CN104392027B - A kind of parametric modeling method of turbo blade turbulence columns - Google Patents
A kind of parametric modeling method of turbo blade turbulence columns Download PDFInfo
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- CN104392027B CN104392027B CN201410627704.1A CN201410627704A CN104392027B CN 104392027 B CN104392027 B CN 104392027B CN 201410627704 A CN201410627704 A CN 201410627704A CN 104392027 B CN104392027 B CN 104392027B
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Abstract
The present invention proposes a kind of parametric modeling method of turbo blade turbulence columns, meridian is obtained by connecting the blade inner mold trailing edge center of circle, blade inner mold mean camber line and middle cambered surface are generated using two-tube Dow process, turbulence columns starting point is determined in middle cambered surface, reference plane perpendicular to Z axis is made by starting point, find reference plane and meridianal intersection point, and then along meridian so that intersection point is moved into given number of times to set a distance, a row are obtained along meridianal point, the reference plane a little done perpendicular to Z axis is crossed respectively, obtain the intersection collection of reference plane and middle cambered surface, above-mentioned all intersection points are moved once along each intersection with arc length L, obtain the first row turbulence columns center of circle, n times are moved into the first row turbulence columns center of circle along each intersection with arc length L ', one group of turbulence columns center of circle in distribution in cambered surface is just obtained.In this method every group of turbulence columns center of circle with etc. the equidistant mode of arc length be distributed in middle cambered surface, its position distribution on blade type face evenly, is preferably enhanced the flow-disturbing radiating inside blade.
Description
Technical field
The present invention relates to turbo blade turbulence columns parameterized Formative Design field.
Background technology
Blade of aviation engine is the critical component of aero-engine, with complicated, wide in variety, quantity it is big, to hair
The features such as motivation performance impact is big, to manufacture and design the cycle long.The design of blade, manufacturing technology level are to improving aero-engine
, the lead time can be shortened and cost is reduced and played an important role.
Domestic related personnel has carried out furtheing investigate extensively for blade of aviation engine formative method, and preliminary real
Turbo blade parameterization design method is showed.But existing blade shape construction system focuses primarily upon offer for blade blade type face
Modeling function and blade section line design function on, it is inner mold feature such as turbulence columns to the blade with cooling system, vertical
Also it is not many to the research of the Modeling Technologies such as rib, cross rib, this can not meet the blade design that becomes increasingly complex now
Need.
There is complicated inner chamber inside blade to radiate and cool down.Inner chamber includes turbulence columns, longitudinal rib, cross rib etc.
Structure.The labyrinth of blade inner chamber is all embodied onto blade inner mold in concavo-convex opposite mode, so the knot of inner mold part
Structure is extremely complex.It is inner mold type face respectively and turbulence columns, the knot after Boolean subtraction calculation is done in cross rib and this several part of longitudinal rib
Really.The design and moulding of turbulence columns, cross rib and longitudinal rib formations are a troublesome processes, extract their parametrization
Information will greatly improve their design efficiency, shorten the design cycle, and existing high-end CAD modeling softwares have turned into this and designed
The core of production procedure.In existing blade parameter moulding system, the foundation of turbulence columns characteristic model is to essential characteristic cylinder
It is packaged with array features etc., by setting up turbulence columns design rule, extracts design parameter such as body diameter, geometric parameter
Being realized such as array way etc..
Distribution mode of traditional turbulence columns in inner mold has following three kinds：
The central coordinate of circle of turbulence columns is provided by data file；
The distribution of the central coordinate of circle of turbulence columns is rectangular array；
The distribution of the central coordinate of circle of turbulence columns is complex array；
Above-mentioned turbulence columns be all with certain array way with the reference plane that plane is parallel near cambered surface in blade inner mold
Generation, when in the turbulence columns central projection in reference plane to blade type face, turbulence columns center on blade type face can be caused
Distribution is very uneven, is unfavorable for the flow-disturbing radiating of blade.
The content of the invention
The purpose of the present invention is to generate the problem of position is inaccurate for turbulence columns central coordinate of circle in the prior art, with CAD
Modeling software proposes a kind of new method of blade turbulence columns parametric modeling as platform.Justified by connecting blade inner mold trailing edge
Gains in depth of comprehension generate blade inner mold mean camber line to meridian using two-tube Dow process, and then obtain middle cambered surface, and flow-disturbing is determined in middle cambered surface
Post starting point, makees the reference plane perpendicular to Z axis by starting point, finds reference plane and meridianal intersection point, and then along meridian
So that intersection point is moved into given number of times to set a distance, a row are obtained along meridianal point, point does the benchmark perpendicular to Z axis excessively respectively
Face, obtains the intersection collection of reference plane and middle cambered surface, and above-mentioned all intersection points are moved once along each intersection with arc length L, obtains
The one row turbulence columns center of circle, moves n times with arc length L ' along each intersection by the first row turbulence columns center of circle, has just obtained one group in distribution
The turbulence columns center of circle in cambered surface.In the new method of this blade turbulence columns parametric modeling, every group of turbulence columns center of circle with etc. arc length
Equidistant mode is distributed in middle cambered surface, is made its position distribution on blade type face evenly, is preferably enhanced blade
Internal flow-disturbing radiating.
The technical scheme is that：
A kind of parametric modeling method of the turbo blade turbulence columns, it is characterised in that：Comprise the following steps：
Step 1：Meridian is obtained by connecting the blade inner mold trailing edge center of circle；
Step 2：Blade inner mold mean camber line is generated using two-tube Dow process, arc in blade inner mold is obtained by blade inner mold mean camber line
Face；
Step 3：Turbulence columns starting point is chosen in middle cambered surface, makes the direction that turbulence columns are generated positive along long-pending folded axle；
Step 4：Turbulence columns central coordinate of circle distributing position is determined, one of which turbulence columns central coordinate of circle is true using following steps
It is fixed：
Step 4.1：Cross the turbulence columns starting point that step 3 obtains and make reference plane perpendicular to blade coordinate system Z axis, hung down
The straight reference plane in blade coordinate system Z axis and meridianal intersection point P1；
Step 4.2：Intersection point P1 is moved N1 times along meridian according to given apart from D1, obtained along meridianal row point
Collect Gp1；
Step 4.3：The every bit crossed in the point set Gp1 that step 4.2 is obtained does the reference plane perpendicular to long-pending folded axle respectively, obtains
To corresponding to each point perpendicular to long-pending folded axle reference plane and middle cambered surface intersection；
Step 4.4：Every bit in point set Gp1 is moved once along each self-corresponding intersection according to given arc length L1,
Obtain the turbulence columns center of circle that first group of first row is distributed in middle cambered surface；
Step 4.5：By first group of first row be distributed in the turbulence columns center of circle in middle cambered surface along each self-corresponding intersection according to
Given arc length L1 ' is mobile several times, obtains first group of all turbulence columns center of circle being distributed in middle cambered surface；
Step 5：The every group of turbulence columns center of circle generated in middle cambered surface is moved along turbulence columns center line toward the direction away from blade
Dynamic equal distance, obtains the central coordinate of circle during generation of flow-disturbing cylinder；Central coordinate of circle and turbulence columns when being generated by flow-disturbing cylinder
Diameter, direction, cylinder stretching height obtain every group of turbulence columns.
Further preferred scheme, a kind of parametric modeling method of turbo blade turbulence columns, it is characterised in that：The
K group turbulence columns central coordinate of circle determination process is：
Step a：Intersection point P (k-1) is moved once along meridian according to setpoint distance, intersection point P (k) is obtained；
Step b：Intersection point P (k) is obtained along meridianal one along meridian according to given secondary apart from the mobile N (k) of D (k)
Row point set Gp (k)；
Step c：The every bit crossed in the point set Gp (k) that step b is obtained does the reference plane perpendicular to long-pending folded axle respectively, obtains
The intersection of the corresponding reference plane perpendicular to long-pending folded axle of each point and middle cambered surface；
Step d：By the every bit in point set Gp (k) along each self-corresponding intersection according to given arc length L (k) mobile one
It is secondary, obtain the turbulence columns center of circle that kth group first row is distributed in middle cambered surface；
Step e：Kth group first row is distributed in the turbulence columns center of circle in middle cambered surface along each self-corresponding intersection according to given
Arc length L (k) ' it is mobile several times, obtain all turbulence columns centers of circle of kth group being distributed in middle cambered surface.
Beneficial effect
The beneficial effects of the invention are as follows, in the new method of this blade turbulence columns parametric modeling, every group of turbulence columns center of circle
With etc. the equidistant mode of arc length be distributed in middle cambered surface, make its position distribution on blade type face evenly, meet enterprise
Industry demand, overcomes the deficiencies in the prior art, improves design efficiency and quality, and have very high flexibility, and we
Method is not limited the platform of three-dimensional software, can be with the method in multi software platform, with good versatility.
Brief description of the drawings
Fig. 1 is blade inner mold and meridian schematic diagram.
In figure, 1- blade inner mold；The meridian that the 2- connection blade inner mold trailing edges center of circle is obtained.
Fig. 2 is cambered surface schematic diagram in blade inner mold.
In figure, 3- mean camber lines；Cambered surface in 4-.
Fig. 3 is starting point schematic diagram.
In figure, 5- starting points.
Fig. 4 is the intersection schematic diagram of cambered surface and reference plane in blade inner mold.
In figure, 6- reference planes；7- intersections.
Fig. 5 is distribution schematic diagram of two groups of turbulence columns centers of circle in middle cambered surface.
In figure, first turbulence columns center of circle of first group of first row of 8-；First turbulence columns circle of second group of first row of 9-
The heart.
Fig. 6 is the turbulence columns schematic diagram generated in blade inner mold posterior border position.
Fig. 7 is that the blade inner mold schematic diagram after boolean's difference is made with turbulence columns.
Fig. 8 is blade inner mold and the result schematic diagram after blade profile boolean difference.
Embodiment
The present invention is described with reference to specific embodiment：
The present embodiment is by taking certain blade turbulence columns parameterized Formative Design process as an example, and CAD software design environment is UGNX7.5
Software.
Imported in UG NX7.5 softwares after blade inner mold, using following steps：
Step 1：The blade inner mold trailing edge section line center of circle is found, meridian is obtained by connecting the blade inner mold trailing edge center of circle,
Such as Fig. 1.
Step 2：Blade inner mold mean camber line is generated using two-tube Dow process, arc in blade inner mold is obtained by blade inner mold mean camber line
Face, such as Fig. 2.
Step 3：Turbulence columns starting point is chosen in middle cambered surface, the selection of starting point must cause the direction that turbulence columns are generated
Positive along long-pending folded axle, starting point determines starting altitude of the turbulence columns away from engine center plane, such as Fig. 3.
Step 4：Turbulence columns design parameter (direction of turbulence columns central axis and diameter) determine after it is necessary to determining its geometry
Parameter, i.e., the distributing position (having two groups of turbulence columns in the present embodiment) in the turbulence columns center of circle in middle cambered surface：
Step 4.1：Cross the turbulence columns starting point that step 3 obtains and make reference plane perpendicular to blade coordinate system Z axis, hung down
The straight reference plane in blade coordinate system Z axis and meridianal intersection point P1；
Step 4.2：Intersection point P1 is moved N1 times along meridian according to given apart from D1, obtained along meridianal row point
Collect Gp1；N1=8 in this example；
Step 4.3：The every bit crossed in the point set Gp1 that step 4.2 is obtained does the reference plane perpendicular to long-pending folded axle respectively, obtains
To corresponding to each point perpendicular to long-pending folded axle reference plane and middle cambered surface intersection, such as Fig. 4；
Step 4.4：Every bit in point set Gp1 is moved once along each self-corresponding intersection according to given arc length L1,
Obtain the turbulence columns center of circle that first group of first row is distributed in middle cambered surface；
Step 4.5：By first group of first row be distributed in the turbulence columns center of circle in middle cambered surface along each self-corresponding intersection according to
Given arc length L1 ' is mobile 2 times, obtains first group of all turbulence columns center of circle being distributed in middle cambered surface；
Step 4.6：Intersection point P1 is moved once along meridian according to D1/2 distance, intersection point P2 is obtained；
Step 4.7：Intersection point P2 is moved N2 times along meridian according to given apart from D2, obtained along meridianal another row
Point set Gp2；D1=D2 in the present embodiment, N1=N2；
Step 4.8：The every bit crossed in the point set Gp2 that step 4.7 is obtained does the reference plane perpendicular to long-pending folded axle respectively, obtains
To corresponding to each point perpendicular to long-pending folded axle reference plane and middle cambered surface intersection；
Step 4.9：Every bit in point set Gp2 is moved once along each self-corresponding intersection according to given arc length L2,
Obtain the turbulence columns center of circle that second group of first row is distributed in middle cambered surface；In the present embodiment, L2=2*L1；
Step 4.10：By second group of first row be distributed in the turbulence columns center of circle in middle cambered surface along each self-corresponding intersection according to
Given arc length L2 ' is mobile 2 times, obtains second group of all turbulence columns center of circle being distributed in middle cambered surface；L2 ' in the present embodiment=
L1’。
It is distribution of two groups of turbulence columns centers of circle in middle cambered surface as shown in Figure 5.
Step 5：The every group of turbulence columns center of circle generated in middle cambered surface is moved along turbulence columns center line toward the direction away from blade
Dynamic equal distance, obtains the central coordinate of circle during generation of flow-disturbing cylinder；Central coordinate of circle and turbulence columns when being generated by flow-disturbing cylinder
Diameter, direction, cylinder stretching height obtain every group of turbulence columns.The generation of turbulence columns is carried out in units of group, and every group is disturbed
The direction of fluidization tower and diameter can be different.If Fig. 6 is the flow-disturbing cylinder that blade inner mold rear edge part is generated；Fig. 7 is and turbulence columns
Body does the blade inner mold after boolean's difference；Fig. 8 blades external form and the result after blade inner mold boolean difference.
Claims (2)
1. a kind of parametric modeling method of turbo blade turbulence columns, it is characterised in that：Comprise the following steps：
Step 1：Meridian is obtained by connecting the blade inner mold trailing edge center of circle；
Step 2：Blade inner mold mean camber line is generated using two-tube Dow process, cambered surface in blade inner mold is obtained by blade inner mold mean camber line；
Step 3：Turbulence columns starting point is chosen in middle cambered surface, makes the direction that turbulence columns are generated positive along long-pending folded axle；
Step 4：Determine turbulence columns central coordinate of circle distributing position：
Step 4.1：Cross the turbulence columns starting point that step 3 obtains and make reference plane perpendicular to blade coordinate system Z axis, obtain perpendicular to
The reference plane of blade coordinate system Z axis and meridianal intersection point P1；
Step 4.2：Intersection point P1 is moved N1 times along meridian according to given apart from D1, obtained along meridianal row point set
Gp1；
Step 4.3：The every bit crossed in the point set Gp1 that step 4.2 is obtained does the reference plane perpendicular to long-pending folded axle respectively, obtains each
The intersection of the corresponding reference plane perpendicular to long-pending folded axle of point and middle cambered surface；
Step 4.4：Every bit in point set Gp1 is moved once along each self-corresponding intersection according to given arc length L1, obtained
First group of first row is distributed in the turbulence columns center of circle in middle cambered surface；
Step 4.5：First group of first row is distributed in the turbulence columns center of circle in middle cambered surface along each self-corresponding intersection according to given
Arc length L1 ' it is mobile several times, obtain first group of all turbulence columns center of circle being distributed in middle cambered surface；
Step 5：By the every group of turbulence columns center of circle generated in middle cambered surface along turbulence columns center line toward the direction mobile phase away from blade
Deng distance, obtain flow-disturbing cylinder generation when central coordinate of circle；Central coordinate of circle and turbulence columns when being generated by flow-disturbing cylinder it is straight
Footpath, direction, cylinder stretching height obtain every group of turbulence columns.
2. a kind of parametric modeling method of turbo blade turbulence columns according to claim 1, it is characterised in that：Kth group is disturbed
Fluidization tower central coordinate of circle determination process is：
Step a：Intersection point P (k-1) is moved once along meridian according to setpoint distance, intersection point P (k) is obtained；
Step b：Intersection point P (k) is obtained along meridianal row point along meridian according to given secondary apart from the mobile N (k) of D (k)
Collect Gp (k)；
Step c：The every bit crossed in the point set Gp (k) that step b is obtained does the reference plane perpendicular to long-pending folded axle respectively, obtains each point
The intersection of the corresponding reference plane perpendicular to long-pending folded axle and middle cambered surface；
Step d：Every bit in point set Gp (k) is mobile once according to given arc length L (k) along each self-corresponding intersection, obtain
The turbulence columns center of circle in middle cambered surface is distributed in kth group first row；
Step e：Kth group first row is distributed in the turbulence columns center of circle in middle cambered surface along each self-corresponding intersection according to given arc
Long L (k) ' is mobile several times, obtains all turbulence columns centers of circle of kth group being distributed in middle cambered surface.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410627704.1A CN104392027B (en) | 2014-11-10 | 2014-11-10 | A kind of parametric modeling method of turbo blade turbulence columns |
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| CN201410627704.1A CN104392027B (en) | 2014-11-10 | 2014-11-10 | A kind of parametric modeling method of turbo blade turbulence columns |
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| CN104392027B true CN104392027B (en) | 2017-07-28 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104881540B (en) * | 2015-05-27 | 2018-04-10 | 西北工业大学 | A kind of turbine air cooling accurate wall thickness control modeling method of blade and blade body inner mold |
| CN107060890B (en) * | 2017-05-25 | 2019-01-25 | 北京航空航天大学 | A kind of parametric modeling method of turbo blade conjugate heat transfer computational domain geometrical model |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201474728U (en) * | 2009-08-31 | 2010-05-19 | 中国航空动力机械研究所 | Turbo cooling blade |
| EP1961917A3 (en) * | 2007-02-21 | 2011-12-21 | United Technologies Corporation | Local indented trailing edge heat transfer devices |
| CN102637233A (en) * | 2012-04-17 | 2012-08-15 | 西北工业大学 | Parameterization modeling method for turbine blade root extension segment profile |
| CN203584470U (en) * | 2013-11-28 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Staggered spoiler column end surface structure and turbine air-cooling blade |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7712316B2 (en) * | 2007-01-09 | 2010-05-11 | United Technologies Corporation | Turbine blade with reverse cooling air film hole direction |
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2014
- 2014-11-10 CN CN201410627704.1A patent/CN104392027B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1961917A3 (en) * | 2007-02-21 | 2011-12-21 | United Technologies Corporation | Local indented trailing edge heat transfer devices |
| CN201474728U (en) * | 2009-08-31 | 2010-05-19 | 中国航空动力机械研究所 | Turbo cooling blade |
| CN102637233A (en) * | 2012-04-17 | 2012-08-15 | 西北工业大学 | Parameterization modeling method for turbine blade root extension segment profile |
| CN203584470U (en) * | 2013-11-28 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Staggered spoiler column end surface structure and turbine air-cooling blade |
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