CN109614739A - A kind of novel nonlinear contact processing method for shrouded blade - Google Patents
A kind of novel nonlinear contact processing method for shrouded blade Download PDFInfo
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- CN109614739A CN109614739A CN201811585919.6A CN201811585919A CN109614739A CN 109614739 A CN109614739 A CN 109614739A CN 201811585919 A CN201811585919 A CN 201811585919A CN 109614739 A CN109614739 A CN 109614739A
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- shrouded blade
- blade
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- shrouded
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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
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/06—Power analysis or power optimisation
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- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Computational Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a kind of novel nonlinear contact processing methods for shrouded blade, this method root shrouded blade replicates a shrouded blade, the first cut surface is determined according to shrouded blade model integral shroud interstitial site, and it is replicated to obtain the second cut surface according to the first cut surface, then original tape shroud blade is cut using the first cut surface, the shrouded blade for replicating obtained the second cut surface cutting duplication, finally obtains the model comprising integral shroud gap.Model partition grid merges a part of node being in contact in grid node in the bottom cribbing point of position node selection gap site.The processing method calculates cost and substantially reduces, model can be used for fluid structurecoupling flutter analysis compared to nonlinear contact model.
Description
Technical field
The present invention relates to rotating machinery blade vibration analysis fields, and in particular to a kind of novel for the non-of shrouded blade
Linear contact processing method.
Background technique
In turbomachinery Bladed disk, the operating condition of blade is more and more severe, and blade may be because the period of air-flow
Property disturbance and be abnormal vibration, or high all or low-cycle fatigue occurs because bearing resonant stress and fails.It can lead to when design
Blade frequency modulation is crossed to avoid resonant frequency, but after certain working cycles, blade frequencies may be reduced, and fall into resonance
Area causes blade cracked, blade arrisdefect, or even is broken.And the damping for increasing blade can inhibit the vibration of blade,
Reduce blade dynamic stress.The mode of blade damping can be generated in addition to material damping, there are also at mid-span shroud, platform and lacing wire
Dry-friction damping.Time of the vibration attenuation mechanism of integral shroud pre- twisted blade when being exactly the initial assembly force and turbine rotation between utilizing integral shroud
Torsion makes to obtain normal pressure appropriate between integral shroud, and blade is by vibration is generated when gas shock, so that integral shroud contact surface be made to generate phase
To sliding, vibrational energy is consumed to reduce the amplitude of vibration by frictional force, and since the contact between integral shroud changes blade
System stiffness achievees the purpose that vibration damping and the resonance point that averts danger so that the resonant frequency to blade is adjusted.Crown structure
Design parameter mainly have contact area and contact angle etc., relatively common blade shroud structure has at present: parallel integral shroud, saw
Tooth form integral shroud, concave-convex integral shroud etc..Damping vane with hat structure, which can be effectively reduced dynamic stress and play frequency modulation to blade, to be made
With, theoretically, mainly since the contact between hat and hat produces structural damping, such as frictional damping and collisional damping,
The vibratory response of blade system is decayed quickly.But the vibration that blade with tips generates under Airflow Exciting-Vibration Force effect
Characteristic is originally sufficiently complex, along between hat and hat contact movement it is non-linear so that entire blade damping system at
For complicated nonlinear dynamic system, therefore, no matter from theoretical method or experimentally the vibration of shrouded blade is studied
Characteristic all has very big difficulty.Especially when scale of model continues to increase, the workload for calculating Non-Linear Vibration will be extremely huge
Greatly.It is necessary that Rational Simplification is carried out to model when especially carrying out flutter analysis to shrouded blade.Simplified model should guarantee
The precision of FEM modal analysis and modal, Controlling model scale is able to bear in range in design conditions again.
Summary of the invention
It is an object of the invention to overcome the above-mentioned prior art, propose that a kind of novel band that is directed to is preced in engineering
The nonlinear contact processing method of blade.
In order to achieve the above objectives, the present invention is achieved by the following scheme:
A kind of novel nonlinear contact processing method for shrouded blade, comprising the following steps:
Step 1: providing shrouded blade geometrical model, the geometrical model of the shrouded blade includes integral shroud and blade.
Step 2: according to shrouded blade, duplication obtains shrouded blade, cut surface is constructed according to shrouded blade, according to cut surface
Duplication obtains cut surface
Step 3: cutting shrouded blade along cut surface, along the shrouded blade of the cut surface cutting duplication of duplication, cutting is obtained
Shrouded blade model as grid dividing model.
Step 4: model meshes divide, and obtain integral shroud gap site Local grid node, determine integral shroud gap-contact position
Grid node chooses a bottom cribbing point in grid node, merges part of node, obtained grid model is as meter
Calculate model.
The medicine have the advantages that
1, the present invention is handled for the nonlinear contact of shrouded blade, and the Three-dimensional CAD being simplified can be fast
Mode is calculated in speed, calculates for later period flutter and vibration stress.
2, when carrying out the FLUTTER CALCULATION of full threedimensional model, non-linear factor is eliminated, model can be greatly simplified, improves and calculates
Efficiency will flow solid coupling FLUTTER CALCULATION and be used for industrial calculating, compared with Accurate Prediction Flutter Problem.
3, the method balances computational efficiency and computational accuracy problem.
Detailed description of the invention
Fig. 1 is the flow chart of one embodiment of the invention
Fig. 2 is the structural schematic diagram of shrouded blade geometrical model employed in the embodiment of the present invention
Fig. 3 is the geometrical model structural schematic diagram that duplication shrouded blade and duplication cut surface obtain in the embodiment of the present invention
Fig. 4 is the geometrical model structural schematic diagram obtained after cut surface cutting in the embodiment of the present invention
Fig. 5 is integral shroud gap site Local grid node in the embodiment of the present invention
Fig. 6 is integral shroud gap-contact position grid node in the embodiment of the present invention
In figure: 1- shrouded blade geometrical model, 2- integral shroud, 3- blade, the shrouded blade that 4- is replicated, 5- cut surface,
The cut surface that 6- is replicated, the shrouded blade model that 7- is cut, 8- integral shroud gap site Local grid node, 9- integral shroud
Gap-contact position grid node
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, is clearly and completely retouched to the technical solution in embodiment
It states.Obviously, described embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.
As shown in Figure 1, a kind of one reality of nonlinear contact processing method of novel pin provided by the invention to shrouded blade
The flow chart for applying example, with reference to Fig. 2~Fig. 6, this method comprises:
Shrouded blade geometrical model 1 is provided, the geometrical model 1 of the shrouded blade includes integral shroud 2 and blade 3.
According to shrouded blade 1, duplication obtains shrouded blade 4, cut surface 5 is constructed according to shrouded blade 1, according to cut surface 5
Duplication obtains cut surface 6；
Shrouded blade 1 is cut along cut surface 5, cuts shrouded blade 4, the shrouded blade model 7 cut along cut surface 6
As grid dividing model；
Model meshes divide, and obtain integral shroud gap site Local grid node 8, determine integral shroud gap-contact position grid section
Point 9；
A bottom cribbing point is chosen in 9 section view of grid node, merges part of node, obtained grid model
As computation model.
According to Fig. 1 the embodiment described, when constructing cut surface 5 according to shrouded blade 1, constructed cut surface should be as far as possible
Blade 3 is avoided, across the center line of integral shroud 2 and shrouded blade 1, and it is moderate with 2 Edge Distance of integral shroud.
According to Fig. 1 the embodiment described, before replicating shrouded blade 1 further include:
Determine predetermined angle θ；
According to shrouded blade 1, duplication obtains the concrete operations of shrouded blade 4 are as follows:
The predetermined angle θ is selected along 1 central axial direction of shrouded blade, duplication obtains shrouded blade 4.
The concrete operations of the determining predetermined angle θ are as follows:
If the sum that the shrouded blade 1 one encloses is n, the predetermined angle θ is calculated according to following formula:
θ=360 °/n.
According to Fig. 1 the embodiment described, before replicating cut surface 5 further include:
Determine predetermined angle β；
According to cut surface 5, duplication obtains the concrete operations with cut surface 6 are as follows:
Centerline direction along the cut surface 5 and shrouded blade 1 selects the predetermined angle β, and duplication obtains cut surface
6。
The concrete operations of the determining predetermined angle β are as follows:
If the sum that the shrouded blade 1 one encloses is n, the predetermined angle β is calculated according to following formula:
β=360 °/n.
According to Fig. 1 the embodiment described, a bottom cribbing point, the number of node are chosen in 9 section view of grid node
For N, merge part of node, interstitial content M, wherein M≤N.
Pass through the explanation to the present invention for the embodiment of the nonlinear contact processing method of shrouded blade, it can be seen that this
The Three-dimensional CAD being simplified is invented, mode can quickly be calculated, is calculated for later period flutter and vibration stress.
Claims (7)
1. a kind of novel nonlinear contact processing method for shrouded blade characterized by comprising
Shrouded blade geometrical model (1), the geometrical model (1) of the shrouded blade include integral shroud (2) and blade (3)；
According to shrouded blade (1), duplication obtains shrouded blade (4), cut surface (5) is constructed according to shrouded blade (1), according to cutting
Face (5) duplication obtains cut surface (6)；
Shrouded blade (1) is cut along cut surface, cuts shrouded blade (4) along cut surface (6), the shrouded blade model cut
(7) it is used as grid dividing model；
Model meshes divide, and obtain integral shroud gap site Local grid node (8), determine integral shroud gap-contact position grid node
(9)；
A bottom cribbing point is chosen in grid node (9) section view, merges part of node, and obtained grid model is made
For computation model.
2. the nonlinear contact processing method of shrouded blade according to claim 1, which is characterized in that according to shrouded blade
(1) when constructing cut surface (5), constructed cut surface should avoid blade (3) as far as possible, pass through integral shroud (2) and shrouded blade (1)
Center line, and it is moderate with integral shroud (2) Edge Distance.
3. the nonlinear contact processing method of shrouded blade according to claim 1, which is characterized in that be preced with leaf in dubs
Before piece (1) further include:
Determine predetermined angle θ；
According to shrouded blade (1), duplication obtains the concrete operations of shrouded blade (4) are as follows:
The predetermined angle θ is selected along the shrouded blade (1) central axial direction, duplication obtains shrouded blade (4).
4. the nonlinear contact processing method of shrouded blade according to claim 3, which is characterized in that the determination is default
The concrete operations of angle, θ are as follows:
If the sum that the shrouded blade (1) one encloses is n, the predetermined angle θ is calculated according to following formula:
θ=360 °/n.
5. the nonlinear contact processing method of shrouded blade according to claim 1, which is characterized in that in duplication cut surface
(5) before further include:
Determine predetermined angle β；
According to cut surface (5), duplication obtains the concrete operations with cut surface (6) are as follows:
Centerline direction along the cut surface (5) and shrouded blade (1) selects the predetermined angle β, and duplication obtains cut surface
(6)。
6. the nonlinear contact processing method of shrouded blade according to claim 5, which is characterized in that the determination is default
The concrete operations of angle beta are as follows:
If the sum that the shrouded blade (1) one encloses is n, the predetermined angle β is calculated according to following formula:
β=360 °/n.
7. the nonlinear contact processing method of shrouded blade according to claim 1, which is characterized in that
A bottom cribbing point is chosen in grid node (9) section view, the number of node is N, merges part of node, section
Point number is M, wherein M≤N.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811585919.6A CN109614739A (en) | 2018-12-24 | 2018-12-24 | A kind of novel nonlinear contact processing method for shrouded blade |
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| CN201811585919.6A CN109614739A (en) | 2018-12-24 | 2018-12-24 | A kind of novel nonlinear contact processing method for shrouded blade |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113125158A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Device for fixing detected shrouded blade and shrouded blade detection equipment |
| CN114357847A (en) * | 2022-03-21 | 2022-04-15 | 成都中科翼能科技有限公司 | Nonlinear modal analysis method, device and equipment for shrouded blade |
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| CN101599104A (en) * | 2009-07-16 | 2009-12-09 | 北京航空航天大学 | A kind of analogy method of blade flutter boundary of aviation turbine engine |
| EP2360606A2 (en) * | 2008-10-28 | 2011-08-24 | Airbus Operations S.L. | Optimized-cost method for computer-assisted calculation of the aerodynamic forces in an aircraft |
| CN103886164A (en) * | 2014-04-14 | 2014-06-25 | 湘潭大学 | Finite element modeling method of thermal barrier coating of turbine blade with multiple cooling channels |
| CN103886163A (en) * | 2014-04-14 | 2014-06-25 | 湘潭大学 | Meshing method of finite element model of turbine blade thermal barrier coating |
| CN106557638A (en) * | 2016-12-07 | 2017-04-05 | 重庆科技学院 | The method for building up of the two-way transition element grid model of welding mixing |
| CN108133067A (en) * | 2016-11-30 | 2018-06-08 | 中国航发商用航空发动机有限责任公司 | The computation model processing method of blisk |
-
2018
- 2018-12-24 CN CN201811585919.6A patent/CN109614739A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2360606A2 (en) * | 2008-10-28 | 2011-08-24 | Airbus Operations S.L. | Optimized-cost method for computer-assisted calculation of the aerodynamic forces in an aircraft |
| CN101599104A (en) * | 2009-07-16 | 2009-12-09 | 北京航空航天大学 | A kind of analogy method of blade flutter boundary of aviation turbine engine |
| CN103886164A (en) * | 2014-04-14 | 2014-06-25 | 湘潭大学 | Finite element modeling method of thermal barrier coating of turbine blade with multiple cooling channels |
| CN103886163A (en) * | 2014-04-14 | 2014-06-25 | 湘潭大学 | Meshing method of finite element model of turbine blade thermal barrier coating |
| CN108133067A (en) * | 2016-11-30 | 2018-06-08 | 中国航发商用航空发动机有限责任公司 | The computation model processing method of blisk |
| CN106557638A (en) * | 2016-12-07 | 2017-04-05 | 重庆科技学院 | The method for building up of the two-way transition element grid model of welding mixing |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113125158A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Device for fixing detected shrouded blade and shrouded blade detection equipment |
| CN113125158B (en) * | 2019-12-31 | 2023-04-07 | 中国航发商用航空发动机有限责任公司 | Device for fixing detected shrouded blade and shrouded blade detection equipment |
| CN114357847A (en) * | 2022-03-21 | 2022-04-15 | 成都中科翼能科技有限公司 | Nonlinear modal analysis method, device and equipment for shrouded blade |
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Application publication date: 20190412 |