CN108563872B - Grid parameterization method and axial flow turbine aerodynamic optimization design method based on grid parameterization method - Google Patents
Grid parameterization method and axial flow turbine aerodynamic optimization design method based on grid parameterization method Download PDFInfo
- Publication number
- CN108563872B CN108563872B CN201810338508.0A CN201810338508A CN108563872B CN 108563872 B CN108563872 B CN 108563872B CN 201810338508 A CN201810338508 A CN 201810338508A CN 108563872 B CN108563872 B CN 108563872B
- Authority
- CN
- China
- Prior art keywords
- control
- grid
- blade
- pneumatic
- establishing
- 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.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- 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
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/06—Multi-objective optimisation, e.g. Pareto optimisation using simulated annealing [SA], ant colony algorithms or genetic algorithms [GA]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Evolutionary Computation (AREA)
- Computer Hardware Design (AREA)
- General Engineering & Computer Science (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a mesh parameterization method, which comprises the steps of decomposing a three-dimensional pneumatic analysis mesh into two-dimensional cross-section pneumatic analysis meshes with different leaf span heights according to the structural characteristics of an impeller mechanical pneumatic analysis mesh; designing a topological structure of a two-dimensional section pneumatic analysis grid control body, and establishing a relation between blade design parameters and control body node coordinate displacement; parameterizing the two-dimensional section pneumatic analysis grid according to the relation between the design parameters and the control body node coordinate displacement; establishing control bodies with different leaf span heights on the basis of two-dimensional section pneumatic analysis grid parameterization; and parameterizing the three-dimensional pneumatic analysis grid according to the relation between the design parameters and the coordinate displacement of the control body nodes with different leaf span heights. According to the grid parameterization method, the control point coordinate movement is associated with the blade design parameters, and the grid quality of the grid in the deformation process can be effectively guaranteed, so that the pneumatic analysis precision is guaranteed.
Description
Technical Field
The disclosure belongs to the technical field of structural design, and particularly relates to a grid parameterization method and an axial flow turbine aerodynamic optimization design method based on the grid parameterization method.
Background
The impeller machine is widely applied to the fields of aviation propulsion, ship propulsion, industrial power generation and the like, and is high-end equipment which is mainly developed in various countries in the world. As a core component of the impeller machine, the blades directly determine the overall efficiency, power and the like of the impeller machine. In order to increase the performance of the turbomachinery as much as possible, modern turbomachinery are often optimized to achieve an optimal design.
In the past, when the pneumatic optimization iteration of impeller machinery is carried out, the pneumatic appearance of a blade is required to be generated according to a modeling design method, a grid division tool is used for generating a pneumatic analysis grid, and a computational fluid mechanics program is called for carrying out pneumatic analysis; in the optimization process, the pneumatic appearance and the grid division can be generated only by adopting an automatic method; however, the automatic grid division is usually only simple, and it is difficult to obtain a high-quality analysis grid. Along with improvement of the aerodynamic performance of the impeller, the flow speed of the impeller is higher and higher, the internal flow is more and more complex, and the flow characteristics such as a boundary layer, blade tip leakage and wake can be captured only by fine grid division. However, the quality of the grid generated by automatic division in the optimization process is difficult to ensure the accuracy of pneumatic analysis.
Therefore, it is necessary to provide a mesh parameterization method to solve the above problems.
It is to be noted that the information disclosed in the above background section is only for enhancement of understanding of the background of the present disclosure, and thus may include information that does not constitute prior art known to those of ordinary skill in the art.
Disclosure of Invention
The present disclosure is directed to a mesh parameterization method and an axial turbine aerodynamic optimization design method based on the mesh parameterization method, which overcome one or more of the problems due to the limitations and disadvantages of the related art, at least to some extent.
Additional features and advantages of the disclosure will be set forth in the detailed description which follows, or in part will be obvious from the description, or may be learned by practice of the disclosure.
According to an aspect of the present disclosure, there is provided a mesh parameterization method, comprising:
decomposing the three-dimensional pneumatic analysis grid into two-dimensional cross-section pneumatic analysis grids with different leaf span heights according to the structural characteristics of the mechanical pneumatic analysis grid of the impeller;
designing a topological structure of the two-dimensional section pneumatic analysis grid control body, and establishing a relation between blade design parameters and control body node coordinate displacement;
parameterizing the two-dimensional section pneumatic analysis grid according to the relation between the design parameters and the control body node coordinate displacement;
establishing the control bodies with different leaf span heights on the basis of the parameterization of the two-dimensional section pneumatic analysis grid;
and parameterizing the three-dimensional pneumatic analysis grid according to the relation between the design parameters and the coordinate displacement of the control body nodes with different leaf span heights.
In an exemplary embodiment of the present disclosure, the designing a topology structure of the two-dimensional cross-section aerodynamic analysis grid control body establishes a relationship between a blade design parameter and a control body node coordinate displacement; the method comprises the following steps:
calculating blade profile points according to a blade profile modeling method by using the design parameters, and establishing blade profile control nodes;
establishing a flow channel control node according to the characteristics of the flow channel;
establishing a correlated movement of the flow path control node and the blade profile control node.
In an exemplary embodiment of the present disclosure, the calculating of the blade profile points according to the blade profile modeling method using the design parameters and the establishing of the blade profile control nodes are performed; the method comprises the following steps:
with axial chord length L of said bladewMounting angle gamma and inlet airflow angle beta1Angle of outlet air flow beta2And the mean camber curve control point weight is used as a design parameter;
passing the axial chord length L of the blade according to the geometrical relationwMounting angle gamma and inlet airflow angle beta1Angle of outlet air flow beta2Determining a mean camber line control point p1，p2，p3；
From said mean camber line control point p1，p2，p3Determining a mean camber line by the mean camber line curve control point weight;
equally dividing the camber line, and determining curve coordinates of equally divided points, wherein the curve coordinates of the equally divided points are leaf-shaped points;
and determining the profile control node of the blade according to the profile point and the profile thickness distribution of the blade.
In an exemplary embodiment of the disclosure, the axial chord length L passing through the blade according to the geometric relationshipwMounting angle gamma, inlet flow angle beta1Outlet flow angle beta2Determining a mean camber line control point p1，p2，p3(ii) a The method comprises the following steps:
giving the control point p according to the vane position1Coordinate (x) of1，y1)；
The control point p2Coordinate (x)2，y2) The calculation formula of (2) is as follows:
x2＝Lw/cosγ/sin(180-β1-β2)·sin(β2-γ)·sin(90+β1)+x1
y2＝Lw/cosγ/sin(180-β1-β2)·sin(β2-γ)·cos(90+β1)+y1
the control point p3Coordinate (x)3，y3) The calculation formula of (2) is as follows:
x3＝Lw+x1
y3＝Lw·tanγ+y1
in an exemplary embodiment of the present disclosure, the establishing of the flow channel control node according to the flow channel characteristics; the method comprises the following steps:
and establishing the flow channel control node according to the flow channel profile of the two-dimensional cross section pneumatic analysis grid control body and by combining the position of the blade profile control node.
In an exemplary embodiment of the present disclosure, the establishing of the associated movement of the flow path control node with the blade profile control node; the method comprises the following steps:
dividing the blade profile point, the blade profile line control node and the flow channel control node into a leading edge control point, a suction surface control point, a mean camber line control point, a pressure surface control point and a trailing edge control point;
the associated movement between the control points is established by a deformation method.
In an exemplary embodiment of the present disclosure, the mesh parameterization method further includes:
establishing the control body with a plurality of rows of blades, and parameterizing the pneumatic analysis grids of the plurality of rows of blades according to the relation between the design parameters and the node coordinate displacement of the control body with the plurality of rows of blades.
According to one aspect of the present disclosure, there is provided an axial flow turbine aerodynamic optimization design method comprising the mesh parameterization method according to any one of claims 1-7.
In an exemplary embodiment of the present disclosure, the pneumatic optimization design method includes:
determining design parameters of pneumatic optimization, and carrying out parametric deformation on the grid according to the grid parameterization method;
determining a design variable of pneumatic optimization according to the number of the design parameters;
designing sample points by using an optimal Latin hypercube method according to the quantity of the design variables, and establishing a kriging proxy model through the sample points;
and replacing a pneumatic analysis process with the kriging proxy model, and selecting a specific algorithm to perform multi-objective optimization analysis on the axial flow turbine.
In an exemplary embodiment of the present disclosure, the specific algorithm is a multi-island genetic algorithm.
The grid parameterization method provided by the exemplary embodiment of the disclosure realizes the correlation deformation of the pneumatic design variables and the pneumatic analysis grid, and ensures the consistency of the grid deformation and the change of the pneumatic design variables.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.
FIG. 1 is a flow diagram illustrating a method of mesh parameterization according to one embodiment;
FIG. 2 is a schematic view of the vane aerodynamic analysis grid control volume shown in FIG. 1;
FIG. 3 is a schematic diagram illustrating a mean camber line design method, according to one embodiment;
FIG. 4 is a schematic illustration of the camber line airfoil point shown in FIG. 3;
FIG. 5 is a schematic view of the mean camber blade profile line control node shown in FIG. 3;
FIG. 6 is a schematic illustration of the bucket profile shown in FIG. 5;
FIG. 7 is a schematic diagram of the two-dimensional cross-sectional pneumatic analysis grid control body shown in FIG. 1;
FIG. 8 is a comparison graph illustrating a mesh before and after deformation according to one embodiment;
FIG. 9 is a comparison of a two-dimensional cross-sectional solid with the deformed mesh shown in FIG. 8;
FIG. 10 is a schematic flow diagram illustrating an axial flow turbine aerodynamic optimization design method according to one embodiment;
FIG. 11 is a flow chart of a pneumatic optimization design based on the mesh parameterization method shown in FIG. 1.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
Furthermore, the drawings are merely schematic illustrations of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus their repetitive description will be omitted. Some of the block diagrams shown in the figures are functional entities and do not necessarily correspond to physically or logically separate entities. These functional entities may be implemented in the form of software, or in one or more hardware modules or integrated circuits, or in different networks and/or processor devices and/or microcontroller devices.
As shown in fig. 1, the present embodiment provides a mesh parameterization method, which mainly includes:
s11, decomposing the three-dimensional pneumatic analysis grid into two-dimensional cross-section pneumatic analysis grids with different leaf span heights according to the structural characteristics of the impeller mechanical pneumatic analysis grid;
s12, designing a topological structure of the two-dimensional section pneumatic analysis grid control body, and establishing a relation between blade design parameters and control body node coordinate displacement;
s13, parameterizing the two-dimensional section pneumatic analysis grid according to the relation between the design parameters and the control body node coordinate displacement;
s14, establishing the control bodies with different leaf span heights on the basis of the parameterization of the two-dimensional section pneumatic analysis grid;
s15, parameterizing the three-dimensional pneumatic analysis grid according to the relation between the design parameters and the coordinate displacement of the control body nodes with different leaf span heights.
The grid parameterization method provided by the exemplary embodiment of the disclosure realizes the correlation deformation of the pneumatic design parameters and the pneumatic analysis grid, and ensures the consistency of the grid deformation and the pneumatic design parameter change. The mesh parameterization method provided by the exemplary embodiment is described in detail below with reference to the accompanying drawings.
As shown in fig. 2, in step S11, the three-dimensional aerodynamic analysis grid is decomposed into two-dimensional cross-sectional aerodynamic analysis grids with different spanwise heights according to the structural characteristics of the impeller mechanical aerodynamic analysis grid.
In the embodiment, a topological structure of a two-dimensional cross-section pneumatic analysis grid control body is designed, and a relation between a pneumatic design parameter and node coordinate displacement of the control body is established. Step S12 mainly includes the following steps:
s121, calculating blade profile points according to a blade profile modeling method by using pneumatic design parameters, and establishing blade profile control nodes;
s122, establishing a flow channel control node according to the characteristics of the flow channel;
and S123, establishing the associated movement of the flow channel control node and the blade type line control node.
As shown in fig. 3,4,5 and 6, in the present embodiment, step S121 may include:
s1211 with axial chord length L of the bladewMounting angle gamma, inlet flow angle beta1Outlet flow angle beta2And the weight of the control point of the mean camber curve is taken as a design parameter;
s1212, passing the axial chord length L of the blade according to the geometrical relationwMounting angle gamma and inlet airflow angle beta1Outlet flow angle beta2Determining a mean camber line control point p1，p2，p3；
S1213, controlling point p by mean camber line1，p2，p3Determining the mean camber line by the mean camber line curve control point weight;
s1214, bisecting the mean arc line, and determining the curve coordinates of the bisection points, wherein the curve coordinates of the bisection points are the leaf-shaped points;
and S1215, determining the profile control node of the blade according to the profile point and the profile thickness distribution of the blade.
Further, in the present embodiment, the specific procedure of step S121 is as follows:
by axial chord length L of the bladewMounting angle gamma, inlet flow angle beta1Angle of outlet air flow beta2And camber line curve control point weight as design parameter, and blade type line control node by constructing camber line and thickness distribution by adopting non-uniform rational B-spline (NURBS) curve, i.e. aerodynamic profile control pointThe design of (3).
Can pass through the axial chord length L of the blade according to the geometric relationshipwMounting angle gamma and inlet airflow angle beta1Angle of outlet air flow beta2Determining a mean camber line control point p1，p2，p3. Wherein the control point p1Coordinate (x)1，y1) Given according to the turbine blade position, the control point p2Coordinate (x)2，y2) The calculation formula is as follows:
control point p3Coordinate (x)3，y3) The calculation formula is as follows:
control of point p by mean camber line1，p2，p3And the control point weight of the camber line curve, a quasi-uniform method node vector construction method is used, and the camber line can be determined by combining the NURBS theory. Wherein the mean camber line is represented by p in the figure1，p2，p3Three control points are determined as shown in fig. 3.
And obtaining the blade profile point according to the curve coordinate after determining the mean camber line. The mean camber line may be equally divided into eight segments, for a total of nine leaf points, using curvilinear coordinates d = i/8 (i =0,1, \ 8230;, 8), respectively, as shown in fig. 4. The blade profile control nodes can be determined according to the blade profile thickness distribution, namely the normal distance of the blade profile point, and comprise camber line control points p1，p3Points, 20 control points in total, as shown in fig. 5. The leaf-shaped curve is constructed by the 20 control points and the weight of the control points by using a quasi-uniform method node vector construction method and combining the NURBS curve modeling theory, which is specifically shown in FIG. 6.
In step S122, the flow channel control nodes are established according to the flow channel profile of the two-dimensional cross-section aerodynamic analysis mesh control body and the positions of the blade-shaped line control nodes.
In this embodiment, the control body of the two-dimensional cross-section pneumatic analysis grid is mainly composed of camber line profile points of each profile of the blade, blade profile control nodes, and flow channel control nodes surrounding the fluid grid. The flow channel control node can be determined by combining the position of the blade type line control node according to the flow channel profile of the two-dimensional cross section pneumatic analysis grid control body.
In step S123, the associated movement of the flow path control node and the blade-shaped line control node is established. The method comprises the following specific steps:
as shown in fig. 7, in the present embodiment, the two-dimensional cross-sectional pneumatic analysis grid control body may be composed of 65 control points in 5 rows and 13 columns. The 65 control points are numbered according to row number, as shown in the table below. Wherein i-j (i =2,3,4 j =3,4,5, \8230;, 11) control points are mean camber line blade profile points and blade profile control nodes.
When the design parameters of the blade are changed, the blade profile points and the control nodes of the blade profile can be calculated according to a blade profile modeling method, namely coordinates of control points i-j (i =2,3,4, j =3,4,5, \8230;, 11) are calculated, and the control points are moved. The 65 control points can be divided into 5 classes, each of which is divided into several groups for moving respectively. For example, the first type is a leading edge control point, which includes 10 control points in the first row and the second row, and the control points are not moved because they are not related to the shape of the blade; the second type is nine groups of control points of the molded line suction surface of the axial flow turbine blade, each group comprises a control point (2-j), j =3,4, \ 8230, 11, and the control points move along with the control points 2-j after blade molded line control nodes are calculated according to blade design parameters; the third type is nine groups of camber line control points of the molded line of the axial flow turbine blade, each group comprises three control points, the three control points are (1-j, 3-j, 5-j), j =3,4, \8230, and 11, the point moves along with the control point 3-j after the blade profile point is calculated by blade design parameters; the fourth type is nine groups of control points of the molded line suction surface of the axial flow turbine blade, each group comprises a control point (4-j), j =3,4, \ 8230, 11, and the control points move along with the control points 4-j after blade molded line control nodes are calculated according to blade design parameters; the fifth type is a group of trailing edge control points, which includes 10 control points in the 12 th row and the 13 th row, because changing the x coordinate of the control point will affect the matching of moving blades and static blades, the movement y direction of the blade type line control node following the control point 3-j is calculated, as shown in the following table:
in step S13, the two-dimensional cross-sectional pneumatic analysis mesh is parameterized according to the relationship between the design parameters and the control volume node coordinate displacement.
As shown in fig. 8, in the present embodiment, the two-dimensional cross-section pneumatic analysis mesh is deformed according to the above two-dimensional cross-section pneumatic analysis mesh parameterization method, and when the blade installation angle is increased by 5 °, it is known from the figure that the blade profile after mesh deformation is smooth, the mesh shape is good, and the purpose of mesh deformation is achieved. The quality of the grids before and after deformation is checked, and the result shows that the quality of the grids before and after deformation is basically the same, and the deformation method can ensure the quality of the grids after deformation.
As shown in fig. 9, a two-dimensional section entity of the blade is created by using three-dimensional modeling software according to the blade profile design parameters, and the two-dimensional section entity of the blade is compared with the deformed grid. The graph shows that the grid parameterization method has the same deformation capacity as the geometric parameterization method, and the deformation effect is good.
In step S14, on the basis of the two-dimensional cross-section pneumatic analysis mesh parameterization, control bodies of different leaf span heights are established.
In step S15, the three-dimensional pneumatic analysis grid is parameterized according to the relationship between the design parameters and the coordinate displacements of the nodes of the control volume at different leaf span heights.
In the present embodiment, on the basis of the parameterization of the two-dimensional cross-section aerodynamic analysis mesh, control bodies with different blade span heights can be established to further implement the parameterization of the three-dimensional aerodynamic analysis mesh of the turbine blade, as shown in fig. 1. The three-dimensional pneumatic analysis mesh parameterization process such as the two-dimensional cross-section pneumatic analysis mesh parameterization process is not described herein again.
The mesh parameterization method according to the present embodiment may further include step S16: establishing a multi-row blade control body, and parameterizing the pneumatic analysis grid of the multi-row blades according to the relation between the design parameters and the node coordinate displacement of the multi-row blade control body.
In this embodiment, if the pneumatic analysis model includes multiple rows of blades, the control body for each blade can be established separately, and the parameterized deformation of the pneumatic analysis grid for multiple rows of blades can be realized according to the relationship between the design variables and the node coordinate displacement of each blade control body. The parameterization process of the multi-row blade pneumatic analysis grid, such as the parameterization process of the two-dimensional section pneumatic analysis grid, is not described in detail herein.
As shown in fig. 10, the present disclosure also proposes an aerodynamic optimization design method for an axial turbine blade, where the aerodynamic analysis mesh parameterization of the axial turbine blade is based on the mesh parameterization method. The aerodynamic optimization design method of the axial flow turbine mainly comprises the following steps:
s21, determining design parameters of pneumatic optimization, and carrying out parametric deformation on the grid according to the grid parameterization method;
s22, determining a design variable of the axial flow turbine pneumatic optimization according to the number of the design parameters;
s23, designing sample points by using an optimal Latin hypercube method according to the number of design variables, and establishing a kriging proxy model through the sample points;
and S24, replacing a pneumatic analysis process with a kriging proxy model, and selecting a multi-island genetic algorithm to perform multi-objective optimization analysis on the axial flow turbine.
Fig. 11 shows a pneumatic optimization design flow chart based on the mesh parameterization. In this embodiment, the specific process is as follows: on the basis of grid parameterization, performing experimental design by using an optimal Latin hypercube method, and determining main design variables influencing aerodynamic performance; performing test design in a design space by using an optimal Latin hypercube method to obtain initial sample points, and establishing a kriging proxy model; carrying out optimization design on the basis of a kriging proxy model; and updating the kriging proxy model in the optimization process until convergence, thereby ensuring the optimization design precision.
In conclusion, the grid parameterization method and the axial flow turbine aerodynamic optimization design method based on the grid parameterization method have the following advantages:
1. the structural characteristics of the impeller mechanical pneumatic analysis grid are reasonably considered, the deformation control of the three-dimensional pneumatic analysis grid is decomposed into the deformation control of two-dimensional pneumatic analysis grids with different blade span heights, the control body design of pneumatic shapes, runners and the like is respectively carried out based on the grid deformation method, a set of method for generating pneumatic shape grid control nodes by using pneumatic design parameters is established, and the correlation control of the two-dimensional runner control nodes is realized.
2. And (3) carrying out parametric deformation on the two-dimensional pneumatic analysis grids with different sections, namely realizing the parametric deformation of the three-dimensional pneumatic analysis grid. The method realizes the correlation deformation of the pneumatic design parameters and the pneumatic analysis grid, and ensures the consistency of the grid deformation and the pneumatic design parameter change.
3. A pneumatic optimization design flow established based on a grid parameterization method comprehensively utilizes a test design to carry out primary and secondary factor analysis, an approximate proxy model replaces actual simulation analysis and the like, and the design efficiency of pneumatic optimization is improved by reducing the number of design variables and the time of simulation analysis.
It should be noted that although the various steps of the methods of the present disclosure are depicted in the drawings in a particular order, this does not require or imply that these steps must be performed in this particular order, or that all of the depicted steps must be performed, to achieve desirable results. Additionally or alternatively, certain steps may be omitted, multiple steps combined into one step execution, and/or one step broken into multiple step executions, etc.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
It will be understood that the present disclosure is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the present disclosure is to be limited only by the terms of the appended claims.
Claims (9)
1. A mesh parameterization method, comprising:
decomposing the three-dimensional pneumatic analysis grid into two-dimensional cross-section pneumatic analysis grids with different leaf span heights according to the structural characteristics of the mechanical pneumatic analysis grid of the impeller;
designing a topological structure of the two-dimensional section pneumatic analysis grid control body, and establishing a relation between blade design parameters and control body node coordinate displacement;
parameterizing the two-dimensional section pneumatic analysis grid according to the relation between the design parameters and the control body node coordinate displacement;
establishing the control bodies with different leaf span heights on the basis of the parameterization of the two-dimensional section pneumatic analysis grid;
parameterizing the three-dimensional pneumatic analysis grid according to the relation between the design parameters and the control body node coordinate displacement at different leaf span heights;
designing a topological structure of the two-dimensional section pneumatic analysis grid control body, and establishing a relation between blade design parameters and control body node coordinate displacement; the method comprises the following steps:
calculating blade profile points according to a blade profile modeling method by using the design parameters, and establishing blade profile control nodes;
establishing a flow channel control node according to the characteristics of the flow channel;
establishing an associated movement of the flow control node with the blade profile control node.
2. The mesh parameterization method according to claim 1, wherein said design parameters are used to calculate blade profile points according to a blade profile modeling method and to establish blade profile control nodes; the method comprises the following steps:
with axial chord length L of said bladewMounting angle gamma and inlet airflow angle beta1Angle of outlet air flow beta2And the mean camber curve control point weight is used as a design parameter;
passing the axial chord length L of the blade according to the geometrical relationwMounting angle gamma and inlet airflow angle beta1Outlet flow angle beta2Determining a mean camber line control point p1，p2，p3；
From said mean camber line control point p1，p2，p3Determining a mean camber line by the mean camber line curve control point weight;
equally dividing the camber line, and determining curve coordinates of equally divided points, wherein the curve coordinates of the equally divided points are leaf-shaped points;
and determining the profile control node of the blade according to the profile point and the profile thickness distribution of the blade.
3. The mesh parameterization method according to claim 2, wherein said axial chord length L is determined by the geometric relationship of the bladeswMounting angle gamma and inlet airflow angle beta1Outlet flow angle beta2Determining a mean camber line control point p1，p2，p3(ii) a The method comprises the following steps:
giving the control point p according to the vane position1Coordinate (x) of (2)1，y1)；
The control point p2Coordinate (x)2，y2) The calculation formula of (c) is:
x2＝Lw/cosγ/sin(180-β1-β2)·sin(β2-γ)·sin(90+β1)+x1
y2＝Lw/cosγ/sin(180-β1-β2)·sin(β2-γ)·cos(90+β1)+y1
the control point p3Coordinate (x)3，y3) The calculation formula of (c) is:
4. the grid parameterization method according to claim 1, wherein said establishing flow channel control nodes according to flow channel characteristics; the method comprises the following steps:
and establishing the flow channel control node according to the flow channel profile of the two-dimensional cross section pneumatic analysis grid control body and by combining the position of the blade profile control node.
5. The mesh parameterization method of claim 1 wherein said establishing an associated movement of said flow path control node with said blade profile control node; the method comprises the following steps:
dividing the blade profile point, the blade profile line control node and the flow channel control node into a leading edge control point, a suction surface control point, a mean camber line control point, a pressure surface control point and a trailing edge control point;
and establishing the associated movement between the control points through a deformation method.
6. The mesh parameterization method according to claim 1, further comprising:
establishing the control body with a plurality of rows of blades, and parameterizing the pneumatic analysis grids of the plurality of rows of blades according to the relation between the design parameters and the node coordinate displacement of the control body with the plurality of rows of blades.
7. An axial flow turbine aerodynamic optimization design method, characterized by comprising the mesh parameterization method according to any one of claims 1 to 6.
8. The aerodynamic optimization design method of claim 7, comprising:
determining design parameters of pneumatic optimization, and carrying out parametric deformation on the grid according to the grid parameterization method;
determining a design variable of pneumatic optimization according to the number of the design parameters;
according to the number of the design variables, designing sample points by using an optimal Latin hypercube method, and establishing a kriging proxy model through the sample points;
and replacing a pneumatic analysis process with the kriging proxy model, and selecting a specific algorithm to perform multi-objective optimization analysis on the axial flow turbine.
9. The pneumatic optimal design method according to claim 8, wherein the specific algorithm is a multi-island genetic algorithm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810338508.0A CN108563872B (en) | 2018-04-16 | 2018-04-16 | Grid parameterization method and axial flow turbine aerodynamic optimization design method based on grid parameterization method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810338508.0A CN108563872B (en) | 2018-04-16 | 2018-04-16 | Grid parameterization method and axial flow turbine aerodynamic optimization design method based on grid parameterization method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108563872A CN108563872A (en) | 2018-09-21 |
| CN108563872B true CN108563872B (en) | 2022-11-01 |
Family
ID=63535231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810338508.0A Active CN108563872B (en) | 2018-04-16 | 2018-04-16 | Grid parameterization method and axial flow turbine aerodynamic optimization design method based on grid parameterization method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108563872B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109515739B (en) * | 2018-11-21 | 2020-11-20 | 中国航天空气动力技术研究院 | Aerodynamic characteristic rapid prediction method |
| CN110069848B (en) * | 2019-04-18 | 2020-10-27 | 西安交通大学 | Modeling method for turbine blade pneumatic-dehumidification-cooling test |
| CN110593960B (en) * | 2019-09-19 | 2021-03-23 | 西安交通大学 | Axial flow turbine mechanical blade parameterization method for bending and twisting |
| CN114861315B (en) * | 2022-05-16 | 2024-07-05 | 北京航空航天大学 | Turbine two-dimensional blade profile optimization method based on machine learning |
| CN116227268B (en) * | 2022-12-30 | 2023-11-17 | 上海尚实航空发动机股份有限公司 | Method, device, equipment and medium for determining thermal parameters of turbine blade of engine |
| CN115788598B (en) * | 2023-02-10 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Turbine blade air film hole parameterization control and design method |
| CN116720265B (en) * | 2023-08-09 | 2023-12-08 | 北京航空航天大学 | Unified parameterization method and device for variable-dimension FFD-based turbine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2485192A2 (en) * | 2011-02-03 | 2012-08-08 | Rolls-Royce plc | A method of connecting meshes |
| CN104281751A (en) * | 2014-10-14 | 2015-01-14 | 北京航空航天大学 | Feature-based parametric build system and method of turbine cooling blade |
| CN104298805A (en) * | 2014-08-13 | 2015-01-21 | 天津大学 | CFD pneumatic modeling method for hypersonic aerocraft |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2913901B1 (en) * | 2007-03-20 | 2009-09-04 | Snecma Services Sa | PROCESS FOR REPAIRING FACTORY PARTS SUCH AS TURBOMACHINE BLADES OR DAM BLADES |
| US8366057B2 (en) * | 2009-07-28 | 2013-02-05 | University Of Kansas | Method and apparatus for pressure adaptive morphing structure |
| CN104317997A (en) * | 2014-10-17 | 2015-01-28 | 北京航空航天大学 | Optimized design method for modelling of end wall of high load fan/compressor |
| CN106156383B (en) * | 2015-04-03 | 2019-05-31 | 北京临近空间飞行器系统工程研究所 | A kind of parametrization aerodynamic configuration digital-to-analogue and structured grid automatic generation method |
| CN106446324B (en) * | 2016-07-19 | 2019-12-06 | 杭州汽轮机股份有限公司 | Design method of final-stage twisted blade of large industrial steam turbine |
| CN106250652B (en) * | 2016-08-16 | 2017-12-29 | 深圳友铂科技有限公司 | A kind of construction method and compressor blade of compressor blade blade profile |
| CN106777482A (en) * | 2016-11-18 | 2017-05-31 | 西北工业大学 | A kind of structure Multidisciplinary design optimization method based on mesh parameterization |
-
2018
- 2018-04-16 CN CN201810338508.0A patent/CN108563872B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2485192A2 (en) * | 2011-02-03 | 2012-08-08 | Rolls-Royce plc | A method of connecting meshes |
| CN104298805A (en) * | 2014-08-13 | 2015-01-21 | 天津大学 | CFD pneumatic modeling method for hypersonic aerocraft |
| CN104281751A (en) * | 2014-10-14 | 2015-01-14 | 北京航空航天大学 | Feature-based parametric build system and method of turbine cooling blade |
Non-Patent Citations (1)
| Title |
|---|
| 叶片参数化有限元建模与罩量优化设计;王振培等;《航空动力学报》;20111115(第11期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108563872A (en) | 2018-09-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108563872B (en) | Grid parameterization method and axial flow turbine aerodynamic optimization design method based on grid parameterization method | |
| CN108549773B (en) | Grid parameterization method and turbine blade multidisciplinary reliability design optimization method based on grid parameterization method | |
| CN110727995B (en) | Blade shape construction method, blade, and computer device | |
| CN115081130B (en) | Blade and end wall combined aerodynamic optimization method based on dynamic support vector regression | |
| Chi et al. | Multi-dimensional platform for cooling design of air-cooled turbine blades | |
| Gra¨ sel et al. | A full parametric model for turbomachinery blade design and optimisation | |
| CN114861315B (en) | Turbine two-dimensional blade profile optimization method based on machine learning | |
| CN115374576B (en) | Integrated stability expansion design method for treatment of compressor blade and casing | |
| CN110414168B (en) | Hypersonic velocity isolation section design method and system based on coupling optimization with front fuselage | |
| CN108799199A (en) | The design method of high load capacity allowance camber is adjustable tandem cascade | |
| CN113094964B (en) | Method and device for generating blade machining coordinates | |
| CN113250755B (en) | Blade profile design method based on non-uniform rational B-spline curve and blade | |
| CN106874526A (en) | The generation method and device of the production coordinate of turbine blade | |
| Cheng et al. | A phased aerodynamic optimization method for compressors based on multi-degrees-of-freedom surface parameterization | |
| CN112199777A (en) | Method suitable for modeling bionic leading edge flow field characteristics | |
| CN113886979A (en) | Two-dimensional blade profile modeling method, blade optimization method and two-dimensional blade profile | |
| Çelebioğlu et al. | Development and implementation of a methodology for reverse engineering design of Francis turbine runners | |
| CN116882051A (en) | High-ultra-internal-rotation type air inlet channel pneumatic optimization design method based on discrete accompaniment | |
| Luers et al. | Adjoint-based volumetric shape optimization of turbine blades | |
| CN105909316A (en) | Blade body structure of super-long last-stage rotor blade of large-scale steam turbine | |
| Popov et al. | Optimization algorithm for axial multistage compressor workflow | |
| Alnaga et al. | Optimal design of hydraulic turbine distributor | |
| CN113486512A (en) | Flutter analysis method for functional gradient variable-thickness blade model | |
| Milli et al. | Full-parametric design system to improve the stage efficiency of a high-fidelity HP turbine configuration | |
| CN113268828B (en) | Turbine blade asymmetric leading edge structure optimization design method based on uniform design |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |