CN105739440A - Adaptive machining method of wide-chord hollow fan blade - Google Patents
Adaptive machining method of wide-chord hollow fan blade Download PDFInfo
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- 238000003754 machining Methods 0.000 title claims abstract description 43
- 230000003044 adaptive effect Effects 0.000 title claims abstract description 25
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- 238000005259 measurement Methods 0.000 claims description 51
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- 238000009826 distribution Methods 0.000 claims description 14
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- 238000012952 Resampling Methods 0.000 description 3
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- 238000009792 diffusion process Methods 0.000 description 3
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- 230000008646 thermal stress Effects 0.000 description 1
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- G—PHYSICS
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/18—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
- G05B19/4097—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by using design data to control NC machines, e.g. CAD/CAM
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Abstract
The invention provides an adaptive machining method of a wide-chord hollow fan blade. The adaptive machining method of the wide-chord hollow fan blade comprises the following steps of a, measuring the actual shape of a blank, and obtaining measured data of the blank shape; b, reconstructing a CAD model of the blank according to the measured data which are acquired in the step a; c, performing matching comparison on the CAD model of the blank and a workpiece designing model; and d, optimizing a technological solution according to a matching comparison result, and beginning to machine the blank. The adaptive machining is beneficial in that the adaptive machining method of the wide-chord hollow fan blade can realize uniform distribution of machining allowances of each part of the workpiece blank; and furthermore correction can be performed according to the difference between the blank and the designing model, thereby improving machining precision and machining efficiency of the wide-chord hollow fan blade and furthermore reducing rejection ratio.
Description
Technical field
The present invention relates to a kind of adaptive machining method of wide-chord hollow fan blade.
Background technology
Along with the development of China's aviation, the demand of aero-engine production domesticization is more urgent, and wherein the manufacture of blade of aviation engine is one of key technology of aero-engine.
In existing blade of aviation engine manufacturing technology, titanium alloy is blade material, the enclosed construction that the geometry of blade is hollow truss and entity portion combines.Superplastic forming/the diffusion connecting process adopted due to blade blank circulates with multiple heat, and in cooling procedure, the release of thermal stress and redistribution cause that blade deforms.Current technique is difficult to one-shot forming and goes out to meet appearance profile precision and the titanium alloy wide-chord hollow fan blade of hollow Thickness Distribution precision.Therefore, except the hollow truss structure in blade blank, surplus and skewness are all left in blade tip and intake and exhaust limit, it is necessary to be aided with different digital control processing means respectively for blade blank different parts and could meet final required precision.
The processing of existing titanium alloy wide-chord hollow fan blade mainly faces three problems.First, blank dimension difference is big.Owing to superplastic forming/process conditions such as diffusion connecting process strain rate and cooling parameter are difficult to accurate control, cause shaping the blade blank dimensional state difference each other obtained big.Must measuring and obtain respective size distribution to each processing object respectively before digital control processing, the data reconstruction according to measuring goes out to react the cad model of blade blank actual size state for digital control processing.
Second, allowance balance is uneven.Blade blank each position allowance skewness, blade tip leaves bigger surplus, and intake and exhaust limit surplus is less, and hollow truss structure profile is almost without surplus.The variation that determine numerical-control processing method different from allowance balance of the construction features of working position, brings difficulty to digital control processing.
3rd, appearance profile processing is retrained by interior shape.The hollow truss structure Thickness Distribution precision of titanium alloy wide-chord hollow fan blade is the key factor affecting serviceability.Due to the closure of hollow blade hollow area, interior shape profile in thermoforming process once formed just cannot pass through mechanical processing tools be revised.
Therefore, it is necessary to provide a kind of space curved surface contour structures machining path based on Tolerance Allocation, and provide, for the application in aero-engine of the titanium alloy wide-chord hollow fan blade, the adaptive machining method of wide-chord hollow fan blade supported.
Summary of the invention
It is an object of the invention to provide a kind of space curved surface contour structures machining path based on Tolerance Allocation, and the adaptive machining method of the wide-chord hollow fan blade supported is provided for the application in aero-engine of the titanium alloy wide-chord hollow fan blade.
Technical scheme is as follows: a kind of adaptive machining method of wide-chord hollow fan blade comprises the steps:
A, measure blank true form, obtain the measurement data of described blank shape；
B, according to the step a described measurement data obtained reconstruct described blank cad model；
C, being designed a model with workpiece by the cad model of described blank carries out mating contrast；
D, according to coupling comparing result, process program is optimized, and starts machining blanks.
Preferably, step a comprises the steps:
Assess the size shape of described blank, filter size shape and be unsatisfactory for the blank of processing request；
Space curved surface based on described blank surface sets up the measurement coordinate system relevant to measuring feature；
The contour structures of the space curved surface of described blank is measured by described measurement coordinate system；
Measure the wall thickness of described blank.
Preferably, step b comprises the steps:
The described measurement data obtained in step a is carried out fairing denoising, obtains the measurement data after denoising；
Measurement data after described denoising is carried out simplification process, the measurement data after being simplified；
Measurement data after described simplification is carried out repairing treatment, the measurement data after being repaired；
Measurement data after described repairing is carried out piecemeal process, obtains the measurement data after piecemeal；
The cad model of described blank is reconstructed based on the measurement data after described piecemeal.
Preferably, step c comprises the steps:
Cad model and the described workpiece of described blank are designed a model and contrast by the number of components die repair correction method based on distortion of the mesh；
Cad model and described workpiece to described blank design a model and carry out registration operation；
Distribution processing tolerance, and calculate the allowance at each position of described blank.
Preferably, step d comprises the steps:
The process program of described blank processing is optimized based on described allowance；
The movement locus of process tool is carried out emulating and optimization process by the distribution based on described processing tolerance；
Generated numerical control code by computer and be transferred to lathe, described blank is carried out numerical control cutting processing.
The beneficial effects of the present invention is: the adaptive machining method of described wide-chord hollow fan blade, for the uncertainty of blade blank dimensional state, the true form of on-machine measurement quick obtaining blade, re-constructs the cad model of blade blank according to measurement data；Based on the blank cad model rebuild, within the scope of machining tolerance, revise part C AD model.On this basis, distribution processing tolerance, the programming mode of design specialized, generate unique personalized numerical control program for each blade and complete digital control processing.Therefore, the adaptive machining method 100 of described wide-chord hollow fan blade can so that the allowance at each position of workpiece blank be uniformly distributed, and can according to blank and between designing a model difference be modified, thus improving machining accuracy and the working (machining) efficiency of described wide-chord hollow fan blade, and then reduce bad ratio defective product.
Accompanying drawing explanation
Fig. 1 is the structural representation of the wide-chord hollow fan blade relevant to the adaptive machining method of the wide-chord hollow fan blade of embodiment of the present invention offer；
Fig. 2 is the structural representation of another angle of wide-chord hollow fan blade shown in Fig. 1；
Fig. 3 is the FB(flow block) of the adaptive machining method of the wide-chord hollow fan blade that embodiments of the invention provide.
Detailed description of the invention
In order to make the purpose of the present invention, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, the present invention is further elaborated.Should be appreciated that specific embodiment described herein is only in order to explain the present invention, is not intended to limit the present invention.
The description of specific distinct unless the context otherwise, element in the present invention and assembly, the form that quantity both can be single exists, it is also possible to multiple forms exists, and this is not defined by the present invention.Although the step in the present invention has arranged with label, but being not used to limit the precedence of step, the order of step or the execution of certain step need based on other steps unless expressly stated, and otherwise the relative rank of step is adjustable in.It is appreciated that term "and/or" used herein relates to and contain the one or more of any and all possible combination in the Listed Items being associated.
Structural representation please refer to the relevant wide-chord hollow fan blade of the adaptive machining method of wide-chord hollow fan blade that Fig. 1 and Fig. 2, Fig. 1 are to the embodiment of the present invention provides；Fig. 2 is the structural representation of another angle of wide-chord hollow fan blade shown in Fig. 1.Described wide-chord hollow fan blade includes combination formation and has the hollow truss 100 of enclosed construction of geometry, blade root 201, blade tip 202 and intake and exhaust limit 203.And, it is each formed with welding procedure boss 300 at tenon tooth both ends of the surface and described blade tip 202 top of described blade root 201.
Refer to Fig. 3, be the FB(flow block) of the adaptive machining method of the wide-chord hollow fan blade that embodiments of the invention provide.The adaptive machining method 100 of the wide-chord hollow fan blade that the embodiment of the present invention provides can apply to the titanium alloy wide-chord hollow fan blade of processing aero-engine.The adaptive machining method 100 of described wide-chord hollow fan blade comprises the steps:
Step S1, measure blank true form, obtain the measurement data of described blank shape.
Specifically, described step a comprises the steps:
(1) assess the size shape of described blank, filter size shape and be unsatisfactory for the blank of processing request.
Specifically, set up measuring basis based on described blank, and adopt three coordinate machine measurement method to measure.Such as, adopt principle of six-point fixing, based on blade design digital-to-analogue, leaf basin is chosen 3 points, leaf by choose a bit, aerofluxus limit is chosen a bit, and blade tip top is chosen a bit.First Non-follow control three coordinate measuring machine obtains this approximate location of 6, then given Chosen Point normal vector deviation range, is automatically found optimum point on blade blank part by PC-DMIS software iteration control three coordinate measuring machine.Set up according to six optimum points obtained and measure coordinate system.Under this coordinate system, in the middle part of blade root, blade tip, blade, choose three profiles be respectively scanned measuring.By scanning result in PC-DMIS software with design a model comparison, it is determined that deviation value between the two, deviation value is scrapped more than setting value then this blank.
(2) the measurement coordinate system relevant to measuring feature is set up based on the space curved surface of described blank surface.
Specifically, in order to ensure to obtain measurement data accuracy, in the present embodiment, coordinate survey is adopted to set up unified measurement coordinate system.Such as, coordinate system is measured at welding procedure boss 300 place at the tenon tooth both ends of the surface of described blade root 201 and described blade tip 202 top.And, according to blade position centering blade in the position measuring coordinate system, process the measurement datum of three vertical direction (that is, orthogonal XYZ direction) meeting required precision, in order to set up measurement coordinate system.
(3) contour structures of the space curved surface of described blank is measured by described measurement coordinate system.
Specifically, in the present embodiment, adopt the mode that laser feeler and three coordinate measuring machine combine, and with equidistant section line and two kinds of measuring route of helix, the contour structures of the space curved surface of described blank is measured.
Such as, according to blade construction and curvature variation, measuring route of making rational planning for, and adopt piecemeal subregion to measure, to ensure the integrity of measurement data；And, it is ensured that each segmented areas leaves overlap near cut-off rule, thus improving the splicing precision of data.
(4) wall thickness of described blank is measured.
PLYMPUS38DL ultrasonic pachymetry is adopted to measure the wall thickness of the hollow truss structure of titanium alloy wide-chord hollow fan blade.
Step S2, according to the step S1 described measurement data obtained reconstruct described blank cad model；
Specifically, the measurement data according to each blank, reconstruct the blade blank cad model for numerical control cutting processing, revise blade design model mating by blank cad model and blade design model accordingly, distribute allowance, planning machining path.
And, described step S2 comprises the steps:
(1) the described measurement data obtained in step S1 is carried out fairing denoising, obtain the measurement data after denoising.
Specifically, in described fairing denoising process, adopting Laplace algorithm that model is carried out fairing, each summit of model is applied Laplace operator, by noise diffusion to the field on summit, the surface making model is smoothened.Adopt the point model Denoising Algorithm based on MLS, set up Moving Least Squares for point model and approach curved surface, noise spot is moved to the curved surface approached reaches denoising purpose.
(2) measurement data after described denoising is carried out simplification process, the measurement data after being simplified.
Specifically, in described simplification processing procedure, the measurement data amount obtained due to laser optical method scanning is big, therefore, MLS is adopted to solve the differential attribute measuring point model, for instance to include normal direction and curvature etc., and simplify point data model according to given normal direction precision, the data after simplifying are made to be distributed less point in curvature of curved surface smaller area, and at the point that curvature is relatively big or the reservation of Sharp edge place is more.
(3) measurement data after described simplification is carried out repairing treatment, the measurement data after being repaired.
Specifically, in repairing treatment process, owing to the curvature of curved surface on titanium alloy width string hollow blade intake and exhaust limit changes greatly, it may appear that shortage of data phenomenon, therefore needed the data message reparation of disappearance before curved surface modeling.In the present embodiment, adopting point model texture and geometry to repair unified method, texture known on curved surface is sample, realizes the texture repairing of point model by minimizing the global energy function of a belt restraining.
(4) measurement data after described repairing is carried out piecemeal process, obtain the measurement data after piecemeal.
Specifically, in described piecemeal processing procedure, patch surface joining method is adopted to form monoblock curved surface.Such as, adopt limit split-run, first judge according to the law vector of local surface sheet and higher derivative, from cloud data, extract the edge feature point of patch, and all edge feature points found are coupled together the border constituting curved surface；Then, by judging that data point is positioned at border or border is external realizes data segmentation.
(5) cad model of described blank is reconstructed based on the measurement data after described piecemeal.
Specifically, coordinate method measures the cloud data obtained according to measuring successively uiform section or helical row, forms structural data collection；Laser optical method obtains cloud data and arranges out of order, forms unstructured data collection.
For described structural data collection, it is primarily based on non-homogeneous B spline curve anti-inference method, obtains control point according to data point data.That is, under a common knot vector premise, each cross section is carried out cubic NURBS spline curve fitting；Each curve same parameters sequence is carried out resampling and obtains a series of new data point, and directly construct interpolant spline curve by new data point, then go to produce Skinning Surfaces with new SPL.
For described unstructured data collection, it is respectively adopted implicit surface restructing algorithm MLS and RBF method carries out surface reconstruction:
When adopting MLS method to carry out surface reconstruction, adopt local higher order polynomial to provide one for discrete sampling point one group given to approach or interpolation curved surface, set up a local coordinate system for point to be projected, utilize a bivariant multinomial under this local coordinate system, these points to be fitted；
When adopting RBF method to carry out surface reconstruction, by the zero level emergency of the weights centered by each data point and the RBF Implicitly function of scattered data being structure, surface model is described；And also adopt FMM method to solve the room and time challenge of RBF method process large-scale data.
Step S3, being designed a model with workpiece by the cad model of described blank carries out mating contrast.
Specifically, described step S3 comprises the steps:
(1) based on the number of components die repair correction method of distortion of the mesh, cad model and the described workpiece of described blank are designed a model and contrast.
Specifically, blade part cad model being carried out resampling, as source point model, the measurement pointcloud data after being processed by blade blank, as impact point model, generate triangle gridding respectively, adopt the deformation method correction part C AD model based on grid vertex deformation gradient.Set up the k contiguous calculating deformation gradient of grid vertex, set up the corresponding relation between source grid vertex model and target gridding vertex model based on deformation gradient and Moving Least Squares method.This corresponding relation is with part machining tolerance for constraints.Grid vertex deformation gradient is carried out Matrix Polar Decomposition, constant in constraints with part grid model volume and leaf length, each component after decomposing is deformed respectively, realizes the deformation of grid model again through an overall second energy optimization.Grid model after deformation is fitted to curved surface again, thus just realizing number of components die repair.
(2) cad model of described blank and described workpiece are designed a model carry out registration operation.
Specifically, first the cad model of fan blade blank and described workpiece are designed a model and carry out registration operation.Described registration operation is divided into initial registration and accuracy registration two step.First, logarithmic mode resampling obtains blank point model and part point model.For a cloud initial registration, adopt principal direction laminating method.According to calculating some Yun Zhongsuo covariance matrix a little, obtain the characteristic vector of this matrix.Set up with a cloud center of gravity for initial point, using above-mentioned characteristic vector as a reference frame for cloud coordinate axes.The coordinate system of two some clouds is adjusted to and unanimously namely completes a cloud initial registration.Point cloud accuracy registration adopts the ICP algorithm of standard, utilizes k-d tree to find impact point closest approach of each point in reference point clouds, completes registration based on ICP algorithm.
(3) distribution processing tolerance, and calculate the allowance at each position of described blank.
Specifically, the blank cad model reconstructed according to titanium alloy width string hollow blade and revised part mathematical model, symmetrical for target with hollow truss structure wall thickness along airfoil center line, in conjunction with the ICP registration Algorithm of distinguished point based, each working position tolerance of optimized distribution blade.And according to comparison result, it is thus achieved that blade each position machine-finish allowance.
Step S4, according to coupling comparing result, process program is optimized, and starts machining blanks.
Specifically, described step S4 comprises the steps:
(1) process program of described blank processing is optimized based on described allowance.
Specifically, the titanium alloy wide-chord hollow fan blade each working position tolerance obtained is optimized and incomplete same.By analyzing each working position surplus size and the regularity of distribution thereof, adopt the processing mode of " first overall behind local ", namely first carry out roughing for the position that allowance is bigger, remove major part surplus.Whole blade is adopted spiral ring cutting, it is ensured that blade smooths fairing.
(2) carry out emulating and optimization process to the movement locus of process tool based on the distribution of described processing tolerance.
Specifically, reconstruct cad model, part correction cad model and the distribution of machining tolerance according to blade blank, the original machining track formulated by blank and part theory cad model is modified, obtain the cutter location data for personalized blade object.Cutter location is carried out mathematical modeling, sets up each cutter location k contiguous, calculate its differential attribute, carry out cutter location optimization process on this basis, correct including flaw point and redundancy cutter location is deleted.According to cutter location amount of curvature, set threshold values, set up the Processing Algorithm of correspondence respectively.
(3) generated numerical control code by computer and be transferred to lathe, described blank is carried out numerical control cutting processing.
Compared to prior art, the adaptive machining method 100 of wide-chord hollow fan blade provided by the invention is for the uncertainty of blade blank dimensional state, the true form of on-machine measurement quick obtaining blade, re-constructs the cad model of blade blank according to measurement data；Based on the blank cad model rebuild, within the scope of machining tolerance, revise part C AD model.On this basis, distribution processing tolerance, the programming mode of design specialized, generate unique personalized numerical control program for each blade and complete digital control processing.Therefore, the adaptive machining method 100 of described wide-chord hollow fan blade can so that the allowance at each position of workpiece blank be uniformly distributed, and can according to blank and between designing a model difference be modified, thus improving machining accuracy and the working (machining) efficiency of described wide-chord hollow fan blade, and then reduce bad ratio defective product.
It is obvious to a person skilled in the art that the invention is not restricted to the details of above-mentioned one exemplary embodiment, and when without departing substantially from the spirit of the present invention or basic feature, it is possible to realize the present invention in other specific forms.Therefore, no matter from which point, embodiment all should be regarded as exemplary, and be nonrestrictive, the scope of the invention rather than described above limits, it is intended that all changes in the implication of the equivalency dropping on claim and scope included in the present invention.Any accompanying drawing labelling in claim should be considered as the claim that restriction is involved.
In addition, it is to be understood that, although this specification is been described by according to embodiment, but not each embodiment only comprises an independent technical scheme, this narrating mode of description is only for clarity sake, description should be made as a whole by those skilled in the art, and the technical scheme in each embodiment through appropriately combined, can also form other embodiments that it will be appreciated by those skilled in the art that.
Claims (5)
1. the adaptive machining method of a wide-chord hollow fan blade, it is characterised in that comprise the steps:
A, measure blank true form, obtain the measurement data of described blank shape；
B, according to the step a described measurement data obtained reconstruct described blank cad model；
C, being designed a model with workpiece by the cad model of described blank carries out mating contrast；
D, according to coupling comparing result, process program is optimized, and starts machining blanks.
2. the adaptive machining method of wide-chord hollow fan blade according to claim 1, it is characterised in that: step a comprises the steps:
Assess the size shape of described blank, filter size shape and be unsatisfactory for the blank of processing request；
Space curved surface based on described blank surface sets up the measurement coordinate system relevant to measuring feature；
The contour structures of the space curved surface of described blank is measured by described measurement coordinate system；
Measure the wall thickness of described blank.
3. the adaptive machining method of wide-chord hollow fan blade according to claim 1, it is characterised in that: step b comprises the steps:
The described measurement data obtained in step a is carried out fairing denoising, obtains the measurement data after denoising；
Measurement data after described denoising is carried out simplification process, the measurement data after being simplified；
Measurement data after described simplification is carried out repairing treatment, the measurement data after being repaired；
Measurement data after described repairing is carried out piecemeal process, obtains the measurement data after piecemeal；
The cad model of described blank is reconstructed based on the measurement data after described piecemeal.
4. the adaptive machining method of wide-chord hollow fan blade according to claim 1, it is characterised in that: step c comprises the steps:
Cad model and the described workpiece of described blank are designed a model and contrast by the number of components die repair correction method based on distortion of the mesh；
Cad model and described workpiece to described blank design a model and carry out registration operation；
Distribution processing tolerance, and calculate the allowance at each position of described blank.
5. the adaptive machining method of wide-chord hollow fan blade according to claim 4, it is characterised in that: step d comprises the steps:
The process program of described blank processing is optimized based on described allowance；
The movement locus of process tool is carried out emulating and optimization process by the distribution based on described processing tolerance；
Generated numerical control code by computer and be transferred to lathe, described blank is carried out numerical control cutting processing.
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