CN108145393A - A kind of aero-engine compressor blade and its processing method - Google Patents
A kind of aero-engine compressor blade and its processing method Download PDFInfo
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- CN108145393A CN108145393A CN201711221958.3A CN201711221958A CN108145393A CN 108145393 A CN108145393 A CN 108145393A CN 201711221958 A CN201711221958 A CN 201711221958A CN 108145393 A CN108145393 A CN 108145393A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
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Abstract
The invention belongs to aero-engine technology fields, a kind of gas compressor blade slice processing method are disclosed, including 1. three-dimensional measurements：Each section actual curve wave crest point and trough point are extracted according to compressor blade graphics to build ridge curves and trough curve；Build the imaginary line of blade and tenon；2. data reduction：Actual curve, ridge curves and trough curvature of curve in analysis 1 are adjusted ridge curves and trough curvature of curve by foundation of actual curve curvature；According to ridge curves and trough curve structure center line；3. curve reestablishing：By the center line structure grid surface generation blade three-dimensional digitalization model in each section；4. process adjusting：Blade three-dimensional digitalization model is imported in three coordinate softwares, the blade master body comparing amendment with the scanning of three coordinates；5. digital control processing：According to 4 blade three-dimensional digitalization model numerical control programming, numerical control mill is carried out to blade with rose cutter.This processing method can effectively ensure that compressor blade precision and surface roughness.
Description
Technical field
The present invention relates to aero-engine technology fields, and in particular, to a kind of aero-engine compressor blade and its
Processing method.
Background technology
Aero-engine compressor blade is one of core component of engine, and the performance of engine largely depends on
In the design and manufacture level of blade profile, blade is a kind of typical Free-form Surface Parts, its curve form and manufacture essence
Degree also directly determines the size of the propulsive efficiency of aero-engine.
Traditional aero-engine compressor blade machining process is time-consuming and laborious, and precision is difficult to ensure that, with Numeric Control Technology
Development, current compressor blade manufactured mostly using CNC milling machine, but easily causes machining stress deformation, machining accuracy
Still it is undesirable.
Current compressor blade, since blade profile curved surface is complicated, blade is thin and big, is led when being processed on multi-axis processing center
Cause is unstable in process, is forced to its and polishes surplus increasing, increases the difficulty of polishing and manufacture cost.
And with continuing to optimize in process, numerical control program and cutter are depended on by multi-axis processing center, and
Numerical control program is generated by programming software through blade three-dimensional digitalization model, and the crucial work step of three-dimensional modeling is the data point of blade
The modeling of precision, the structure of each cross section curve, driving curved surface, since designer gives some positions data to have in data acquisition
Practical tolerance variation, leads to the data point of actual acquisition and the data point position of Theoretical Design forms tolerance up and down, according to actually adopting
The data point structure actual curve of collection forms peaks and troughs, and the driving built by each cross section curve curved surface is caused to produce wrinkle
Line face has seriously affected the establishment of follow-up numerical control program.
Invention content
Present invention solves the technical problem that the defects of being to overcome the prior art, provides one kind and effectively improves compressor blade
The processing method of machining accuracy and surface roughness.
Present invention simultaneously provides a kind of compressor blades processed by above-mentioned processing method.
The object of the invention is achieved through the following technical solutions：
A kind of aero-engine compressor blade machining process, includes the following steps：
S1. three-dimensional measurement：According to compressor blade three dimensional design figure, wave crest point and trough point on each section actual curve are extracted
To rebuild a ridge curves and trough curve；The imaginary line of blade and tenon is built simultaneously；
S2. data reduction：Analyze S1 in actual curve, ridge curves and trough song curvature of a curve, using the curvature of actual curve as
Ridge curves and trough song curvature of a curve are micro-adjusted in reference frame；It is built according to obtained ridge curves and trough curve
One center line；
S3. curve reestablishing：The center line structure grid surface generation blade three-dimensional digitalization model obtained by each section；
S4. process adjusting：Blade three-dimensional digitalization model is imported in three-coordinates measuring machine software, is scanned with three-coordinates measuring machine
Blade master body related data amendment is compared；
S5. digital control processing：Numerical control programming is carried out according to the blade three-dimensional digitalization model of S4, using machining rose cutter to leaf
Piece carries out numerical control mill.
Further, the part more than hilted broadsword road removal compressor blade machining allowance is used in S5.
Further, leaf basin and blade back remove surplus simultaneously.
Further, the processing in S5 from blade tip to blade root uses Spiral cutting path.
Further, it is processed as clockwise along blade tip to blade root being added by blade back leading edge from blade tip to blade root
Work.
Further, S5 is driven using hilted broadsword road according to the imaginary line of blade in S1 and tenon and removed more than blade root machining
Amount.
Further, hilted broadsword road machining control allowance for finish is consistent, is finish-machined to blade profile size.
Further, S5 further includes final polished surface tool marks step.
A kind of compressor blade processing essence processed by above-mentioned aero-engine compressor blade machining process
Degree is high.
Compared with prior art, the invention has the advantages that：
1）Blade three-dimensional digitalization model is obtained by curve reestablishing before digital control processing, with the blade three-dimensional digital
Model is according to progress numerical control programming, and the accuracy for digital control processing provides strong guarantee；
2）It is processed simultaneously using leaf basin, blade back, relative to the thin and big characteristic of blade, reduces blade back or when leaf basin is individually processed
Because upper work step brings internal stress caused by lower work step, the deformation in blade machining process is effectively alleviated, it is easier to protect
Demonstrate,prove blade back and consistency of the leaf basin switching R fillets with designing R fillets；
3）It relies on leaf basin and blade back while processes the blade processing brought and deform small advantage, be strict controlled in blade shape
Within the margin of tolerance, so as to which number milling can directly process zero surplus, the polishing difficulty and processing cost of polishing process are greatly reduced；
4）Blade root machining allowance is removed using the driving of hilted broadsword road by the imaginary line of blade and tenon, i.e., by blade and tenon
The milling of connecting portion digit to zero surplus, reduce polishing work step, the stress concentration during polishing work step effectively avoided to cause
The risk of fracture and the irregular problem of switching R fillet polishings；
5）The compressor blade surface roughness processed by the processing method of the present invention is within 1.6.
Description of the drawings
Fig. 1 is schematic diagram of the center line in gas compressor blade on piece；
Fig. 2 is the schematic diagram of each section center line.
Specific embodiment
The present invention is further illustrated With reference to embodiment, wherein, attached drawing only for illustration,
What is represented is only schematic diagram rather than pictorial diagram, it is impossible to be interpreted as the limitation to this patent；In order to which the reality of the present invention is better described
Example is applied, the certain components of attached drawing have omission, zoom in or out, and do not represent the size of actual product；To those skilled in the art
For, the omitting of some known structures and their instructions in the attached drawings are understandable.
Embodiment
Compressor blade as shown in Figure 1, the present embodiment provides a kind of aero-engine compressor blade machining process, packets
Include following steps：
S1. three-dimensional measurement：According to compressor blade three dimensional design figure, wave crest point and trough point on each section actual curve are extracted
To rebuild a ridge curves and trough curve；The imaginary line of blade and tenon is built simultaneously；
S2. data reduction：Analyze S1 in actual curve, ridge curves and trough song curvature of a curve, using the curvature of actual curve as
Ridge curves and trough song curvature of a curve are micro-adjusted in reference frame；It is built according to obtained ridge curves and trough curve
One center line；
S3. curve reestablishing：The center line structure grid surface generation blade three-dimensional digitalization model obtained by each section；
S4. process adjusting：Blade three-dimensional digitalization model is imported in three-coordinates measuring machine software, is scanned with three-coordinates measuring machine
Blade master body related data amendment is compared；
S5. digital control processing：Numerical control programming is carried out according to the blade three-dimensional digitalization model of S4, using machining rose cutter to leaf
Piece carries out numerical control mill.
It is to form a point position, ridge curves every 0.2~0.3mm by section that wave crest point and trough point are extracted in wherein S1
For the line that the line that collected multiple wave crest points are formed, trough curve are formed for collected multiple trough points, specifically exist certainly
When each point position is linked to be line, using the method for matched curve, the point position of curvature farther out will be deviated and carry out leakage choosing.
Being to the concrete operations that ridge curves and trough song curvature of a curve are micro-adjusted in S2 will be by removing data point
Or interpolation data point is adjusted.
The center line obtained in S2 is to optimize the blade profile optimal curvatures curve that ridge curves and trough curve obtain, accurately
Reacted blade shape tolerance, for subsequent curve reestablishing, numerical control programming and etc. sufficient theoretical foundation is provided.
In S4 when blade three-dimensional digitalization model is compared with blade master body related data, such as comparison result
Well, then digital control processing step can be directly entered, differs greatly as compared, then needs to repair blade three-dimensional digitalization model
Just, makeover process is specially and ridge curves and trough song curvature of a curve is micro-adjusted again, that is, is back to S2 steps again
Build center line.
To improve processing efficiency, while avoid generating random knife track or unnecessary during the processing of multitool road between cutter track and cutter track
Cutter track, using the part more than hilted broadsword road removal compressor blade machining allowance in S5.
The present embodiment is in process in a manner that leaf basin and blade back remove surplus simultaneously, due to compressor blade is thin
Greatly, using it is this surplus mode is gone on the one hand can to effectively reduce blade back or when leaf basin is individually processed because upper work step brings lower work step institute
On the other hand the internal stress of generation, the effective deformation alleviated in compressor blade machining process are also easier to ensure blade back
With leaf basin switching R fillets and design R fillet consistency.
To avoid the adverse effect crossed feed during compressor blade is processed, when milling cutter realize along three coordinate directions it is continuous
During feeding, preferably machining locus is a smooth helix, therefore the processing in S5 from blade tip to blade root uses spiral feed
Track can so accomplish to stay seldom allowance or be machined directly to no surplus, have compressor blade preferable
Processing quality and higher processing efficiency.
Specifically, the spiral feed from blade tip to blade root is processed as being carried out along blade tip to blade root clockwise by blade back leading edge
Processing, allow knife and leaf basin and the blade back effectively solved in process are transferred R fillet scramblings.
Due to the shortcoming of existing processing technology, the blade of compressor blade and the joining place R fillets of tenon are irregular, subsequently
Dependent on craft to being polished at this, great work intensity, and be still not achieved required standard after polishing, and in the present embodiment due to
There is a structure of the imaginary line of blade and tenon in S1 steps, cutter is driven according to program using hilted broadsword road during digital control processing
The perfect shape presentation that blade and tenon junction can be realized in blade root machining allowance is removed, and such operation is avoided and added
Due to compressor blade risk of breakage caused by stress concentration during work.
The above-mentioned connecting portion digit milling by blade and tenon simultaneously reduces polishing work step, effectively avoids to zero surplus
The irregular problem of switching R fillet polishings.
Since compressor blade is applied to the special operation condition requirement of aero-engine, the material of generally use lighter weight
It makes, but this kind of material is usually yielding, the compressor blade in prior art processing usually occurs in follow-up polishing process
Moderate finite deformation, to avoid the appearance of this situation, the hilted broadsword road machining control allowance for finish of the present embodiment is consistent, and finishes
To blade profile size, without considering follow-up polishing surplus.
It is machined to size with aforementioned finishing, but S5 also needs to carry out final polished surface tool marks step, the surface knife
Trace is about the surplus of 1.5.
This processing method has overturned the present situation that the follow-up craft in existing processing technology significantly polishes, only need to be to surface knife
Trace is polished, and process time is greatly saved, and improves production efficiency.
It is the surface roughness for further improving compressor blade in the present embodiment, it in process can be by adjusting knife
Tool parameter is realized with appropriate optimization cutter track step pitch.
In addition, for the blade of different face curvatures, the rose cutter with corresponding cutters parameter can be formulated to process.
The processing method of the present embodiment is equivalent to carries out secondary moulding to compressor blade, it is made to reach after machining and is set
The size and surface finish requirements of meter, process obtained compressor blade to improve engine performance, shorten the lead time and
Manufacturing expense is reduced to play an important role.
Obviously, above-described embodiment is only intended to clearly illustrate technical scheme of the present invention example, and is not
Restriction to embodiments of the present invention.For those of ordinary skill in the art, on the basis of the above description also
It can make other variations or changes in different ways.There is no necessity and possibility to exhaust all the enbodiments.It is all
All any modification, equivalent and improvement made within the spirit and principles in the present invention etc., should be included in right of the present invention will
Within the protection domain asked.
Claims (9)
1. a kind of aero-engine compressor blade machining process, which is characterized in that include the following steps：
S1. three-dimensional measurement：According to compressor blade three dimensional design figure, wave crest point and trough point on each section actual curve are extracted
To rebuild a ridge curves and trough curve；The imaginary line of blade and tenon is built simultaneously；
S2. data reduction：Analyze S1 in actual curve, ridge curves and trough song curvature of a curve, using the curvature of actual curve as
Ridge curves and trough song curvature of a curve are micro-adjusted in reference frame；It is built according to obtained ridge curves and trough curve
Center line；
S3. curve reestablishing：The center line structure grid surface generation blade three-dimensional digitalization model obtained by each section；
S4. process adjusting：Blade three-dimensional digitalization model is imported in three-coordinates measuring machine software, is scanned with three-coordinates measuring machine
Blade master body related data amendment is compared；
S5. digital control processing：Numerical control programming is carried out according to the blade three-dimensional digitalization model of S4, using machining rose cutter to leaf
Piece carries out numerical control mill.
2. aero-engine compressor blade machining process according to claim 1, which is characterized in that hilted broadsword is used in S5
Part more than road removal compressor blade machining allowance.
3. aero-engine compressor blade machining process according to claim 2, which is characterized in that leaf basin and blade back are same
When removal needed for allowance.
4. aero-engine compressor blade machining process according to claim 2, which is characterized in that in S5 from blade tip to
The processing of blade root uses Spiral cutting path.
5. aero-engine compressor blade machining process according to claim 4, which is characterized in that from blade tip to blade root
Be processed as be processed clockwise along blade tip to blade root by blade back leading edge.
6. aero-engine compressor blade machining process according to claim 1, which is characterized in that S5 is according to the S1 middle periods
The imaginary line of body and tenon removes blade root machining allowance using the driving of hilted broadsword road.
7. the aero-engine compressor blade machining process according to claim 2~6 any one, which is characterized in that
Hilted broadsword road machining control allowance for finish is consistent, is finish-machined to blade profile size.
8. aero-engine compressor blade machining process according to claim 1, which is characterized in that S5 is further included finally
Polished surface tool marks step.
9. the pressure that the aero-engine compressor blade machining process according to claim 1~8 any one is processed
Mechanism of qi blade.
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| CN201711221958.3A CN108145393B (en) | 2017-11-29 | 2017-11-29 | A kind of aero-engine compressor blade and its processing method |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109352790A (en) * | 2018-11-29 | 2019-02-19 | 佛山市盈胜智造科技有限公司 | A kind of shoe tree followed by processing method and its equipment |
| CN109365884A (en) * | 2018-12-17 | 2019-02-22 | 中国航发动力股份有限公司 | A kind of rotor blade tip cutting off processing method and its application |
| CN109530768A (en) * | 2018-11-06 | 2019-03-29 | 中国航发贵州黎阳航空动力有限公司 | A kind of processing method of blade tip chamfered edge thinning area |
| CN110523929A (en) * | 2019-08-30 | 2019-12-03 | 中国航发动力股份有限公司 | A kind of vane foil dimensional control methods |
| CN110908333A (en) * | 2019-12-20 | 2020-03-24 | 苏州千机智能技术有限公司 | Blade allowance-variable cutter position compensation method for integral blade disc type part |
| CN110969697A (en) * | 2019-12-20 | 2020-04-07 | 杭州汽轮动力集团有限公司 | Gas turbine moving blade key structure detection device and processing method |
| CN112676768A (en) * | 2020-11-16 | 2021-04-20 | 中国航发西安动力控制科技有限公司 | CAM (computer-aided manufacturing) processing programming method and special processing tool for complex free-form surface impeller |
| CN113145905A (en) * | 2021-03-26 | 2021-07-23 | 力度工业智能科技(苏州)有限公司 | Measuring, predicting and optimizing method and device for milling cutter marks on top surface of engine cylinder block |
| CN114082988A (en) * | 2021-10-28 | 2022-02-25 | 浙江意动科技股份有限公司 | Method for repairing aero-engine cold and hot end blade |
| CN115026706A (en) * | 2022-06-29 | 2022-09-09 | 中国航发动力股份有限公司 | Aircraft engine blade polishing method and system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109530768A (en) * | 2018-11-06 | 2019-03-29 | 中国航发贵州黎阳航空动力有限公司 | A kind of processing method of blade tip chamfered edge thinning area |
| CN109352790A (en) * | 2018-11-29 | 2019-02-19 | 佛山市盈胜智造科技有限公司 | A kind of shoe tree followed by processing method and its equipment |
| CN109365884A (en) * | 2018-12-17 | 2019-02-22 | 中国航发动力股份有限公司 | A kind of rotor blade tip cutting off processing method and its application |
| CN110523929A (en) * | 2019-08-30 | 2019-12-03 | 中国航发动力股份有限公司 | A kind of vane foil dimensional control methods |
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| CN110969697A (en) * | 2019-12-20 | 2020-04-07 | 杭州汽轮动力集团有限公司 | Gas turbine moving blade key structure detection device and processing method |
| CN110969697B (en) * | 2019-12-20 | 2023-09-19 | 杭州汽轮控股有限公司 | Gas turbine moving blade key structure detection device and processing method |
| CN112676768A (en) * | 2020-11-16 | 2021-04-20 | 中国航发西安动力控制科技有限公司 | CAM (computer-aided manufacturing) processing programming method and special processing tool for complex free-form surface impeller |
| CN113145905A (en) * | 2021-03-26 | 2021-07-23 | 力度工业智能科技(苏州)有限公司 | Measuring, predicting and optimizing method and device for milling cutter marks on top surface of engine cylinder block |
| CN114082988A (en) * | 2021-10-28 | 2022-02-25 | 浙江意动科技股份有限公司 | Method for repairing aero-engine cold and hot end blade |
| CN115026706A (en) * | 2022-06-29 | 2022-09-09 | 中国航发动力股份有限公司 | Aircraft engine blade polishing method and system |
| CN115026706B (en) * | 2022-06-29 | 2023-09-15 | 中国航发动力股份有限公司 | Aeroengine blade polishing method and system |
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