CN103084639A - Method for strengthening process rigidity of thin-wall blade based on non-uniform allowance - Google Patents
Method for strengthening process rigidity of thin-wall blade based on non-uniform allowance Download PDFInfo
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Abstract
The invention discloses a method for strengthening the process rigidity of a thin-wall blade based on non-uniform allowance; from the perspective of adjusting the process rigidity of a blank in ahead of finely processing the thin-wall blade, the milling is carried out according to the method, so that the processing deformation of a thin-wall blade machine can be effectively controlled, and the processing error is reduced; because the deformation of the blade generated under the action of milling force is mainly in the normal direction of the blade, the rigidity of various points of the blade under the milling conditions and the rigidity variation tendency of the whole blade are researched and found out by analyzing the deformation of the various points of the blade under the same cutting force; on the basis, a method for distributing the fine processing allowance of the blade is optimized; and the cutting deformation of the thin-wall blade in the fine processing is reduced. The stability in the cutting process is improved from two aspects comprising the optimization of processing and cutting force and the optimization of the rigidity of work-pieces; and therefore, the deformation problem caused by insufficient numerical control milling and fine-processing rigidity of the thin-wall blade is solved.
Description
Technical field
The present invention relates to a kind of method of the enhancing thin wall vane process rigidity based on non-homogeneous surplus, belong to blade of aviation engine manufacturing and precision cutting manufacture field.
Background technology
Blade is the core part of aero-engine, is also a kind of typical thin wall component, and its manufacture level directly affects the aeroperformance of aero-engine.Along with the development of pneumatic design technology, structure technology and material technology, that blade of aviation engine has occurred is curved, turn round, thin, plunder, light design feature, have higher requirement also for simultaneously its accuracy of manufacture.
In the Milling Processes of reality, due to the acting in conjunction that is subject to cutting force, heat in metal cutting and metal metallographic and tears, blade can produce machining deformation, and precision of blades and profile tolerance after causing processing are relatively poor.At present, domestic thin wall vane manufacturing fine-processing technique is numerical control semifinishing and manual grinding fine finishining; Mainly because blade belongs to the thin-wall curved-surface part, machining deformation is difficult to control, for avoiding occurring waste product, must leave the distortion that enough surplus compensation digital control processings cause, polishing is carried out in the last resort manually-operated, with the method for " limit polishing, frontier inspection are tested ", the surplus that blade leaves is progressively got rid of.But without cooling fluid, control blade profile shape by model due to the manual grinding process, therefore working (machining) efficiency is low, labour intensity is large, surface accuracy is low, percent ripple is large, easily burns, quality is unstable, can't satisfy thin wall vane to the requirement of wall thickness and the control of blade profile precision.
Simultaneously, in engineering practice, in order to eliminate machining deformation to the adverse effect of thin wall vane numerical control (NC) Machining Accuracy, often by adopting some technological measures to reduce the machining deformation of blade, thereby guarantee that machining accuracy reaches designing requirement.The means of mainly taking at present have: optimize NC Cutting Parameters to reduce cutting force, for example, along the cutting path of cutter, the local cutting parameters such as the speed of mainshaft and feed speed of adjusting, make the size of cutting force be no more than limiting value, the off-gage phenomenon that can avoid the distortion of elasticity cutter relieving to cause; By improving and optimizing the clamping scheme to increase the rigidity of part, for example, adopt the means of blade special fixture or employing supplemental support; These measures can reduce machining deformation and the mismachining tolerance of blade, but this just must increase a lot of extra operations, and these technological measures are mainly take qualitative analysis and actual processing experience as the basis, lack quantitative analysis and working specification, the not only precision of part and difficult quality guarantee, and had a strong impact on working (machining) efficiency.
Machining deformation is the key factor that affects thin wall vane efficiency of numerical control (NC) machining, precision and surface quality.For the deficiency that existing thin wall vane processing technology exists, necessary existing technological method for processing is optimized and improves.Thereby seek a kind of new blade processing distortion, realize the effective control to the thin wall vane machining deformation, significantly improve machining accuracy and efficient, to satisfy correlative technology field to the active demand of Improvement and perfection thin-walled, Ultrathin bucket precision milling process technology.
Summary of the invention
Deficiency for fear of prior art exists overcomes the problem on deformation that thin-wall part numerical control milling fine finishining insufficient rigidity causes, the present invention proposes a kind of method of the enhancing thin wall vane process rigidity based on non-homogeneous surplus.
The present invention regulates the angle of blank technology rigidity before thin wall vane fine finishining, carry out Milling Process according to the method and can effectively control the thin wall vane machining distortion, reduces mismachining tolerance; The distortion that produces under the effect of Milling Force due to blade is mainly in the normal orientation of blade; By analyzing the blade each point at the deflection that applies under identical cutting force, the each point rigidity of blade under milling condition is found out in research, and the stiffness variation trend of whole blade, on this basis blade allowance for finish location mode is optimized, reduces the cutting deformation in thin wall vane fine finishining process.
The present invention is based on the method for the enhancing thin wall vane process rigidity of non-homogeneous surplus, be characterized in comprising the following steps:
Step 1. adopts limited element analysis technique to carry out deformation analysis to thin wall vane, choose u * v node respectively on the blade back of thin wall vane and leaf basin, definition along sharf to be U to, along blade profile line direction be V to, u * v node is at U, the parameter distribution such as V direction apply certain cutting force on each node, obtain the deformation of thin-wall part each point under this cutting force;
λ=K+αδ (1)
Wherein K is constant;
Step 6. consists of face with the curve negotiating that the obtains method of scanning, and obtains the fine finishining front vane curved surface by non-homogeneous surplus method construct.
Beneficial effect
The method of a kind of enhancing thin wall vane process rigidity based on non-homogeneous surplus of the present invention, regulate the angle of blank technology rigidity before thin wall vane fine finishining, carry out Milling Process according to the method and can effectively control the thin wall vane machining distortion, reduce mismachining tolerance; The distortion that produces under the effect of Milling Force due to blade is mainly in the normal orientation of blade, by analyzing the blade each point at the deflection that applies under identical cutting force, study, find out the each point rigidity of blade under milling condition, and the stiffness variation trend of whole blade, on this basis blade allowance for finish location mode is optimized, reduces the cutting deformation in thin wall vane fine finishining process.The present invention has improved the stability of working angles from processing cutting force optimization and workpiece stiffness optimization two aspects, solved the problem on deformation that thin wall vane numerical control milling fine finishining insufficient rigidity causes.
Description of drawings
Be described in further detail below in conjunction with the method for drawings and embodiments to a kind of enhancing thin wall vane process rigidity based on non-homogeneous surplus of the present invention.
Fig. 1 is the thin wall vane structural representation.
Fig. 2 is for applying power node distribution schematic diagram on blade.
Fig. 3 is non-homogeneous surplus design thin-wall part blade schematic cross-section vertically.
Fig. 4 is even surplus design thin-wall part blade schematic cross-section vertically.
In figure:
1. tenon root 2. rafter plate 3. blade back profile 4. exhaust limit 5. leaf basin profile 6. leading edges
The specific embodiment
The present embodiment is a kind of method of the enhancing thin wall vane process rigidity based on non-homogeneous surplus.
Consult Fig. 1, Fig. 2, Fig. 3, Fig. 4, the present invention is based on the method for the enhancing thin wall vane process rigidity of non-homogeneous surplus, to regulate the angle of blank technology rigidity before thin wall vane fine finishining, according to the method, blade allowance for finish location mode is optimized, reduce the cutting deformation in thin wall vane fine finishining process, reduce mismachining tolerance.
In the thin wall vane Milling Process, because cutting force is mainly determined by cutting depth, cutting width, feed engagement factors, in the situation that other condition is constant, the place that allowance for finish is little, cutting depth is just little, and consequent cutting force is also little.If carrying out the thin wall vane allowance for finish according to the method for traditional even surplus distributes, in the situation that cutting phase congruence quantities produces close cutting force, the machining deformation of blade rigid weak part and vibration are larger, machining accuracy and the surface quality of blade are relatively poor, even make this position work in-process lose precision, finished surface severe exacerbation when the vibration aggravation; And at the stronger position of rigidity, its machining deformation and vibration are very little, and blade processing precision and surface quality can be protected.Under this surplus location mode, the different parts machining status in whole blade cutting process changes greatly, and precision and the surface quality of blade differ greatly.Therefore, under blade geometry condition, the impregnable prerequisite of design parameter, the method that adopts the non-homogeneous surplus of fine finishining to distribute, by the allowance for finish that suitably reduces the relatively poor position of rigidity, the allowance for finish that increases the better position of rigidity, reduce the machining deformation that in blade processing, cutting force causes on the one hand; This surplus location mode is larger at root and middle part surplus on the other hand, less in tip and edge surplus, make the supporting position thickness reinforcement in the blade processing process, play the effect of rigidity reinforced, improved the stability of working angles from processing cutting force optimization and workpiece rigidity optimization two aspects.
The below is aero titanium alloy TC4 for blade material, and blade dimensions is: the thin wall vane of certain type aero-engine of 303mm * 115mm * 1.8mm is example, and concrete steps are as follows:
The 1st step, in the middle of being imported to finite element analysis software ABAQUS, leaf model carries out deformation analysis, take the blade back of thin wall vane as example, according to parameter distribution such as uv directions, 45 nodes (u=5 is set, v=9), as shown in Figure 2, apply respectively certain cutting force on node, obtain the strain situation of thin-wall part each node under this cutting force, (each node elastic deflection of table 1) as shown in table 1.
In the 2nd step, take the calculated deformation amount as foundation, the local surplus large according to distortion is little, the little large principle of local surplus of distortion is carried out surplus and distributed, i.e. λ=K+ α δ; According to u=1, the corresponding minimum finishing surplus 0.2mm of v=1 point deformation amount 0.0911mm, u=5, the deflection 0.0000mm that v=5 is ordered answers the method for maximum finishing surplus 0.4mm, the solving equation group obtains K=0.4, α=-2.2082489, thus the functional relation λ of surplus and deflection=0.4-2.2082489 δ obtained.
In the 3rd step, can obtain the allowance of the blade back every bit of realistic processing, (each node allowance of table 2 designs) as shown in table 2 according to step 2 surplus and deflection functional relation.
The 4th step was loaded into the chipping allowance that obtains respectively on u * v=45 node, obtained the non-homogeneous margin value of fine finishining of these nodes; With 9 o'clock of every row as one group of parameter point, the structure cubic spline curve.
The 5th step is according to the leaf pelvic curvature face surplus cross section cubic spline of above-mentioned same method structure thin wall vane; To obtain respectively blade back, leaf basin surplus cross section curve carries out fairing and scans into face, namely obtain by the thin wall vane surplus curved surface before the fine finishining of non-homogeneous surplus method construct, as shown in Figure 3.
Each node elastic deflection of table 1
Each node allowance design of table 2
The present invention is based on the method for the enhancing thin wall vane process rigidity of non-homogeneous surplus, by analyzing the blade each point at the deflection that applies under identical cutting force, study, find out the each point rigidity of blade under milling condition, and the stiffness variation trend of whole blade; Improve on this basis the stability of its working angles from processing cutting force optimization and workpiece stiffness optimization aspect, the effective control of realization to the cutting deformation in thin wall vane fine finishining process, significantly improve machining accuracy and efficient, to satisfy correlative technology field to the active demand of Improvement and perfection thin-walled, Ultrathin bucket precision milling process technology.
Claims (1)
1. method based on the enhancing thin wall vane process rigidity of non-homogeneous surplus is characterized in that comprising the following steps:
Step 1. adopts limited element analysis technique to carry out deformation analysis to thin wall vane, choose u * v node respectively on the blade back of thin wall vane and leaf basin, definition along sharf to be U to, along blade profile line direction be V to, u * v node is at U, the parameter distribution such as V direction apply certain cutting force on each node, obtain the deformation of thin-wall part each point under this cutting force;
Step 2. is according to substantially linear between each column joints deformation amount and cutting force and cutting depth, and the linear function of structure take the thin-wall part deflection as independent variable calculates chipping allowance; Because the cutting deformation amount is less, definition deflection amplification coefficient α makes deflection δ be used for thin-wall part is carried out surplus λ structure, to improve workpiece stiffness, is defined as follows:
λ=K+αδ(1)
Wherein K is constant;
Step 3. is according to the thin wall vane actual processing, at the least amount of deformation δ of correspondence
minU
mSection line v
nThe maximum finishing surplus of node determination λ
max, corresponding maximum deformation quantity δ
maxU
gThe v of section line
hThe minimum allowance for finish λ of node determination
minAccording to two groups of solution (δ of equation group
min, λ
max), (δ
max, λ
min) Coefficient of determination K, α, and calculate u * v the margin value that node is corresponding;
Step 4. will obtain chipping allowance and be loaded into respectively on each load node, obtain the non-homogeneous margin value of these node fine finishining;
Step 5. as the control point, is constructed cubic spline curve L along one group of surplus distributed constant point on each section line of thin-wall part axial direction
1, L
2, L
3L
u, namely can be used as thin-wall part after fairing at this depth of section allowance for finish outline line;
Step 6. consists of face with the curve negotiating that the obtains method of scanning, and obtains the fine finishining front vane curved surface by non-homogeneous surplus method construct.
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|---|---|---|---|---|
| CN103962612A (en) * | 2014-05-19 | 2014-08-06 | 中国南方航空工业(集团)有限公司 | Numerical control milling machining method for stator blade |
| CN104227103A (en) * | 2014-07-24 | 2014-12-24 | 西安航空学院 | Method for stepped symmetrical milling of thin-wall part |
| CN104376162A (en) * | 2014-11-12 | 2015-02-25 | 中国航空动力机械研究所 | Blade modeling method |
| CN104816028A (en) * | 2015-03-19 | 2015-08-05 | 上海应用技术学院 | Process for strengthening milling rigidity of aluminum-alloy ultrathin-blade integral impeller |
| CN105834702A (en) * | 2016-05-31 | 2016-08-10 | 西北工业大学 | In-situ synthesis type TiB2 particle-reinforced aluminum matrix composite blade cutting machining method |
| CN107037779A (en) * | 2017-05-09 | 2017-08-11 | 西北工业大学 | Free form surface NC process tool track optimizing methods under non-homogeneous tolerance |
| CN109128317A (en) * | 2018-09-18 | 2019-01-04 | 西北工业大学 | Blade intake and exhaust side relict amount based on elliptic parametric equation controls precision milling method |
| CN109605120A (en) * | 2018-12-15 | 2019-04-12 | 浙江大学自贡创新中心 | A method of it improving aerial blade and processes yields |
| CN109648157A (en) * | 2019-02-19 | 2019-04-19 | 成都飞机工业（集团）有限责任公司 | A kind of weak rigid edge strip numerical-control processing method of structural member |
| CN110605543A (en) * | 2019-08-30 | 2019-12-24 | 江西佳时特精密机械有限责任公司 | Novel machining process for turbine blade |
| CN111077846A (en) * | 2019-12-16 | 2020-04-28 | 西北工业大学 | Thin-wall blade allowance removal sequence planning method |
| CN112131683A (en) * | 2020-09-22 | 2020-12-25 | 河南科技大学 | Method for determining parameters of gear blank for gear cutting machining of split straight bevel gear |
| CN112395790A (en) * | 2020-11-04 | 2021-02-23 | 上海应用技术大学 | Method for reserving allowance for side milling finish machining of thin-wall blade |
| CN113182565A (en) * | 2021-03-30 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Weak-rigidity molded surface regional milling method |
| CN113231677A (en) * | 2021-05-27 | 2021-08-10 | 贵州永红航空机械有限责任公司 | Anti-vibration milling method for ultrathin blade of integral impeller |
| CN113406926A (en) * | 2021-06-30 | 2021-09-17 | 中国航发动力股份有限公司 | Processing method for automatically adjusting edge shape of die forging blade |
| CN113751974A (en) * | 2021-09-29 | 2021-12-07 | 中国航发航空科技股份有限公司 | Machining and forming method of aero-engine blade |
| CN112131683B (en) * | 2020-09-22 | 2024-04-19 | 河南科技大学 | Gear blank parameter determination method for gear cutting machining of split straight bevel gear |
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| CN104227103A (en) * | 2014-07-24 | 2014-12-24 | 西安航空学院 | Method for stepped symmetrical milling of thin-wall part |
| CN104376162B (en) * | 2014-11-12 | 2019-01-11 | 中国航空动力机械研究所 | Leaf modeling method |
| CN104376162A (en) * | 2014-11-12 | 2015-02-25 | 中国航空动力机械研究所 | Blade modeling method |
| CN104816028A (en) * | 2015-03-19 | 2015-08-05 | 上海应用技术学院 | Process for strengthening milling rigidity of aluminum-alloy ultrathin-blade integral impeller |
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| CN109605120A (en) * | 2018-12-15 | 2019-04-12 | 浙江大学自贡创新中心 | A method of it improving aerial blade and processes yields |
| CN109648157A (en) * | 2019-02-19 | 2019-04-19 | 成都飞机工业（集团）有限责任公司 | A kind of weak rigid edge strip numerical-control processing method of structural member |
| CN110605543A (en) * | 2019-08-30 | 2019-12-24 | 江西佳时特精密机械有限责任公司 | Novel machining process for turbine blade |
| CN111077846A (en) * | 2019-12-16 | 2020-04-28 | 西北工业大学 | Thin-wall blade allowance removal sequence planning method |
| CN112131683A (en) * | 2020-09-22 | 2020-12-25 | 河南科技大学 | Method for determining parameters of gear blank for gear cutting machining of split straight bevel gear |
| CN112131683B (en) * | 2020-09-22 | 2024-04-19 | 河南科技大学 | Gear blank parameter determination method for gear cutting machining of split straight bevel gear |
| CN112395790A (en) * | 2020-11-04 | 2021-02-23 | 上海应用技术大学 | Method for reserving allowance for side milling finish machining of thin-wall blade |
| CN112395790B (en) * | 2020-11-04 | 2023-08-01 | 上海应用技术大学 | Reservation method for side milling finish machining allowance of thin-wall blade |
| CN113182565A (en) * | 2021-03-30 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Weak-rigidity molded surface regional milling method |
| CN113182565B (en) * | 2021-03-30 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Weak-rigidity molded surface regional milling method |
| CN113231677A (en) * | 2021-05-27 | 2021-08-10 | 贵州永红航空机械有限责任公司 | Anti-vibration milling method for ultrathin blade of integral impeller |
| CN113231677B (en) * | 2021-05-27 | 2022-04-01 | 贵州永红航空机械有限责任公司 | Anti-vibration milling method for ultrathin blade of integral impeller |
| CN113406926A (en) * | 2021-06-30 | 2021-09-17 | 中国航发动力股份有限公司 | Processing method for automatically adjusting edge shape of die forging blade |
| CN113751974A (en) * | 2021-09-29 | 2021-12-07 | 中国航发航空科技股份有限公司 | Machining and forming method of aero-engine blade |
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