CN202922262U - Clamp special for thin-wall blade area symmetric precision cutting machining method - Google Patents
Clamp special for thin-wall blade area symmetric precision cutting machining method Download PDFInfo
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- CN202922262U CN202922262U CN 201220487325 CN201220487325U CN202922262U CN 202922262 U CN202922262 U CN 202922262U CN 201220487325 CN201220487325 CN 201220487325 CN 201220487325 U CN201220487325 U CN 201220487325U CN 202922262 U CN202922262 U CN 202922262U
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Abstract
The utility model discloses a clamp special for a thin-wall blade area symmetric precision cutting machining method. The clamp special for the thin-wall blade area symmetric precision cutting machining method comprises a base, a positioning column and stand columns, wherein the base is fixed on an operation platform of a machine tool, the positioning column is vertically inserted into a pin hole of the base and used for adjusting space positions of blades, and two stand columns are fixed on the base. One stand column fixes a long-thin shaft portion of an adjustable blade, and the other stand column fixes a drum-shaped portion of the adjustable blade. By adoption of the clamp and application of a corresponding method, cutting machining of a blade back and a blade basin type face and clamping and arranging once can be completed, simultaneously, positioning precision and machining efficiency can be improved, semi-precision machining and precision machining of blade type face subregions can be symmetrically completed in an alternating mode, twisting deformation of the machining process can be effectively restrained, and machining precision is improved. Machining allowance of the front and back edge portions of the blades are firstly cut off, bearing effect of the machining allowance of the middle of the blades is utilized, and cutter relieving deformation phenomenon of the front and back edges in the machining process can be effectively avoided.
Description
Technical field
The utility model relates to precision, Ultra-precision machining technical field, is specially the special fixture of the symmetrical precision cutting machining method in a kind of thin wall vane subregion, mainly solves the fine finishining Deformation control problem of aero-engine thin wall vane.
Background technology
The complex thin-wall constitutional details such as thin wall vane obtain using more and more widely, realize that the high-efficiency and precision Computerized Numerical Control processing technology of this type of part has become one of important behaviour form of advanced manufacturing enterprise core competitiveness.
Along with the improvement of method for designing, utilize advanced spindle technology and gapless linear roller guide rail technology etc., modern numerical control machining center body has very high rigidity and accurate motion control, can satisfy the demand of most of processing tasks.Take Mikron UCP 1350 as example, the positioning accuracy of this lathe is respectively (franchise mm): X-axis is 0.010, and Y-axis is 0.008, and Z axis is that 0.008, C axle is 8 ", the A axle is 6 ".But, in cutting process, because the machining deformation error that cutting force, residual stress etc. causes but only just can not avoided by improving grinding machine structure design fully, thereby limited to a great extent the application of high-precision numerical control machine.These contradictions are particularly remarkable in the process of machining thin-walled parts.
Traditional blade single face milling process respectively in semifinishing and finishing step, or is first processed the blade back profile, or is first processed leaf basin profile.Can find, take this tool path pattern, due to the nonequilibrium condition of blade back, leaf basin profile milling surface residual stress, thin wall vane has presented obvious bending metaboly.The deficiency that often directly causes the regional area allowances for finish such as blade tip and front and back rafter, i.e. so-called " misrun " phenomenon also will have a strong impact on the contour accuracy of blade simultaneously.
Shortcoming for existing thin wall vane processing technology, a kind of brand-new technological method for processing of necessary proposition, the effective control of realization to the thin wall vane machining deformation, significantly improve machining accuracy and efficient, to satisfy relevant scientific and technological engineering field to the active demand of Improvement and perfection thin-walled, Ultrathin bucket precision cutting process technology.
Summary of the invention
The technical problem that solves
The problem that exists for solving prior art, the utility model proposes the special fixture of the symmetrical precision cutting machining method in a kind of thin wall vane subregion, the method is in symmetrical in twos mode, alternately complete semifinishing and the fine finishining of each sub regions on blade back, leaf basin profile, thereby reach the purpose that suppresses thin wall vane fine finishining torsional deformation.
Technical scheme
The utility model is divided into several symmetrical subregions along the string of a musical instrument direction of blade with blade back profile, leaf basin profile, and alternately completes semifinishing and the finishing step of each sub regions.The processing sequence of all subregions by symmetrical in twos mode by near the part of the front and back rafter mid portion to blade back and leaf basin.For certain two sub regions that is in symmetric position on blade back, leaf basin profile, the subregion on semifinishing blade back profile at first; Then, 180 ° of worktable rotaries, corresponding subregion on semifinishing leaf basin profile; And then, the subregion on fine finishining leaf basin profile; At last, 180 ° of worktable rotaries are completed the fine finishining of the subregion on the blade back profile.
The special fixture of the symmetrical precision cutting machining method in described a kind of thin wall vane subregion, it is characterized in that: comprise base, locating dowel and column, base is fixed on platen, in the pin-and-hole of the vertical inserted base of locating dowel, be used for adjusting the dimensional orientation of blade, two columns are fixed on base, and one of them column is the elongate shaft portion of adjustable vane fixedly, and another column is the cydariform part of adjustable vane fixedly.
Beneficial effect
Use the symmetrical precision cutting machining method in thin wall vane subregion and special fixture that the utility model proposes, the outstanding advantages with following three aspects:
1) clamped one time is completed the machining of blade back and leaf basin profile simultaneously, can improve positioning accuracy and working (machining) efficiency.
2) alternately symmetrical semifinishing and the fine finishining of completing each sub regions of blade profile, can effectively suppress the torsional deformation in process, improves machining accuracy.
3) allowance of rafter part is at first cut before and after blade, utilizes the supporting role of blade middle part allowance, can effectively avoid in process before and after the cutter relieving metaboly of rafter part.
Description of drawings
Fig. 1: aero-engine adjustable vane schematic diagram;
Fig. 2: the symmetrical precision cutting processing process in adjustable vane subregion;
Fig. 3: the adjustable vane blank rough mill profile;
Fig. 4: the cutter path of roughing blade back profile;
Fig. 5: blade special fixture;
Fig. 6: the machining area of blade profile is divided schematic diagram;
Fig. 7: the subregion of fine finishining blade back profile.
Wherein: the cydariform of the elongate shaft portion of rafter, 3-blade back profile, 4-leaf basin profile, 5-blade one end, 6-blade other end part, the elongated axle head clamp of 7-, the elongated axle head column of 8-, 9-cydariform part clamp, 10-cydariform part column, 11-base, 12-workbench, 13-clamp trip bolt, 14-base trip bolt, 15-locating dowel after the front rafter of 1-, 2-;
Q in Fig. 6
1, Q
2Be projection plane, 19,20,21 ... 30 is Q
1Subarea number in the plane, 31,32,33 ... 42 is Q
2Subarea number in the plane.
The specific embodiment
Below in conjunction with specific embodiment, the utility model is described:
The present embodiment is take aero-engine thin-walled adjustable vane shown in Figure 1 as example, this aero-engine adjustable vane is comprised of front rafter 1, rear rafter 2, blade back profile 3, leaf basin profile 4, and the elongate shaft portion 5 at blade two ends is connected with interior ring with the casing of engine respectively with cydariform part 6.The Main Function of adjustable vane in aero-engine is to adjust air inlet angle and gas flow.The flow process of this symmetrical precision cutting processing technology in thin-walled adjustable vane subregion as shown in Figure 2.
Choose the square blank of appropriate size according to the size of the aero-engine thin-walled adjustable vane of required processing, be convenient to processing and loading clamp in early stage location, make material removal amount less and improve working (machining) efficiency.Then cut out the general shape of blade with wire cutting machine tool, remove a large amount of surplus on blank.The allowance of general line cutting is 1mm ~ 2mm.Adopt the processing method of rough milling again, with large-sized rose cutter machining blade profile, remove most surplus on blade profile, the rough milling surplus is generally 1mm ~ 1.5mm.At last the blade after roughing is placed in temperature conditions and is 10-12h under the environment of 45 ℃ ± 5 ℃, discharge the internal stress that produce in process early stage.
In the present embodiment, the adjustable vane rough forging is of a size of 328mm * 92mm * 56mm, rough mills four barbed portion of blade both sides, and at two ends numerical control drilling center hole.Through the blank shape after rough milling as shown in Figure 3.
Rough mill blade back, leaf basin profile on common three coordinate numerical control milling machine, surplus 1mm not only satisfies processing request but also saved processing cost.Adopt traditional single-sided process technique, namely first process the blade back profile, rear processing leaf basin profile.Use existing CAM software such as UG, Cimatron etc. and can generate easily rough machined cutter path.The cutter path that Fig. 4 provides when being roughing blade back profile 3.
Take center hole and platform termination as the rough turn elongate shaft portion 5 of benchmark and cydariform part 6.
Adjustable vane by material requirements after to roughing carries out artificial aging to be processed.
Press elongate shaft portion 5 and the cydariform part 6 at figure paper size finish turning blade two ends.
Next blade is carried out the symmetrical semifinishing in subregion and fine finishining, its allowance is respectively 0.3mm-0.5mm and 0.03mm-0.05mm.When half essence of planning adjustable vane profile, finishing tool track, adopt the face type of drive to carry out cutter orbit making.According to true form, size and the required precision etc. of blade, blade profile is carried out the zoning before processing, concrete division methods is:
At first, with the profile border of blade respectively upright projection to plane Q
1With plane Q
2On, described plane Q
1With plane Q
2Lay respectively at outside the blade back outside and leaf basin, and plane Q
1With plane Q
2All be parallel to the plane that is formed by the blade two ends string of a musical instrument.
Secondly, with the blade two ends string of a musical instrument at plane Q
1With plane Q
2On Projection Line Segment all be divided into the n section, L/10≤n≤L/5 wherein, n is the positive integer greater than 1, L=max{L1, L2}, L1 are that the blade one end string of a musical instrument is at plane Q
1The length of Projection Line Segment, L2 is that the blade other end string of a musical instrument is at plane Q
1The length of Projection Line Segment, the unit of L1 and L2 is mm; With plane Q
1The Along ent of upper two Projection Line Segments is corresponding to be connected, thus with blade at plane Q
1On the projected outline zone be divided into the n sub regions, in the past rafter is g to rear rafter number consecutively
iTo g
i+nWith plane Q
2The Along ent of upper two Projection Line Segments is corresponding to be connected, thus with blade at plane Q
2On the projected outline zone be divided into the n sub regions, in the past rafter is h to rear rafter number consecutively
iTo h
i+nThese subregions are the drive surface when generating D. C. Machining Cutter Track respectively.
In the present embodiment, the blade two ends string of a musical instrument is at plane Q
1With plane Q
2On Projection Line Segment length be respectively 76.212mm and 52.736mm, therefore, get L=max{76.212,52.736}=76.212mm, the subregion number n that divides should satisfy: 76.212/10≤n≤76.212/5, i.e. 7.6212≤n≤15.2424.So can get n is 12, be about to the subregion that blade profile view field is divided into 12 symmetries.Along the string of a musical instrument direction of respective vanes with plane Q
1And Q
2On the outline projection zone be divided into the subregion of 12 symmetries, be positioned at the plane Q of blade back one side
1On the numbering from 19 to 30 of subregion, be positioned at the plane Q of leaf basin one side
2On the numbering from 31 to 42 of subregion.Drive surface when as shown in Figure 6, these subregions are respectively as the generation D. C. Machining Cutter Track.
Again, to special fixture, as shown in Figure 5, special fixture comprises base 11, locating dowel 15 and column with the blade clamping, and base through screws is fixed on platen 12, and rotates with workbench.In the pin-and-hole of the vertical inserted base of locating dowel, be used for adjusting the dimensional orientation of blade.Elongated axle head clamp 7 and elongated axle head column 8 are used for the fixedly elongate shaft portion 5 of adjustable vane, and use screw fastening; Cydariform part clamp 9 and cydariform part column 10 are used for the fixedly cydariform part 6 of adjustable vane, and use screw fastening.In Fig. 5, cutter 16 has represented the relative position relation between the major axes orientation of Four-axis NC Welding machining center and fixture, adjustable vane.The slender axles of fixed blade and cydariform part, 4 frees degree (2 translation freedoms that can limit blade
2 rotational freedom X, Z), the multidiameter end face in the blade slender axles can limit 1 translation freedoms
After the cylinder of locating dowel and blade and blade basin, rafter is tangent, a free degree Y who sways of limit blade.
Blade is after clamping on special fixture is fixing, according to the subregion of aforementioned division, according to symmetrical in twos mode, by processing successively all subregions near part to the mid portion of blade back and leaf basin of rafter before and after blade.Namely first process the go forward subregion g at rafter place of blade back profile
iWith the go forward subregion h at rafter place of leaf basin profile
i, on the blade back profile after the subregion g at rafter place
i+nWith on leaf basin profile after the subregion h at rafter place
i+nNext processes subregion g
I+n-1And h
I+n-1, g
i+1And h
i+1, g
I+n-2And h
I+n-2, g
i+2And h
i+2, g
I+n-3And h
I+n-3, g
i+3And h
i+3,, g
I+n-4And h
I+n-4, g
i+4And h
i+4Process at last the subregion g at blade back profile and leaf basin profile middle part
I+n/2And h
I+n/2(when n is even number) or g
I+ (n-1)/2And h
I+ (n-1)/2(when n is odd number).So far, all subregions all are machined into.
For two sub regions that are in symmetric position on blade back, leaf basin profile, with the subregion g on the blade back profile
i+kWith the subregion h on leaf basin profile
i+kBe example, it replaces symmetrical semifinishing and accurately machined process is: the subregion g on semifinishing blade back profile
i+k180 ° of worktable rotaries, corresponding subregion h on semifinishing leaf basin profile
i+kSubregion h on fine finishining leaf basin profile
i+k180 ° of worktable rotaries are completed the subregion g on the blade back profile
i+kFine finishining.
For the blade that processes, carry out the blade profile processing dimension and detect on three coordinate measuring machine, if the blade profile parameter-size that records and form and position tolerance etc. within the margin of tolerance of design, illustrate that processing is qualified; Otherwise, defective.Detection method is: for the fine finishining of blade profile, be mainly that the precision that guarantees its profile meets the demands, therefore, detecting as accurately machined profile is mainly to detect profile after fine finishining whether within the margin of tolerance.Because blade profile is free form surface, providing t(t during design is the contour number) the bar contour, to any contour, provide m
i(m
iBe that design on i bar contour is counted, i=1 ... t) individual design point.Detection method generally adopts contouring method to detect.At first spoon of blade is divided into front rafter, rear rafter, leaf dish, blade back four zones.When detecting along any contour, each piece zone is suitably chosen the test point (curvature general goal select test point intensive) of some according to the size of curvature, detect position after these fine finishining whether within the margin of tolerance of drawing requirement, if all test points are all qualified, illustrate that this regional Free-Form Surface Machining size is qualified.All n bar contours are carried out similarly operation, if the Free-Form Surface Machining size of All Ranges is all qualified, the profile processing dimension of this blade is qualified; Otherwise, defective.
Process qualified part, carry out polishing, can remove the ball head knife point and mill the microcosmic Wave crest and wave trough that causes, realize the surface roughness and the optimizing surface integrality that require.General polishing surplus is 0.02mm.According to the requirement of design drawing, require (Ra value size) according to polishing, select rational burnishing parameters.The polishing vestige that stays when needing after polishing is completed to carry out vibration finishing with the removal polishing.
Claims (1)
1. the special fixture of the symmetrical precision cutting machining method in thin wall vane subregion, it is characterized in that: comprise base, locating dowel and column, base is fixed on platen, in the pin-and-hole of the vertical inserted base of locating dowel, be used for adjusting the dimensional orientation of blade, two columns are fixed on base, and one of them column is the elongate shaft portion of adjustable vane fixedly, and another column is the cydariform part of adjustable vane fixedly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220487325 CN202922262U (en) | 2012-09-24 | 2012-09-24 | Clamp special for thin-wall blade area symmetric precision cutting machining method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220487325 CN202922262U (en) | 2012-09-24 | 2012-09-24 | Clamp special for thin-wall blade area symmetric precision cutting machining method |
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| Publication Number | Publication Date |
|---|---|
| CN202922262U true CN202922262U (en) | 2013-05-08 |
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ID=48212255
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220487325 Expired - Fee Related CN202922262U (en) | 2012-09-24 | 2012-09-24 | Clamp special for thin-wall blade area symmetric precision cutting machining method |
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Cited By (11)
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|---|---|---|---|---|
| CN102862035A (en) * | 2012-09-24 | 2013-01-09 | 西北工业大学 | Method for symmetrically and precisely cutting and machining thin-wall blade by regions and special clamp thereof |
| CN104439987A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method for guaranteeing shape completeness of air inlet and air outlet side circular arcs of blade |
| CN104475841A (en) * | 2014-10-28 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Long-cantilever large-scale integral blade-disc blade one-step milling method |
| CN104858682A (en) * | 2015-05-07 | 2015-08-26 | 北京航空航天大学 | Double-arm self-adapting fixture used for controlling machining deformation of blade |
| CN105817918A (en) * | 2016-04-11 | 2016-08-03 | 西北工业大学明德学院 | Special positioning fixture for blade numerical control precision machining |
| CN106881648A (en) * | 2017-03-27 | 2017-06-23 | 江苏科技大学 | A kind of tuning for Controllable Pitch Propeller blade surface sanding apparatus and polishing process |
| CN107838642A (en) * | 2017-12-18 | 2018-03-27 | 中国航发贵州黎阳航空动力有限公司 | A kind of processing method of bipode thin wall vane part |
| CN108406374A (en) * | 2018-06-13 | 2018-08-17 | 中国航发常州兰翔机械有限责任公司 | Process two grade blade recruitment dress of aero-engine free turbine |
| CN112207524A (en) * | 2020-08-26 | 2021-01-12 | 成都市新美加机械设备制造有限公司 | Small blade processing technology |
| CN112427885A (en) * | 2020-10-27 | 2021-03-02 | 上海航天精密机械研究所 | Method and supporting mechanism suitable for machining large thin-wall frame ring part |
| CN114178785A (en) * | 2021-11-23 | 2022-03-15 | 南昌沪航工业有限公司 | Method for processing brim-shaped curved wall plate part |
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- 2012-09-24 CN CN 201220487325 patent/CN202922262U/en not_active Expired - Fee Related
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102862035A (en) * | 2012-09-24 | 2013-01-09 | 西北工业大学 | Method for symmetrically and precisely cutting and machining thin-wall blade by regions and special clamp thereof |
| CN102862035B (en) * | 2012-09-24 | 2015-01-28 | 西北工业大学 | Method for symmetrically and precisely cutting and machining thin-wall blade by regions and special clamp thereof |
| CN104475841A (en) * | 2014-10-28 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Long-cantilever large-scale integral blade-disc blade one-step milling method |
| CN104439987A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method for guaranteeing shape completeness of air inlet and air outlet side circular arcs of blade |
| CN104858682B (en) * | 2015-05-07 | 2017-12-26 | 北京航空航天大学 | A kind of blade processing Deformation control both arms Self adapting fixture |
| CN104858682A (en) * | 2015-05-07 | 2015-08-26 | 北京航空航天大学 | Double-arm self-adapting fixture used for controlling machining deformation of blade |
| CN105817918A (en) * | 2016-04-11 | 2016-08-03 | 西北工业大学明德学院 | Special positioning fixture for blade numerical control precision machining |
| CN105817918B (en) * | 2016-04-11 | 2017-11-07 | 西北工业大学明德学院 | A kind of precision machined special positioning fixture of blade digital control |
| CN106881648A (en) * | 2017-03-27 | 2017-06-23 | 江苏科技大学 | A kind of tuning for Controllable Pitch Propeller blade surface sanding apparatus and polishing process |
| CN106881648B (en) * | 2017-03-27 | 2022-12-27 | 江苏科技大学 | Blade surface polishing device and method for controllable-pitch propeller |
| CN107838642B (en) * | 2017-12-18 | 2019-03-05 | 中国航发贵州黎阳航空动力有限公司 | A kind of processing method of bipode thin wall vane part |
| CN107838642A (en) * | 2017-12-18 | 2018-03-27 | 中国航发贵州黎阳航空动力有限公司 | A kind of processing method of bipode thin wall vane part |
| CN108406374A (en) * | 2018-06-13 | 2018-08-17 | 中国航发常州兰翔机械有限责任公司 | Process two grade blade recruitment dress of aero-engine free turbine |
| CN112207524A (en) * | 2020-08-26 | 2021-01-12 | 成都市新美加机械设备制造有限公司 | Small blade processing technology |
| CN112207524B (en) * | 2020-08-26 | 2022-07-19 | 成都市新美加机械设备制造有限公司 | Small blade processing technology |
| CN112427885A (en) * | 2020-10-27 | 2021-03-02 | 上海航天精密机械研究所 | Method and supporting mechanism suitable for machining large thin-wall frame ring part |
| CN112427885B (en) * | 2020-10-27 | 2022-09-13 | 上海航天精密机械研究所 | Method and supporting mechanism suitable for machining large thin-wall frame ring part |
| CN114178785A (en) * | 2021-11-23 | 2022-03-15 | 南昌沪航工业有限公司 | Method for processing brim-shaped curved wall plate part |
| CN114178785B (en) * | 2021-11-23 | 2022-11-15 | 南昌沪航工业有限公司 | Method for processing brim-shaped curved wall plate part |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130508 Termination date: 20150924 |
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| EXPY | Termination of patent right or utility model |