CN102332037A - Blade body sectional surface design method for die forging blade - Google Patents
Blade body sectional surface design method for die forging blade Download PDFInfo
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- CN102332037A CN102332037A CN2010102269512A CN201010226951A CN102332037A CN 102332037 A CN102332037 A CN 102332037A CN 2010102269512 A CN2010102269512 A CN 2010102269512A CN 201010226951 A CN201010226951 A CN 201010226951A CN 102332037 A CN102332037 A CN 102332037A
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Abstract
The invention relates to a blade body sectional surface design method for a die forging blade. The blade body sectional surface design of the die forging blade is carried out according to the following requirements that: (1) firstly, a mathematical model of a blade body sectional surface line is built according to the coordinate values of the blade part blade body sectional surface points; (2) the inscribed circle of the air inlet and exhaust edges of the blade body is obtained according to the mathematical model; (3) the edge radius or the sectional line is optimized so that the sectional surface is precise and smooth; and (4) a blade forging element mathematical model is built on the basis, and in addition, the allowance increase is carried out. The method has the advantages that the design process is simple, the parametric design can be realized, the blade body sectional surface is smooth, the design model precision is high, and the like. The fast conversion and output process of the process files or parts, forging elements and the like can be realized, simultaneously, the resource sharing and the digital manufacture can be simultaneously realized, the design and manufacture period can be greatly shortened, the development process is accelerated, and the production efficiency is improved.
Description
Technical field
The present invention relates to the die forging blade blade profile designing technique in material forming engineering field, a kind of die forging blade blade profile method for designing is provided especially.
Background technology
At present, external CAD/CAM research work to complex-shaped finish forge blade does not also have relevant report.Units such as domestic Wuxi blade Ltd, the safe and sound blade technology in Xi'an company limited have developed and have been fit to forming technology and the mould Design CAD/CAM system that its use needs, but these softwares did not carry out secondary development to the design of finish forge blade.
At present die forging (comprising finish forge) blade blade profile and based on the process engineering of blade profile design have low precision, shortcoming such as design process is loaded down with trivial details and the design cycle is long.Most importantly the link of design is independently carried out often; This has just brought following problem: 1) repeatability of design is poor; Do not make full use of the design result of last design phase, the designer need repeat input and calculate mass data, its design process easy error; 2) design effort amount is big, makes the designer not to be placed on energy on the emphasis problem of care, makes design focal point not outstanding.3) the engineering change (EC) difficulty often makes blade forging have the little modification in a place can cause the cataclysm of a whole set of mould, need recomputate many data.The blade position design of especially die forging (comprising finish forge) blade, the blade modeling is still imported blade profile coordinate points by repeating, and sets up the blade model; Do not set up blade profile mathematical model; The blade profile is not optimized processing, not fairing of profile; Limit portion surplus places still leans on designer's hand debugging, often brings very big error.
People catch at the good die forging blade blade profile method for designing of a kind of technique effect.
Summary of the invention
The purpose of this invention is to provide the good die forging blade blade profile method for designing of a kind of technique effect.Emphasis be set up that die forging (comprising finish forge) blade finish-forging spare blade profile surplus places, the aided design system of profile optimization and blade tip lengthening.
Concrete technical thought of the present invention is: the design software that uses blade finish forge spare blade profile to handle carries out the back work of the design of die forging (comprising finish forge) blade blade profile and relevant other link.
A kind of die forging blade of the present invention blade profile method for designing is characterized in that: carry out the design of die forging blade blade profile according to following requirement successively:
(1) at first according to the coordinate figure of blade part blade profile point, sets up the mathematical model of blade profile line; (2), obtain the incircle on blade inlet and outlet limit according to this mathematical model; (3) optimize edge radii or molded lines, make the accurate and fairing of profile; (4) set up blade forging mathematical model on this basis, and carry out surplus and place.
Said die forging blade blade profile method for designing also has following preferred the requirement:
In step (1), following specific requirement is arranged:, adopt Chebyshev's curve-fitting method to set up the mathematical model of blade profile line according to the coordinate figure of blade part blade profile point.
In step (4), require on the basis that blade part profile is optimized, to carry out placing of forging surplus:
According to the mathematical model that the blade profile is set up, directly calculate the coordinate figure that places the leaf basin blade back profile point after the surplus, and then optimize the mathematical model of blade forging profile again, make profile accurately, fairing.
What need Special attention will be given to is: die forging blade blade profile method for designing according to the invention is characterized in that: in step (4), carrying out the specific requirement that surplus places is:
Adopt the method for designing of blade tip profile extrapolation, the coordinate points on the blade tip profile is projected on the plane after the extension, realize the extension of blade tip simultaneously according to the trend of blade profile.
In step (4), carrying out the specific requirement that surplus places is:
Flat plate margin places: according to the incenter of section line that blade provides and the computation model of intake and exhaust limit radius; Obtain the mathematical model Ly of circle center line connecting through the match of incenter point; And then obtain blade part intake and exhaust limit outermost points at; And be starting point with this point, increase the surplus Δ along the tangential direction of incenter line Ly
1, Δ
2, and utilize the mathematical model of circle center line connecting Ly, obtain the incenter after the blade forging edge places surplus;
Through specifying new unified edge radii R, optimize leaf basin blade back curve again, make that leaf basin blade back curve and intake and exhaust edge are tangent, see accompanying drawing 1.Extend for blade tip, traditional differential technique can not get the profile of fairing sometimes, shown in accompanying drawing 2.
Related content brief introduction of the present invention:
The design of blade forging needs the technician to have senior experience and a large amount of troublesome calculation usually, and a finish forge blade design needs very long design time, and this is seriously restricting the required quick-reaction capability (QRC) of plane development.
What the present invention is based on that area of computer aided Three-dimensional Design Software platform also developed is applicable to the finish forge blade software of design fast.These software systems have that design process is simple, parameterisable design, the fairing of blade profile, the precision that designs a model advantages of higher; Can realize the quick conversion and the output procedure of technical paperss such as part, forging; Realize resource sharing and digitizing manufacturing simultaneously; Shorten design and manufacturing cycle significantly, accelerate the development process, enhance productivity.
Developing software that the present invention is correlated with is present domestic first design system that is exclusively used in the finish forge blade based on area of computer aided Three-dimensional Design Software platform development, can be successfully applied to the design of polytypic engine blade.It has blade blade design process simple, have an inheritability; Model accuracy is than higher, blade profile be optimized (fairing); Simultaneously can carry out resource sharing, satisfy the information-based requirement of making; Improved the design philosophy of traditional die forging blade.Its economic worth is huge, and application prospect is extensive.
Use the present invention can save the manufacturing cycle of design cycle and mould greatly, improve the precision that mould is made, for scientific research and produced on-site provide strong guarantee by node.Reduced technologist's repetitive operation simultaneously, made the technologist have more time to serve the scene.The application of related software of the present invention is the lifting of fine forging technology, also is a sign that forges the digital information skill upgrading.
From considering economically, can practice thrift the great amount of manpower resource and greatly shorten the product development production cycle, improve research and development ability, bring huge economic benefit.
Description of drawings
Below in conjunction with accompanying drawing and embodiment the present invention is done further detailed explanation:
Fig. 1 is for to place and optimization figure for blade molded lines flat plate margin;
The blade not fairing model of Fig. 2 for setting up with traditional interpolation method;
The blade fairing model of Fig. 3 for setting up with blade tip profile extrapolation method of the present invention;
Fig. 4 is a finish forge blade blade design system actions menu;
Fig. 5 is a finish forge blade blade design system operation interface;
Fig. 6 certain machine finish forge blade forging figure for coming out through the design's system design.
Embodiment
A kind of die forging blade blade profile method for designing, carry out the design of die forging blade blade profile according to following requirement successively:
(1) at first according to the coordinate figure of blade part blade profile point, sets up the mathematical model of blade profile line; (2), obtain the incircle on blade inlet and outlet limit according to this mathematical model; (3) optimize edge radii or molded lines, make the accurate and fairing of profile; (4) set up blade forging mathematical model on this basis, and carry out surplus and place.
Said die forging blade blade profile method for designing also includes following specific requirement:
In step (1), following specific requirement is arranged:, adopt Chebyshev's curve-fitting method to set up the mathematical model of blade profile line according to the coordinate figure of blade part blade profile point.
In step (4), require on the basis that blade part profile is optimized, to carry out placing of forging surplus:
According to the mathematical model that the blade profile is set up, directly calculate the coordinate figure that places the leaf basin blade back profile point after the surplus, and then optimize the mathematical model of blade forging profile again, make profile accurately, fairing.
What need Special attention will be given to is: carrying out the specific requirement that surplus places in the step (4) of said die forging blade blade profile method for designing is: the method for designing that adopts the extrapolation of blade tip profile; Coordinate points on the blade tip profile is projected on the plane after the extension, realize the extension of blade tip simultaneously according to the trend of blade profile.
In step (4), carrying out the specific requirement that surplus places is:
Flat plate margin places: according to the incenter of section line that blade provides and the computation model of intake and exhaust limit radius; Obtain the mathematical model Ly of circle center line connecting through the match of incenter point; And then obtain blade part intake and exhaust limit outermost points at; And be starting point with this point, increase the surplus Δ along the tangential direction of incenter line Ly
1, Δ
2, and utilize the mathematical model of circle center line connecting Ly, obtain the incenter after the blade forging edge places surplus;
Through specifying new unified edge radii R, optimize leaf basin blade back curve again, make that leaf basin blade back curve and intake and exhaust edge are tangent, see accompanying drawing 1.Extend for blade tip, traditional differential technique can not get the profile of fairing sometimes, shown in accompanying drawing 2.
The design of any finish forge blade can be accomplished through the system operation menu, shown in accompanying drawing 3.Click blade data fitting button, eject blade design operation interface, work such as shown in accompanying drawing 4, this interface carries out mainly that forging blade leaf basin blade back surplus places, limit portion surplus places, the optimization of blade profile and blade tip extension.At first set up the text of the various millet cake coordinate figure of blade part, in the path of window 1 specified document of accompanying drawing 5; Secondly, provide profile point coordinate value input mode, confirm that promptly input leaf basin data still are the blade back data earlier.Point out the blade modes of emplacement again, promptly confirm the leaf basin up still blade back up, shown in the window 2 and 3 of accompanying drawing 5.Then, confirm that the blade surplus places mode, confirm that promptly blade profile Y direction still is that blade profile normal direction places surplus, shown in accompanying drawing 5 windows 4.Indicate the data file path on blade intake and exhaust limit, shown in accompanying drawing 5 windows 5.With reference to picture file that design interface is given, provide following parameter (like accompanying drawing 5 windows 6): 1) blade tip prolongs distance; 2) the leaf basin places margin value; 3) blade back places margin value; 4) leading edge margin value; Exhaust limit margin value; 5) whether provide the unified value of edge radii, if provide edge radii.And result of calculation is output as text, so that subsequent design work uses, shown in accompanying drawing 5 windows 7.
Claims (5)
1. die forging blade blade profile method for designing is characterized in that: carry out the design of die forging blade blade profile according to following requirement successively:
(1) at first according to the coordinate figure of blade part blade profile point, sets up the mathematical model of blade profile line; (2), obtain the incircle on blade inlet and outlet limit according to this mathematical model; (3) optimize edge radii or molded lines, make the accurate and fairing of profile; (4) set up blade forging mathematical model on this basis, and carry out surplus and place.
2. according to the said die forging blade of claim 1 blade profile method for designing, it is characterized in that:
In step (1), following specific requirement is arranged:, adopt Chebyshev's curve-fitting method to set up the mathematical model of blade profile line according to the coordinate figure of blade part blade profile point.
3. according to claim 1 or 2 said die forging blade blade profile methods for designing, it is characterized in that: in step (4), require on the basis that blade part profile is optimized, to carry out placing of forging surplus:
According to the mathematical model that the blade profile is set up, directly calculate the coordinate figure that places the leaf basin blade back profile point after the surplus, and then optimize the mathematical model of blade forging profile again, make profile accurately, fairing.
4. according to the said die forging blade of claim 3 blade profile method for designing, it is characterized in that: in step (4), carrying out the specific requirement that surplus places is:
Adopt the method for designing of blade tip profile extrapolation, the coordinate points on the blade tip profile is projected on the plane after the extension, realize the extension of blade tip simultaneously according to the trend of blade profile.
5. according to the said die forging blade of claim 4 blade profile method for designing, it is characterized in that: in step (4), carrying out the specific requirement that surplus places is:
Flat plate margin places: according to the incenter of section line that blade provides and the computation model of intake and exhaust limit radius; Obtain the mathematical model Ly of circle center line connecting through the match of incenter point; And then obtain blade part intake and exhaust limit outermost points at; And be starting point with this point, increase the surplus Δ along the tangential direction of incenter line Ly
1, Δ
2, and utilize the mathematical model of circle center line connecting Ly, obtain the incenter after the blade forging edge places surplus;
Through specifying new unified edge radii R, optimize leaf basin blade back curve again, make that leaf basin blade back curve and intake and exhaust edge are tangent.
Priority Applications (1)
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| CN 201010226951 CN102332037B (en) | 2010-07-15 | 2010-07-15 | Blade body sectional surface design method for die forging blade |
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| CN 201010226951 CN102332037B (en) | 2010-07-15 | 2010-07-15 | Blade body sectional surface design method for die forging blade |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103244195A (en) * | 2013-05-10 | 2013-08-14 | 西安航空动力股份有限公司 | Precision forging blade thickness plastic deformation compensation method |
| CN103252536A (en) * | 2013-05-20 | 2013-08-21 | 西北工业大学 | Rolled blade flange head smooth transferring machining method |
| CN103577635A (en) * | 2013-10-19 | 2014-02-12 | 沈阳黎明航空发动机(集团)有限责任公司 | Fitting method of blade surface data |
| CN103927426A (en) * | 2014-05-06 | 2014-07-16 | 南京航空航天大学 | Aero-engine blisk feature recognition method |
| CN104462677A (en) * | 2014-11-29 | 2015-03-25 | 中国航空动力机械研究所 | Blade tip mold line design method and application for rotatable stationary blade |
| CN106529069A (en) * | 2016-11-24 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for designing blade body margin of over-bent blade forge piece |
| CN107391779A (en) * | 2016-05-17 | 2017-11-24 | 中国科学院金属研究所 | A kind of blank shape design method of die forging crankshaft of diesel engine |
| CN107825388A (en) * | 2017-09-28 | 2018-03-23 | 中国航发动力股份有限公司 | Blade blade section chalker design method and device based on 3D printing |
| CN109684687A (en) * | 2018-12-11 | 2019-04-26 | 中国航发贵州黎阳航空动力有限公司 | A kind of modeling method of rotor blade forging blade tip technique extended segment |
| CN110773694A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Die for forging blade |
| CN110773699A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103244195B (en) * | 2013-05-10 | 2015-05-27 | 西安航空动力股份有限公司 | Precision forging blade thickness plastic deformation compensation method |
| CN103244195A (en) * | 2013-05-10 | 2013-08-14 | 西安航空动力股份有限公司 | Precision forging blade thickness plastic deformation compensation method |
| CN103252536A (en) * | 2013-05-20 | 2013-08-21 | 西北工业大学 | Rolled blade flange head smooth transferring machining method |
| CN103252536B (en) * | 2013-05-20 | 2015-01-28 | 西北工业大学 | Rolled blade flange head smooth transferring machining method |
| CN103577635A (en) * | 2013-10-19 | 2014-02-12 | 沈阳黎明航空发动机(集团)有限责任公司 | Fitting method of blade surface data |
| CN103927426B (en) * | 2014-05-06 | 2017-07-28 | 南京航空航天大学 | Aero-engine blisk characteristic recognition method |
| CN103927426A (en) * | 2014-05-06 | 2014-07-16 | 南京航空航天大学 | Aero-engine blisk feature recognition method |
| CN104462677A (en) * | 2014-11-29 | 2015-03-25 | 中国航空动力机械研究所 | Blade tip mold line design method and application for rotatable stationary blade |
| CN107391779A (en) * | 2016-05-17 | 2017-11-24 | 中国科学院金属研究所 | A kind of blank shape design method of die forging crankshaft of diesel engine |
| CN106529069A (en) * | 2016-11-24 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for designing blade body margin of over-bent blade forge piece |
| CN106529069B (en) * | 2016-11-24 | 2019-06-11 | 中国航发沈阳黎明航空发动机有限责任公司 | It is a kind of to cross bent blades forging blade surplus design method |
| CN107825388A (en) * | 2017-09-28 | 2018-03-23 | 中国航发动力股份有限公司 | Blade blade section chalker design method and device based on 3D printing |
| CN109684687A (en) * | 2018-12-11 | 2019-04-26 | 中国航发贵州黎阳航空动力有限公司 | A kind of modeling method of rotor blade forging blade tip technique extended segment |
| CN109684687B (en) * | 2018-12-11 | 2023-02-28 | 中国航发贵州黎阳航空动力有限公司 | Modeling method for rotor blade forging tip process extension section |
| CN110773694A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Die for forging blade |
| CN110773699A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
| CN110773699B (en) * | 2019-11-10 | 2021-02-09 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
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| CN102332037B (en) | 2013-05-01 |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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