CN102922227B - A kind of processing method in titanium alloy incline bench hole - Google Patents
A kind of processing method in titanium alloy incline bench hole Download PDFInfo
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- CN102922227B CN102922227B CN201210308709.9A CN201210308709A CN102922227B CN 102922227 B CN102922227 B CN 102922227B CN 201210308709 A CN201210308709 A CN 201210308709A CN 102922227 B CN102922227 B CN 102922227B
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 43
- 238000003672 processing method Methods 0.000 title claims abstract description 24
- 238000012545 processing Methods 0.000 claims abstract description 42
- 150000001875 compounds Chemical class 0.000 claims abstract description 30
- 238000005520 cutting process Methods 0.000 claims abstract description 21
- 238000012360 testing method Methods 0.000 claims abstract description 13
- 238000005259 measurement Methods 0.000 claims abstract description 5
- 230000010354 integration Effects 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims description 32
- 238000005553 drilling Methods 0.000 claims description 17
- 238000003754 machining Methods 0.000 claims description 5
- 238000002474 experimental method Methods 0.000 claims description 4
- 238000010998 test method Methods 0.000 claims description 4
- 230000000717 retained effect Effects 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 238000011161 development Methods 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 description 12
- 230000000694 effects Effects 0.000 description 11
- 238000013461 design Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 239000002826 coolant Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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Abstract
A kind of processing method in titanium alloy incline bench hole, it is characterized in that: use special compound cutting tool, described compound cutting tool is coaxial segmented formula integration overall structure cutter, the sequential series following three-stage structure of layout drawn near according to the distance with handle of a knife (4): bit part (1), cornish bit part (2), nut (3)；The processing method specific requirement in described titanium alloy incline bench hole is: be 1. adjusted by nut (3)；2. testpieces test is carried out；3. testpieces carries out part processing after measurement is qualified.The present invention breaks through the technical bottleneck of titanium alloy incline bench hole machined, it is ensured that being smoothed out of compressor disk development and production, and the processing for later like parts provides valuable referential experience.
Description
Technical field
The present invention relates to titanium alloy and close deep chamber threading tool and processing, the processing method specifically providing a kind of titanium alloy incline bench hole.
Background technology
In machinery skilled worker's technology, particularly in titanium alloy fan axial workpiece fabricates, closing deep chamber screw thread process is big technological difficulties, and this type of technology is former to be had no precedent, and is initial contact, is not similar to referential processing technology.Titanium alloy fan shaft, is key component, and this design of part is complicated, closes deep chamber screw thread process narrow space, and pitch of thread end face distance is very deep, and it is poor to open wide property, the easy chatter of cutter and cannot observing, and screw thread is as easy as rolling off a log disorderly to be detained, and difficulty of processing is very big.Material is titanium alloy, belongs to difficult-to-machine material, and its inner sealing deep chamber screw thread process cannot be realized by traditional process.Close deep chamber screw thread process technology, it is necessary to assure cutter has enough rigidity and do not interferes with axle endoporus, and guarantee cutter can processed safely deep chamber screw thread.For the closing deep chamber screw thread that diameter of bore is the least, there is no relevant processing experience and cutter scheme.The continuous lifting required along with design performance, the design structure of fan axial workpiece is also being continually changing.Close deep chamber screw thread process technology and have become as a technical barrier urgently to be resolved hurrily.
The processing method in the titanium alloy incline bench hole that a kind of technique effect of the highly desirable acquisition of people is excellent.
Summary of the invention
The processing method that this purpose is to provide the excellent titanium alloy incline bench hole of a kind of technique effect.
It is an object of the present invention to provide a kind of processing method that can realize titanium alloy incline bench hole and dedicated tool thereof, break through titanium alloy and close the technical bottleneck of deep chamber screw thread process, ensureing being smoothed out of fan shaft development, the processing for later like parts provides valuable experience.
Originally the processing method providing a kind of titanium alloy incline bench hole, it is characterized in that: use special compound cutting tool, described compound cutting tool is coaxial segmented formula integration overall structure cutter, the sequential series following three-stage structure of layout drawn near according to the distance with handle of a knife (4): bit part 1, cornish bit part 2, nut 3；
The processing method specific requirement in described titanium alloy incline bench hole is:
1. nut 3 is adjusted: adjust to the position meeting step depth dimensional requirement, the reamer just adjusting nut 3 is arranged on radial drilling machine the row trial cut that spouts, utilize Spline Depth Plug to detect, readjust the position of nut 3, until step hole depth is qualified preferably；Measure bit part 1 and the diameter dimension of cornish bit part so that it is all in the margin of tolerance of stepped hole, it is ensured that step aperture size；
2. testpieces test is carried out: part is arranged on fixture Working position that is fixing and that set hole, mounting plane counterbit on radial drilling machine, it is plane with the drill bit of plane counterbit by oblique surface machining at part tenon grain, gradient cutting-in according to inclined-plane is not more than 0.5mm, it is ensured that axially bored line is perpendicular to the axis of engine；Plane counterbit is removed, install compound expanding drill head, trial cut cuts stepped hole, owing to being to use compound expanding drill to process this structural ledge hole first, can only in test grope machined parameters and tool sharpening feature, for ensureing preferable cutting effect, sufficient coolant not only can have preferable cooling effect also discharge smooth to chip can have certain effect simultaneously, compound expanding drill completes to stepped hole is machined at position limiting structure, lifts reaming bit, removes cutter；Measure each aperture of stepped hole and the degree of depth, complete testpieces processing；
3. testpieces carries out part processing after measurement is qualified: according to step and the experience of processing experiment part, in kind process part, at part circumference tongue-and-groove, there is the stepped hole of 53 uniform circumference, process this circumferential apertures by above-mentioned test method and machined parameters, the most qualified through picking up test amount；Hole of topping bar, the method processing inclined-plane breaches that titanium alloy incline bench hole machined efficiency is low and the technical bottleneck of axiality difference；
The processing method in described titanium alloy incline bench hole processed to as if aero-engine titanium alloy wheel disc incline bench hole, at titanium alloy wheel disc chase mortise, pin-and-hole is positioned at wheel diameter Ф 411.3mm, surface slope is 18 ° 22 ', stepped hole axis requires vertical with engine horizontal axis, if ensureing, high-efficiency high-accuracy difficulty of processing is the biggest.By manufacturing and designing the dedicated tool of special construction, brand-new process, test is used to grope process, meet the technology requirement of disk-like accessory incline bench hole machined.Breach the processing technology being in my innocent life similar to processing experience, solve the unmanageable technical bottleneck in incline bench hole, ensure that Element Design requirement, can promote the use of in same kind of parts, referential experience is provided for like parts processing, lifting to aero-engine manufacturing technology level, has profound significance and inestimable economic benefit.
In special compound cutting tool used in the processing method in described titanium alloy incline bench hole: the front portion of bit part 1 is the drill bit meeting hole bottom step aperture size, drill bit is dextrorotation, drill head helix angle is 27 degree, and drill bit spiral is away from for 28.05mm, the long 20mm of drill bit；Cornish bit part 2 meets upper strata, hole step aperture size, the reamer number of teeth 4, and the reamer hand of spiral is dextrorotation, and hole drill helical angle is 29 degree, and reamer spiral, away from for 40.81mm, working portion length 15mm, has the undercut of 3mm between two parts；Nut 3 is the location structure of reamer, the fastening means using nut 3 is threadedly secured to combine on reamer, trial cut mode is used to determine fixed position, during work with drilling tool on drill bushing with the use of, illustrate that when positioning screw cap part 3 baseplane is touched with drill bushing flat face step depth is machined to put in place, reaming bit can be lifted and complete processing, determine the degree of depth of processing step hole with this；Nut 3 is the bascule that can regulate the degree of depth, and degree of depth adjusting range is 15mm；Handle of a knife 4 is afterbody retained part, and afterbody is No. 1 Morse's cone, is connected with radial drilling machine；Compound cutting tool overall length is 196mm；
Machined parameters is amount of feeding f=0.08mm/r, rotating speed s=350-500r/min.
The present invention breaks through the technical bottleneck of titanium alloy incline bench hole machined, it is ensured that being smoothed out of compressor disk development and production, and the processing for later like parts provides valuable referential experience.
Accompanying drawing explanation
Below in conjunction with the accompanying drawings and embodiment the present invention is further detailed explanation:
Fig. 1 is part deep chamber screw thread schematic diagram；
Fig. 2 is compound cutting tool structural representation sketch；
Fig. 3 is compound cutting tool scale diagrams；
Fig. 4 is the left view with Fig. 3 as front view corresponding with Fig. 3；
Fig. 5 is incline bench pore structure schematic diagram；
Fig. 6 is incline bench hole machined test specimen schematic diagram.
Detailed description of the invention
Embodiment 1
A kind of processing method that can realize titanium alloy incline bench hole and dedicated tool thereof, break through titanium alloy and close the technical bottleneck of deep chamber screw thread process, it is ensured that being smoothed out of fan shaft development, and the processing for later like parts provides valuable experience.
A kind of processing method in titanium alloy incline bench hole, it uses special compound cutting tool, described compound cutting tool is coaxial segmented formula integration overall structure cutter, the sequential series following three-stage structure of layout according to drawing near with the distance of handle of a knife 4: bit part 1, cornish bit part 2, nut 3；
The processing method specific requirement in described titanium alloy incline bench hole is:
1. nut 3 is adjusted: adjust to the position meeting step depth dimensional requirement, the reamer just adjusting nut 3 is arranged on radial drilling machine the row trial cut that spouts, utilize Spline Depth Plug to detect, readjust the position of nut 3, until step hole depth is qualified preferably；Measure bit part 1 and the diameter dimension of cornish bit part 2 so that it is all in the margin of tolerance of stepped hole, it is ensured that step aperture size；
2. testpieces test is carried out: part is arranged on fixture Working position that is fixing and that set hole, mounting plane counterbit on radial drilling machine, it is plane with the drill bit of plane counterbit by oblique surface machining at part tenon grain, gradient cutting-in according to inclined-plane is not more than 0.5mm, it is ensured that axially bored line is perpendicular to the axis of engine；Plane counterbit is removed, install compound expanding drill head, trial cut cuts stepped hole, owing to being to use compound expanding drill to process this structural ledge hole first, can only in test grope machined parameters and tool sharpening feature, for ensureing preferable cutting effect, sufficient coolant not only can have preferable cooling effect also discharge smooth to chip can have certain effect simultaneously, compound expanding drill completes to stepped hole is machined at position limiting structure, lifts reaming bit, removes cutter；Measure each aperture of stepped hole and the degree of depth, complete testpieces processing；
3. testpieces carries out part processing after measurement is qualified: according to step and the experience of processing experiment part, in kind process part, at part circumference tongue-and-groove, there is the stepped hole of 53 uniform circumference, process this circumferential apertures by above-mentioned test method and machined parameters, the most qualified through picking up test amount；Hole of topping bar, the method processing inclined-plane breaches that titanium alloy incline bench hole machined efficiency is low and the technical bottleneck of axiality difference；
The processing method in described titanium alloy incline bench hole processed to as if aero-engine titanium alloy wheel disc incline bench hole, at titanium alloy wheel disc chase mortise, pin-and-hole is positioned at wheel diameter Ф 411.3mm, surface slope is 18 ° 22 ', stepped hole axis requires vertical with engine horizontal axis, if ensureing, high-efficiency high-accuracy difficulty of processing is the biggest.By manufacturing and designing the dedicated tool of special construction, brand-new process, test is used to grope process, meet the technology requirement of disk-like accessory incline bench hole machined.Breach the processing technology being in my innocent life similar to processing experience, solve the unmanageable technical bottleneck in incline bench hole, ensure that Element Design requirement, can promote the use of in same kind of parts, referential experience is provided for like parts processing, lifting to aero-engine manufacturing technology level, has profound significance and inestimable economic benefit.
In special compound cutting tool used in the processing method in described titanium alloy incline bench hole: the front portion of bit part 1 is the drill bit meeting hole bottom step aperture size, drill bit is dextrorotation, drill head helix angle is 27 degree, and drill bit spiral is away from for 28.05mm, the long 20mm of drill bit；Cornish bit part 2 meets upper strata, hole step aperture size, the reamer number of teeth 4, and the reamer hand of spiral is dextrorotation, and hole drill helical angle is 29 degree, and reamer spiral, away from for 40.81mm, working portion length 15mm, has the undercut of 3mm between two parts；Nut 3 is the location structure of reamer, the fastening means using nut 3 is threadedly secured to combine on reamer, trial cut mode is used to determine fixed position, during work with drilling tool on drill bushing with the use of, illustrate that when nut 3 baseplane is touched with drill bushing flat face step depth is machined to put in place, reaming bit can be lifted and complete processing, determine the degree of depth of processing step hole with this；Nut 3 is the bascule that can regulate the degree of depth, and degree of depth adjusting range is 15mm；Handle of a knife 4 is afterbody retained part, and afterbody is No. 1 Morse's cone, is connected with radial drilling machine；Compound cutting tool overall length is 196mm；
Machined parameters is amount of feeding f=0.08mm/r, rotating speed s=350-500r/min.
Work piece titanium alloy incline bench hole Ф 4.5/+0.12 described in the present embodiment and the Ф 6.8/+0.12mm degree of depth 9.5 ± 0.2mm, it is positioned in tongue-and-groove tenon grain symmetrical center line, whole circumference totally 53 step radial holes are uniform, vent surface is the inclined-plane of 18 ° 22 ', because being required for the tongue-and-groove position that independent centering is corresponding for each stepped hole, can not meet the needs that processing is actual, the automation advantage of CNC milling machine is not in full use.So this circumference radially stepped hole can only be processed under radial drilling machine.The repetitive positioning accuracy of radial drilling machine clamping cutter is low, process a step need clamping and dismantle cutter 4 times, cause stepped hole axiality poor, even misplace, repeatedly process the aperture size brought and do not reach requirement, installing backing pin difficulty big, in part time job, pin-and-hole easily departs from part, and engine is caused catastrophic collapse.
The present embodiment uses a kind of new drill to complete the processing in titanium alloy incline bench hole.This new drill is an overall composite drill bit, and this drill bit structure is divided into four parts (such as Fig. 2), and this compound cutting tool overall length is 196mm.
Processing completes after cutter-secondary clamping the required size of stepped hole, each aperture not coaxial line phenomenon oneself be addressed, each aperture size requires to be ensured by compound expanding drill diameter, after the first boring of stepped hole larger aperture, the processing method of reaming is achieved in a drilling process by compound expanding drill, improves the working (machining) efficiency of part.
In testpieces process of the test, first part is arranged on fixture Working position that is fixing and that set hole, the reaming cobalt just adjusting nut 3 is arranged on radial drilling machine and carries out trial cut, utilize Spline Depth Plug to detect, readjust the position of nut 3, until step hole depth is qualified preferably.Mounting plane counterbit on radial drilling machine, is plane with the drill bit of plane counterbit by oblique surface machining at part tongue-and-groove, is not more than 0.5mm according to the gradient cutting-in on inclined-plane, it is ensured that axially bored line is perpendicular to the axis of engine；Being removed by plane counterbit, install compound expanding drill head, trial cut cuts stepped hole, owing to being to use compound expanding drill to process this structural ledge hole first, can only in test grope machined parameters and tool sharpening feature.Finally show that optimum cutting parameter is amount of feeding f=0.08mm/r, rotating speed s=350-500r/min, for ensureing preferable cutting effect, sufficient coolant not only can have preferable cooling effect also discharge smooth to chip can have certain effect simultaneously, compound expanding drill completes to stepped hole is machined at position limiting structure, lift reaming bit, remove cutter.Testpieces processing is qualified.
Testpieces carries out part processing after measurement is qualified.Step according to processing experiment part and experience, in kind process part, has the stepped hole of 53 uniform circumference, process this circumferential apertures by above-mentioned test method and machined parameters at part circumference tongue-and-groove, and it is the most qualified to measure through inspection.Hole of topping bar, the method processing inclined-plane breaches that titanium alloy incline bench hole machined efficiency is low and the technical bottleneck of axiality difference.
The present embodiment breaks through the technical bottleneck of titanium alloy incline bench hole machined, it is ensured that being smoothed out of compressor disk development and production, and the processing for later like parts provides valuable referential experience.
Claims (3)
1. the processing method in a titanium alloy incline bench hole, it is characterized in that: use special compound cutting tool, described compound cutting tool is coaxial segmented formula integration overall structure cutter, the sequential series following three-stage structure of layout drawn near according to the distance with handle of a knife (4): bit part (1), cornish bit part (2), nut (3)；
The processing method specific requirement in described titanium alloy incline bench hole is:
1. nut (3) is adjusted: adjust to the position meeting step depth dimensional requirement, the reamer just adjusting nut (3) is arranged on radial drilling machine the row trial cut that spouts, Spline Depth Plug is utilized to detect, readjust the position of nut (3), until step hole depth is qualified preferably；Measure bit part (1) and the diameter dimension of cornish bit part (2) so that it is all in the margin of tolerance of stepped hole, it is ensured that step aperture size；
2. testpieces test is carried out: part is arranged on fixture Working position that is fixing and that set hole, mounting plane counterbit on radial drilling machine, it is plane with the drill bit of plane counterbit by oblique surface machining at part tenon grain, gradient cutting-in according to inclined-plane is not more than 0.5mm, it is ensured that axially bored line is perpendicular to the axis of engine；Being removed by plane counterbit, install compound expanding drill head, trial cut cuts stepped hole, and at compound expanding drill to position limiting structure, stepped hole is machined completes, and lifts reaming bit, removes cutter；Measure each aperture of stepped hole and the degree of depth, complete testpieces processing；
3. testpieces carries out part processing after measurement is qualified: according to step and the experience of processing experiment part, in kind processes part, has the stepped hole of 53 uniform circumference, process this circumferential apertures by above-mentioned test method and machined parameters at part circumference tongue-and-groove.
2. according to the processing method in titanium alloy incline bench hole described in claim 1, it is characterized in that: the processing method in described titanium alloy incline bench hole processed to as if aero-engine titanium alloy wheel disc incline bench hole, at titanium alloy wheel disc chase mortise, pin-and-hole is positioned at wheel diameter Ф 411.3mm, surface slope is 18 ° 22 ', and stepped hole axis requires vertical with engine horizontal axis.
3. according to the processing method in titanium alloy incline bench hole described in claim 1 or 2, it is characterized in that: in the special compound cutting tool used in the processing method in described titanium alloy incline bench hole: the front portion of bit part (1) is the drill bit meeting hole bottom step aperture size, drill bit is dextrorotation, drill head helix angle is 27 degree, drill bit spiral is away from for 28.05mm, the long 20mm of drill bit；Cornish bit part (2) meets upper strata, hole step aperture size, the reamer number of teeth 4, and the reamer hand of spiral is dextrorotation, and hole drill helical angle is 29 degree, and reamer spiral, away from for 40.81mm, working portion length 15mm, has the undercut of 3mm between two parts；Nut (3) is the location structure of reamer, the fastening means using nut (3) is threadedly secured to combine on reamer, trial cut mode is used to determine fixed position, during work with drilling tool on drill bushing with the use of, illustrate that when positioning screw cap part (3) baseplane is touched with drill bushing flat face step depth is machined to put in place, reaming bit can be lifted and complete processing, determine the degree of depth of processing step hole with this；Nut (3) is the bascule that can regulate the degree of depth, and degree of depth adjusting range is 15mm；Handle of a knife (4) is afterbody retained part, and afterbody is No. 1 Morse's cone, is connected with radial drilling machine；Compound cutting tool overall length is 196mm；
Machined parameters is amount of feeding f=0.08mm/r, rotating speed s=350-500r/min.
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| CN201210308709.9A CN102922227B (en) | 2012-08-28 | 2012-08-28 | A kind of processing method in titanium alloy incline bench hole |
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| CN201210308709.9A CN102922227B (en) | 2012-08-28 | 2012-08-28 | A kind of processing method in titanium alloy incline bench hole |
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| CN102922227B true CN102922227B (en) | 2016-08-17 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103506702B (en) * | 2013-07-23 | 2015-09-30 | 浙江吉利罗佑发动机有限公司 | Processing step hole dedicated tool |
| CN103706817B (en) * | 2013-12-13 | 2017-01-04 | 中国燃气涡轮研究院 | A kind of Novel integral multistage hub rotor unit deep cavity process tool and method thereof |
| CN103990836B (en) * | 2014-05-21 | 2016-09-28 | 芜湖求精紧固件有限公司 | Drill bit and drilling machine |
| CN104741651A (en) * | 2015-03-17 | 2015-07-01 | 成都飞机工业（集团）有限责任公司 | Method for manufacturing holes in different-material laminated structures through automatic drilling and riveting system |
| CN109926796A (en) * | 2018-12-31 | 2019-06-25 | 陕西航宇有色金属加工有限公司 | TC6 titanium alloy rigid wheel shell and processing method thereof |
| CN110369971B (en) * | 2019-08-19 | 2021-04-20 | 四川航天烽火伺服控制技术有限公司 | Grinding rod machining process with externally threaded taper shank for grinding machine |
| CN112620737A (en) * | 2020-12-09 | 2021-04-09 | 贵州黎阳国际制造有限公司 | Deep hole processing device |
| CN114406698B (en) * | 2022-03-17 | 2023-08-25 | 重庆水轮机厂有限责任公司 | Oblique oil hole processing method for hydraulic turbine sliding rotor |
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| EP1363756B1 (en) * | 2000-09-28 | 2007-12-05 | SECO TOOLS AB; (publ) | Tool and countersinker for chip removing machining |
| CN201076935Y (en) * | 2007-09-07 | 2008-06-25 | 济南重工股份有限公司 | Simple composite drilling bit |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1931550B (en) * | 2006-10-11 | 2010-12-22 | 赖其淡 | Drilling bit with both drilling and reaming function |
| JP5236562B2 (en) * | 2009-04-15 | 2013-07-17 | 株式会社神戸製鋼所 | Drill and drilling method |
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|---|---|---|---|---|
| EP1363756B1 (en) * | 2000-09-28 | 2007-12-05 | SECO TOOLS AB; (publ) | Tool and countersinker for chip removing machining |
| CN2612485Y (en) * | 2003-04-01 | 2004-04-21 | 郑州泰阳影视光电研究所 | Aiguille |
| CN201076935Y (en) * | 2007-09-07 | 2008-06-25 | 济南重工股份有限公司 | Simple composite drilling bit |
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