CN102909573B - Machining method of thin-wall heterogenic titanium alloy part - Google Patents
Machining method of thin-wall heterogenic titanium alloy part Download PDFInfo
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- CN102909573B CN102909573B CN201210390172.5A CN201210390172A CN102909573B CN 102909573 B CN102909573 B CN 102909573B CN 201210390172 A CN201210390172 A CN 201210390172A CN 102909573 B CN102909573 B CN 102909573B
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Abstract
The invention discloses a machining method of a thin-wall heterogenic titanium alloy part. The part is clamped by a rigidity reinforced tool in an internal and external opposite pushing manner, and placed on a base of the rigidity reinforced tool, a machining position of the part is clamped by the rigidity reinforced tool in an external opposite pushing manner, and the interior of the part adopts a main beam of the rigidity reinforced tool as a force transmission device. The method aims at improving the rigidity of the part to be machined, and the rigidity reinforced tool is designed to reinforce supporting and improve the body rigidity of the part. For the selection of machining parameters of titanium alloy, the entire oscillation stability domain analysis based on cutter part equipment is adopted, and appropriate cutting parameters are selected; for a shape forming method of the cut part, the cutter base plane modeling is adopted; a cutting tool adopts a circular inserted cutter; the strength of the cutter is improved; a cutting angle is controlled by a cutting depth; and a cutting force and cutting heat are reduced.
Description
Technical field
The invention belongs to Machining Technology field, relate to a kind of processing method of thin-wall special-shaped titanium alloy component.
Background technology
Because have lightweight, feature such as saving material, compact conformation etc., thin-walled parts is applied in each industrial department increasingly extensively.And titanium alloy is as the high material of specific strength, becomes the Material selec-tion of thin-walled parts.And its cutting force of titanium alloy material is large, thermal conductivity is low, work hardening phenomenon is serious; Thin-walled parts poor rigidity, intensity are weak, and the as easy as rolling off a log distortion of work in-process, not easily ensures the crudy of part.These special performances determine aspects such as being machined in cutter, Selecting parameter, design of technological arrangement and must be in optimized selection.
The processing and loading clamp mode of current thin-walled cabin body part is more, and clamping position generally concentrates on the stronger position of the rigidity such as end frame reinforcing frame, but the clamping of part can be caused to be out of shape, poor rigidity.
Easily there is the flutter of knife part Whole Equipment in titanium alloy thin-wall part process, affect machining accuracy.
Because the cutting force of titanium alloy material is large, the consumption of cutter is also larger.
Summary of the invention
Technical scheme of the present invention is to overcome poor rigidity in thin-wall titanium alloy part process, yielding problem.A kind of thin-walled opposite sex titanium alloy component processing method is provided, adopts the clamping tooling of the inside and outside clamping of energy, eliminate clamping and be out of shape.
Technical scheme of the present invention: the processing method of a kind of thin-wall special-shaped Ti alloy casting cabin body, it is inside and outside to top formula clamping holding parts that the method adopts rigidity to strengthen frock, part is placed in rigidity and strengthens on the base of frock, the working position of part adopts rigidity to strengthen the outer of frock and clamps top formula clamping, and inside parts adopts rigidity to strengthen the girder of frock as load transfer device.
The girder that described rigidity strengthens frock is multi-claw type.
Described processing method also adopts overall chatter stability lobes analytical method to choose cutting parameter.
It is as a whole that described entirety refers to that lathe, cutter, part and rigidity strengthen frock.
Described overall chatter stability lobes analytical method is that choose the method for cutting parameter at the lower zone of flutter curve, the method can overcome the Flutter Problem in process by testing overall flutter frequency curve.
Described processing method adopts the method for cutter baseplane profiling to carry out the processing of part.
Described cutter baseplane profiling method adopts CAM software Modling model, generates cutting path, then uses the cutting way of baseplane profiling to carry out part processing.
Described processing method adopts circular built-in cutter as cutting edge.
Described processing method controls the change of the tool cutting edge angle of circular built-in cutter by cutting depth, carry out part processing.
Beneficial effect of the present invention:
The present invention is for the purpose of the rigidity strengthening part to be processed, and design rigidity is strengthened frock and strengthened supporting, and strengthens the body rigidity of part.Machined parameters for titanium alloy is selected, adopt and select mode based on the domain analysis of knife part Whole Equipment flutter instability, choose suitable cutting parameter, for the shape molding method of machined part, select the mode of cutter baseplane profiling to carry out, circular built-in cutter selected by cutting tool, improves the intensity of cutter, control cutting angle by cutting depth, reduce cutting force and heat in metal cutting.
Processing method designed by the present invention by strengthen the design of technological equipment, installation way, the selecting of cutter and cutting parameter, processing mode adjustment efficiently solve Flutter Problem in thin-wall special-shaped titanium alloy component process, can working special-shaped titanium alloy component wall thickness 3mm, material removing rate reaches 60cm^3/min.
Accompanying drawing explanation
Fig. 1 is the schematic diagram after rigidity strengthens frock clamping part;
Fig. 2 is that cutting parameter selects flutter simulation figure;
Detailed description of the invention
Method of the present invention is described in detail below in conjunction with accompanying drawing.
A processing method for thin-wall special-shaped titanium alloy component, adopts rigidity to strengthen frock inside and outside to top formula clamping, based on the parameters selection mode of knife part Whole Equipment flutter instability domain analysis, and the processing mode of bottom surface profiling, tool selection circular shear blade; The method concrete steps are as follows:
The first step: design rigidity strengthens the rigidity that frock strengthens part, according to the inner case of part 1, adopts rigidity to strengthen frock 2 inside and outside to top formula clamping holding parts, part 1 and rigidity is strengthened frock 2 and effectively connects into a rigid bodies; The inside and outside mode to top formula clamping is adopted to offset the clamping distortion of part in clamping process; Wherein, part 1 is placed in rigidity and strengthens on the base 23 of frock 2, and the working position of part adopts rigidity to strengthen the outer of frock 2 and clamps top formula clamping 22, and inside parts adopts rigidity to strengthen the girder 21 of frock 2 as load transfer device.
Second step: lathe, cutter, part 1 and rigidity are strengthened frock 2 and integrally carries out flutter analysis, the flutter frequency curve that test is overall, choose cutting parameter at the lower zone of flutter curve, according to flutter simulation scenarios, choose rational cutting parameter;
3rd step: utilize CAM software Modling model, select the mode of cutter baseplane profiling, carry out cutting path generation, utilizes the cutting way of baseplane profiling to complete the processing of part;
4th step: utilize circular shear blade as cutting edge, is controlled the change of tool cutting edge angle, completes the processing of part by cutting depth.
Operation principle: the present invention is a kind of processing method of thin-wall special-shaped titanium alloy component, by strengthen the design of technological equipment, installation way, the selecting of cutter and cutting parameter, processing mode adjustment solve Flutter Problem in the body process of thin-wall special-shaped Ti alloy casting cabin.
Processing method of the present invention, its technical scheme is: rigidity is strengthened frock and adopted three girders 21 as main load transfer device, and adopt outer to top formula clamping 22 at working position, bottom adopts base 23 as main bearing.First according to the feature design rigidity strengthening process equipment of part, consider volume and weight two aspect factor, determine that rigidity strengthens girder 21 size of frock 2, girder 21 is the basic structure of rigidity reinforced, becomes the primary structure of whole process system rigidity; According to shape feature design support claw structure in part, make that the covering of part 1 is stressed is effectively delivered to girder 21, make part 1 and rigidity strengthen frock 2 and form a rigid bodies, as shown in Figure 1.Select rational bite, make the inside and outside clamping masterpiece of part for same point, counteract the part clamping distortion that clamping power produces.Utilize flutter analysis software that lathe, rigidity reinforcement frock 2, part 1, cutter are integrally carried out flutter analysis, cutting parameter is chosen on the basis analyzed, the object of this Selecting All Parameters is the vibration frequency in order to avoid process system, thus avoid the chatter phenomenon in process, cutting parameter selects flutter simulation figure to see Fig. 2.By CAM software, flat built-in cutter is adopted to adopt the mode of bottom surface processing profiling to carry out the copying of External Shape, adopt this kind of cutting way, effectively can reduce the cutting force in working angles, improve the stressing conditions in part process, make stressed mainly the concentrating on of the cutting of part be parallel to outerplanar direction, reduce the cutting force perpendicular to part 1, effectively avoid the vertical impact to thin-wall regions in part process, avoid the generation of chatter phenomenon.Circular shear blade has strong cutting edge, and by changing cutting-in, controlling rational tool cutting edge angle, is the load on uniform distribution cutting edge, adopts the mode of slope feed to cut.Control uniform corner cutting speed, maintain uniform chip-load.
Above-mentioned method is not limit the present invention to be undertaken by above-mentioned steps, but can, according to the part of reality processing on the basis adopting rigidity reinforcement frock, select arbitrarily above-mentioned steps to process.
Instantiation
The part of test processing is space flight titanium alloy thin-wall part, use the OPTICUT software of BJ University of Aeronautics & Astronautics to carry out cutting parameter to select, UG software is utilized to carry out CAM programming and design of technological arrangement, use the KPU4000 of Spain's production as process equipment, tool specification 20mm, cutting-in 1mm, cut wide 12mm, rotating speed 900r/min, feeding 400mm/min.Part 1 structure is casting cabin body.
Main process design process is as follows: design rigidity strengthens frock as shown in Figure 1, according to part 1 size adjusting clamping position.Utilize CAM Software Create flat-bottomed cutter bottom surface copying program, utilize flutter analysis software to carry out tremor syndrome analysis as shown in Figure 2, select circular built-in cutter, the blade circular shear blade of its cutter carries out the machining of part, part wall thickness 3mm after processing.
Part after utilizing above-mentioned processing method to process, appearance and size tolerance 0.1mm, there is not chatter phenomenon in process in surface roughness 1.6.
The present invention proposes the new method for processing of thin-wall special-shaped titanium alloy component, improve the Flutter Problem in thin-wall special-shaped titanium alloy component process, improve crudy, reduce processing cost, improve working (machining) efficiency.This intellectual achievement applies to produce very large economic benefit in actual production, has very strong application prospect.
Claims (6)
1. the processing method of a thin-wall special-shaped titanium alloy component, it is characterized in that, rigidity is adopted to strengthen frock inside and outside to top formula clamping holding parts, part is placed in rigidity and strengthens on the base of frock, the working position of part adopts rigidity to strengthen the outer of frock and clamps top formula clamping, inside parts adopts rigidity to strengthen the girder of frock as load transfer device, and the girder that described rigidity strengthens frock is multi-claw type; Described processing method also adopts overall chatter stability lobes analytical method to choose cutting parameter, and it is as a whole that described entirety refers to that lathe, cutter, part and rigidity strengthen frock.
2. the processing method of thin-wall special-shaped titanium alloy component according to claim 1, is characterized in that, described overall chatter stability lobes analytical method is by testing overall flutter frequency curve, choosing the method for cutting parameter at the lower zone of flutter curve.
3. the processing method of thin-wall special-shaped titanium alloy component according to claim 1, is characterized in that, described processing method adopts the method for cutter baseplane profiling to carry out the processing of part.
4. the processing method of thin-wall special-shaped titanium alloy component according to claim 3, it is characterized in that, described cutter baseplane profiling method adopts CAM software Modling model, generates cutting path, then uses the cutting way of baseplane profiling to carry out part processing.
5. the processing method of thin-wall special-shaped titanium alloy component according to claim 1, is characterized in that, described processing method adopts circular built-in cutter as cutting edge.
6. the processing method of thin-wall special-shaped titanium alloy component according to claim 5, is characterized in that, described processing method controls the change of the tool cutting edge angle of circular built-in cutter by cutting depth, carry out part processing.
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| JP4909092B2 (en) * | 2007-01-10 | 2012-04-04 | 本田技研工業株式会社 | Light alloy extrusion frame |
| CN101774122B (en) * | 2010-02-03 | 2012-05-23 | 韩晓云 | Cutter head and machine tool for circular step plane processing and processing technology thereof |
| CN201760770U (en) * | 2010-09-19 | 2011-03-16 | 南车株洲电机有限公司 | Deformation-proof device for motor-car thin wall aluminium alloy end cover processing |
| CN102126140B (en) * | 2010-12-22 | 2012-09-26 | 北京遥测技术研究所 | Combined clamp and clamping method for small-mouth large-cavity thin-walled part |
| CN201997786U (en) * | 2011-04-14 | 2011-10-05 | 大连机床集团有限责任公司 | Milling fixture mechanism for workpiece of crank cases |
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