CN106529069A - Method for designing blade body margin of over-bent blade forge piece - Google Patents
Method for designing blade body margin of over-bent blade forge piece Download PDFInfo
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- CN106529069A CN106529069A CN201611044363.0A CN201611044363A CN106529069A CN 106529069 A CN106529069 A CN 106529069A CN 201611044363 A CN201611044363 A CN 201611044363A CN 106529069 A CN106529069 A CN 106529069A
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- blade
- forging
- bent blades
- section line
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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
The invention provides a method for designing a blade body margin of an over-bent blade forge piece. The method comprises the following steps: drawing a three-dimensional model of a part blade body; executing an offset command according to machining margin to obtain a three-dimensional model of the part blade body with the margin increased; extracting section lines of the part and the forge piece according to a sectional distance on a part drawing; importing the section lines in two-dimensional drawing software; drawing two continuous inscribed circles on the exhaust edge of the section line of the part, and drawing an extension line of a connecting line of circle centers; drawing a normal of the extension line on a cross point of the extension line and the section line of the part; offsetting both sides of the extension line to obtain two symmetrical first offset lines, wherein the offset is a half of the thickness of a deckle edge of the exhaust edge of the section line at an over-bent site; offsetting a single side of the normal to obtain a second offset line, wherein the offset is the margin of the exhaust edge at the over-bent site, and the cross points of the first offset lines and the second offset line are respectively marked as first and second edge control points; moving two outer end points of the section line of the forge piece to the first and second edge control points; and inquiring all control points of the section line of the forge piece, and importing the same into a three-dimensional drawing software to generate a three-dimensional model of the blade body of the forge piece.
Description
Technical field
The invention belongs to blade of aviation engine manufacturing technology field, more particularly to a kind of to cross more than bent blades forging blade
Amount method for designing.
Background technology
With the continuous improvement required to aeroengine thrust, the blade shape of aero-engine also tends to complicate,
So that one kind crosses bent blades as an example, the line of each centroid of section of bent blades blade is crossed, near tip segment song curvature of a curve urgency
Increase severely big, that crosses bent blades blade crosses bending angle maximum up to 60 °, if adopting traditional blades forging blade surplus design side
Method, is obtained blade forging as shown in Figure 1, and the blade forging blade crosses the local machining allowance of crook by deficiency
30%, and the overall machining allowance distribution of bent blades forging blade excessively is also very uneven, this can cause bent blades part
Easily occurs stress deformation after machining, so as to seriously reduce the conforming product rate of bent blades part.
The content of the invention
For the problem that prior art is present, the present invention provides one kind and crosses bent blades forging blade surplus design method, energy
The overall machining allowance that bent blades forging blade was enough effectively ensured is evenly distributed, and bent blades part excessively is after machining
Stress distribution is more reasonable, and stress deformation scope is little, effectively improves the conforming product rate of bent blades part.
To achieve these goals, the present invention is adopted the following technical scheme that：It is a kind of to cross bent blades forging blade surplus design
Method, comprises the steps：
Step one：Bent blades part blade threedimensional model is crossed by three-dimensional drawing Software on Drawing；
Step 2：Bias command is performed in three-dimensional drawing software, according to actually required machining allowance setting biasing
Amount, and obtain the bent blades part blade threedimensional model excessively after surplus increases；
Step 3：According to the drawing cross-sectional distance of bent blades part excessively, the bent blades part blade excessively after surplus increases
Part section line and forging section line is extracted on threedimensional model；
Step 4：The part section line for extracting and forging section line are imported in two-dimensional graphicses software, is 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, the first inscribed circle and is designated as respectively
Two inscribed circles；
Step 6：The center of circle of the first inscribed circle and the second inscribed circle is carried out into line, the extended line of circle center line connecting is remake；
Step 7：Make the normal of extended line on intersection point of the extended line with part section line；
Step 8：Bilateral biasing is carried out to extended line, two the first symmetrical offset lines, and the biasing of extended line is obtained
Measure be crook intake and exhaust side burr thickness half；
Step 9：Unilateral biasing is carried out to normal, the second offset line is obtained, and the amount of bias of normal was that row is entered in crook
Gas side surplus, and the intersection point of the second offset line and two the first offset lines is designated 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 into first edge control point and second edge control
Point；
Step 11：Inquire whole control point of forging section line in two-dimensional graphicses software, then by the forging for inquiring
Part section line whole control point is imported in three-dimensional drawing software, you can what generation was brand-new crosses bent blades forging blade threedimensional model.
That crosses bent blades forging blade crosses crook intake and exhaust side burr thickness by being calculated, and its computing formula is：Cross
Crook intake and exhaust burr thickness/cos α in burr thickness=non- crook intake and exhaust excessively, in formula, α crosses bending angle for blade.
Row is entered in the non-crook of crossing crossed crook intake and exhaust side surplus with cross bent blades forging blade for crossing bent blades forging blade
Gas side surplus is consistent.
Beneficial effects of the present invention：
The present invention compared with prior art, can effectively ensure that the overall 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 scope is little, effectively improves curved leaf
The conforming product rate of piece part, the actual measuring and calculating of Jing, conforming product rate improve about 30%, and rate also phase is repaiied in the throwing in blade type face
About 23% should be reduced.
Description of the drawings
Fig. 1 is the blade forging schematic diagram obtained using traditional blades forging blade surplus design method；
Fig. 2 is to cross the blade forging schematic diagram that bent blades forging blade surplus design method is obtained using 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；
Surplus adjustment schematic diagrams of the Fig. 5 for forging section line；
Fig. 6 is the bent blades forging blade threedimensional model schematic diagram excessively after surplus adjustment；
In figure, 1 part section line, 2 forging section lines, 3 first inscribed circles, 4 second inscribed circles, 5 extend
Line, 6 normals, 7 first offset lines, 8 second offset lines, 9 first edge control point, 10 second edge control point,
11 cross crook, and A crosses crook intake and exhaust side burr thickness, and B crosses crook intake and exhaust side surplus.
Specific embodiment
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings.
It is a kind of to cross bent blades forging blade surplus design method, comprise the steps：
Step one：Bent blades part blade threedimensional model was drawn by three-dimensional drawing software (UG softwares), such as Fig. 3 institutes
Show；
Step 2：Bias command is performed in three-dimensional drawing software (UG softwares), according to actually required machining allowance
Setting amount of bias, and the bent blades part blade threedimensional model excessively after surplus increases is obtained, as shown in Figure 4；
Step 3：According to the drawing cross-sectional distance of bent blades part excessively, the bent blades part blade excessively after surplus increases
Part section line 1 and forging section line 2 is extracted on threedimensional model；
Step 4：The part section line 1 for extracting and forging section line 2 are imported into two-dimensional graphicses software (CAXA softwares)
In, preparation carries 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 1,3 He of the first inscribed circle is designated as respectively
Second inscribed circle 4；
Step 6：The center of circle of the first inscribed circle 3 and the second inscribed circle 4 is carried out into line, the extended line of circle center line connecting is remake
5；
Step 7：Make the normal 6 of extended line 5 on intersection point of the extended line 5 with part section line 1；
Step 8：Bilateral biasing is carried out to extended line 5, available two the first symmetrical offset lines 7, and extended line 5
Amount of bias was the half of crook intake and exhaust side burr thickness A；Wherein, that crosses bent blades forging blade crosses crook intake and exhaust side hair
By being calculated, its computing formula is side thickness A：Cross crook intake and exhaust burr in burr thickness=non- crook intake and exhaust excessively
Thickness/cos α, in formula, α crosses bending angle for blade；
Step 9：Unilateral biasing is carried out to normal 6, the second offset line 8 is 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 designated as first edge control point 9 and respectively
2 Edge position control points 10；Wherein, cross crossing crook intake and exhaust side surplus B and crossing bent blades forging blades for bent blades forging blade
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 into first edge control point 9 and second edge control
System point 10；
Step 11：Whole control point of forging section line 2 are inquired in two-dimensional graphicses software (CAXA softwares), then will
The 2 whole control point of forging section line for inquiring are imported in three-dimensional drawing software (UG softwares), you can generate brand-new excessively curved leaf
Piece forging blade threedimensional model, as shown in Figure 6.
As shown in Fig. 2 be that the blade forging that bent blades forging blade surplus design method is obtained is crossed using 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
Overall machining allowance distribution is also more uniform, thus, it is also possible to bent blades part answering after machining was effectively ensured
Power distribution is more reasonable.
Scheme in embodiment being not used to limits the scope of patent protection of the present invention, it is all without departing from carried out by the present invention etc.
Effect is implemented or is changed, and is both contained in the scope of the claims of this case.
Claims (3)
1. it is a kind of to cross bent blades forging blade surplus design method, it is characterised in that to comprise the steps：
Step one：Bent blades part blade threedimensional model is crossed by three-dimensional drawing Software on Drawing；
Step 2：Bias command is performed in three-dimensional drawing software, according to actually required machining allowance setting amount of bias, and
Obtain the bent blades part blade threedimensional model excessively after surplus increases；
Step 3：According to the drawing cross-sectional distance of bent blades part excessively, the bent blades part blade excessively after surplus increases is three-dimensional
Part section line and forging section line is extracted on model；
Step 4：The part section line for extracting and forging section line are imported in two-dimensional graphicses software, is 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, is designated 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 carried out into line, the extended line of circle center line connecting is remake；
Step 7：Make the normal of extended line on intersection point of the extended line with part section line；
Step 8：Bilateral biasing is carried out to extended line, two the first symmetrical offset lines are obtained, and the amount of bias of extended line is
Cross the half of crook intake and exhaust side burr thickness；
Step 9：Unilateral biasing is carried out to normal, the second offset line is 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 designated 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 into first edge control point and second edge control point；
Step 11：Whole control point of forging section line are inquired in two-dimensional graphicses software, then the forging for inquiring is cut
Upper thread whole control point is imported in three-dimensional drawing software, you can what generation was brand-new crosses bent blades forging blade threedimensional model.
2. one kind according to claim 1 crosses bent blades forging blade surplus design method, it is characterised in that：Cross bent blades
The crook intake and exhaust side burr thickness of crossing of forging blade passes through to be calculated, and its computing formula is：Cross crook intake and exhaust side burr
Thickness=non- crook intake and exhaust side burr thickness/cos α excessively, in formula, α crosses bending angle for blade.
3. one kind according to claim 1 crosses bent blades forging blade surplus design method, it is characterised in that：Cross bent blades
The crook intake and exhaust excessively of forging blade are consistent with surplus when crossing the non-crook intake and exhaust excessively of bent blades forging blade in surplus.
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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 CN106529069B (en) | 2019-06-11 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN109214032A (en) * | 2017-12-07 | 2019-01-15 | 中国航空制造技术研究院 | A kind of adaptive machining method of hollow blade |
| CN109684686A (en) * | 2018-12-10 | 2019-04-26 | 中国航发贵州黎阳航空动力有限公司 | A kind of blade blade molded line immediate processing method |
| 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 |
| CN110941900A (en) * | 2019-11-26 | 2020-03-31 | 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 |
| CN113486477A (en) * | 2021-08-20 | 2021-10-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for designing prefabricated blank of high-temperature-resistant alloy complex single-tenon blade forging |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN109214032A (en) * | 2017-12-07 | 2019-01-15 | 中国航空制造技术研究院 | A kind of adaptive machining method of hollow blade |
| CN109684686A (en) * | 2018-12-10 | 2019-04-26 | 中国航发贵州黎阳航空动力有限公司 | A kind of blade blade molded line immediate processing method |
| 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 |
| CN110941900A (en) * | 2019-11-26 | 2020-03-31 | 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 |
| 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 |
| CN113486477A (en) * | 2021-08-20 | 2021-10-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for designing prefabricated blank of high-temperature-resistant alloy complex single-tenon blade forging |
| 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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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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