CN106529069B - It is a kind of to cross bent blades forging blade surplus design method - Google Patents
It is a kind of to cross bent blades forging blade surplus design method Download PDFInfo
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- CN106529069B CN106529069B CN201611044363.0A CN201611044363A CN106529069B CN 106529069 B CN106529069 B CN 106529069B CN 201611044363 A CN201611044363 A CN 201611044363A CN 106529069 B CN106529069 B CN 106529069B
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- forging
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- section line
- bent blades
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
Abstract
It is a kind of to cross bent blades forging blade surplus design method, step are as follows: to draw part blade threedimensional model；Bias command is executed by machining allowance, the part blade threedimensional model after obtaining surplus increase；Part, forging section line are extracted according to detail drawing cross-sectional distance；Section line is imported in two-dimensional graphics software；Continuous two inscribed circles are made to part section line intake and exhaust side, to circle center line connecting and make extended line；Make the normal of extended line on extended line and part section line intersection point；Extended line bilateral biases to obtain two symmetrical first offset lines, and amount of bias was the half of crook intake and exhaust side flash thickness；Normal unilateral side biases to obtain the second offset line, and amount of bias was crook intake and exhaust side surplus, and the first, second offset line intersection point is denoted as the first, second Edge position control point respectively；Two the outer end points of forging section line are moved to the first, second Edge position control point；It inquires forging section line whole control point and imports in three-dimensional drawing software, generate forging blade threedimensional model.
Description
Technical field
The invention belongs to blade of aviation engine manufacturing technology fields, more than a kind of bent blades forging blade excessively
Measure design method.
Background technique
With the continuous improvement required aeroengine thrust, the blade shape of aero-engine also tends to complicate,
By taking a kind of bent blades excessively as an example, the line of each centroid of section of bent blades blade is crossed, anxious close to tip segment song curvature of a curve
Increase severely big, that crosses bent blades blade crosses bending angle maximum up to 60 °, if using traditional blades forging blade surplus design side
Blade forging as shown in Figure 1 can be obtained in method, and the local machining allowance that the blade forging blade crosses crook will be insufficient
30%, and the whole machining allowance distribution for crossing bent blades forging blade is also very uneven, this will lead to bent blades part
Stress deformation is easy to appear after machining, to seriously reduce the product qualification rate of bent blades part.
Summary of the invention
In view of the problems of the existing technology, the present invention provides a kind of bent blades forging blade surplus design method excessively, energy
The whole machining allowance that bent blades forging blade was enough effectively ensured is evenly distributed, and crosses bent blades part after machining
Stress distribution is more reasonable, and stress deformation range is small, effectively improves the product qualification rate of bent blades part.
To achieve the goals above, the present invention adopts the following technical scheme: a kind of cross bent blades forging blade surplus design
Method includes the following steps:
Step 1: bent blades part blade threedimensional model is crossed by three-dimensional drawing Software on Drawing；
Step 2: executing bias command in three-dimensional drawing software, sets biasing according to actually required machining allowance
Amount, and obtain crossing bent blades part blade threedimensional model after surplus increase；
Step 3: according to the drawing cross-sectional distance for crossing bent blades part, bent blades part blade is crossed after surplus increase
Part section line and forging section line are extracted on threedimensional model；
Step 4: the part section line extracted and forging section line are imported in two-dimensional graphics software, are prepared to forging
Section line carries out surplus adjustment；
Step 5: making continuous two inscribed circles to the intake and exhaust side of part section line, is denoted as the first inscribed circle and respectively
Two inscribed circles；
Step 6: the center of circle of the first inscribed circle and the second inscribed circle is subjected to line, remakes the extended line of circle center line connecting；
Step 7: make the normal of extended line on the intersection point of extended line and part section line；
Step 8: carrying out bilateral biasing to extended line, and two symmetrical first offset lines, and the biasing of extended line can be obtained
Amount was the half of crook intake and exhaust side flash thickness；
Step 9: carrying out unilateral biasing to normal, can be obtained the second offset line, and the amount of bias of normal was crook into row
Gas Bian Yuliang, and the intersection point of the second offset line and two the first offset lines is denoted as first edge control point and second edge control respectively
Point processed；
Step 10: two the outer end points of forging section line are moved respectively to first edge control point and second edge controls
Point；
Step 11: whole control points of forging section line, then the forging that will be inquired are inquired in two-dimensional graphics software
Part section line whole control point imports in three-dimensional drawing software, that is, produces completely new bent blades forging blade threedimensional model excessively.
The crook intake and exhaust side flash thickness of crossing for crossing bent blades forging blade is obtained by calculation, its calculation formula is: mistake
Crook intake and exhaust flash thickness/cos α when flash thickness=non- crosses crook intake and exhaust, in formula, α is that blade crosses bending angle.
The non-crook of crossing of bent blades forging blade crossed crook intake and exhaust side surplus and cross bent blades forging blade is crossed into row
Gas side surplus is consistent.
Beneficial effects of the present invention:
Compared with prior art, the present invention can effectively ensure that the whole machining allowance distribution of bent blades forging blade
Uniformly, stress distribution of the bent blades part after machining excessively is more reasonable, and stress deformation range is small, effectively improves curved leaf
The product qualification rate of piece part, through practical measuring and calculating, product qualification rate improves about 30%, and rate also phase is repaired in the throwing in blade type face
About 23% should be reduced.
Detailed description of the invention
Fig. 1 is the blade forging schematic diagram obtained using traditional blades forging blade surplus design method；
Fig. 2 is using the blade forging schematic diagram crossing bent blades forging blade surplus design method and obtaining of the invention；
Fig. 3 was bent blades part blade threedimensional model schematic diagram；
Fig. 4 is the bent blades part blade threedimensional model schematic diagram excessively after surplus increase；
Fig. 5 is that the surplus of forging section line adjusts schematic diagram；
Fig. 6, which is that surplus is adjusted, crosses bent blades forging blade threedimensional model schematic diagram；
In figure, 1-part section line, 2-forging section lines, the 3-the first inscribed circle, the 4-the second inscribed circle, 5-extend
Line, 6-normals, the 7-the first offset line, the 8-the second offset line, 9-first edge control points, 10-second edge control points,
11-cross crook, A-mistake crook intake and exhaust side flash thickness, B-mistake crook intake and exhaust side surplus.
Specific embodiment
The present invention is described in further detail in the following with reference to the drawings and specific embodiments.
It is a kind of to cross bent blades forging blade surplus design method, include the following steps:
Step 1: bent blades part blade threedimensional model was drawn by three-dimensional drawing software (UG software), such as Fig. 3 institute
Show；
Step 2: bias command is executed in three-dimensional drawing software (UG software), according to actually required machining allowance
Amount of bias is set, and obtains crossing bent blades part blade threedimensional model after surplus increase, as shown in Figure 4；
Step 3: according to the drawing cross-sectional distance for crossing bent blades part, bent blades part blade is crossed after surplus increase
Part section line 1 and forging section line 2 are extracted on threedimensional model；
Step 4: the part section line 1 extracted and forging section line 2 are imported into two-dimensional graphics software (CAXA software)
In, prepare to carry out surplus adjustment to forging section line 2, as shown in Figure 5；
Step 5: continuous two inscribed circles are made to the intake and exhaust side of part section line 1, are denoted as 3 He of the first inscribed circle respectively
Second inscribed circle 4；
Step 6: the center of circle of the first inscribed circle 3 and the second inscribed circle 4 is subjected to line, remakes the extended line of circle center line connecting
5；
Step 7: make the normal 6 of extended line 5 on the intersection point of extended line 5 and part section line 1；
Step 8: bilateral biasing, available two symmetrical first offset lines 7, and extended line 5 are carried out to extended line 5
Amount of bias was the half of crook intake and exhaust side flash thickness A；Wherein, that crosses bent blades forging blade crosses crook intake and exhaust side hair
Side thickness A is obtained by calculation, its calculation formula is: crook intake and exhaust flash in flash thickness=non- crook intake and exhaust excessively excessively
Thickness/cos α, in formula, α is that blade crosses bending angle；
Step 9: carrying out unilateral biasing to normal 6, the second offset line 8 can be obtained, and the amount of bias of normal 6 was crook
Intake and exhaust side surplus B, and the intersection point of the second offset line 8 and two article of first offset line 7 is denoted as first edge control point 9 and respectively
2 Edge position control points 10；Wherein, crossing crook intake and exhaust side surplus B and crossing bent blades forging blade for bent blades forging blade is crossed
Non- crook intake and exhaust side surplus excessively is consistent；
Step 10: two the outer end points of forging section line 2 are moved respectively to first edge control point 9 and second edge control
System point 10；
Step 11: whole control points of forging section line 2 are inquired in two-dimensional graphics software (CAXA software), then will
The whole control points of the forging section line 2 inquired import in three-dimensional drawing software (UG software), that is, produce completely new excessively curved leaf
Piece forging blade threedimensional model, as shown in Figure 6.
As shown in Fig. 2, to use the blade forging crossing bent blades forging blade surplus design method and obtaining of the invention,
As can be seen that the blade forging blade local machining allowance of crossing crook 11 is more sufficient in figure, and bent blades forging blades
Whole machining allowance distribution is also more uniform, thus, it is also possible to which bent blades part answering after machining was effectively ensured
Power distribution is more reasonable.
The scope of patent protection that scheme in embodiment is not intended to limit the invention, it is all without departing from carried out by the present invention etc.
Effect implements or change, is both contained in the scope of the patents of this case.
Claims (3)
1. a kind of cross bent blades forging blade surplus design method, it is characterised in that include the following steps:
Step 1: bent blades part blade threedimensional model was drawn by three-dimensional drawing software UG；
Step 2: executing bias command in three-dimensional drawing software UG, sets amount of bias according to actually required machining allowance,
And it obtains crossing bent blades part blade threedimensional model after surplus increase；
Step 3: according to the drawing cross-sectional distance for crossing bent blades part, bent blades part blade three-dimensional is crossed after surplus increase
Part section line and forging section line are extracted on model；
Step 4: the part section line extracted and forging section line are imported in two-dimensional graphics software CAXA, are prepared to forging
Section line carries out surplus adjustment；
Step 5: continuous two inscribed circles are made to the intake and exhaust side of part section line, are denoted as in the first inscribed circle and second respectively
The circle of contact；
Step 6: the center of circle of the first inscribed circle and the second inscribed circle is subjected to line, remakes the extended line of circle center line connecting；
Step 7: make the normal of extended line on the intersection point of extended line and part section line；
Step 8: bilateral biasing is carried out to extended line, two symmetrical first offset lines can be obtained, and the amount of bias of extended line is
Cross the half of crook intake and exhaust side flash thickness；
Step 9: unilateral biasing is carried out to normal, the second offset line can be obtained, and the amount of bias of normal was crook intake and exhaust side
Surplus, and the intersection point of the second offset line and two the first offset lines is denoted as first edge control point and second edge control respectively
Point；
Step 10: two the outer end points of forging section line are moved respectively to first edge control point and second edge control point；
Step 11: whole control points of forging section line, then the forging that will be inquired are inquired in two-dimensional graphics software CAXA
Part section line whole control point imports in three-dimensional drawing software UG, that is, produces completely new bent blades forging blade three-dimensional mould excessively
Type.
2. a kind of bent blades forging blade surplus design method excessively according to claim 1, it is characterised in that: cross bent blades
The crook intake and exhaust side flash thickness of crossing of forging blade is obtained by calculation, its calculation formula is: cross crook intake and exhaust side flash
Thickness=non- crosses crook intake and exhaust side flash thickness/cos α, and in formula, α is that blade crosses bending angle.
3. a kind of bent blades forging blade surplus design method excessively according to claim 1, it is characterised in that: cross bent blades
The crook intake and exhaust excessively of forging blade surplus when surplus is with the non-crook intake and exhaust excessively for crossing bent blades forging blade is consistent.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201611044363.0A CN106529069B (en) | 2016-11-24 | 2016-11-24 | It is a kind of to cross bent blades forging blade surplus design method |
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| CN201611044363.0A CN106529069B (en) | 2016-11-24 | 2016-11-24 | It is a kind of to cross bent blades forging blade surplus design method |
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| CN106529069B true CN106529069B (en) | 2019-06-11 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107825388B (en) * | 2017-09-28 | 2019-07-30 | 中国航发动力股份有限公司 | Blade blade section lineation device design method and device based on 3D printing |
| CN109214032B (en) * | 2017-12-07 | 2019-06-21 | 中国航空制造技术研究院 | A kind of adaptive machining method of hollow blade |
| CN109684686B (en) * | 2018-12-10 | 2023-04-07 | 中国航发贵州黎阳航空动力有限公司 | Rapid processing method for blade body profile of blade |
| CN110773694B (en) * | 2019-11-10 | 2021-02-09 | 中国航发南方工业有限公司 | Die for forging 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 |
| CN110941900B (en) * | 2019-11-26 | 2022-10-18 | 中国航发沈阳黎明航空发动机有限责任公司 | Blade forging prefabricated blank design method capable of accurately controlling material flow distribution |
| CN113486477B (en) * | 2021-08-20 | 2023-06-09 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of high-temperature-resistant alloy complex single-tenon blade forging preform |
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| US7377037B2 (en) * | 2004-05-25 | 2008-05-27 | General Electric Company | Fillet machining method without adaptive probing |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Applicant after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Applicant before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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