CN110489887A - Modeling method that a kind of turbine blade based on CFD is through-flow - Google Patents
Modeling method that a kind of turbine blade based on CFD is through-flow Download PDFInfo
- Publication number
- CN110489887A CN110489887A CN201910782938.6A CN201910782938A CN110489887A CN 110489887 A CN110489887 A CN 110489887A CN 201910782938 A CN201910782938 A CN 201910782938A CN 110489887 A CN110489887 A CN 110489887A
- Authority
- CN
- China
- Prior art keywords
- flow
- turbine blade
- cfd
- modeling method
- blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Modeling method that a kind of turbine blade based on CFD is through-flow, it is related to a kind of modeling method, it includes (1), geometrical model pre-treatment: the data in through-flow to turbine blade carry out the identification of Geometric Modeling parameter, programmed process, carry out geometrical model identification and topological subregion, grid dividing；(2), computation model pre-treatment: utilizing software, establish corresponding zoning, gives the working medium for calculating and needing, model setting and parameter setting, the solution setting that numerical value calculates is given, to complete the foundation of equation group；(3), numerical value calculates: being solved using solver, stops calculating after meeting specified calculating residual error and requiring；(4), it post-processes: aforementioned calculated result being handled, the data of each variable of entire calculating process are obtained, it is through-flow to turbine blade to analyze by cloud atlas and data graphs.The present invention can be effectively reduced the scale of the through-flow blowing test of blade, effectively push the through-flow analysis and design of turbine blade.
Description
Technical field
The present invention relates to a kind of modeling method, in particular to modeling method that a kind of turbine blade based on CFD is through-flow.
Background technique
More stringent requirements are proposed for economy of the Steam Turbine to product.The economy that steam turbine is through-flow is entire steamer
The main body of machine system economy, promotes it, is the key that promote steam turbine overall economy quality.And turbine blade is through-flow
Great influence is played to the performance of steam turbine, blade is high to the susceptibility of unit load, leads to machine when power plant's underrun
Group low efficiency to improve the through-flow adaptability of blade, improves steam turbine therefore, it is necessary to develop, Design and optimization turbine blade
Blade is through-flow to the adaptability of operating condition under unit varying duty especially underload, significant to the promotion of power plant's overall efficiency.
In addition, the through-flow design of previous turbine blade and optimization, the theory and blowing test for relying primarily on turbomachinery principle come into
Row, the test period being related to is long, and testing expenses are also more expensive.
Summary of the invention
The present invention is in order to overcome the deficiencies of the prior art, to provide a kind of through-flow modeling method of the turbine blade based on CFD,
This method can be effectively reduced the scale of the through-flow blowing test of blade, reduce corresponding experimentation cost, effectively push steam turbine leaf
The analysis and design that piece is through-flow.
Modeling method that a kind of turbine blade based on CFD is through-flow, it includes:
(1), geometrical model pre-treatment
Data in through-flow to turbine blade carry out the identification of Geometric Modeling parameter, and programmed process carries out geometrical model knowledge
Not and topological subregion, grid dividing check the quality of grid；
(2), computation model pre-treatment
Using software, corresponding zoning is established, the working medium for calculating and needing, model setting and parameter setting is given, gives
The solution setting that fixed number value calculates, to complete the foundation of equation group；
(3), numerical value calculates
It is solved using the solver that software carries, stops calculating after meeting specified calculating residual error and requiring；
(4), it post-processes
Aforementioned calculated result is handled using CFD-POST, the data of each variable of entire calculating process is obtained, passes through
Cloud atlas and data graphs analyze the through-flow aeroperformance of turbine blade.
The present invention has the effect that compared with prior art
Reduce cost, previous turbine blade is through-flow design and optimization, rely primarily on turbomachinery principle theory and
Blowing test carries out, and the test period being related to is long, testing expenses are more expensive.Test can be greatly reduced in CFD calculating
Scale reduce cost to reduce testing expenses.
It improves efficiency, with the fast development of mainframe computer, the computing capability of the available computer of enterprise is suitable at present
It is surprising.Engineer can design multiple schemes in a relatively short period of time, and calculated and analyzed by CFD, select optimal design.
Ancillary test, some turbine blades are through-flow, may be limited due to itself testing equipment etc., not can be carried out test and grind
Study carefully, such as: the through-flow test of entire high pressure cylinder.CFD, which is calculated, can make up the deficiency of test in this regard, logical for turbine blade
Stream design and optimization provide another important tool.
The present invention is further described with reference to the accompanying drawings and detailed description:
Detailed description of the invention
Fig. 1 is that the present invention is based on the modeling procedure figures of CFD；
Fig. 2 is a through-flow figure of steam-turbine unit medium pressure grade in embodiment；
Fig. 3 is the steam-turbine unit movable vane geometric parameter figure；
Fig. 4 is the geometrical model figure for importing Turbogrid typical grade movable vane；
Fig. 5 is the twisting coefficient and aspect ratio relational graph of grid cell；
Fig. 6 is middle pressure typical grade movable vane grid schematic diagram；
Fig. 7 is the surface chart of turbulence model and wall model setting in CFX software；
Fig. 8 is the surface chart of the inlet and outlet boundary condition setting of CFX software；
Fig. 9 is the surface chart that iterative steps and the setting of iteration residual error are calculated in CFX software；
Figure 10 is blade S1 stream interface Mach Number Distribution cloud atlas；
Figure 11 is the profile loss of 10% leaf relative superiority or inferiority with the variation diagram of the angle of attack；
Figure 12 is the profile loss of 50% leaf relative superiority or inferiority with the variation diagram of the angle of attack；
Figure 13 is the profile loss of 90% leaf relative superiority or inferiority with the variation diagram of the angle of attack；
Figure 14 be 10% leaf relative superiority or inferiority movable vane pitch be averaged deviation angle with the angle of attack variation；
Figure 15 be 50% leaf relative superiority or inferiority movable vane pitch be averaged deviation angle with the angle of attack variation；
Figure 16 be 90% leaf relative superiority or inferiority movable vane pitch be averaged deviation angle with the angle of attack variation.
Specific embodiment
Shown in Figure 1, modeling method that a kind of turbine blade based on CFD is through-flow, it includes:
(1), geometrical model pre-treatment
Data in through-flow to turbine blade carry out the identification of Geometric Modeling parameter, and programmed process carries out geometrical model knowledge
Not and topological subregion, grid dividing check the quality of grid；It is by programmed process by the through-flow data of turbine blade
File is imported Turbogrid software by the identifiable file of Turbogrid software, topological subregion is carried out, according to practical blade
Form carries out grid dividing to geometrical model using Turbogrid software；
(2), computation model pre-treatment
Using ANSYS CFX software, establish corresponding zoning, give CFD calculate need working medium, model setting and
Parameter setting gives the solution setting that numerical value calculates, to complete the foundation of N-S equation group；
(3), numerical value calculates
It is solved using the Solver solver that ANSYS CFX is carried, is stopped after meeting specified calculating residual error and requiring
Only calculate；
(4), it post-processes
Aforementioned calculated result is handled using CFD-POST, the data of each variable of entire calculating process is obtained, passes through
Cloud atlas and data graphs analyze the through-flow aeroperformance of turbine blade.
Referring to Fig. 1, the whole flow process that the through-flow modeling of turbine blade is carried out using CFD includes four parts: before geometry
Processing, CFD computation model pre-treatment, CFD numerical value calculate, CFD post-processing.Geometry pre-treatment be by turbine blade it is through-flow in
Data features such as (such as blade height, average blade ring diameter and root, the top angle of flare and blade bending) plunderring, pass through programming
The mode of processing, be transformed into file that Turbogrid software can identify (typical file be Hub.curve,
Blade.curve and Shroud.curve).File is imported into Turbogrid, topological subregion is carried out, according to the shape of practical blade
Formula carries out careful grid dividing, from the quality of twisting coefficient and aspect ratio item inspection grid.Computation model pre-treatment is to establish
Corresponding zoning gives CFD and calculates the working medium needed, setting turbulence model, corresponding calculation of boundary conditions and corresponding
Primary condition gives the solution setting that numerical value calculates, to complete the foundation of N-S equation group.
CFD numerical value, which calculates, mainly to be solved using the Solver solver that ANSYS CFX is carried.In the process of solution
In can whole monitoring target variable, and specified calculating residual error (generally 10 can met according to Cost Benefit Principle-5) want
Stop calculating after asking.It is that the result calculated for aforementioned CFD carries out.It is calculated by above-mentioned CFD, engineering staff is entirely counted
The data (such as pressure, temperature, enthalpy, entropy) of each variable of calculation process.Engineering staff is right by forms such as cloud atlas and data graphs
Turbine blade is through-flow to carry out detailed analysis (including the Flow details such as S1 stream interface, S2 stream interface), proposes optimisation strategy and scheme.
Referring to fig. 2, shown in Fig. 3 and Fig. 4, the present invention is for pressing through-flow typical grade in certain type steam turbine.Specific blade
Molded line and size are fully according to through-flow given.For through-flow parameter (such as blade height, average blade ring diameter), pass through programming
Method, be converted into the geometrical model that Turbogrid can be identified.It is through-flow to blade in order to guarantee the convergence calculated
Inlet and outlet be appropriately extended.Topological subregion is carried out for the geometrical model of importing, for flow field parameter variation compared with
The grid of big region (as close to blade inlet, outlet side and inner arc, back arc region) given smaller size, to meet turbulence model
Requirement to wall surface Y+.It is outside from wall surface, gradually increase the size of grid.
Shown in referring to figs. 5 and 6, check that Turbogrid generates the quality of grid.Judge the quality of grid it is main there are two
Standard: first is twisting coefficient, and second is the aspect ratio of grid cell.Since the blade studied has than more typical structure spy
Sign, use is structured grid, and twisting coefficient is smaller.The aspect ratio of grid cell can also impact calculating, grid list
The maximum aspect ratio of member is no more than 100, effectively to meet the requirement of CFD calculating.
It is imported in CFX software referring to the grid file that shown in Fig. 7, Fig. 8 and Fig. 9, Turbogrid is generated, carries out CFD meter
Calculate pre-treatment.In order to really reflect the state of the through-flow flow field of steam turbine, the present embodiment selects turbulence model in model setting
And wall model.Through-flow for turbine blade, the main working medium being related to is superheated steam and moist steam, herein according to IAPWS-
The chart of IFC97 selects corresponding working medium type.Total temperature, stagnation pressure (or stagnation pressure, total enthalpy) perimeter strip are given in the import of blade
Part；Constant static-pressure boundary condition is given in outlet.Then corresponding primary condition is arranged in the region according to locating for blade.Finally carry out CFD
Calculating and setting, herein mainly to calculate iterative steps and iteration residual error etc. be configured.
Referring to Figure 10, this figure is the Mach number cloud atlas of blade S1 stream interface.The flow field characteristic of blade inner flow passage is mainly and blade
Numerous aerodynamic parameters such as the angle of attack it is related.By taking the angle of attack as an example, when the angle of attack is zero, it is considered that it is with optimal pneumatic property
Energy.Blade is under the inlet flow conditions of the different angles of attack, the pressure and other parameters distribution of blade surface and the aerodynamic parameter of blade inner flow passage
Distribution has different performances.It is calculated by the leaf model CFD under the different angles of attack, blade inner flow passage flow field can be obtained
Population parameter and Flow details.
It is the profile loss of same grade blade with relation curve (its of angle of attack variation referring to shown in Figure 11, Figure 12 and Figure 13
Middle α indicates that the angle of attack, Cpt indicate profile loss parameter).It can be seen that profile loss is minimum when the angle of attack is zero；Work as the angle of attack
When positive and negative both direction constantly increases, the loss coefficient of blade profile also constantly increases.After being carried out to CFD numerical result
Processing, can also obtain other relation curves, including but not limited to: indicate that movable vane pitch is average shown in Figure 14, Figure 15 and Figure 16
Deviation angle with the angle of attack variation (wherein α indicates that the angle of attack, δ indicate that pitch is averaged deviation angle).
The present invention is disclosed as above with preferable case study on implementation, and however, it is not intended to limit the invention, any to be familiar with this profession
Technical staff, without departing from the scope of the present invention, according to the technical essence of the invention to the above case study on implementation institute
Any simple modification, equivalent change and modification done still belong to technical solution of the present invention range.
Claims (8)
1. modeling method that a kind of turbine blade based on CFD is through-flow, it is characterised in that: it includes:
(1), geometrical model pre-treatment
Data in through-flow to turbine blade carry out the identification of Geometric Modeling parameter, programmed process, carry out geometrical model identification and
Topological subregion, grid dividing check the quality of grid；
(2), computation model pre-treatment
Using software, corresponding zoning is established, the working medium for calculating and needing, model setting and parameter setting is given, gives fixed number
The solution setting that value calculates, to complete the foundation of equation group；
(3), numerical value calculates
It is solved using the solver that software carries, stops calculating after meeting specified practical residual error and requiring；
(4), it post-processes
Aforementioned calculated result is handled using CFD-POST, the data of each variable of entire calculating process is obtained, passes through cloud atlas
And data graphs, it is through-flow to turbine blade to analyze.
2. the through-flow modeling method of a kind of turbine blade based on CFD according to claim 1, it is characterised in that: step (1)
Described in file identification mode are as follows: by the through-flow data of turbine blade by programmed process be Turbogrid software it is identifiable
File is imported Turbogrid software by file, carries out topological subregion, soft using Turbogrid according to the form of practical blade
Part carries out grid dividing to geometrical model.
3. the through-flow modeling method of a kind of turbine blade based on CFD according to claim 2, it is characterised in that: step (2)
Computation model pre-treatment establishes corresponding zoning using ANSYS CFX software, gives CFD and calculates the working medium needed, mould
Type setting and parameter setting give the solution setting that numerical value calculates, to complete the foundation of N-S equation group.
4. the through-flow modeling method of a kind of turbine blade based on CFD according to claim 3, it is characterised in that: step (3)
Numerical value calculates, and is solved using the Solver solver that ANSYS CFX is carried, and stops after meeting specified practical residual error and requiring
Only calculate.
5. the through-flow modeling method of a kind of turbine blade based on CFD according to claim 4, it is characterised in that: steam turbine
Data during blade is through-flow include blade height, average blade ring diameter, the root of blade angle of flare, the vane tip angle of flare and leaf
Piece bending is plunderred.
6. the through-flow modeling method of a kind of turbine blade based on CFD according to claim 5, it is characterised in that: the mould
Turbulence model and wall model are selected in type setting.
7. the through-flow modeling method of a kind of turbine blade based on CFD according to claim 6, it is characterised in that: utilize torsion
Curvature and aspect ratio check the quality of grid.
8. the through-flow modeling method of a kind of turbine blade based on CFD according to claim 7, it is characterised in that: divide net
Lattice are structured grid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910782938.6A CN110489887A (en) | 2019-08-23 | 2019-08-23 | Modeling method that a kind of turbine blade based on CFD is through-flow |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910782938.6A CN110489887A (en) | 2019-08-23 | 2019-08-23 | Modeling method that a kind of turbine blade based on CFD is through-flow |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110489887A true CN110489887A (en) | 2019-11-22 |
Family
ID=68552842
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910782938.6A Withdrawn CN110489887A (en) | 2019-08-23 | 2019-08-23 | Modeling method that a kind of turbine blade based on CFD is through-flow |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110489887A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113609619A (en) * | 2021-08-10 | 2021-11-05 | 西安西热节能技术有限公司 | Multidimensional coupling simulation method for long blade blast of low-pressure through-flow area of steam turbine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104298805A (en) * | 2014-08-13 | 2015-01-21 | 天津大学 | CFD pneumatic modeling method for hypersonic aerocraft |
| CN106227967A (en) * | 2016-08-01 | 2016-12-14 | 杭州汽轮机股份有限公司 | Industrial steam turbine low-pressure stage group vane type line optimization method |
| CN107895069A (en) * | 2017-10-30 | 2018-04-10 | 北京理工大学 | A kind of fluid structurecoupling Numerical Predicting Method based on composite structure |
| CN109902384A (en) * | 2019-02-28 | 2019-06-18 | 上海交通大学 | A kind of wind energy conversion system flexible blade pre-bending pre-twist design method based on air spring pole |
| CN109948233A (en) * | 2019-03-14 | 2019-06-28 | 哈尔滨汽轮机厂有限责任公司 | The wide load blade design optimization system of small enthalpy drop and method based on CFD |
| CN110020489A (en) * | 2019-04-15 | 2019-07-16 | 哈尔滨汽轮机厂有限责任公司 | The method for determining turbine blade erosion protection sheild geomery is analyzed based on CFD |
-
2019
- 2019-08-23 CN CN201910782938.6A patent/CN110489887A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104298805A (en) * | 2014-08-13 | 2015-01-21 | 天津大学 | CFD pneumatic modeling method for hypersonic aerocraft |
| CN106227967A (en) * | 2016-08-01 | 2016-12-14 | 杭州汽轮机股份有限公司 | Industrial steam turbine low-pressure stage group vane type line optimization method |
| CN107895069A (en) * | 2017-10-30 | 2018-04-10 | 北京理工大学 | A kind of fluid structurecoupling Numerical Predicting Method based on composite structure |
| CN109902384A (en) * | 2019-02-28 | 2019-06-18 | 上海交通大学 | A kind of wind energy conversion system flexible blade pre-bending pre-twist design method based on air spring pole |
| CN109948233A (en) * | 2019-03-14 | 2019-06-28 | 哈尔滨汽轮机厂有限责任公司 | The wide load blade design optimization system of small enthalpy drop and method based on CFD |
| CN110020489A (en) * | 2019-04-15 | 2019-07-16 | 哈尔滨汽轮机厂有限责任公司 | The method for determining turbine blade erosion protection sheild geomery is analyzed based on CFD |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113609619A (en) * | 2021-08-10 | 2021-11-05 | 西安西热节能技术有限公司 | Multidimensional coupling simulation method for long blade blast of low-pressure through-flow area of steam turbine |
| CN113609619B (en) * | 2021-08-10 | 2022-09-20 | 西安西热节能技术有限公司 | Multidimensional coupling simulation method for long blade blast of low-pressure through-flow area of steam turbine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110929357A (en) | Pneumatic design method for high-performance ship gas turbine compressor | |
| CN103939389A (en) | Multiple-working-condition hydraulic design method for guide vane type centrifugal pump | |
| JP2009144716A (en) | Method of designing multistage turbine for turbomachine | |
| CN112594064B (en) | S2 flow field diagnosis method based on interstage measurement parameters of axial flow compressor | |
| KR20130098179A (en) | Turbo-machinery stage families tuning/calibration system and method | |
| CN109578085B (en) | Method for weakening unsteady acting force of turbine movable blade through guide blade inclination | |
| CN109598081A (en) | Radial turbine Aerodynamic optimization method based on Data Dimensionality Reduction and more two-dimentional stream interfaces | |
| Marchukov et al. | Improving of the working process of axial compressors of gas turbine engines by using an optimization method | |
| Ju et al. | Optimization of centrifugal impellers for uniform discharge flow and wide operating range | |
| CN104200003A (en) | Self-locking damping vane gas flow bending stress design method based on fluid-solid interaction | |
| Havakechian et al. | Aerodynamic design of 50 per cent reaction steam turbines | |
| CN111027148B (en) | Automatic calibration and industrial axial flow compressor performance calculation method for loss lag angle model | |
| Goryachkin et al. | Three-stage low pressure compressor modernization by means of optimization methods | |
| CN110489887A (en) | Modeling method that a kind of turbine blade based on CFD is through-flow | |
| CN109948233A (en) | The wide load blade design optimization system of small enthalpy drop and method based on CFD | |
| Pinelli et al. | Aeromechanical characterization of a last stage steam blade at low load operation: Part 2—computational modelling and comparison | |
| CN110863861A (en) | Multi-stage small enthalpy drop blade pneumatic design method for improving through-flow efficiency of steam turbine | |
| CN116595682A (en) | Blade pump transient process performance optimization design method | |
| Lübbe et al. | Design and Validation of a Large Steam Turbine End-Stage Blade to Meet Current and Future Market Demands | |
| CN108416181A (en) | A kind of all-pass stream turbine multi-dimensional Coupling Fast design method | |
| Elliott et al. | Performance improvement of a mixed flow turbine using 3D blading | |
| CN112699505B (en) | Dynamic stress finite element calculation method for long blade of low-pressure cylinder of nuclear power unit | |
| CN112580164B (en) | Design method of low-pressure long blade of nuclear turbine | |
| Chen et al. | Parameter extraction of featured section in turbine blade inspection | |
| Pinelli et al. | Aeroelastic investigation of an open 3D steam turbine test case and blade shape optimization with improved flutter behavior |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20191122 |