CN109332772A - A kind of aero-engine stator blade front and rear edge adaptive machining method - Google Patents
A kind of aero-engine stator blade front and rear edge adaptive machining method Download PDFInfo
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- CN109332772A CN109332772A CN201811396482.1A CN201811396482A CN109332772A CN 109332772 A CN109332772 A CN 109332772A CN 201811396482 A CN201811396482 A CN 201811396482A CN 109332772 A CN109332772 A CN 109332772A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C3/00—Milling particular work; Special milling operations; Machines therefor
- B23C3/16—Working surfaces curved in two directions
- B23C3/18—Working surfaces curved in two directions for shaping screw-propellers, turbine blades, or impellers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C9/00—Details or accessories so far as specially adapted to milling machines or cutter
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Abstract
The present invention discloses a kind of aero-engine stator blade front and rear edges adaptive machining method, using space geometry adaptive machining technology, acquires the coordinate data in front and rear edges corresponding region by contactless measuring system, and handle data.Process modeling needed for constructing processing according to scan data and theoretical model, and adaptive cutter location file is generated for current part, complete the processing of blade.This method breaks traditional hand polish and numerical control processing mode, improves blade front and rear edges passing rate of processing, saves processing cost；It solves dimensional accuracy and edge in no mounting plate class stator blade front and rear edges process and forms unqualified, finished surface and connect knife and be difficult to the problems such as eliminating；Process after optimization is stablized, and a large amount of manual interventions are reduced.With stronger versatility and practicability.
Description
Technical field
The invention belongs to aerospace Computerized Numerical Control processing technology field, it is related to originating from before and after a kind of aero-engine stator blade
Adapt to processing method.
Background technique
Aero-engine is main at present using artificial polishing and numerical control processing without the processing of mounting plate class stator blade front and rear edge
Two ways, using artificial polishing mode, front and rear edge dimensional accuracy is difficult to ensure with edge shape, often occur chamfered edge,
The problems such as tack；Using traditional numeric-control processing method, front and rear edge dimensional accuracy can guarantee with edge shape, but due to blade
Type face has completed the process, and causing marginal portion to connect with blade, knife is obvious, and adding work, there are still the risks for destroying dimensional accuracy.
Domestic and international researcher has been achieved in adaptive machining field compared with quantum jump, at the adaptive aspect of space geometry,
Preliminary grasp measures, the technologies such as model reconstruction, amendment and registration, and real in automobile, ship domain Related product numerical control processing
Now integrate application, and it is still unmature in no mounting plate class stator blade front and rear edge process of manufacture in aviation field
Adaptive machining restorative procedure.
Summary of the invention
The object of the present invention is to provide a kind of aero-engine stator blade front and rear edge adaptive machining methods, to improve leaf
Piece front and rear edge machining accuracy, ensure that front and rear edge edge shape and round and smooth switching.
The present invention provides a kind of aero-engine stator blade front and rear edges adaptive machining method, includes the following steps:
Step 1: will be on blade adaptive machining special fixture clamping to lathe and centering；
Step 2: blade being put into fixture front end blade holding position, guarantees that root of blade process area both ends of the surface are corresponding to fixture
Plane fitting；
Step 3: blade front and rear edges being scanned using contactless on-machine measurement system and obtain leaf basin and blade back region
Position coordinate data, and to position coordinate data carry out processing generate point cloud data；
Step 4: point cloud data is subjected to bad point and screens and rejects, the reality according to spoon of blade property reduction scanning area
Section line；
Step 5: based on the actual cross-section line of scanning area, reconstruct adds under the guidance of theoretical model and design tolerance
Process modeling needed for work；
Step 6: blade digital control processing criterion cutter location file is generated in conjunction with intelligent algorithm according to process modeling；
Step 7: standard cutter location file being handled, the NC code processing program file of lathe identification is generated, completes leaf
The processing and detection of piece front and rear edges.
In aero-engine stator blade front and rear edges adaptive machining method of the invention, the step 1 specifically:
Fixture flange side surface is installed on lathe first, by fine tuning fixture position, guarantees fixture ring flange outer circle
Face bounce, bottom surface bounce are in 0.01mm, to make the fixture centre of gyration be overlapped with machine tool rotary center, using ground as fixture
Angular plane.
In aero-engine stator blade front and rear edges adaptive machining method of the invention, the step 3 specifically:
Step 3.1: blade being divided into 4 machining areas, is respectively as follows: leading edge leaf pelvic surface of sacrum, leading edge leaf back, rear leaf basin
Face and rear leaf back；Fixture is divided into 2 localization regions, is respectively as follows: fixture ring flange periphery and the angular face of clamp base；
Step 3.2: 4 machining areas being scanned, each machining area scans 40 section lines, and every section line is swept
Retouching length is 3mm, and the coordinate of 10 points is acquired on every section line；Fixture ring flange periphery is scanned, totally 1 section
Line acquires the coordinate of 7 points, is scanned, totally 1 section line to the angular face of clamp base, acquires the coordinate of 2 points；
Step 3.3: by 2 points of the coordinate of 7 points of circular scan and the angular Surface scan of clamp base outside fixture ring flange
Coordinate pre-processed as positioning datum data, and save as " pretreatment DW data "；
Step 3.4: one by one being carried out the coordinate data that 4 machining area scannings obtain on the basis of " pretreatment DW data "
Merging treatment generates the point cloud data that adaptive machining is read.
In aero-engine stator blade front and rear edges adaptive machining method of the invention, the step 4 specifically:
Step 4.1: point cloud data being subjected to bad point examination and rejecting, error amount are set as 0.05mm；
Step 4.2: by determining that reference axis is sequence principal direction, completing scan data row according to actual cross-section line feature
Sequence, also the actual cross-section line of protocosta leaf pelvic surface of sacrum, leading edge leaf back, rear leaf pelvic surface of sacrum and rear leaf back.
In aero-engine stator blade front and rear edges adaptive machining method of the invention, the step 5 specifically:
Step 5.1: according to leading edge leaf pelvic surface of sacrum, leading edge leaf back, the rear leaf of the theoretical curved surface of blade front and rear edges and reduction
The actual cross-section line of pelvic surface of sacrum, rear leaf back generates leading edge leaf pelvic surface of sacrum, leading edge leaf back, rear leaf pelvic surface of sacrum, rear leaf back 4
The practical curved surface of a working region；
Step 5.2: under the guidance of theoretical model and design tolerance, by the practical song of leading edge leaf pelvic surface of sacrum and leading edge leaf back
Face is reconstructed into blade inlet edge model according to scan data trend；By the practical curved surface of rear leaf pelvic surface of sacrum and rear leaf back according to sweeping
It retouches data trend and is reconstructed into trailing edge model, process modeling needed for ultimately producing processing.
In aero-engine stator blade front and rear edges adaptive machining method of the invention, the step 6 specifically:
Choose blade inlet edge model and trailing edge model setting Cutter coordinate system and cutter axis orientation, determine working position and
Surface offset direction, rough mill, leading edge finish-milling, rear are rough milled, four cutter location files of rear finish-milling by leading edge for the generation of operation algorithm.
In aero-engine stator blade front and rear edges adaptive machining method of the invention, the step 7 specifically:
Step 7.1: 4 cutter location files being imported in postpositive disposal software, the identifiable NC code of export lathe processes journey
Preface part；
Step 7.2: completing adaptive thick, the finish-milling processing of front and rear edges on lathe, and carry out three coordinate measurements, blade
The requirement of finished size shape Design of Symbols connects knife without obvious.
A kind of aero-engine stator blade front and rear edge adaptive machining method of the invention, for the first time by adaptive machining skill
Art is applied in the front and rear edges numerical control processing of no mounting plate class stator blade, breaks traditional hand polish and numerical control processing side
Formula improves blade front and rear edges passing rate of processing, saves processing cost；It solves no mounting plate class stator blade front and rear edges to add
Dimensional accuracy and edge, which form unqualified, finished surface and connect knife, during work is difficult to the problems such as eliminating；Process after optimization
Stablize, reduces a large amount of manual interventions.With stronger versatility and practicability.
Detailed description of the invention
Fig. 1 is a kind of flow chart of aero-engine stator blade front and rear edges adaptive machining method of the invention.
Specific embodiment
A kind of aero-engine stator blade front and rear edges adaptive machining method of the invention, it is adaptive using space geometry
Answer processing technology, by contactless measuring system acquire front and rear edges corresponding region in coordinate data, and to data at
Reason.Process modeling needed for constructing processing according to scan data and theoretical model, and generated adaptively for current part
Cutter location file completes the processing of blade.Present invention will be further explained below with reference to the attached drawings and examples.
A kind of aero-engine stator blade front and rear edges adaptive machining method of the invention, includes the following steps:
Step 1, clamping centering special fixture: by blade adaptive machining special fixture clamping to lathe and centering, tool
Body are as follows:
Fixture flange side surface is installed on lathe first, by fine tuning fixture position, guarantees fixture ring flange outer circle
Face bounce, bottom surface bounce are in 0.01mm, to make the fixture centre of gyration be overlapped with machine tool rotary center, using ground as fixture
Angular plane.
Step 2, clamping centering blade: blade is put into fixture front end blade holding position, guarantees root of blade process area two
End face is bonded with fixture respective planes；
Step 3, scanning and processing position coordinate data: using contactless on-machine measurement system to blade front and rear edges into
Row scanning obtains the position coordinate data of leaf basin and blade back region, and carries out processing to position coordinate data and generate point cloud data,
Specifically:
Step 3.1: blade being divided into 4 machining areas, is respectively as follows: leading edge leaf pelvic surface of sacrum, leading edge leaf back, rear leaf basin
Face and rear leaf back；Fixture is divided into 2 localization regions, is respectively as follows: fixture ring flange periphery and the angular face of clamp base；
Step 3.2: 4 machining areas being scanned, each machining area scans 40 section lines, and every section line is swept
Retouching length is 3mm, and the coordinate of 10 points is acquired on every section line；Fixture ring flange periphery is scanned, totally 1 section
Line acquires the coordinate of 7 points, is scanned, totally 1 section line to the angular face of clamp base, acquires the coordinate of 2 points；
Step 3.3: by 2 points of the coordinate of 7 points of circular scan and the angular Surface scan of clamp base outside fixture ring flange
Coordinate pre-processed as positioning datum data, and save as " pretreatment DW data "；
Step 3.4: one by one being carried out the coordinate data that 4 machining area scannings obtain on the basis of " pretreatment DW data "
Merging treatment generates the point cloud data that adaptive machining is read.
Step 4, reduction scanning area section line: point cloud data is subjected to bad point and screens and rejects, according to spoon of blade
Matter restores the actual cross-section line of scanning area, specifically:
Step 4.1: point cloud data being subjected to bad point examination and rejecting, error amount are set as 0.05mm；
Step 4.2: by determining that reference axis is sequence principal direction, completing scan data row according to actual cross-section line feature
Sequence, also the actual cross-section line of protocosta leaf pelvic surface of sacrum, leading edge leaf back, rear leaf pelvic surface of sacrum and rear leaf back.
Step 5, restructuring processes model: based on the actual cross-section line of scanning area, in theoretical model and design tolerance
Guidance under reconstruct processing needed for process modeling, specifically:
Step 5.1: according to leading edge leaf pelvic surface of sacrum, leading edge leaf back, the rear leaf of the theoretical curved surface of blade front and rear edges and reduction
The actual cross-section line of pelvic surface of sacrum, rear leaf back generates leading edge leaf pelvic surface of sacrum, leading edge leaf back, rear leaf pelvic surface of sacrum, rear leaf back 4
The practical curved surface of a working region；
Step 5.2: under the guidance of theoretical model and design tolerance, by the practical song of leading edge leaf pelvic surface of sacrum and leading edge leaf back
Face is reconstructed into blade inlet edge model according to scan data trend；By the practical curved surface of rear leaf pelvic surface of sacrum and rear leaf back according to sweeping
It retouches data trend and is reconstructed into trailing edge model, process modeling needed for ultimately producing processing.
Step 6 generates cutter location file: generating blade digital control processing criterion knife position in conjunction with intelligent algorithm according to process modeling
File, specifically:
Choose blade inlet edge model and trailing edge model setting Cutter coordinate system and cutter axis orientation, determine working position and
Surface offset direction, rough mill, leading edge finish-milling, rear are rough milled, four cutter location files of rear finish-milling by leading edge for the generation of operation algorithm.
Step 7, generation processing program file are processed and are detected: being handled standard cutter location file, generated lathe
The NC code processing program file of identification completes the processing and detection of blade front and rear edges, specifically:
Step 7.1: 4 cutter location files being imported in postpositive disposal software, the identifiable NC code of export lathe processes journey
Preface part；
Step 7.2: completing adaptive thick, the finish-milling processing of front and rear edges on lathe, and carry out three coordinate measurements, blade
The requirement of finished size shape Design of Symbols connects knife without obvious.
The present invention proposes a kind of aero-engine stator blade front and rear edges under the premise of not changing part process route
Adaptive machining method, effectively improves the qualification rate of blade front and rear edges size and edge shape processing, and guarantees blade
Rounding off.
The foregoing is merely presently preferred embodiments of the present invention, the thought being not intended to limit the invention, all of the invention
Within spirit and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (7)
1. a kind of aero-engine stator blade front and rear edges adaptive machining method, which comprises the steps of:
Step 1: will be on blade adaptive machining special fixture clamping to lathe and centering；
Step 2: blade being put into fixture front end blade holding position, guarantees root of blade process area both ends of the surface and fixture respective planes
Fitting；
Step 3: using contactless on-machine measurement system blade front and rear edges are scanned with the position for obtaining leaf basin and blade back region
Coordinate data is set, and processing is carried out to position coordinate data and generates point cloud data；
Step 4: point cloud data is subjected to bad point and screens and rejects, the actual cross-section according to spoon of blade property reduction scanning area
Line；
Step 5: based on the actual cross-section line of scanning area, the reconstruct processing institute under the guidance of theoretical model and design tolerance
The process modeling needed；
Step 6: blade digital control processing criterion cutter location file is generated in conjunction with intelligent algorithm according to process modeling；
Step 7: standard cutter location file is handled, the NC code processing program file of generation lathe identification, before completion blade,
The processing and detection of rear.
2. aero-engine stator blade front and rear edges adaptive machining method as described in claim 1, which is characterized in that institute
State step 1 specifically:
Fixture flange side surface is installed on lathe first, by fine tuning fixture position, guarantees that fixture ring flange periphery is jumped
Dynamic, bottom surface bounce is in 0.01mm, to make the fixture centre of gyration be overlapped with machine tool rotary center, using ground as the angle of fixture
To plane.
3. aero-engine stator blade front and rear edges adaptive machining method as described in claim 1, which is characterized in that institute
State step 3 specifically:
Step 3.1: blade is divided into 4 machining areas, be respectively as follows: leading edge leaf pelvic surface of sacrum, leading edge leaf back, rear leaf pelvic surface of sacrum and
Rear leaf back；Fixture is divided into 2 localization regions, is respectively as follows: fixture ring flange periphery and the angular face of clamp base；
Step 3.2: 4 machining areas being scanned, each machining area scans 40 section lines, every section line scanning length
Degree is 3mm, and the coordinate of 10 points is acquired on every section line；Fixture ring flange periphery is scanned, totally 1 section line,
The coordinate for acquiring 7 points is scanned the angular face of clamp base, 1 section line, acquires the coordinate of 2 points totally；
Step 3.3: by the seat of 2 points of the coordinate and angular Surface scan of clamp base of 7 points of circular scan outside fixture ring flange
It is denoted as being pre-processed for positioning datum data, and saves as " pretreatment DW data "；
Step 3.4: one by one being merged the coordinate data that 4 machining area scannings obtain on the basis of " pretreatment DW data "
Processing generates the point cloud data that adaptive machining is read.
4. aero-engine stator blade front and rear edges adaptive machining method as described in claim 1, which is characterized in that institute
State step 4 specifically:
Step 4.1: point cloud data being subjected to bad point examination and rejecting, error amount are set as 0.05mm；
Step 4.2: by determining that reference axis is sequence principal direction, completing scan data sequence according to actual cross-section line feature, also
Protocosta leaf pelvic surface of sacrum, leading edge leaf back, rear leaf pelvic surface of sacrum and rear leaf back actual cross-section line.
5. aero-engine stator blade front and rear edges adaptive machining method as described in claim 1, which is characterized in that institute
State step 5 specifically:
Step 5.1: according to the theoretical curved surface of blade front and rear edges and the leading edge leaf pelvic surface of sacrum of reduction, leading edge leaf back, rear leaf basin
Face, rear leaf back actual cross-section line, generate leading edge leaf pelvic surface of sacrum, leading edge leaf back, rear leaf pelvic surface of sacrum, rear leaf back 4
The practical curved surface of working region；
Step 5.2: under the guidance of theoretical model and design tolerance, the practical curved surface of leading edge leaf pelvic surface of sacrum and leading edge leaf back being pressed
Blade inlet edge model is reconstructed into according to scan data trend；By the practical curved surface of rear leaf pelvic surface of sacrum and rear leaf back according to scanning number
It is reconstructed into trailing edge model according to trend, process modeling needed for ultimately producing processing.
6. aero-engine stator blade front and rear edges adaptive machining method as described in claim 1, which is characterized in that institute
State step 6 specifically:
Blade inlet edge model and trailing edge model setting Cutter coordinate system and cutter axis orientation are chosen, determines working position and curved surface
Biased direction, rough mill, leading edge finish-milling, rear are rough milled, four cutter location files of rear finish-milling by leading edge for the generation of operation algorithm.
7. aero-engine stator blade front and rear edges adaptive machining method as claimed in claim 8, which is characterized in that institute
State step 7 specifically:
Step 7.1: 4 cutter location files being imported in postpositive disposal software, the identifiable NC code processing program text of export lathe
Part；
Step 7.2: completing adaptive thick, the finish-milling processing of front and rear edges on lathe, and carry out three coordinate measurements, blade processing
Size shape Design of Symbols requirement afterwards connects knife without obvious.
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| CN201811396482.1A CN109332772A (en) | 2018-11-22 | 2018-11-22 | A kind of aero-engine stator blade front and rear edge adaptive machining method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110716502A (en) * | 2019-11-27 | 2020-01-21 | 北京航空航天大学 | Tool path generation method and device for engine blade repair |
| CN111702490A (en) * | 2020-06-17 | 2020-09-25 | 陕西飞机工业（集团）有限公司 | Automatic finish machining process method for end faces of assembly butt joint parts |
| CN112099433A (en) * | 2020-09-17 | 2020-12-18 | 中国航空制造技术研究院 | Adjusting method for near-net-shape blade reconstructed profile tool path |
| CN113814673A (en) * | 2021-11-01 | 2021-12-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Geometric self-adaptive machining method for titanium alloy blisk welding part of large fan |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104246635A (en) * | 2012-04-24 | 2014-12-24 | 斯奈克玛 | Method for machining the trailing edge of a turbine engine blade |
| CN104484533A (en) * | 2014-12-23 | 2015-04-01 | 中国民航大学 | Point-cloud-based three-dimensional modeling method for damaged turbine blade of aero-engine |
| CN106354927A (en) * | 2016-08-29 | 2017-01-25 | 西北工业大学 | Construction method of optimization model for adaptive processing of front and rear edges of precisely-forged blade |
| CN106897501A (en) * | 2017-01-23 | 2017-06-27 | 西北工业大学 | The positioning and optimizing method based on blade parts deformation towards in adaptive machining |
| CN107790793A (en) * | 2017-09-28 | 2018-03-13 | 中国航发动力股份有限公司 | A kind of aviation finish forge blade self-adapting type milling method |
| CN107806836A (en) * | 2017-09-28 | 2018-03-16 | 中国航发动力股份有限公司 | A kind of finish forge blade profile detection method based on five-axle linkage spot light |
-
2018
- 2018-11-22 CN CN201811396482.1A patent/CN109332772A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104246635A (en) * | 2012-04-24 | 2014-12-24 | 斯奈克玛 | Method for machining the trailing edge of a turbine engine blade |
| CN104484533A (en) * | 2014-12-23 | 2015-04-01 | 中国民航大学 | Point-cloud-based three-dimensional modeling method for damaged turbine blade of aero-engine |
| CN106354927A (en) * | 2016-08-29 | 2017-01-25 | 西北工业大学 | Construction method of optimization model for adaptive processing of front and rear edges of precisely-forged blade |
| CN106897501A (en) * | 2017-01-23 | 2017-06-27 | 西北工业大学 | The positioning and optimizing method based on blade parts deformation towards in adaptive machining |
| CN107790793A (en) * | 2017-09-28 | 2018-03-13 | 中国航发动力股份有限公司 | A kind of aviation finish forge blade self-adapting type milling method |
| CN107806836A (en) * | 2017-09-28 | 2018-03-16 | 中国航发动力股份有限公司 | A kind of finish forge blade profile detection method based on five-axle linkage spot light |
Non-Patent Citations (1)
| Title |
|---|
| 蔺小军等: "面向自适应加工的精锻叶片前后缘模型重构", 《航空学报》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110716502A (en) * | 2019-11-27 | 2020-01-21 | 北京航空航天大学 | Tool path generation method and device for engine blade repair |
| CN110716502B (en) * | 2019-11-27 | 2020-10-23 | 北京航空航天大学 | Tool path generation method and device for engine blade repair |
| CN111702490A (en) * | 2020-06-17 | 2020-09-25 | 陕西飞机工业（集团）有限公司 | Automatic finish machining process method for end faces of assembly butt joint parts |
| CN112099433A (en) * | 2020-09-17 | 2020-12-18 | 中国航空制造技术研究院 | Adjusting method for near-net-shape blade reconstructed profile tool path |
| CN112099433B (en) * | 2020-09-17 | 2021-12-24 | 中国航空制造技术研究院 | Adjusting method for near-net-shape blade reconstructed profile tool path |
| CN113814673A (en) * | 2021-11-01 | 2021-12-21 | 中国航发沈阳黎明航空发动机有限责任公司 | Geometric self-adaptive machining method for titanium alloy blisk welding part of large fan |
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Application publication date: 20190215 |