CN109684687A - A kind of modeling method of rotor blade forging blade tip technique extended segment - Google Patents
A kind of modeling method of rotor blade forging blade tip technique extended segment Download PDFInfo
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- CN109684687A CN109684687A CN201811510873.1A CN201811510873A CN109684687A CN 109684687 A CN109684687 A CN 109684687A CN 201811510873 A CN201811510873 A CN 201811510873A CN 109684687 A CN109684687 A CN 109684687A
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- blade
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- extended segment
- blade tip
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
Abstract
The invention discloses a kind of modeling methods of rotor blade forging blade tip technique extended segment, comprising the following steps: one, parsing blade molded line data；Two, camber line in calculating；Three, make the trend control line in leaf exhibition direction；Four, camber line in extended segment is calculated；Five, the leaf basin and blade back molded line of the control line of extended segment three are calculated；Six, each section molded line of fairing.The present invention uses the precision forged blade without surplus design for blade, and the modeling method of this extended segment can preferably guarantee that the leaf of the profile tolerance at blade tip position, torsional angle, bending and entire blade opens up percent ripple.
Description
Technical field
The present invention relates to the forging G- Designs of aero-engine compressor rotor blade, in particular to blade tip extended segment
Design.
Background technique
The blade tip extended segment of rotor blade forging woollen is according to blade design design feature, to meet forging technology need
It asks, places locating axle journal, extend the part of 10mm~20mm, blade forging figure such as Fig. 1 institute by blade profile trend at blade tip
Show.
Blade forging figure mostly uses greatly three-dimensional mapping software UG to be designed at present, when handling blade tip extended segment, by leaf
Sharp section copies 10mm~20mm upwards, does translation and rotation transformation further according to section of the trend to copy, finally with " passing through song
Line group " order obtains blade entity.This way will cause that extended segment transition is unsmooth, and three aspects are mainly generated to blade
Influence: 1. tip section anchor point K3 fitting error is big, influences the positioning accuracy of blade subsequent mechanical processing；2. in tip section
Place be resiliently deformed there are stress concentration, after forging process for fuel it is big, not close to several sections of profiles tolerance of a surface of tip, torsional angle and bending
Easily guarantee；3. influencing metal fluidity, there are stress concentrations at switching, and then influence die life.
Summary of the invention
The technical problem to be solved in the present invention: a kind of method designing compressor rotor blade blade tip extended segment is provided, is protected
It demonstrate,proves blade and extended segment seamlessly transits.
Technical solution of the present invention:
One, blade molded line data are parsed: the blade profile coordinate point in blade design figure being automatically parsed, the parsing
Process integration is in UG plug-in unit；
Two, camber line in calculating: the point coordinate obtained according to parsing calculates the middle camber line of each blade section blade profile；
Three, make the trend control line in leaf exhibition direction: the middle camber line according to the middle camber line of step 2, in each blade section
On, 5 points are taken by equal arc length, from blade root to blade tip, successively each section corresponding points is connected, obtain the control trend in 5 directions V
Line.
Four, calculate camber line in extended segment: extended segment is by three stripe shape line traffic controls, according to extension segment length respectively in blade tip section
Up certain distance calculates three middle camber lines, and middle camber line is controlled by 5 points, extended respectively from V to 5 control lines along the direction Z+
It arrives, in YZ plane, for the control line in the direction each V, takes out last three control points, successively named from blade root to blade tip
For point P1, point P2, point P3, it is the straight line L for crossing P2 and P3, calculates the distance d1 of point P1 to straight line L, chosen when point P4 is to directly
The extended segment control line in leaf exhibition direction of the distance d2=0.8*d1 and point P4 and point P1 of line L at the same side of straight line L, obtains
Into first extended segment, the Y-coordinate value of camber line calculates available X-coordinate in XZ plane in the same way；With original
Point P2 be P1, point P3 be P2, point P4 be P3, calculate new point P4；Article 2, Article 3 are successively calculated according to the method described above
The coordinate value of camber line in blade tip extended segment.
Five, the leaf basin and blade back molded line of the control line of extended segment three are calculated: by the middle arc in blade tip section and three extended segments
Line equal part becomes N number of point, according to the thickness at each point in blade tip section, by the leaf basin of the control line of this THICKNESS CALCULATION extended segment three
With blade back point coordinate, to obtain the Controlling outline curve of extended segment.
Six, it each section molded line of fairing: according to identical N number of points, controls fairing and accidentally the control in all sections is counted
Fairing one time, obtain final forging molded line.
In step 2, the leaf basin of blade and blade back molded line are divided into 300-1000 point, then take corresponding point
Midpoint is come camber line in defining.
In step 4, if extension segment length is L, in blade tip section up the distance calculating three of L/4, L/2, L
Camber line.
In step 6, fairing control errors are within 0.001.
The invention has the advantages that:
Precision forged blade without surplus design is used for blade, the modeling method of this extended segment can preferably guarantee
The profile tolerance at blade tip position, torsional angle, bending and entire blade leaf open up percent ripple.Meanwhile this method has versatility, will design
For process settings at the form of UG plug-in unit, the blade profile coordinate point provided according to blade design figure is introduced directly into plug-in unit, automatic raw
At blade molded line, design efficiency is improved.
Present invention utilizes the calculating advantage of computer quickly and efficiently, can accurately calculate blade blade auxiliary extended segment
Extension trend and profile；
The design method for optimizing extended segment avoids the curvature mutation of blade Yu extended segment transition, realizes smooth transition,
Greatly reduce workload and design time；
It overcomes because of extended segment and the stiff bring a series of problems of blade switching, can guarantee blade tip section well
Profile tolerance, torsional angle etc., the stress that smooth transition eliminates mold corresponding position concentrates, and improves die life.
Detailed description of the invention:
Fig. 1 is the typical forging structural schematic diagram that this method is applicable in；
Fig. 2 is the control Trendline explanatory diagram that plug-in unit automatically generates；
Fig. 3 is to calculate camber line method schematic diagram in extended segment；
Fig. 4 is plug-in unit startup interface and major function area；
Fig. 5 is the modeling method of the invention and the old forging effect contrast figure for modeling design of violating the law；
Specific embodiment:
Embodiment: the purpose of the invention is realized by following technical solutions:
One, blade molded line data are parsed: according to HB5647-98 " mark, tolerance and the blade rough surface of vane foil
Degree " specified in blade coordinate representation format, the blade profile coordinate point in blade design figure is automatically parsed, the parsing
Process integration is in UG plug-in unit, and parsing technology used is mainstream analytical tool: regular expression, and java language provides can be right
The regex development kit that regular expression perfection is supported, can accurately and conveniently parse blade profile point coordinate.
Two, camber line in calculating: the point coordinate obtained according to parsing calculates the middle camber line of each blade section blade profile, middle arc
Line is observation trend use, not high to required precision, and herein to improve computational efficiency, the leaf basin of blade and blade back molded line are divided into
Then 500 points take the midpoint of corresponding point come camber line in defining, when the points of segmentation are enough, this defines method and use
The calculated result that tangent circle defines method differs within 0.01, the Caton at interface when avoiding UG mapping.
Three, make the trend control line in leaf exhibition direction: the middle camber line according to the middle camber line of step 2, in each blade section
On, 5 points are taken by equal arc length, from blade root to blade tip, successively each section corresponding points is connected, obtain the control trend in 5 directions V
Line, as shown in Figure 2.
Four, calculate camber line in extended segment: extended segment is by three stripe shape line traffic controls, such as when extending segment length is 20mm, respectively
Three middle camber lines are calculated at blade tip section up 5mm, 10mm, 20mm, middle camber line control by 5 points, respectively from V to 5 controls
Line processed extends to obtain along the direction Z+, and the calculation method of middle wire looping point is as shown in Figure 3.In YZ plane, for each side V
To control line, take out last three control points and successively ordered from blade root to blade tip as shown in Article 2 V direction controlling line in Fig. 2
Entitled point P1, point P2, point P3 are the straight line L for crossing P2 and P3, calculate the distance d1 of point P1 to straight line L, pass through test of many times
Observation, as the distance d2=0.8*d1 of point P4 to straight line L, and point P4 and point P1 are at the same side of straight line L, calculated to obtain
The extended segment control line in the leaf exhibition direction arrived is best, the Y-coordinate value of camber line in first extended segment available in this way.Similarly exist
In XZ plane, available X-coordinate is calculated in the same way.Again with V to last three control points of control line be point P1,
(i.e. original point P2 is P1, and point P3 is P2, and point P4 is P3, and calculating new point P4, point P4 is the control at Z=10 by point P2, point P3
Point), successively calculate Article 2, in Article 3 blade tip extended segment camber line coordinate value.
Five, the leaf basin and blade back molded line of the control line of extended segment three are calculated: by the middle arc in blade tip section and three extended segments
Line is divided into 100 parts, obtains 100 points, according to the thickness at each point in blade tip section, by the control of this THICKNESS CALCULATION extended segment three
Leaf basin and blade back the point coordinate of line processed, to obtain the Controlling outline curve of extended segment.
Six, each section molded line of fairing: according to identical points, fairing control errors are within 0.001, by all sections
Control count fairing one time, obtain final forging molded line.
Design details is integrated in UG plug-in unit by the present invention, and specific embodiment is exactly the utilization of plug-in unit, key step
It is as follows:
1. data preparation: the blade coordinate points of design drawing are generally provided with the format of CAD, will be counted by format as defined in navigation mark
According to arrangement into excel table.
2. running UG plug-in unit: by the data copy of arrangement to formatted text area, when text area loses focus, plug-in unit is automatic
It calculates, and makes camber line in blade molded line and extended segment.
3. manual fine-tuning: if initial data tendency is preferable, the extended segment calculated automatically is there is no need to manually adjust, directly
Complete blade molded line and extended segment molded line can be made by clicking determination.It is carried out manually conversely, 15 points can be amounted to extended segment
Every control line when insert design, is placed on different figure layers by adjustment, it may be convenient to switching display, and song adjusted
Line energy real-time update, when manual fine-tuning, facilitate intuitive, it is easy to the effect of smooth transition are recalled, as shown in Fig. 2, plug-in interface is such as
Shown in Fig. 4.
4. making complete forging drawing: design method of the present invention and aging method comparison are as shown in Figure 5.
Claims (4)
1. a kind of modeling method of rotor blade forging blade tip technique extended segment, characterized by comprising:
One, blade molded line data are parsed: the blade profile coordinate point in blade design figure being automatically parsed, the resolving
It is integrated in UG plug-in unit；
Two, camber line in calculating: the point coordinate obtained according to parsing calculates the middle camber line of each blade section blade profile；
Three, make the trend control line in leaf exhibition direction: being pressed on the middle camber line in each blade section according to the middle camber line of step 2
Equal arc length takes 5 points, from blade root to blade tip, successively connects each section corresponding points, obtains the control Trendline in 5 directions V.
Four, calculate camber line in extended segment: extended segment by three stripe shape line traffic controls, according to extend segment length respectively blade tip section up
Certain distance calculates three middle camber lines, and middle camber line is controlled by 5 points, extends to obtain along the direction Z+ from V to 5 control lines respectively,
In YZ plane, for the control line in the direction each V, last three control points is taken out, are successively named as from blade root to blade tip
Point P1, point P2, point P3 are the straight line L for crossing P2 and P3, calculate the distance d1 of point P1 to straight line L, choose as point P4 to straight line
The extended segment control line in leaf exhibition direction of the distance d2=0.8*d1 and point P4 and point P1 of L at the same side of straight line L, obtains
The Y-coordinate value of camber line calculates available X-coordinate in XZ plane in the same way in first extended segment；With original
Point P2 is P1, and point P3 is P2, and point P4 is P3, calculates new point P4；Article 2, Article 3 leaf are successively calculated according to the method described above
The coordinate value of camber line in sharp extended segment.
Five, the leaf basin and blade back molded line of the control line of extended segment three are calculated: by the middle camber line etc. in blade tip section and three extended segments
It is divided into N number of point, according to the thickness at each point in blade tip section, by the leaf basin and leaf of the control line of this THICKNESS CALCULATION extended segment three
Antapex coordinate, to obtain the Controlling outline curve of extended segment.
Six, each section molded line of fairing: according to identical N number of points, fairing is controlled accidentally for the control points fairing in all sections
One time, obtain final forging molded line.
2. the modeling method of rotor blade forging blade tip technique extended segment according to claim 1, it is characterised in that: in step
In two, the leaf basin of blade and blade back molded line are divided into 300-1000 point, take the midpoint of corresponding point then come arc in defining
Line.
3. the modeling method of rotor blade forging blade tip technique extended segment according to claim 1, it is characterised in that: in step
In four, if extension segment length be L, blade tip section up L/4, L/2, L distance calculate three middle camber lines.
4. the modeling method of rotor blade forging blade tip technique extended segment according to claim 1, it is characterised in that: in step
In six, fairing control errors are within 0.001.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112983558A (en) * | 2021-03-17 | 2021-06-18 | 中国航发动力股份有限公司 | Rotor blade precision forging piece structure and manufacturing method thereof |
| CN113255068A (en) * | 2020-02-13 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Modeling method of aero-engine blade blank and machining method of aero-engine blade |
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| CN113255068A (en) * | 2020-02-13 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Modeling method of aero-engine blade blank and machining method of aero-engine blade |
| CN113255068B (en) * | 2020-02-13 | 2022-10-11 | 中国航发商用航空发动机有限责任公司 | Modeling method of aero-engine blade blank and machining method of aero-engine blade |
| CN112983558A (en) * | 2021-03-17 | 2021-06-18 | 中国航发动力股份有限公司 | Rotor blade precision forging piece structure and manufacturing method thereof |
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