CN108133067A - The computation model processing method of blisk - Google Patents
The computation model processing method of blisk Download PDFInfo
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- CN108133067A CN108133067A CN201611090314.0A CN201611090314A CN108133067A CN 108133067 A CN108133067 A CN 108133067A CN 201611090314 A CN201611090314 A CN 201611090314A CN 108133067 A CN108133067 A CN 108133067A
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- blisk
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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
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
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- Evolutionary Computation (AREA)
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Abstract
The present invention relates to a kind of computation model processing methods of blisk,This method establishes the first cut surface according to the first cutting line determined on disk body,And the second cut surface is established according to the second cutting line drawn on disk edge,Then the first cut surface and the second cut surface split are formed into the first integral cutting face,The second integral cutting face is determined therefrom that again,Finally cut along the first integral cutting face and the second integral cutting in face of the geometrical model of blisk,Obtained computation model includes the blade of target bolt hole and predetermined number,Contain the characteristic of blisk,Bolt hole or blade are carried out for simplified computation model in compared with the prior art,Simplification is reduced using the obtained computation model of processing method of the present invention,The stress of bolt hole and the stress of blade can be calculated simultaneously,And computational accuracy higher.
Description
Technical field
The present invention relates to aero-engine technology field more particularly to a kind of computation model processing methods of blisk.
Background technology
Blisk is a kind of new structure component of aero-engine, is that the working-blade of rotation and rotor hub is straight
A kind of structure type being connected as one is connect, it, can since the structure eliminates the tenon, tongue-and-groove and locking device of connection
To reduce construction weight and number of parts, tenon windage loss can also be avoided, is avoided micro- between blade, wheel disc mechanical connection
Accidental damage of dynamic abrasion, microfissure and mechanical fastener etc. makes the working efficiency of engine, thrust-weight ratio, working life
It is further improved with security reliability, therefore blisk is widely used now.
The precise intensity calculated relationship of blisk the success or not of aero-engine strength test, service life direct shadow
Ring the service life of entire aero-engine.The blisk of bolt hole is carried at present, in the intensity for calculating bolt hole, often to leaf
Piece carries out simplifying processing；In the intensity for calculating blade, often bolt hole is simplified, therefore cannot be simulated very accurately true
The stressing conditions of real blisk.
It should be noted that the information for being disclosed in background of invention part is merely intended to increase the totality to the present invention
The understanding of background, and be not construed as recognizing or imply in any form the information form by those skilled in the art public affairs
The prior art known.
Invention content
The purpose of the present invention is to propose to a kind of computation model processing methods of blisk, and essence is calculated to improve as much as possible
Degree.
To achieve the above object, the present invention provides a kind of computation model processing method of blisk, including：
The geometrical model of blisk is provided, the geometrical model of the blisk includes disk body and disk edge, the disk body
Equipped with multiple bolts hole, the side at geometrical model center of the disk edge far from the blisk is equipped with multiple blades；
Selection target bolt hole determines the first cutting line, so according to the position of the target bolt hole on the disk body
Afterwards the first cut surface is established along first cutting line；
The second cutting line is drawn on the disk edge, then establishes the second cut surface along second cutting line；
By first cut surface and the second cut surface split, the first integral cutting face is formed；
Second integral cutting face is determined according to the first integral cutting face so that the first integral cutting face and described
Part between second integral cutting face can include the blade of the target bolt hole and predetermined number；
It is carried out along the first integral cutting face and second integral cutting in face of the geometrical model of the blisk
Cutting, obtains the geometrical model of cut length, using the computation model as the blisk.
Further, it is further included before the operation of selection target bolt hole：
Determine predetermined angle θ；
According to the position of the target bolt hole, the concrete operations of determining first cutting line are on the disk body：
Along the target bolt hole central point and the disk body central point between line to first direction rotate institute
Predetermined angle θ is stated, determines the first cutting line.
Further, the concrete operations of the determining predetermined angle θ are：
If the total number of the bolt hole is n, the predetermined angle θ is calculated according to the following formula：
θ=180 °/n.
Further, after selection target bolt hole, and according to the position of the target bolt hole in the disk
Before determining the first cutting line on body, further include：
Centered on the target bolt hole, establish corresponding with cutting segment model with reference to fan-shaped section, the reference sector
The angle of section is 2 θ.
Further, it is also wrapped before the operation that the second integral cutting face is determined according to the first integral cutting face
It includes：
According to the total number n of the bolt hole and the total number m of the blade, default of blade in computation model is determined
Number p, wherein：If N-1<M/n≤N, N are natural number, then p=N.
Further, the second integral cutting face is determined according to the first integral cutting face so that first entirety is cut
Part between face and the second integral cutting face can include the blade of the target bolt hole and predetermined number
Concrete operations be：
By first integral cutting towards 2 θ of second direction rotation angle, the second integral cutting face is formed so that described
Part between first integral cutting face and the second integral cutting face includes the target bolt hole and predetermined number just
The blade.
Further, second cutting line is straight line, between second cutting line and the leading edge intersection point of the blade
Distance be 1~3mm；And/or the distance between second cutting line and the rear intersection point of the blade are 1~3mm.
Further, the distance between second cutting line and the leading edge intersection point of the blade are 2mm, and described second cuts
The distance between secant and the rear intersection point of the blade are 2mm.
Further, after the first cut surface is established along first cutting line, and is drawn on the disk edge
Before two cutting lines, further include：
Determine the height of first cut surface, the geometrical model of the blisk further includes so that the disk body is to institute
The laryngeal structure of disk edge transition is stated, the line of demarcation between first cut surface and second cut surface is located at throat knot
On structure.
Further, in the line of demarcation between first cut surface and second cut surface and the blisk
The distance between heart is 170~190mm.
Based on above-mentioned technical proposal, the present invention establishes the first cut surface according to the first cutting line determined on disk body, and
The second cutting line according to being drawn on disk edge establishes the second cut surface, then by the first cut surface and the second cut surface split shape
Into the first integral cutting face, then the second integral cutting face is determined therefrom that, finally along the first integral cutting face and the second integral cutting
Geometrical model in face of blisk is cut, and obtained computation model includes the leaf of target bolt hole and predetermined number
Piece contains the characteristic of blisk, compared with the prior art in simplified calculating mould is carried out to bolt hole or blade
For type, simplification is reduced using the obtained computation model of processing method of the present invention, the stress of bolt hole can be calculated simultaneously
With the stress of blade, and computational accuracy higher.
Description of the drawings
Attached drawing described herein is used to provide further understanding of the present invention, and forms the part of the application, this hair
Bright illustrative embodiments and their description do not constitute improper limitations of the present invention for explaining the present invention.In the accompanying drawings：
Fig. 1 is the flow chart of computation model processing method one embodiment of blisk of the present invention.
Fig. 2 is the flow chart of another embodiment of the computation model processing method of blisk of the present invention.
Fig. 3 is the several of the blisk employed in computation model processing method one embodiment of blisk of the present invention
The structure diagram of what model.
Schematic diagrames of the Fig. 4 for the first cutting line in computation model processing method one embodiment of blisk of the present invention.
Schematic diagrames of the Fig. 5 for the first cut surface in computation model processing method one embodiment of blisk of the present invention.
Fig. 6 for drawn on disk edge in computation model processing method one embodiment of blisk of the present invention second
The schematic diagram of cutting line.
Fig. 7 is the first integral cutting formed in computation model processing method one embodiment of blisk of the present invention
The schematic diagram in face.
Knots of the Fig. 8 for obtained computation model in computation model processing method one embodiment of blisk of the present invention
Structure schematic diagram.
In figure：The geometrical model of 1- blisks, 2- disk bodies, 3- disk edge, 4- laryngeal structures, 5- blades, 6- bolts hole, 7-
First cutting line, the first cut surfaces of 8-, the second cutting lines of 9-, the first integral cuttings of 10- face, 11- computation models.
Specific embodiment
Below in conjunction with the attached drawing in the embodiment of the present invention, the technical solution in embodiment is clearly and completely retouched
It states.Obviously, described embodiment is only the part of the embodiment of the present invention, instead of all the embodiments.Based on this hair
Bright embodiment, the every other implementation that those of ordinary skill in the art are obtained without making creative work
Example, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that term " " center ", " transverse direction ", " longitudinal direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " on ", " under ", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " are
Based on orientation shown in the drawings or position relationship, it is for only for ease of the description present invention and simplifies description rather than instruction or dark
Show that signified device or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that right
The limitation of the scope of the present invention.
As shown in Figure 1, the stream of computation model processing method one embodiment for a kind of blisk provided by the invention
Cheng Tu, with reference to 3~Fig. 8 of figure, which includes：
The geometrical model 1 of blisk is provided, the geometrical model 1 of blisk includes disk body 2 and disk edge 3, and disk body 2 is equipped with
Multiple bolts hole 6, the side at geometrical model 1 center of the disk edge 3 far from blisk are equipped with multiple blades 5；
Selection target bolt hole determines the first cutting line 7, then along the according to the position of target bolt hole on disk body 2
One cutting line 7 establishes the first cut surface 8；
The second cutting line 9 is drawn on disk edge 3, then establishes the second cut surface along the second cutting line 9；
By the first cut surface 8 and the second cut surface split, the first integral cutting face 10 is formed；
Second integral cutting face is determined according to the first integral cutting face 10 so that the first integral cutting face 10 and second is whole
Part between cut surface can include the blade 5 of target bolt hole and predetermined number, which should be intact leaf；
It is cut, is obtained in face of the geometrical model 1 of blisk along the first integral cutting face 10 and the second integral cutting
The geometrical model of cut length, with the computation model 11 of leaf dish as a whole.
In this embodiment, the first cut surface 8 is established, and according in disk according to the first cutting line 7 determined on disk body 2
The second cutting line 9 drawn on edge 3 establishes the second cut surface, and the first cut surface 8 and the second cut surface split then are formed the
One integral cutting face 10, then determine therefrom that the second integral cutting face, finally along the first integral cutting face 10 and the second integral cutting
Geometrical model 1 in face of blisk is cut, and obtained computation model includes target bolt hole and predetermined number
Blade 5 contains the characteristic of blisk, compared with the prior art in simplified calculating is carried out to bolt hole or blade
For model, simplification is reduced using the obtained computation model of processing method in the embodiment, bolt hole can be calculated simultaneously
Stress and blade stress, and computational accuracy higher.
In an embodiment as illustrated in figure 2, it is further included before the operation of selection target bolt hole：
Determine predetermined angle θ；
According to the position of target bolt hole, the concrete operations of determining first cutting line 7 are on disk body 2：
Along target bolt hole central point and disk body 2 central point between line to first direction rotate predetermined angle θ,
Determine the first cutting line 7.Wherein, first direction can be clockwise, can also counterclockwise, as shown in figure 4, first
Direction is clockwise.
Specifically, the first cutting line 7 can be along the radial direction of disk body 2, the central point of the first cutting line 7 and target bolt hole
The angle between line between the central point of disk body 2 is predetermined angle θ.
The concrete operations for determining predetermined angle θ are：If the total number of bolt hole 6 is n, preset angle is calculated according to the following formula
Spend θ：
θ=180 °/n.
Certainly, the method for determining predetermined angle θ in addition to the above method, can also have other modes, such as can be direct
Measure the angle between two neighboring bolt hole, which can be used as predetermined angle θ, predetermined angle θ can also be slightly larger than or
Person is slightly smaller than the angle.
The first cutting is determined on disk body 2 after selection target bolt hole, and in the position according to target bolt hole
Before line 7, it can also include：
Centered on target bolt hole, foundation is corresponding with cutting segment model with reference to fan-shaped section, with reference to the angle of fan-shaped section
For 2 θ.This, can be when determining the first cutting line 7 to will cut with reference to the cutting fan-shaped section that fan-shaped section is virtual disk body 2
The computation model cut provides a macroscopical concept shape.
Further, it is further included before the operation that the second integral cutting face is determined according to the first integral cutting face 10：
According to the total number n of bolt hole 6 and the total number m of blade 5, the predetermined number p of blade 5 in computation model is determined,
Wherein：If N-1<M/n≤N, N are natural number, then p=N.
In a preferred embodiment, the second integral cutting face is determined according to the first integral cutting face 10 so that first
Part between 10 and second integral cutting face of integral cutting face can include the tool of the blade 5 of target bolt hole and predetermined number
Gymnastics conduct：
By the first integral cutting face 10 to 2 θ of second direction rotation angle, the second integral cutting face is formed so that first is whole
Part between 10 and second integral cutting face of body cut surface includes the blade 5 of target bolt hole and predetermined number just.Wherein,
Second direction be with first party in the opposite direction.
In this preferred embodiment, the second selected integral cutting face is by 10 rotation angle of the first integral cutting face, 2 θ
It obtains, and the second integral cutting face obtained in this way just disclosure satisfy that the blade 5 including target bolt hole and predetermined number
Requirement.
Certainly, above-mentioned preferred embodiment is a kind of special choosing method, in other embodiments, can also be used
Other methods determine the position in the second integral cutting face, it is only necessary to ensure the first integral cutting face 10 and the second integral cutting
Part between face can include the blade 5 of target bolt hole and predetermined number.
About the method for drafting of the second cutting line 9, a preferred embodiment is provided here：Second cutting line 9 is straight line,
The distance between second cutting line 9 and the leading edge intersection point of blade 5 are 1~3mm；And/or second cutting line 9 and blade 5 rear
The distance between intersection point is 1~3mm.
Wherein, leading edge intersection point refers to the intersection point of pressure face leading edge portion and suction surface leading edge portion at 5 tip of blade, after
Edge intersection point refers to the intersection point of pressure face rear edge part and suction surface rear edge part at 5 tip of blade, and leading edge intersection point and rear are handed over
Point is two endpoints of 5 mean camber line of blade.
Preferably, the distance between the second cutting line 9 and the leading edge intersection point of blade 5 are 2mm, the second cutting line 9 and blade 5
The distance between rear intersection point be 2mm.
In addition, due between 5 numbers of blade and bolt hole number not just into the limitation of integral multiple, on disk edge 3
Two cutting line 9 is possibly can not be with the first cutting line 7 on disk body 2 on same straight line, it is therefore desirable to consider the first cut surface 8
And second the problem of how being demarcated between cut surface, i.e. how the height of the first cut surface 8 determines.
As an illustrative examples, after the first cut surface 8 is established along the first cutting line 7, and on disk edge 3
Before drawing the second cutting line 9, it can also include：
Determine the height of the first cut surface 8, the geometrical model 1 of blisk, which further includes, causes disk body 2 to 3 transition of disk edge
Laryngeal structure 4, the line of demarcation between the first cut surface 8 and the second cut surface are located on laryngeal structure 4.
Wherein, the height of the first cut surface 8 can be understood as between the edge line of 2 central point of disk body and the first cut surface 8
Distance, i.e., with reference to the radius size of fan-shaped section.
The stress that laryngeal structure 4 is subject to is smaller, therefore line options of demarcating can make calculating as much as possible at laryngeal structure 4
Model is close to blisk, influence caused by when reducing due to line of demarcation and carrying out Stress calculation blisk.
Preferably, the distance between the line of demarcation between the first cut surface 8 and the second cut surface and the center of blisk
For 170~190mm.
In above each embodiment, the explanation that is carried out so that target bolt hole includes one as an example, in other embodiments,
According to practical calculating needs, two or more bolts hole can also be included in computation model.
With reference to operations of Fig. 3~Fig. 8 to one embodiment of the computation model processing method of blisk of the present invention
Flow illustrates：
First, the full geometry structural model of certain h type engine h grade disk is opened, as shown in figure 3, the blisk is equipped with
28 bolts hole 6, the number of blade 5 is 49；
The angle of reference fan-shaped section for needing to cut is calculated, for example the angle with reference to fan-shaped section can be 360 °/28=
It 12.857 °, since the number of blade is more than bolt hole count and less than twice of bolt hole count, selectes each fan-shaped section and includes two
A blade 5；
As shown in figure 4, fan-shaped section is established centered on some bolt hole, along in the central point of the bolt hole and disk body 2
The line of heart point rotates 180 °/28=6.429 °, determines the first cutting line 7, and establish the first cut surface along the first cutting line 7
8, as shown in Figure 5；
The height (line of demarcation) of first cut surface 8 is selected as possible far from bolt hole, and is selected in stress value region on the lower side,
For example throat in blisk can be selected, away from 2 central point 180mm of disk body；
As shown in fig. 6, two blades 5 are selected above bolt hole, apart from the position of wheel rim pre-determined distance in the drafting of disk edge 3
It puts and draws the second cutting line 9, for example, the second cutting line 9 is straight line, it is 2mm with leading edge intersection point distance, with rear intersection point distance
For 2mm；
The second cutting line 9 on disk edge 3 and line of demarcation are generated into the second cut surface, which is curved surface；
As shown in fig. 7, the first cut surface 8 and the second cut surface split are formed into the first integral cutting face 10；
First integral cutting face 10 is rotated 12.857 °, obtains the second integral cutting face；
As shown in figure 8, being cut along the first integral cutting face 10 and the second integral cutting face, cut length geometrical model is obtained,
The computation model 11 of leaf dish as a whole.
Pass through the explanation of multiple embodiments of the computation model processing method to blisk of the present invention, it can be seen that this hair
The computation model processing method of bright blisk can be adapted for the computation model processing of the blisk with bolt hole, energy
Enough solve the problems, such as number of bolt hole and the inconsistent model treatment of blade quantity；The computation model obtained using the processing method can
With the intact leaf simultaneously comprising bolt hole and predetermined number, the stress of bolt hole stress and blade can be calculated simultaneously, is reduced
Simplify, be conducive to improve computational accuracy.
Finally it should be noted that：The above embodiments are merely illustrative of the technical scheme of the present invention and are not intended to be limiting thereof；To the greatest extent
The present invention is described in detail with reference to preferred embodiments for pipe, those of ordinary skills in the art should understand that：Still
It can modify to the specific embodiment of the present invention or equivalent replacement is carried out to some technical characteristics；Without departing from this hair
The spirit of bright technical solution should all cover in the claimed technical solution range of the present invention.
Claims (10)
1. a kind of computation model processing method of blisk, which is characterized in that including：
The geometrical model (1) of blisk is provided, the geometrical model (1) of the blisk includes disk body (2) and disk edge (3),
The disk body (2) is equipped with multiple bolts hole (6), and the one of geometrical model (1) center of the disk edge (3) far from the blisk
Side is equipped with multiple blades (5)；
Selection target bolt hole determines the first cutting line (7) according to the position of the target bolt hole on the disk body (2),
Then the first cut surface (8) is established along first cutting line (7)；
The second cutting line (9) is drawn on the disk edge (3), then establishes the second cut surface along second cutting line (9)；
By first cut surface (8) and the second cut surface split, the first integral cutting face (10) is formed；
Second integral cutting face is determined according to the first integral cutting face (10) so that the first integral cutting face (10) and
Part between the second integral cutting face can include the blade (5) of the target bolt hole and predetermined number；
Along the first integral cutting face (10) and second integral cutting in face of the blisk geometrical model (1) into
Row cutting, obtains the geometrical model of cut length, using the computation model (11) as the blisk.
2. the computation model processing method of blisk according to claim 1, which is characterized in that in selection target bolt
It is further included before the operation in hole：
Determine predetermined angle θ；
According to the position of the target bolt hole, the concrete operations of determining first cutting line (7) are on the disk body (2)：
Along the target bolt hole central point and the disk body (2) central point between line to first direction rotation described in
Predetermined angle θ determines the first cutting line (7).
3. the computation model processing method of blisk according to claim 2, which is characterized in that the determining preset angle
Degree θ concrete operations be：
If the total number of the bolt hole (6) is n, the predetermined angle θ is calculated according to the following formula：
θ=180 °/n.
4. the computation model processing method of blisk according to claim 2, which is characterized in that in selection target bolt
After hole, and before the position according to the target bolt hole determines the first cutting line (7) on the disk body (2), also
Including：
Centered on the target bolt hole, establish it is corresponding with cutting segment model refer to fan-shaped section, it is described with reference to fan-shaped section
Angle is 2 θ.
5. the computation model processing method of blisk according to claim 1, which is characterized in that described according to described
One integral cutting face (10) determines to further include before the operation in the second integral cutting face：
According to the total number n of the bolt hole (6) and the total number m of the blade (5), blade in computation model (11) is determined
(5) predetermined number p, wherein：If N-1<M/n≤N, N are natural number, then p=N.
6. the computation model processing method of blisk according to claim 2, which is characterized in that whole according to described first
Body cut surface (10) determines the second integral cutting face so that the first integral cutting face (10) and the second integral cutting face
Between the part concrete operations of the blade (5) that can include the target bolt hole and predetermined number be：
By the first integral cutting face (10) to 2 θ of second direction rotation angle, the second integral cutting face is formed so that described
Part between first integral cutting face (10) and the second integral cutting face includes the target bolt hole and presets just
The blade (5) of number.
7. the computation model processing method of blisk according to claim 1, which is characterized in that second cutting line
(9) it is straight line, the distance between second cutting line (9) and the leading edge intersection point of the blade (5) are 1~3mm；And/or institute
The distance between the second cutting line (9) and the rear intersection point of the blade (5) are stated as 1~3mm.
8. the computation model processing method of blisk according to claim 7, which is characterized in that second cutting line
(9) be 2mm with the distance between the leading edge intersection point of the blade (5), second cutting line (9) with after the blade (5)
The distance between edge intersection point is 2mm.
9. the computation model processing method of blisk according to claim 1, which is characterized in that cut along described first
Secant (7) is established after the first cut surface (8), and before drawing the second cutting line (9) on the disk edge (3), is further included：
Determine the height of first cut surface (8), the geometrical model (1) of the blisk is further included so that the disk body
(2) to the laryngeal structure (4) of disk edge (3) transition, the boundary between first cut surface (8) and second cut surface
Line is located on the laryngeal structure (4).
10. the computation model processing method of blisk according to claim 9, which is characterized in that first cutting
The distance between center in line of demarcation and the blisk between face (8) and second cut surface is 170~190mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611090314.0A CN108133067A (en) | 2016-11-30 | 2016-11-30 | The computation model processing method of blisk |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611090314.0A CN108133067A (en) | 2016-11-30 | 2016-11-30 | The computation model processing method of blisk |
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| CN201611090314.0A Pending CN108133067A (en) | 2016-11-30 | 2016-11-30 | The computation model processing method of blisk |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109002651A (en) * | 2018-08-22 | 2018-12-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | The fly-cutting faceted search method decomposed for parallel numerical simulating area |
| CN109614739A (en) * | 2018-12-24 | 2019-04-12 | 成都安世亚太科技有限公司 | A kind of novel nonlinear contact processing method for shrouded blade |
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| CN105550464A (en) * | 2016-01-07 | 2016-05-04 | 燕山大学 | New submodel finite element analysis method based on cutting boundary deformation constraint |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109002651A (en) * | 2018-08-22 | 2018-12-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | The fly-cutting faceted search method decomposed for parallel numerical simulating area |
| CN109002651B (en) * | 2018-08-22 | 2019-04-09 | 中国空气动力研究与发展中心超高速空气动力研究所 | The fly-cutting faceted search method decomposed for parallel numerical simulating area |
| CN109614739A (en) * | 2018-12-24 | 2019-04-12 | 成都安世亚太科技有限公司 | A kind of novel nonlinear contact processing method for shrouded blade |
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