745242A CN105215968B CN 105215968 B CN105215968 B CN 105215968B CN 201510745242 A CN201510745242 A CN 201510745242A CN 105215968 B CN105215968 B CN 105215968B
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- 238000005266 casting Methods 0.000 title claims abstract description 115
- 238000003754 machining Methods 0.000 title claims abstract description 27
- 238000005516 engineering process Methods 0.000 title claims abstract description 15
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 14
- 238000005520 cutting process Methods 0.000 title claims abstract description 12
- 244000062793 Sorghum vulgare Species 0.000 claims abstract description 14
- 235000019713 millet Nutrition 0.000 claims abstract description 14
- 238000000034 method Methods 0.000 claims description 11
- 238000005259 measurement Methods 0.000 claims description 8
- 230000008569 process Effects 0.000 claims description 8
- 238000012545 processing Methods 0.000 abstract description 22
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000008859 change Effects 0.000 description 3
- 210000000080 chela (arthropods) Anatomy 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000011946 reduction process Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 238000013519 translation Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H7/00—Marking-out or setting-out work
- B25H7/04—Devices, e.g. scribers, for marking
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23D—PLANING; SLOTTING; SHEARING; BROACHING; SAWING; FILING; SCRAPING; LIKE OPERATIONS FOR WORKING METAL BY REMOVING MATERIAL, NOT OTHERWISE PROVIDED FOR
- B23D79/00—Methods, machines, or devices not covered elsewhere, for working metal by removal of material
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Numerical Control (AREA)
Abstract
The present invention relates to titanium alloy casting manufacture field, more particularly to a kind of profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting, its step is：Profile millet cake cloud data in A, comprehensively scanning casting, and cloud data and casting digital-to-analogue are fitted；B, integrated regulation cloud data and casting digital-to-analogue relative position, in the case where ensureing that machining area has the interior shape face deviation of allowance, casting in the range of setting, maximum machining area is adjusted out, it is determined that final machining benchmark, remaining machined surface is used as profile-followed machined surface；C, individually adjust profile-followed machined surface cloud data, it is ensured that casting section thickness deviation；D, it is processed, it is an object of the invention to provide a kind of profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting for improving Mechanical processing of casting yields, improving Mechanical processing of casting efficiency.
Description
Technical field
The present invention relates to titanium alloy casting manufacture field, more particularly to a kind of large aerospace thin-wall titanium alloy casting is cut with the shape
Cut process technology.
Background technology
In aviation field, a certain framework is complex alloy special-shaped titanium face structural casting.Casting is in metallurgical quality
After qualified, dimensionally stable, it is ensured that it is casting quality that each machined surface, which has after allowance, processing wall thickness meet the requirement of drawing size,
It is crucial.
Casting is examined with traditional scribble method, it is impossible to comprehensive detection is made to casting, it is impossible to judge the chi of casting
It is very little whether qualified, optimal machining benchmark can not be correctly determined, casting is difficult processing.
At present, also there is unstable situation in casting state, and subregion has certain deviation, fitted with covering above and below
Surface (Special-Shaped Surface）Requirement can't be fully met, after processing, although outer surface meets standard, but some wall thickness
Can be excessively thin or blocked up, product is not still easily up to standard, and product control is too poor.
The content of the invention
It is an object of the invention to overcome in the presence of prior art above-mentioned not enough there is provided one kind to improve Mechanical processing of casting good
Product rate, the profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting for improving Mechanical processing of casting efficiency.
In order to realize foregoing invention purpose, the invention provides following technical scheme：
A kind of profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting, its step is：
A, profile millet cake cloud data in the casting are scanned comprehensively, and profile millet cake cloud data in casting and the casting
Number of packages mould is fitted；
The relative position of cloud data and casting digital-to-analogue described in B, integrated regulation, ensure machining area have allowance,
In the case that the interior shape face deviation of casting is in the range of the setting, maximum machining area is adjusted out, it is determined that final machining benchmark, remaining
Machined surface be used as profile-followed machined surface；
C, individually adjust the profile-followed machined surface cloud data, it is ensured that casting section thickness deviation；
D, it is processed.
In traditional technique, increase some changes, by scanning profile millet cake cloud data in casting, then again the point
Cloud data sum simulation close because after the completion of this Mechanical processing of casting in use, be outside it with miscellaneous part coordinate, this
Kind coordinating allows certain deviation, and still, the wall thickness after the completion of Mechanical processing of casting must assure that again, and not so bulk strength can be by
Influence, thin place is easily broken off, so, we catch " deviation " for allowing exist within the specific limits, devise this skill
Art, if this casting has 6 faces, by the adjustment after the fitting, and fitting, i.e. step B can make under normal process
The profile and thickness in wherein 5 faces can have enough surpluses to meet, and remaining face a portion surplus is negative, but
Be this " negative " control in certain limit, pass through in step C individually adjustment cloud data, you can process in " deviation " model
In enclosing but thickness and standard compliant workpiece, in this case, can greatly improve yields, unless that defect is very
Big Mechanical processing of casting does not go out, and ordinary circumstance is all possible, compared to traditional technology, can avoid the waste of material, improves good
While the situation of product rate, more preferable cost savings can be brought to enterprise（Secondly, in actual use, swept unused
Retouch before mode, technological preparation needs the plenty of time, in addition it is also necessary to multiple trial cut is made of lathe, repeatedly adjust to determine the actual shape of casting
State, expends the more time, with it, can greatly reduce or cancel trial cut, improves Mechanical processing of casting efficiency）.
As the preferred scheme of the present invention, in step A, profile millet cake cloud data are divided into casting appearance profile in the casting
Graphic data in data, scanning casting, sets before scanning and processes casting benchmark, the casting profile data, scanning casting
Interior graphic data is separately scanned, then merges into the complete cloud data of casting by the casting benchmark, can be with if directly used
The machine in the whole shape faces of scanning, cost can be very high, and utilize and set the casting benchmark, and point cloud number is formed using this combination
According to mode, two kinds of scanning machine can be used separately, compared to directly using including the complicated machines of two kinds of functions
For, the machine for the scanning that this mode is used is cheaply a lot, reduces processing cost.
,, will be profile-followed when individually adjusting the profile-followed machined surface cloud data in step C as the preferred scheme of the present invention
Machined surface and corresponding interior shape face are as two object integrated regulations, with reference to interior shape face allowance balance state, individually
Translate or rotate, can effectively ensure casting section thickness deviation.
As the preferred scheme of the present invention, in step C, after the integrated regulation is carried out, if still it cannot be guaranteed that wall thickness
The subrange of deviation, then carry out local directed complete set, further improves the yields.
As the preferred scheme of the present invention, after profile-followed machined surface has been adjusted described in step C, pass through the casting base of setting
The quasi- amendment final machining benchmark, further improves the yields.
As the preferred scheme of the present invention, in step A, scan in the casting after profile millet cake cloud data, detection is described
Profile millet cake cloud data in casting, under the identical casting benchmark, a measurement, measurement result are taken with three coordinates in cast(ing) surface
With scan data, corresponding cloud data is made comparisons, with region difference≤0.1mm more than the gross area 5%, less than or equal to the gross area 5%
Region difference≤0.20mm standard detected, meet then to be qualified, it is ensured that the accuracy of the cloud data of scanning, enter
One step improves the yields.
As the preferred scheme of the present invention, in step B, the interior shape face deviation of the casting is arranged on 3.0mm~5.0mm models
In enclosing, studied by inventor, when carrying out step B, interior shape face deviation is arranged in the range of this, and the yields is higher.
Compared with prior art, beneficial effects of the present invention：
Improve Mechanical processing of casting yields；
Improve Mechanical processing of casting efficiency.
Brief description of the drawings：
Fig. 1 is the inventive method schematic diagram；
Fig. 2 is percent ripple characteristic parameter definition figure in the embodiment of the present invention.
Embodiment
With reference to embodiment and embodiment, the present invention is described in further detail.But this should not be understood
Following embodiment is only limitted to for the scope of above-mentioned theme of the invention, it is all that this is belonged to based on the technology that present invention is realized
The scope of invention.
Embodiment 1
Such as Fig. 1, a kind of profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting, its step is：
A, pincers worker are rule with reference to casting digital-to-analogue to casting, primarily determine that casting benchmark, and pincers worker is real according to casting according to drawing
Border situation, taking into account each Working position has surplus, through repeatedly adjustment, determines datum plane, determines benchmark centerline hole；
In the present embodiment, according to scribing by bench worker, on lathe, with scriber centering workpiece≤0.3mm, by workpiece upper and lower surface
Processing design size processed, according to scribing by bench worker, 2- Φ 6H8 holes processed；
Profile millet cake cloud data in the casting are scanned comprehensively（Scan after the cloud data, detect the cloud data,
Under the identical casting benchmark, a measurement is taken in cast(ing) surface with three coordinates, measurement result is with scan data respective point cloud number
According to making comparisons, with region difference≤0.1mm more than the gross area 5%, less than or equal to region difference≤0.20mm of the gross area 5%
Standard is detected, is met then to be qualified）, and the cloud data and the casting digital-to-analogue are fitted（The present embodiment
In, the cloud data and casting digital-to-analogue of scanning import Geomagic Qualify softwares simultaneously, do best fit alignment, most
After good fitting, to all cloud data com-parison and analysis, it is ensured that all two-sided machined surfaces be machined with surplus, and step B with
Shape machined surface population deviation must not exceed maximum adjusting range, and the local deformation of interior shape face must not exceed percent ripple requirement, meet
Condition this can be adjusted, process）；
The interior profile millet cake cloud data are divided into casting profile data, scan graphic data in casting, are set before scanning
And process casting benchmark, graphic data is separately scanned in the casting profile data, scanning casting（In the present embodiment, use
Hai Kesikang blue lights, which are taken pictures, shows scanner scanning casting profile data, using Hai Kesikang joint arm laser scanner scans
Graphic data in casting）, then the complete cloud data of casting merged into by the casting benchmark；
The relative position of cloud data and casting digital-to-analogue described in B, integrated regulation, ensure machining area have allowance,
The interior shape face deviation of casting（3.0mm~5.0mm）In the case of in the range of the setting, maximum machining area is adjusted out, it is determined that most
Final processing benchmark, remaining machined surface is used as profile-followed machined surface（As allow profile-followed machined surface inwall allowance balance uniform as possible and become
Change trend is consistent）；
C, dimensional tolerance scope≤± 0.8mm of the casting surface related to aircraft configuration, 10% data point≤± 1.2mm
Requirement, according to the result, the appearance curved surface deviation larger part of profile-followed machined surface is adjusted, it is therefore an objective to meeting outside aircraft
Ensure that type is faced the wall and meditated thickness in the case of the dimensional tolerance of the related casting surface of shape, specifically, as follows：
Individually adjust the profile-followed machined surface cloud data（, will be with when individually adjusting the profile-followed machined surface cloud data
Shape machined surface and corresponding interior shape face are single respectively with reference to interior shape face allowance balance state as two object integrated regulations
Solely translate or rotate, it is ensured that casting section thickness deviation；The scope of profile adjustment is ± 0.8mm, local permission ± 1.2mm）, it is ensured that
Casting section thickness deviation, passes through this two kinds of adjustment modes（Translation rotates）, change profile-followed machined surface and corresponding interior shape
Surplus deviation profile uneven situation in shape face in the physical location in face, correction casting；
After adjustment, it is ensured that the wall thickness of the profile-followed machined surface of casting largely meets and required；
After the integrated regulation is carried out, if still it cannot be guaranteed that the subrange of wall thickness deviation, carries out local directed complete set,
By the adjustment to profile-followed machined surface limit, change the true form in single face, make up the shape that local non-processing interior shape face lacks material
Condition, makes wall thickness meet tolerance（In the present embodiment, local directed complete set need to meet percent ripple requirement（Parameter correspondence such as Fig. 2）：
The percent ripple of cast(ing) surface should meet D≤0.5, D/λ≤0.001, and percent ripple measurement should be along casting vertical and horizontal
With ruler or batten inspection；
λ=wavelength（It is neighbouring to be higher by point the distance between A and B）, the depth capacity of D=ripple；
After the profile-followed machined surface has been adjusted, pass through final machining benchmark described in the casting benchmark amendment；
D, it is processed, cast(ing) surface is processed with the shape：After casting upper and lower surface profile measurement data is obtained, by most
Small milling removal amount and the principle for ensureing upper and lower surface minimum wall thickness (MINI W.), again by casting upper and lower surface shape data and Theoretical Design
Digital-to-analogue is fitted, and casting upper and lower surface is processed by the shape data being newly fitted in the step C, actual profile-followed processing district
Domain should be not less than the 90% of casting upper and lower surface surface area；
Upper and lower surface profile should be met after profile-followed processing：In addition to special mark, the non-processing casting thickness tolerance of casting be 0~
+ 1.0mm, the non-processing casting thickness tolerance in remaining region is -0.2~+0.5mm；The thickness deviation of two-sided machining area should be ±
0.25mm；
Workpiece bottom screw is connected with workbench during processing, and upper end both sides are connected to workbench with frock.Using frock
Supported, workpiece all fixes up and down, workpiece rigidity during increase cutting, the situation of vibration of workpiece, real in reduction process
In the process of border, machined surface surface roughness is good, can meet finishing requirements.
Claims (4)
1. a kind of profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting, its step is：
A, profile millet cake cloud data in the casting are scanned comprehensively, and profile millet cake cloud data in casting and the casting number
Mould is fitted；
The relative position of cloud data and casting digital-to-analogue described in B, integrated regulation, is ensureing that machining area has allowance, casting
Interior shape face deviation in the range of the setting in the case of, adjust out maximum machining area, it is determined that final machining benchmark, it is remaining plus
Work face is used as profile-followed machined surface；
C, individually adjust the profile-followed machined surface cloud data, it is ensured that casting section thickness deviation, specifically, individually adjustment it is described with
During shape machined surface cloud data, using profile-followed machined surface and corresponding interior shape face as two object integrated regulations, with reference to interior
Shape face allowance balance state, individually translates or rotates, it is ensured that casting section thickness deviation, after the integrated regulation is carried out,
If still it cannot be guaranteed that the subrange of wall thickness deviation, carries out local directed complete set, wherein, the profile-followed machined surface adjusted with
Afterwards, final machining benchmark described in the casting benchmark amendment of setting is passed through；
D, it is processed.
2. the profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting according to claim 1, it is characterised in that step
In rapid A, profile millet cake cloud data are divided into casting profile data, scan graphic data in casting in the casting, are set before scanning
Determine and process casting benchmark, graphic data is separately scanned in the casting profile data, scanning casting, then passes through the casting
Benchmark merges into the complete cloud data of casting.
3. the profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting according to claim 1, it is characterised in that step
In rapid A, scan in the casting after profile millet cake cloud data, profile millet cake cloud data in the casting are detected, identical described
Under casting benchmark, a measurement is taken in cast(ing) surface with three coordinates, measurement result with scan data make comparisons by corresponding cloud data, with
More than region difference≤0.1mm of the gross area 5%, the standard less than or equal to region difference≤0.20mm of the gross area 5% is examined
Survey, meet then to be qualified.
4. the profile-followed Machining Technology for Cutting of large aerospace thin-wall titanium alloy casting according to claim 3, it is characterised in that step
In rapid B, the interior shape face deviation of the casting is arranged in the range of 3.0mm~5.0mm.
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| CN108145393B (en) * | 2017-11-29 | 2019-10-11 | 株洲丰发精工实业有限公司 | A kind of aero-engine compressor blade and its processing method |
| CN108121291B (en) * | 2017-12-26 | 2020-01-21 | 湖北三江航天红阳机电有限公司 | Casting machining method |
| CN112685858B (en) * | 2020-12-31 | 2022-11-04 | 上海电气上重铸锻有限公司 | Forging piece correcting and adjusting method based on three-dimensional scanning auxiliary positioning |
| CN114004547B (en) * | 2021-12-30 | 2022-04-05 | 深圳市匠心智汇科技有限公司 | Scanning cutting method, device, equipment and computer readable storage medium |
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Address after: 618400 No. 3, Lantian Avenue, Shifang Economic Development Zone (North District), Deyang City, Sichuan Province Patentee after: Sichuan Xinhang Titanium Technology Co.,Ltd. Address before: 618400 No. 3, Lantian Avenue, Shifang Economic Development Zone (North District), Deyang City, Sichuan Province Patentee before: SICHUAN FUTURE AEROSPACE INDUSTRIAL Co.,Ltd. |
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