CN115238419A - Axial flow compressor blade design method based on composite material - Google Patents

Axial flow compressor blade design method based on composite material Download PDF

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CN115238419A
CN115238419A CN202210961501.0A CN202210961501A CN115238419A CN 115238419 A CN115238419 A CN 115238419A CN 202210961501 A CN202210961501 A CN 202210961501A CN 115238419 A CN115238419 A CN 115238419A
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blade
composite material
axial flow
model
flow compressor
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刘志远
王军利
冯钰茹
李金洋
张宝升
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Shaanxi University of Technology
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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
    • 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
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/26—Composites
    • 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
    • G06F2119/02—Reliability analysis or reliability optimisation; Failure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]

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Abstract

The invention provides a composite material-based axial flow compressor blade design method, which belongs to the field of computer-aided modeling and comprises the following steps: deriving coordinate points of the profile of a plurality of airfoils of the axial flow compressor blade; introducing coordinate points of the outline of the plurality of wing profiles into three-dimensional modeling software to form spline curves of the plurality of wing profile sections, connecting the plurality of spline curves with each other, and forming a three-dimensional model of the blade by sewing; finding out the middle camber lines of a plurality of spline curves, and generating a middle plane on the geometric thickness of the blade by connecting the plurality of middle camber lines; taking the middle plane as a reference to carry out composite material layering, and generating a composite material solid model of the blade by adopting a stretching algorithm on the layered middle plane; and cutting and correcting the composite material entity model of the blade by using the three-dimensional model of the blade to generate the axial flow compressor blade three-dimensional model based on the composite material. The method can be used for quickly carrying out the layering design of the composite material on the blade with a certain torsion angle.

Description

Axial flow compressor blade design method based on composite material
Technical Field
The invention belongs to the technical field of computer assistance, and particularly relates to a composite material-based axial flow compressor blade design method.
Background
The most basic unit of a composite material is a ply, which is a unidirectional layer of composite material formed from one unidirectional tape or fabric of composite material, typically pressed from two or more layers. The composite material can change the elastic modulus and the strength by adjusting the directions of the layers, so that the service strength of the blade is improved.
At present, in the aspect of compressor blade structure design, a systematic layering modeling method is not available in China, only a certain layering method is available according to a model of a certain model, and systematization is not formed. Because the sections of the blades of the air compressor are complex, the chord lengths, the twist angles and the wing profiles of the blades of different types are different, and with the more complex structure of the layer fiber layer, the modeling of the blades made of the composite material is very complex due to different layer angles, layer sequences and layer thicknesses.
At present, no reliable design mode exists in the layering modeling of the composite material of the blade of the axial flow compressor in China.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides a composite material-based axial flow compressor blade design method.
In order to achieve the above purpose, the invention provides the following technical scheme:
a method for designing an axial flow compressor blade based on a composite material comprises the following steps:
deriving coordinate points of the profile of a plurality of airfoils of the axial flow compressor blade;
introducing coordinate points of the outline of the plurality of wing profiles into three-dimensional modeling software to form spline curves of the plurality of wing profile sections, connecting the plurality of spline curves with each other, and forming a three-dimensional model of the blade by sewing;
finding out middle camber lines of a plurality of spline curves, generating a middle plane on the geometric thickness of the blade by connecting the plurality of middle camber lines, and meshing the middle plane;
laying a composite material by taking the middle plane after grid division as a reference to form a composite material laying layer, and generating a composite material solid model of the blade by adopting a stretching algorithm on the laid middle plane;
and cutting and correcting the composite material entity model of the blade by using the three-dimensional model of the blade to generate the axial flow compressor blade three-dimensional model based on the composite material.
Preferably, the deriving of the coordinate points of the profile of the multiple airfoils of the axial flow compressor blade specifically includes the following steps:
calculating and deriving two-dimensional coordinate points of the outline of a plurality of airfoils of the blades of the axial flow compressor by interpolating airfoil design software Profile;
converting the two-dimensional coordinates into three-dimensional coordinates of the wing profile through a coordinate transformation formula of the wing profile;
and saving the three-dimensional coordinate data of the airfoil profile into a TXT format file.
Preferably, the coordinate transformation formula of the airfoil profile is:
(x 1 ,y 1 )＝(x 0 ,y 0 )-(X,Y)
x 2 ＝x 1 ×c×cosθ-y 1 ×c×sinθ
y 2 ＝y 1 ×c×cosθ-y 1 ×c×sinθ
z 2 ＝r
in the formula (x) 0 ,y 0 ) The original coordinates of the airfoil, (X, Y) the coordinates of the intersection of the hub and the chord line, (X) 1 ,y 1 ) For the two-dimensional coordinates of the airfoil prior to transformation, (x) 2 ,y 2 ,z 2 ) C is the chord length of each airfoil section, theta is the twist angle of each airfoil section, and r is the distance from the airfoil section to the blade root.
Preferably, the three-dimensional model of the blade is constructed in three-dimensional modeling software SOLIDWORKS, specifically comprising the steps of:
importing the TXT file into SOLIDWORKS in an XYZ point curve mode to generate spline curves of a plurality of airfoil sections;
adopting a lofting curve command for the plurality of spline curves to generate a basic model of the blade;
filling curves of the blade root and the blade tip of the blade to form a cross section through a curve filling command;
and (4) sewing the filled section through a curved surface sewing command to generate a three-dimensional model of the complete blade.
Preferably, the method for generating the intermediate plane on the geometric thickness of the blade in the three-dimensional modeling software SOLIDWORKS specifically comprises the following steps:
respectively finding out the middle camber lines of the spline curves of the multiple airfoil sections in SOLIDWORKS, so that a connecting line from the front edge to the tail edge can be obtained in the spline curve of each airfoil section;
generating a surface according to the connecting lines, wherein the surface is a middle plane on the geometric thickness of the blade;
and meshing the middle plane on the geometric thickness of the blade to form a middle plane mesh.
Preferably, the composite material solid model of the blade is generated in finite element analysis software ANSYS works bench, comprising in particular the steps of:
in ANSYS WORKBENCH, an ACP module is adopted, and a middle plane after grid division is used as a standard of the laying layer;
arranging fiber Fabric and laminated plates in an ACP module according to materials and a layering scheme, wherein a coordinate system Rosettes selects a trailing coordinate system; a reference point is designated on a middle plane on the geometric thickness of the blade, the normal direction Z of the unit is taken as a laying direction, and fiber cloth is laid from the middle surface of the blade to two opposite directions of a suction surface and a pressure surface; wherein, the X direction is the layering direction of the thickness of the composite material, and the Y direction is the reference direction of the direction selection set, namely the layering direction of 0 degree;
stacking the layering primitives to generate a Modeling combined Modeling group, and then generating a composite material entity model of the blade by adopting a stretching algorithm according to the layering definition information of the mid-plane grid and the composite material.
Preferably, the method for generating the composite-material-based axial-flow compressor blade three-dimensional model in finite element analysis software ANSYS works bench specifically comprises the following steps:
importing the three-dimensional model of the blade into a Geometry module to generate a Virtual Geometry model; the Geometry module belongs to a pretreatment module ACP-pre of composite material analysis of ANSYS WORKBENCH;
cutting the composite material solid model of the blade by using a Virtual geometric model Virtual Geometries and a cut-off command to obtain the composite material solid model of the cut blade;
and importing a three-dimensional model outline of the complete blade, and attaching the composite material entity model of the cut blade to the complete blade model outline by adopting a Snap command to obtain the three-dimensional model of the axial flow compressor blade based on the composite material.
The design method of the axial flow compressor blade based on the composite material has the following beneficial effects:
after the middle plane on the geometric thickness of the blade is subjected to grid division, a composite material solid model of the blade is generated through a stretching algorithm, so that the method is simple, quick, convenient and fast, and meanwhile, certain precision can be ensured, and the reliability of a calculation result is ensured; the three-dimensional model of the blade is combined with the solid model of the composite material of the blade, so that the layering design of the composite material can be quickly and conveniently carried out on the blade with a certain torsion angle, the modeling time is greatly shortened, and meanwhile, the calculation precision is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention and the design thereof, the drawings required for the embodiments will be briefly described below. The drawings in the following description are only some embodiments of the invention and it will be clear to a person skilled in the art that other drawings can be derived from them without inventive effort.
FIG. 1 is a flow chart of a composite material based axial flow compressor blade design method according to embodiment 1 of the present invention;
FIG. 2 is a schematic view of a plurality of airfoil sections of an axial compressor blade;
FIG. 3 is a three-dimensional model of a blade;
FIG. 4 is a flow chart of establishing a mid-plane over the geometric thickness of an axial compressor blade;
FIG. 5 is a reference frame diagram of a fiber lay;
FIG. 6 is a composite material solid model of the resulting blade after stretching through a mid-plane over the geometric thickness of the blade;
fig. 7 is a three-dimensional model of a cut composite-based axial flow compressor blade.
Detailed Description
In order that those skilled in the art will better understand the technical solutions of the present invention and can practice the same, the present invention will be described in detail with reference to the accompanying drawings and specific examples. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.
Example 1
The invention provides a composite material-based axial flow compressor blade design method, which comprises the following steps of:
step 1, deriving coordinate points of the outline of a plurality of airfoils of the axial flow compressor blade, wherein the airfoils refer to an integral frame of the axial flow compressor blade.
In this embodiment, the derivation process specifically includes the following steps:
step 1-1, carrying out interpolation calculation through airfoil design software Profili and deriving two-dimensional coordinate points of the outline of each airfoil of the axial flow compressor blade.
And 1-2, converting the two-dimensional coordinate into a three-dimensional coordinate of the wing profile through a coordinate conversion formula of the wing profile.
And 1-3, storing the three-dimensional coordinate data of the airfoil profile into a TXT format file.
In this embodiment, in step 1-2, the coordinate transformation formula of the airfoil profile is:
(x 1 ,y 1 )＝(x 0 ,y 0 )-(X,Y)
x 2 ＝x 1 ×c×cosθ-y 1 ×c×sinθ
y 2 ＝y 1 ×c×cosθ-y 1 ×c×sinθ
z 2 ＝r
in the formula (x) 0 ,y 0 ) The original coordinates of the airfoil, (X, Y) the coordinates of the intersection of the hub and the chord line, (X) 1 ,y 1 ) For the two-dimensional coordinates of the airfoil prior to transformation, (x) 2 ,y 2 ,z 2 ) C is the chord length of each airfoil section, theta is the twist angle of each airfoil section, and r is the distance from the airfoil section to the blade root.
And 2, introducing coordinate points of the outline of the airfoil profiles into three-dimensional modeling software in an XYZ point curve mode to form spline curves of the airfoil sections, connecting the spline curves and sewing to form a three-dimensional model of the blade, wherein the three-dimensional model of the blade is used for cutting the layered composite material at the later stage.
In this embodiment, referring to fig. 2 and 3, step 2 is to construct a three-dimensional model of a blade in three-dimensional modeling software SOLIDWORKS, and specifically includes the following steps:
and 2-1, importing the TXT file which stores the three-dimensional coordinate data of the airfoil profile into SOLIDWORKS in an XYZ point curve mode, and generating spline curves of a plurality of airfoil profile sections.
And 2-2, generating a basic model of the blade by adopting a lofting curve command for the spline curves in the three-dimensional modeling software.
And 2-3, filling curves of the blade root and the blade tip of the blade through a filling curve command to form a section filling.
And 2-4, generating a three-dimensional model of the complete blade by the filled section through a curved surface sewing command.
And 3, finding out the middle arc lines of the spline curves of the multiple airfoil sections in three-dimensional modeling software, generating a middle plane on the geometric thickness of the blade by connecting the multiple middle arc lines, and meshing the middle plane to form a middle plane mesh.
In this embodiment, referring to fig. 4, step 3 is to generate a middle plane on the geometric thickness of the blade in the three-dimensional modeling software SOLIDWORKS, and specifically includes the following steps:
and 3-1, respectively finding out the middle camber lines of the spline curves of the multiple airfoil sections in SOLIDWORKS, so that a connecting line from the leading edge to the trailing edge can be obtained in the spline curve of each airfoil section.
And 3-2, generating a surface according to the connecting lines, wherein the surface is a middle plane on the geometric thickness of the compressor blade.
And 3-3, performing meshing on the middle plane on the geometric thickness of the blade to form a middle plane mesh.
And 4, laying a composite material by taking the middle plane after grid division as a reference to form a composite material laying layer, and generating a composite material solid model of the blade by using the middle plane after laying according to the middle plane grid and the composite material laying layer definition information by adopting a stretching algorithm.
In this embodiment, referring to fig. 5 and 6, step 4 is to generate a composite material solid model of the blade in the finite element analysis software ANSYS works bench, and specifically includes the following steps:
and 4-1, adopting an ACP module in ANSYS WORKBENCH software, and taking the middle plane obtained in the step 3-3 as the reference of the layer laying.
And 4-2, arranging the fiber Fabric and the laminated plates in the ACP module according to the material and the layering scheme, wherein a random coordinate system is selected as a coordinate system Rosettes. And designating a reference point on the middle plane after grid division, taking the normal direction Z of the unit as a laying direction, and laying the fiber cloth from the middle surface of the blade to two opposite directions of the suction surface and the pressure surface respectively. Wherein, the X direction is the layering direction of the thickness of the composite material, and the Y direction is the reference direction of the direction selection set, namely the layering direction of 0 degree.
And 4-3, stacking the layer primitives to generate a Modeling group (Modeling group), and generating a composite material entity model of the blade by adopting a stretching algorithm according to the layer definition information of the mid-plane grid and the composite material.
And 5, cutting and correcting the composite material solid model of the blade by using the three-dimensional model of the blade obtained in the step 2 to generate the three-dimensional model of the axial flow compressor blade based on the composite material.
In this embodiment, referring to fig. 7, step 5 is to generate a three-dimensional model of an axial flow compressor blade based on a composite material in finite element analysis software ANSYS works research, and specifically includes the following steps:
step 5-1, importing the complete three-dimensional model of the blade in the step 2-4 into a Geometry module to generate a Virtual geometric model; the Geometry module belongs to the preprocessing module ACP-pre of composite analysis of ANSYS WORKBENCH.
And 5-2, cutting the composite material entity model of the blade generated in the step 4-3 by using the Virtual geometric models generated in the step 5-1 by using a cut-off command to obtain the composite material entity model of the cut blade.
And 5-3, importing the outline of the three-dimensional model of the complete blade, and attaching the composite material entity model of the blade obtained in the step 5-2 to the outline of the complete blade by adopting a Snap command to finally obtain the three-dimensional model of the axial flow compressor blade based on the composite material.
The modeling and composite material layering method for the blades of the axial-flow compressor, provided by the embodiment, can be used for layering composite materials for blades with twist angles. After the mesh division is carried out on the middle plane on the geometric thickness of the blade, the composite material solid model of the blade is generated through a stretching algorithm, the method is simple and quick, meanwhile, certain precision can be guaranteed, and the reliability of a calculation result is guaranteed. Meanwhile, the method can be used for quickly and conveniently designing the layering of the composite material for the blade with a certain torsion angle, and compared with the traditional layering modeling mode, the method greatly shortens the modeling time and improves the calculation precision.
The above-mentioned embodiments are only preferred embodiments of the present invention, and the scope of the present invention is not limited thereto, and any simple modifications or equivalent substitutions of the technical solutions that can be obviously obtained by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.

Claims (7)

1. A design method of an axial flow compressor blade based on composite materials is characterized by comprising the following steps:
deriving coordinate points of the profile of a plurality of airfoils of the axial flow compressor blade;
introducing coordinate points of the outline of the plurality of wing profiles into three-dimensional modeling software to form spline curves of the plurality of wing profile sections, connecting the plurality of spline curves with each other, and forming a three-dimensional model of the blade by sewing;
finding out middle camber lines of a plurality of spline curves, generating a middle plane on the geometric thickness of the blade by connecting the plurality of middle camber lines, and meshing the middle plane;
laying a composite material by taking the middle plane after grid division as a reference to form a composite material laying layer, and generating a composite material solid model of the blade by adopting a stretching algorithm on the middle plane after laying;
and cutting and correcting the composite material entity model of the blade by using the three-dimensional model of the blade to generate the composite material-based axial flow compressor blade three-dimensional model.
2. The method for designing axial flow compressor blades based on composite materials according to claim 1, wherein the deriving of coordinate points of the profile of a plurality of airfoils of an axial flow compressor blade specifically comprises the following steps:
calculating and deriving two-dimensional coordinate points of the outline of a plurality of airfoils of the blades of the axial flow compressor by interpolating airfoil design software Profile;
converting the two-dimensional coordinates into three-dimensional coordinates of the wing profile through a coordinate transformation formula of the wing profile;
and saving the three-dimensional coordinate data of the wing profile into a TXT format file.
3. The composite-based axial flow compressor blade design method of claim 2, wherein the coordinate transformation formula of the airfoil is:
(x 1 ,y 1 )＝(x 0 ,y 0 )-(X,Y)
x 2 ＝x 1 ×c×cosθ-y 1 ×c×sinθ
y 2 ＝y 1 ×c×cosθ-y 1 ×c×sinθ
z 2 ＝r
wherein (x) 0 ,y 0 ) Is the original coordinate of the airfoil, and (X, Y) is the intersecting coordinate of the hub and the chord line, and (X) 1 ,y 1 ) For the two-dimensional coordinates of the airfoil before transformation, (x) 2 ,y 2 ,z 2 ) And c is the chord length of each airfoil section, theta is the twist angle of each airfoil section, and r is the distance from the airfoil section to the blade root.
4. The composite material-based axial flow compressor blade design method as claimed in claim 3, wherein the construction of the three-dimensional model of the blade in three-dimensional modeling software SOLIDWORKS specifically comprises the following steps:
importing the TXT file into SOLIDWORKS in an XYZ point curve mode to generate spline curves of a plurality of airfoil sections;
generating a basic model of the blade by adopting a lofting curve command for the spline curves;
filling curves of a blade root and a blade tip of the blade through a filling curve command to form a section;
and sewing the filled section through a curved surface sewing command to generate a three-dimensional model of the complete blade.
5. The composite-based axial compressor blade design method as claimed in claim 4, wherein generating a mid-plane in the blade geometric thickness in three-dimensional modeling software SOLIDWORKS, comprises the following steps:
respectively finding out the middle camber lines of the spline curves of the plurality of airfoil sections in SOLIDWORKS, so that a connecting line from the leading edge to the trailing edge can be obtained in the spline curve of each airfoil section;
generating a surface according to the connecting lines, wherein the surface is a middle plane on the geometric thickness of the blade;
and meshing the middle plane on the geometric thickness of the blade to form a middle plane mesh.
6. The composite-based axial flow compressor blade design method as claimed in claim 5, wherein generating a composite material solid model of the blade in finite element analysis software ANSYS WORKBENCH, comprises the steps of:
in ANSYS WORKBENCH, an ACP module is adopted, and a middle plane after grid division is used as a standard of layering;
arranging fiber Fabric and laminated plates in an ACP module according to materials and a layering scheme, wherein a coordinate system Rosettes selects a trailing coordinate system; a reference point is designated on the middle plane after the grid division, the normal direction Z of the unit is taken as a laying direction, and the fiber cloth is laid from the middle surface of the blade to two opposite directions of the suction surface and the pressure surface; wherein the X direction is the layering direction of the thickness of the composite material, and the Y direction is the reference direction of the direction selection set, namely the layering direction of 0 degree;
stacking the layer primitives to generate a Modeling combined Modeling group, and then generating a composite material entity model of the blade by adopting a stretching algorithm according to the layer definition information of the mid-plane grid and the composite material.
7. The method for designing axial flow compressor blades based on composite materials as claimed in claim 6, wherein the three-dimensional model of the axial flow compressor blades based on composite materials is generated in finite element analysis software ANSYS WORKBENCH, and comprises the following steps:
importing the three-dimensional model of the blade into a Geometry module to generate a Virtual Geometry model; the Geometry module belongs to a pretreatment module ACP-pre of composite material analysis of ANSYS WORKBENCH;
cutting the composite material solid model of the blade by using a Virtual geometric model Virtual Geometries and a cut-off command to obtain the composite material solid model of the cut blade;
and importing a three-dimensional model outline of the complete blade, and attaching the composite material entity model of the cut blade to the complete blade model outline by adopting a Snap command to obtain the three-dimensional model of the axial flow compressor blade based on the composite material.
CN202210961501.0A 2022-08-11 2022-08-11 Axial flow compressor blade design method based on composite material Withdrawn CN115238419A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116522546A (en) * 2023-07-04 2023-08-01 太原理工大学 Container configuration reverse solving method for uniformly removing blade part through barreling finishing
CN117332532A (en) * 2023-12-01 2024-01-02 陕西空天信息技术有限公司 Method and device for constructing axial flow impeller mechanical blade model

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116522546A (en) * 2023-07-04 2023-08-01 太原理工大学 Container configuration reverse solving method for uniformly removing blade part through barreling finishing
CN116522546B (en) * 2023-07-04 2023-09-15 太原理工大学 Container configuration reverse solving method for uniformly removing blade part through barreling finishing
CN117332532A (en) * 2023-12-01 2024-01-02 陕西空天信息技术有限公司 Method and device for constructing axial flow impeller mechanical blade model
CN117332532B (en) * 2023-12-01 2024-03-08 陕西空天信息技术有限公司 Method and device for constructing axial flow impeller mechanical blade model

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Application publication date: 20221025