CN115081280B - Automatic establishment method of H-shaped rib hollow fan blade finite element model - Google Patents
Automatic establishment method of H-shaped rib hollow fan blade finite element model Download PDFInfo
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Abstract
An automatic establishment method of a finite element model of an H-shaped rib hollow fan blade belongs to the technical field of finite element automatic modeling. The automatic establishment method of the H-shaped rib hollow fan blade finite element model comprises the following steps: step 1, determining design parameters, wherein the design parameters comprise solid blade shape data and internal characteristic parameters of the blade; step 2, dividing the blade into a solid section, a transition section, a hollow section, a transition section and a solid section along the radial direction; step 3, establishing finite element models of hollow sections and solid sections of the blade; step 4, establishing a finite element model of the blade transition section; step 5, establishing a finite element model of the blade: and combining the finite element models of the solid segment, the transition segment, the hollow segment, the transition segment and the solid segment of the blade to obtain the finite element model of the blade. The automatic building method of the H-shaped rib hollow fan blade finite element model can quickly build the finite element models of various H-shaped rib structures directly used for calculation and hollow blades with similar structures.
Description
Technical Field
The invention relates to the technical field of finite element automatic modeling, in particular to an automatic building method of an H-shaped rib hollow fan blade finite element model.
Background
Currently, fan blade modeling approaches with truss core structures have tended to be mature. For fan blades with coreless structures, the reinforcing ribs are positioned in the hollow area of the blade body, the upper boundary of the cavity, the lower boundary of the cavity, the front edge of the cavity and the rear edge of the cavity are integrated with the blade body, and the shape of other parts is required to be changed along with the free curved surface of the twisted profile blade body, so that the complicated calculation deduction and the high-difficulty modeling required by the layout of the reinforcing ribs are caused.
The existing common design method of the hollow fan blade of the aeroengine is usually to model through CAD software, then to conduct grid division and strength calculation through finite element calculation software, if the strength requirement is not met, parameters are required to be adjusted to model again, and the method is circulated so as to achieve the strength requirement. Therefore, the structural design of the blade needs to carry out a large number of repeated modeling works on the model, and if a conventional method is adopted, the model needs to be redrawn from the beginning each time, so that the workload is high.
Therefore, the application provides an automatic establishment method of the finite element model of the H-shaped rib hollow fan blade, so as to solve the problems.
Disclosure of Invention
In order to solve the technical problems that in the design of H-shaped rib hollow fan blades, a finite element model needs to be repeatedly built for strength calculation and the like in the prior art, the invention provides an automatic building method of the H-shaped rib hollow fan blade finite element model, which can quickly build various H-shaped rib structures directly used for calculation and finite element models of hollow blades with similar structures, and greatly shortens modeling and calculating time.
In order to achieve the above object, the technical scheme of the present invention is as follows:
An automatic establishment method of an H-shaped rib hollow fan blade finite element model comprises the following steps:
Step 1, determining design parameters:
the design parameters comprise solid blade shape data and blade internal characteristic parameters;
Step 2, radially segmenting the blade:
dividing the blade into a solid section, a transition section, a hollow section, a transition section and a solid section along the radial direction;
specifically, the specific way of segmenting the blade along the radial direction is as follows:
the cross section at the upper boundary of the cavity is S2', and the cross section at the lower boundary of the cavity is S2;
the section S2 'of the upper boundary of the cavity is offset to one side of the cavity by a set distance to obtain a section S1';
the section S2 'of the upper boundary of the cavity is offset to the tip direction by a set distance to obtain a section S3';
The section S2 of the lower boundary of the cavity is offset to one side of the cavity by a set distance to obtain a section S1;
the section S2 of the lower boundary of the cavity is offset to the blade root direction by a set distance to obtain a section S3;
taking sections S3, S1 'and S3' as sectional sections, and dividing the blade into a solid section, a transition section, a hollow section, a transition section and a solid section along the radial direction;
step 3, establishing a finite element model of the hollow section and the solid section of the blade:
step 3.1, building a two-dimensional structure of each section of the solid section and the hollow section of the blade:
a plurality of layers of cavity sections along the chord direction of the blade are arranged on the solid section and the hollow section;
constructing a two-dimensional structure of each cavity section of the solid section and the hollow section of the blade according to the internal characteristic parameters of the blade;
Step 3.2, dividing the two-dimensional structure of each cavity section of the solid section and the hollow section into a section solid area, a section wallboard area and a section fillet area along the chord direction;
Specifically, the cross-section fillet area is an area formed by a transition fillet and a solid part in a set range outside the transition fillet; the cross-section solid area is an area between the front edge of the blade and an adjacent cross-section fillet area, and an area between the rear edge of the blade and an adjacent cross-section fillet area; the cross-sectional wall panel area is the area between two cross-sectional fillet areas located on the same cavity.
Step 3.3, distributing the grid layer number for the solid segment and the hollow segment of the blade:
Specifically, the specific mode for distributing the grid layer number for the solid section and the hollow section of the blade is as follows: the grid layer number of the cross-section solid area along the chord direction is NX1, and the grid layer number along the thickness direction is NY1; the grid layer number of the cross-section wallboard area along the chord direction is NX2, and the grid layer number along the thickness direction is NY2; the grid layer number of the cross-section fillet area along the chord direction is NX3, and the grid layer number along the thickness direction is NY3; and, for each cavity section two-dimensional structure of a solid segment of the blade, ny1=ny2=ny3; for each cavity section two-dimensional structure of the hollow section of the blade, ny1=ny3;
the grid layer number NZ1 of the hollow section of the blade along the radial direction; the grid layer number NZ2 of the solid sections of the blade along the radial direction;
step 3.4, establishing finite element models of hollow sections and solid sections of the blade;
Establishing quadrilateral grids on the two-dimensional structures of each cavity section of the hollow section and the solid section of the blade;
Connecting quadrilateral grids of two adjacent layers of cavity section two-dimensional structures to obtain hexahedral grids of hollow sections and solid sections of the blade;
sequencing hexahedral meshes to obtain finite element models of hollow sections and solid sections of the blades;
Specifically, the concrete mode for establishing the quadrilateral mesh in the two-dimensional structure of each cavity section of the hollow section of the blade is as follows:
Establishing quadrilateral grids for the solid area of the cross section and the wallboard area of the cross section by a chessboard type dividing method;
For the section fillet area, dividing the section fillet area into a leaf basin side fillet area and a leaf back side fillet area by taking a mean camber line L M as a boundary, and establishing a quadrilateral grid on the leaf basin side fillet area and the leaf back side fillet area by adopting a Y-shaped dicing method;
Combining the quadrilateral grids of the cross section solid area, the cross section wallboard area and the cross section fillet area and sequencing the quadrilateral grids in the sequence from the front edge of the blade to the rear edge of the blade along the chord direction to obtain the quadrilateral grid of each cavity cross section two-dimensional structure of the hollow section of the blade;
specifically, the concrete mode for establishing the quadrilateral mesh in each cavity section two-dimensional structure of the solid section of the blade is as follows:
establishing quadrilateral grids in a chessboard dividing method in a section solid area, a section wallboard area and a section fillet area of each cavity section two-dimensional structure of the solid section of the blade, combining the quadrilateral grids in the three areas and sequencing the quadrilateral grids in a sequence from the front edge of the blade to the rear edge of the blade along the chord direction to obtain the quadrilateral grids of each cavity section two-dimensional structure of the solid section of the blade;
step 4, establishing a finite element model of the blade transition section:
step 4.1, establishing a transition section three-dimensional model, wherein the transition section three-dimensional model comprises a transition section solid three-dimensional region, a transition section wallboard three-dimensional region and a transition section fillet three-dimensional region;
Specifically, the specific mode for establishing the transition section three-dimensional model is as follows:
The transition section is positioned at the blade root part, three-dimensional filling is carried out between the section S1 and the corresponding section solid area, section wallboard area and section fillet area on the section S3 to form a transition section solid three-dimensional area, a transition section wallboard three-dimensional area and a transition section fillet three-dimensional area, and the transition section solid three-dimensional area, the transition section wallboard three-dimensional area and the transition section fillet three-dimensional area are combined to form a transition section three-dimensional model of the blade root part;
The transition section positioned at the blade tip part is subjected to three-dimensional filling between a section S1 'and a corresponding section solid area, a section wallboard area and a section fillet area on a section S3' to form a transition section solid three-dimensional area, a transition section wallboard three-dimensional area and a transition section fillet three-dimensional area, and the transition section solid three-dimensional area, the transition section wallboard three-dimensional area and the transition section fillet three-dimensional area are combined to form a transition section three-dimensional model of the blade tip part;
step 4.2, distributing the grid layer number for the transition section;
specifically, the specific mode of allocating the grid layer number for the transition section is as follows:
The grid layer number of the transition section solid three-dimensional region along the chord direction is NX1, and the grid layer number along the thickness direction is NY1;
the grid layer number of the three-dimensional area of the wall plate of the transition section along the chord direction is NX2, and the grid layer number along the thickness direction is NY4 or NY5, wherein NY4=NY2, NY5=NY1=NY3;
The grid layer number of the transition section fillet three-dimensional region along the chord direction is NX3, and the grid layer number along the thickness direction is NY3;
The number of grid layers of the solid three-dimensional area of the transition section, the wallboard three-dimensional area of the transition section and the fillet three-dimensional area of the transition section along the radial direction is NZ3;
The number of distribution grid layers of the transition section three-dimensional model of the blade root part is the same as that of the transition section three-dimensional model of the blade tip part;
Specifically, nz3=nx3.
Step 4.3, respectively establishing hexahedral meshes for the three-dimensional area of the wall plate of the transition section, the solid three-dimensional area of the transition section and the three-dimensional area of the round corner of the transition section;
(1) The concrete mode for establishing the hexahedral mesh for the three-dimensional area of the wall plate of the transition section is as follows:
A plurality of layers of transition section wallboard sections extending along the radial direction and the thickness direction of the blade are arranged in the three-dimensional area of the transition section wallboard; dividing the wall plate section of each layer of transition section into a wall plate leaf basin side fillet subregion and a wall plate leaf back side fillet subregion by taking a mean camber line L M as a boundary line, and establishing a quadrilateral grid on the wall plate leaf basin side fillet subregion and the wall plate leaf back side fillet subregion by adopting a Y-type dicing method;
Connecting quadrilateral grids of the sections of every two adjacent layers of transition section wall plates to obtain a hexahedral grid of the three-dimensional area of the blade transition section wall plate;
(2) The concrete mode for establishing the hexahedral mesh for the solid three-dimensional area of the transition section is as follows:
a plurality of layers of solid sections of the transition section extending along the radial direction and the thickness direction of the blade are arranged in the solid three-dimensional area of the transition section;
establishing a quadrilateral grid on the solid section of the transition section by a chessboard type dividing method;
connecting quadrilateral grids with solid sections of every two adjacent layers of transition sections to obtain solid area hexahedral grids of the blade transition sections;
(3) The concrete mode for establishing the hexahedral mesh for the transition section fillet three-dimensional area is as follows:
Dividing a three-dimensional region of the transition section fillet into a three-dimensional region of the leaf basin side fillet and a three-dimensional region of the leaf back side fillet by taking a mean camber line L M as a boundary line, and establishing a hexahedral mesh in the three-dimensional region of the leaf basin side fillet and the three-dimensional region of the leaf back side fillet;
Step 4.4, combining hexahedral grids of the solid three-dimensional area of the transition section, the three-dimensional area of the wall plate of the transition section and the three-dimensional area of the fillet of the transition section, and sequencing the hexahedral grids in the sequence from the front edge of the blade to the rear edge of the blade along the chord direction to obtain a finite element model of the transition section of the blade;
Step 5, establishing a finite element model of the blade:
And combining the finite element models of the solid sections, the transition sections, the hollow sections, the transition sections and the solid sections of the blade according to the sequence from the blade root to the blade tip to obtain the finite element model of the blade.
The invention has the beneficial effects that:
1) The automatic establishment method of the H-shaped rib hollow fan blade finite element model realizes parameterized automatic modeling, and the parameterized automatic modeling process is as follows: the finite element model of the H-shaped rib hollow fan blade can be quickly and automatically built by setting design parameters, the grid layer number of the solid sections and the hollow sections of the blade and the radial grid layer number NZ3 of the transition section, and the geometric model of the H-shaped rib hollow fan blade can be better closed, and has better fairing property;
2) According to the invention, the density of the blade grids can be flexibly adjusted by setting the grid layer number of the solid segments and the hollow segments, the hexahedral grid is established in a set grid division mode and a combination sequence, the grid subdivision efficiency and precision are ensured, and the method is widely applicable to calculation of hollow blades with various H-shaped rib structures and similar structures;
3) The automatic establishment method of the H-shaped rib hollow fan blade finite element model is applied to design projects, so that modeling and calculating time is greatly shortened, and a good effect is achieved.
Additional features and advantages of the invention will be set forth in part in the detailed description which follows.
Drawings
FIG. 1 is a schematic view of an H-bar hollow fan blade according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a two-dimensional structure of a cavity cross-section on a solid section and a hollow section provided by an embodiment of the present invention;
FIG. 3 is a schematic view of a cross-sectional mesh of hollow sections provided by an embodiment of the present invention;
FIG. 4 is a schematic illustration of a solid segment cross-sectional grid provided by an embodiment of the present invention;
FIG. 5 is a schematic view of a first embodiment of a transition piece grid at a root portion;
FIG. 6 is a second exemplary embodiment of a transition piece grid at a root portion;
FIG. 7 is a schematic view of a transition section portion taken along section A in FIG. 6;
FIG. 8 is a schematic diagram of a quadrilateral mesh established by a Y-shaped dicing method according to an embodiment of the present invention;
Fig. 9 is a schematic diagram of dividing a stereoscopic region of a side fillet of a leaf basin into a plurality of stereoscopic subregions according to an embodiment of the present invention;
Fig. 10 is a schematic diagram one of a hexahedral mesh set up in a stereoscopic region of a side fillet of a leaf basin according to an embodiment of the present invention;
Fig. 11 is a schematic diagram II of a hexahedral mesh established in a stereoscopic area of a side fillet of a leaf basin according to an embodiment of the present invention;
FIG. 12 is a grid schematic of an H-bar hollow fan blade provided in an embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention.
In order to solve the problems in the prior art, as shown in fig. 1 to 12, the invention provides an automatic establishment method of a finite element model of an H-shaped rib hollow fan blade, which comprises the following steps:
Step 1, determining design parameters:
As shown in fig. 1, given solid blade shape data and internal characteristic parameters of the blade, determining a solid model of the solid blade according to the solid blade shape data;
in this embodiment, the internal characteristic parameters of the blade include the distance from the upper boundary of the cavity to the blade tip, the distance from the lower boundary of the cavity to the blade root, the thickness D of the skin panel of the section, the width B of the stiffener, the number N of the stiffener and the radius of the transition fillet; the transition fillet radius comprises a transition fillet radius R1 of the front edge of the cavity, a transition fillet radius R2 between the reinforcing rib and the inner wall surface of the skin and a transition fillet radius R3 of the rear edge of the cavity.
Step 2, radially segmenting the blade:
dividing the blade into a solid section, a transition section, a hollow section, a transition section and a solid section along the radial direction;
as shown in fig. 1, the specific way to segment the blade in the radial direction is:
the cross section at the upper boundary of the cavity is S2', and the cross section at the lower boundary of the cavity is S2;
the section S2 'of the upper boundary of the cavity is offset to one side of the cavity by a set distance to obtain a section S1'; in this embodiment, the cross section S2' of the upper boundary of the cavity biases the transition fillet radius R2 toward one side of the cavity;
the section S2 'of the upper boundary of the cavity is offset to the tip direction by a set distance to obtain a section S3'; in this embodiment, the cross section S2' of the upper boundary of the cavity is offset by the transition fillet radius R2 in the tip direction;
the section S2 of the lower boundary of the cavity is offset to one side of the cavity by a set distance to obtain a section S1; in this embodiment, the cross section S2 of the lower boundary of the cavity biases the transition fillet radius R2 toward one side of the cavity;
The section S2 of the lower boundary of the cavity is offset to the blade root direction by a set distance to obtain a section S3; in this embodiment, the cross section S2 of the lower boundary of the cavity biases the transition fillet radius R2 toward the blade root direction;
Taking sections S3, S1 'and S3' as sectional sections, and dividing the blade into a solid section, a transition section, a hollow section, a transition section and a solid section along the radial direction; specifically, a hollow section is arranged between the section S1 and the section S1'; transition sections are arranged between the section S3 and the section S1 and between the section S1 'and the section S3'; solid segments are provided between the blade root and the section S3 and between the section S3' and the blade tip.
Step 3, establishing finite element models of hollow sections and solid sections of the blade;
step 3.1, building a two-dimensional structure of each cavity section of the solid section and the hollow section of the blade:
The method comprises the steps that a plurality of layers of cavity sections along the chord direction of the blade are arranged on the solid section and the hollow section, and specifically, the cavity sections of the layers are uniformly arranged along the radial direction of the blade to serve as a foundation for establishing a grid of the hollow section and the solid section;
constructing a two-dimensional structure of each cavity section of the solid section and the hollow section of the blade according to the internal characteristic parameters of the blade; the two-dimensional structure of the sections S3, S1 'and S3' is also the two-dimensional structure of the boundary section of the transition section;
In this embodiment, as shown in fig. 2, a two-dimensional structure of each cavity section of the solid segment and the hollow segment of the blade may be built by a method in publication No. CN112214849, and a cavity section similar to the hollow segment is also provided in the solid segment, so as to facilitate division of the finite element structure.
In this embodiment, as shown in fig. 3 and fig. 4, the profile of each cavity section two-dimensional structure of the solid section and the hollow section of the blade includes a blade basin side surface curve L 1, a blade back side surface curve L 2, a transition fillet, a mean camber line L M, a stiffener centerline L H, a blade basin side inner skin wall curve L T1 and a blade back side inner skin wall curve L T2, the tangent point of the transition fillet on the blade basin side inner skin wall curve L T1 is K T1, and the tangent point of the transition fillet on the blade back side inner skin wall curve L T2 is K T2;
Step 3.2, dividing the two-dimensional structure of each cavity section of the solid section and the hollow section into a section solid area, a section wallboard area and a section fillet area along the chord direction;
The cross-section fillet area is an area formed by a transition fillet and a solid part in a set range outside the transition fillet; the cross-sectional solid area is the area between the blade leading edge and the adjacent cross-sectional rounded area, and the area between the blade trailing edge and the adjacent cross-sectional rounded area; the cross-sectional wall panel area is the area between two cross-sectional rounded corner areas located on the same cavity.
In this embodiment, as shown in fig. 3 and 4, the two-dimensional structure of each cavity section of the solid section and the hollow section is divided into a section solid region (a 11、A12), a section wall plate region (a 31、A32、A33、A34), and a section rounded region (a 21、A22、…、A28); each cavity is provided with two transition fillets;
Making a perpendicular L Q1 from a tangent point K T1 to a lateral surface curve L 1 of the leaf basin; making a tangent point K T2 to a perpendicular L Q2 to the blade back surface curve L 2; at the leading edge of the cavity, a molded line tangent to the transition fillet and perpendicular to the mean camber line L M is made, and the molded line is translated towards the leading edge of the blade by a set distance (preferably, the thickness D of the skin panel with the cross section is translated) to obtain a molded line L H0; at the trailing edge of the cavity, a molded line tangent to the transition fillet and perpendicular to the mean camber line L M is made, and the molded line is translated towards the trailing edge of the blade by a set distance (preferably, the thickness D of the skin panel with the section is translated) to obtain a molded line L H1;
The cross-section solid area is bordered as follows: the boundary of the cross-sectional solid area at the trailing edge of the cavity is: blade trailing edge, profile L H1, curve L 1 and curve L 2 between blade trailing edge and profile L H1; the boundary of the cross-sectional solid area at the leading edge of the cavity is: blade leading edge, profile L H0, curve L 1 and curve L 2 between blade leading edge and profile L H0; that is, the cross-sectional solid area is the area between the leading edge of the blade and the adjacent cross-sectional rounded area, and the area between the trailing edge of the blade and the adjacent cross-sectional rounded area;
The boundary dividing mode of the section fillet area is as follows: the boundary of the cross-sectional rounded area at the trailing edge of the cavity is: a transition fillet, a molded line L H1, a perpendicular L Q1 adjacent to the molded line L H1, and a perpendicular L Q2, A curve L 1 between the line L H1 and the adjacent perpendicular L Q1, and a curve L 2 between the line L H1 and the perpendicular L Q2; The boundary of the cross-sectional rounded area at the leading edge of the cavity is: a transition fillet, a molded line L H0, a perpendicular L Q1 adjacent to the molded line L H0, and a perpendicular L Q2, A curve L 1 between the line L H0 and the adjacent perpendicular L Q1, and a curve L 2 between the line L H0 and the adjacent perpendicular L Q2; The boundary of the cross-section fillet area at the reinforcing rib is: a transition fillet, a reinforcing rib center line L H, a perpendicular line L Q1 adjacent to the reinforcing rib center line L H, a perpendicular line L Q2, A curve L 1 between the bead centerline L H and the adjacent perpendicular L Q1, and a curve L 2 between the bead centerline L H and the adjacent perpendicular L Q2; That is, the cross-sectional rounded region is a region formed by the transition rounded and the solid portion within the set range outside thereof;
The cross-sectional wall panel area is bordered as follows: the boundary of the cross-sectional wallboard area of the side of the leaf basin is: two perpendicular lines L Q1 at the same cavity, a curve L 1 between the two perpendicular lines L Q1, and a curve L T1; the boundaries of the cross-sectional wall area on the back side of the blade are: two perpendicular lines L Q2 located in the same cavity, a curve L 2 located between the two perpendicular lines L Q2, and a curve L T2; that is, the cross-sectional wall area is the area between two cross-sectional rounded corner areas located on the same cavity.
Step 3.3, distributing the grid layer number for the solid segment and the hollow segment of the blade:
The specific mode for distributing the grid layer number for the solid section and the hollow section of the blade is as follows: distributing grid layers along the chord direction and the thickness direction of the blade for each cavity section two-dimensional structure of the solid section and the hollow section, wherein the grid layers of the solid section along the chord direction are NX1, and the grid layers along the thickness direction are NY1; the grid layer number of the cross-section wallboard area along the chord direction is NX2, and the grid layer number along the thickness direction is NY2; the grid layer number of the cross-section fillet area along the chord direction is NX3, and the grid layer number along the thickness direction is NY3; and, for each cavity section two-dimensional structure of a solid segment of the blade, ny1=ny2=ny3; for each cavity section two-dimensional structure of the hollow section of the blade, ny1=ny3;
the grid layer number NZ1 of the hollow section of the blade along the radial direction; the grid layer number NZ2 of the solid sections of the blade along the radial direction;
in practical application, the number of grid layers in each area of the two-dimensional structure of the cavity section is determined to be a proper value according to the requirements of the shape of the cavity of the blade and the grid density;
step 3.4, establishing finite element models of hollow sections and solid sections of the blade;
Establishing quadrilateral grids on the two-dimensional structures of each cavity section of the hollow section and the solid section of the blade;
Connecting quadrilateral grids of two adjacent layers of cavity section two-dimensional structures to obtain hexahedral grids of hollow sections and solid sections of the blade;
and sequencing the hexahedral mesh to obtain the finite element models of the hollow sections and the solid sections of the blade.
In this embodiment, establishing the blade hollow section finite element model includes:
As shown in fig. 3, a quadrilateral mesh is established in each cavity section two-dimensional structure of the hollow section of the blade;
connecting quadrilateral grids of two adjacent layers of cavity section two-dimensional structures to obtain a hollow section hexahedral grid of the blade; specifically, the connection mode is: correspondingly connecting nodes of quadrilateral grids of two adjacent layers of cavity section two-dimensional structures to form hexahedral grids;
sequencing hexahedral meshes to obtain a finite element model of the hollow section of the blade; specifically, sorting is performed according to the sequence from the blade root to the blade tip;
the concrete mode for establishing the quadrilateral mesh in each cavity section two-dimensional structure of the hollow section of the blade is as follows:
For the cross-section solid area and the cross-section wallboard area, a quadrilateral grid is established by a chessboard dividing method, and in the embodiment, the grid is uniformly distributed along the thickness direction of the blade and the chord direction of the blade;
For the section fillet area, dividing the section fillet area into a leaf basin side fillet sub-area and a leaf back side fillet sub-area by taking a mean camber line L M as a boundary, and establishing a quadrilateral mesh on the leaf basin side fillet sub-area and the leaf back side fillet sub-area by adopting a Y-shaped dicing method, wherein the mode of establishing the quadrilateral mesh by adopting the Y-shaped dicing method is shown in figure 8;
and combining the quadrilateral grids of the cross-section solid area, the cross-section wallboard area and the cross-section fillet area, and sequencing the quadrilateral grids in the sequence from the front edge of the blade to the rear edge of the blade along the chord direction to obtain the quadrilateral grid of each cavity cross-section two-dimensional structure of the hollow section of the blade.
In this embodiment, establishing the blade solid segment finite element model includes:
as shown in fig. 4, a quadrilateral mesh is established in each cavity section two-dimensional structure of the solid section of the blade;
connecting quadrilateral grids of two adjacent layers of cavity section two-dimensional structures to obtain solid section hexahedral grids of the blades; specifically, the connection mode is: correspondingly connecting nodes of quadrilateral grids of two adjacent layers of cavity section two-dimensional structures to form hexahedral grids;
sequencing hexahedral meshes to obtain a solid segment finite element model of the blade; specifically, sorting is performed according to the sequence from the blade root to the blade tip;
the concrete mode for establishing the quadrilateral mesh in each cavity section two-dimensional structure of the solid section of the blade is as follows:
Establishing quadrilateral grids in a chessboard dividing method in a cross section solid area, a cross section wallboard area and a cross section fillet area of each cavity cross section two-dimensional structure of the solid section of the blade, combining the quadrilateral grids in three areas (the cross section solid area, the cross section wallboard area and the cross section fillet area) and sequencing the quadrilateral grids from the front edge of the blade to the rear edge of the blade along the chord direction to obtain the quadrilateral grids of each cavity cross section two-dimensional structure of the solid section of the blade; in the embodiment, the quadrilateral meshes are established by a checkerboard dividing method and are uniformly distributed along the thickness direction of the blade and the chord direction of the blade.
Step 4, establishing a finite element model of the blade transition section:
step 4.1, establishing a transition section three-dimensional model, wherein the transition section three-dimensional model comprises a transition section solid three-dimensional region, a transition section wallboard three-dimensional region and a transition section round corner three-dimensional region;
The specific mode for establishing the transition section three-dimensional model is as follows:
The transition section is positioned at the blade root part, three-dimensional filling is carried out between the section S1 and the corresponding section solid area, section wallboard area and section fillet area on the section S3 to form a transition section solid three-dimensional area, a transition section wallboard three-dimensional area and a transition section fillet three-dimensional area, and the transition section solid three-dimensional area, the transition section wallboard three-dimensional area and the transition section fillet three-dimensional area are combined to form a transition section three-dimensional model of the blade root part;
And the transition section positioned at the blade tip part is used for three-dimensionally filling the solid cross section area, the cross section wallboard area and the cross section fillet area which correspond to the cross section S1 'and the cross section S3' to form a solid three-dimensional region of the transition section, a three-dimensional region of the transition section wallboard and a three-dimensional region of the transition section fillet, and combining the solid three-dimensional region of the transition section, the three-dimensional region of the transition section wallboard and the three-dimensional region of the transition section fillet to form the three-dimensional model of the transition section of the blade tip part.
Specifically, as shown in fig. 5 to 7, the transition section located at the blade root portion is formed by three-dimensionally filling the space between the solid cross-sectional area of the cross-section S1 and the solid cross-sectional area of the cross-section S3 to form a solid three-dimensional region D 11、D12 of the transition section at the blade root portion; three-dimensionally filling the space between the section wall plate area of the section S1 and the section wall plate area of the section S3 to form a transition section wall plate three-dimensional area D 31、D32、D33、D34 of the blade root part; three-dimensional filling is carried out between the section fillet area of the section S1 and the section fillet area of the section S3 to form a transition section fillet three-dimensional area D 21、D22、D23、…、D28 of the blade root part; the solid three-dimensional area of changeover portion, changeover portion wallboard three-dimensional area and changeover portion fillet three-dimensional area of root part combine to form the changeover portion three-dimensional model of root part.
The solid area of the cross section S1 'and the solid area of the cross section S3' are filled in a three-dimensional manner to form a solid area of the transition section of the blade tip part; three-dimensional filling is carried out between the section wallboard area of the section S1 'and the section wallboard area of the section S3', so as to form a transition section wallboard area of the blade tip part; three-dimensional filling is carried out between the section fillet area of the section S1 'and the section fillet area of the section S3', so as to form a transition section fillet area of the blade tip part; the solid three-dimensional area of changeover portion, changeover portion wallboard three-dimensional area and changeover portion fillet three-dimensional area of changeover portion of apex part combine to form the changeover portion three-dimensional model of apex part.
Step 4.2, distributing the grid layer number for the transition section;
the concrete mode for allocating the grid layer number for the transition section is as follows:
The grid layer number of the transition section solid three-dimensional region along the chord direction is NX1, and the grid layer number along the thickness direction is NY1;
the grid layer number of the three-dimensional area of the wall plate of the transition section along the chord direction is NX2, and the grid layer number along the thickness direction is NY4 or NY5, wherein NY4=NY2, NY5=NY1=NY3;
The grid layer number of the transition section fillet three-dimensional region along the chord direction is NX3, and the grid layer number along the thickness direction is NY3, wherein NZ3=NX3;
The number of grid layers of the solid three-dimensional area of the transition section, the wallboard three-dimensional area of the transition section and the fillet three-dimensional area of the transition section along the radial direction is NZ3;
The number of distribution grid layers of the transition section three-dimensional model of the blade root part and the transition section three-dimensional model of the blade tip part are the same.
Step 4.3, respectively establishing hexahedral meshes for the three-dimensional area of the wall plate of the transition section, the solid three-dimensional area of the transition section and the three-dimensional area of the round corner of the transition section;
(1) The concrete mode for establishing the hexahedral mesh for the three-dimensional area of the wall plate of the transition section is as follows:
In the embodiment, the section of the wall plate of the transition section is provided with 1+NX2 layers, and the sections of the wall plates of the transition section of the 1+NX2 layers are uniformly arranged along the chord direction of the blade; dividing the wall plate section of each layer of transition section into a wall plate leaf basin side fillet subregion and a wall plate leaf back side fillet subregion by taking a mean camber line L M as a dividing line, establishing a quadrilateral mesh on the wall plate leaf basin side fillet subregion and the wall plate leaf back side fillet subregion by adopting a Y-shaped dicing method, wherein the mode of establishing the quadrilateral mesh by adopting the Y-shaped dicing method is shown in figure 8;
connecting quadrilateral grids of the sections of every two adjacent layers of transition section wall plates to obtain a hexahedral grid of the three-dimensional area of the blade transition section wall plate; specifically, the connection mode is: correspondingly connecting nodes of quadrilateral grids of the cross sections of two adjacent layers of transition section wall plates to form hexahedral grids;
(2) The concrete mode for establishing the hexahedral mesh for the solid three-dimensional area of the transition section is as follows:
in the embodiment, the solid section of the transition section is provided with 1+NX1 layers, and the solid sections of the transition section of the 1+NX1 layers are uniformly arranged along the chord direction of the blade;
establishing a quadrilateral grid on the solid section of the transition section by a chessboard type dividing method;
Connecting quadrilateral grids with solid sections of every two adjacent layers of transition sections to obtain solid area hexahedral grids of the blade transition sections; specifically, the connection mode is: correspondingly connecting nodes of quadrilateral grids with solid sections of adjacent two layers of transition sections to form hexahedral grids;
(3) The concrete mode for establishing the hexahedral mesh for the transition section fillet three-dimensional area is as follows:
Dividing a three-dimensional region of the transition section fillet into a three-dimensional region of the leaf basin side fillet and a three-dimensional region of the leaf back side fillet by taking a mean camber line L M as a boundary line, and establishing a hexahedral mesh in the three-dimensional region of the leaf basin side fillet and the three-dimensional region of the leaf back side fillet;
Specifically, dividing a three-dimensional area of a leaf basin side fillet into a plurality of three-dimensional subareas, establishing a hexahedral mesh in each three-dimensional subarea, and combining the hexahedral meshes of the plurality of three-dimensional subareas to obtain the hexahedral mesh of the leaf basin side fillet three-dimensional area; in this embodiment, as shown in fig. 9, the three-dimensional area of the leaf basin side fillet is divided into 7 three-dimensional sub-areas (Q1, Q2, Q3, Q4, Q5, Q6, Q7), as shown in fig. 10 and 11, a hexahedral mesh is built in each three-dimensional sub-area, and then the hexahedral meshes of the 7 three-dimensional sub-areas are combined to obtain the hexahedral mesh of the three-dimensional area of the leaf basin side fillet.
Dividing a three-dimensional area of a leaf back side fillet into a plurality of three-dimensional subareas, establishing a hexahedral mesh in each three-dimensional subarea, and combining the hexahedral meshes of the plurality of three-dimensional subareas to obtain the hexahedral mesh of the leaf back side fillet three-dimensional area; in this embodiment, the three-dimensional area of the leaf back side fillet is divided into 7 three-dimensional subareas, a hexahedral mesh is established in each three-dimensional subarea, and then the hexahedral meshes of the 7 three-dimensional subareas are combined to obtain the hexahedral mesh of the three-dimensional area of the leaf back side fillet, and the manner of establishing the hexahedral mesh in the three-dimensional area of the leaf back side fillet is the same as that of the three-dimensional area of the leaf basin side fillet.
And 4.4, combining hexahedral grids of the solid three-dimensional area of the transition section, the solid three-dimensional area of the wall plate of the transition section and the solid three-dimensional area of the fillet of the transition section, and sequencing the hexahedral grids in the sequence from the front edge of the blade to the rear edge of the blade along the chord direction to obtain the finite element model of the transition section of the blade.
Step 5, establishing a finite element model of the blade:
as shown in fig. 12, the finite element models of the solid, transition, hollow, transition and solid sections of the blade are combined in the order from the blade root to the blade tip to obtain the finite element model of the blade.
The application process of the automatic establishment method of the H-shaped rib hollow fan blade finite element model comprises the following steps:
programming a program for automatically establishing an H-shaped rib hollow fan blade finite element model in an MATLAB environment, constructing a blade cavity section two-dimensional structure through the processes of the steps 1 to 5, dividing different areas, and establishing hexahedral meshes in a set mesh dividing mode and a set combination sequence;
Given the solid blade appearance data, the blade internal characteristic parameters, the grid layer numbers of the solid segments and the hollow segments of the blade and the radial grid layer number NZ3 of the transition segment are input into an established finite element modeling program, the finite element model of the H-shaped rib hollow fan blade can be quickly and automatically established, and the geometrical model of the H-shaped rib hollow fan blade can be better closed, and the smoothness is good.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the spirit and principles of the invention, the scope of which is defined by the claims and their equivalents.
Claims (7)
1. An automatic establishment method of an H-shaped rib hollow fan blade finite element model is characterized by comprising the following steps:
step 1, determining design parameters, wherein the design parameters comprise solid blade shape data and internal characteristic parameters of the blade;
Step 2, dividing the blade into a solid section, a transition section, a hollow section, a transition section and a solid section along the radial direction;
step 3, establishing finite element models of hollow sections and solid sections of the blade;
step 4, establishing a finite element model of the blade transition section;
Step 5, establishing a finite element model of the blade:
combining the finite element models of the solid section, the transition section, the hollow section, the transition section and the solid section of the blade according to the sequence from the blade root to the blade tip to obtain a finite element model of the blade;
the step 3 comprises the following steps:
step 3.1, building a two-dimensional structure of each cavity section of the solid section and the hollow section of the blade according to the internal characteristic parameters of the blade;
Step 3.2, dividing the two-dimensional structure of each cavity section of the solid section and the hollow section into a section solid area, a section wallboard area and a section fillet area along the chord direction;
Step 3.3, distributing the grid layer number for the solid segment and the hollow segment of the blade;
step 3.4, establishing a finite element model of the hollow section and the solid section of the blade:
establishing quadrilateral grids on the two-dimensional structures of each cavity section of the hollow section and the solid section of the blade; connecting quadrilateral grids of two adjacent layers of cavity section two-dimensional structures to obtain hexahedral grids of hollow sections and solid sections of the blade; sequencing hexahedral meshes to obtain finite element models of hollow sections and solid sections of the blades;
The step 4 comprises the following steps:
step 4.1, establishing a transition section three-dimensional model, wherein the transition section three-dimensional model comprises a transition section solid three-dimensional region, a transition section wallboard three-dimensional region and a transition section fillet three-dimensional region;
step 4.2, distributing the grid layer number for the transition section;
Step 4.3, respectively establishing hexahedral meshes for the three-dimensional area of the wall plate of the transition section, the solid three-dimensional area of the transition section and the three-dimensional area of the round corner of the transition section;
Step 4.4, combining hexahedral grids of the solid three-dimensional area of the transition section, the three-dimensional area of the wall plate of the transition section and the three-dimensional area of the fillet of the transition section, and sequencing the hexahedral grids in the sequence from the front edge of the blade to the rear edge of the blade along the chord direction to obtain a finite element model of the transition section of the blade;
in the step 2, the specific way of segmenting the blade along the radial direction is as follows:
the cross section at the upper boundary of the cavity is S2', and the cross section at the lower boundary of the cavity is S2; the section S2 'of the upper boundary of the cavity is offset to one side of the cavity by a set distance to obtain a section S1'; the section S2 'of the upper boundary of the cavity is offset to the tip direction by a set distance to obtain a section S3'; the section S2 of the lower boundary of the cavity is offset to one side of the cavity by a set distance to obtain a section S1; the section S2 of the lower boundary of the cavity is offset to the blade root direction by a set distance to obtain a section S3; taking sections S3, S1 'and S3' as segmented sections, the blade is divided into a solid section, a transition section, a hollow section, a transition section and a solid section along the radial direction.
2. The method for automatically building a finite element model of an H-rib hollow fan blade according to claim 1, wherein in the step 3.2, the cross-section fillet area is an area formed by a transition fillet and a solid portion within a set range outside the transition fillet; the cross-section solid area is an area between the front edge of the blade and an adjacent cross-section fillet area, and an area between the rear edge of the blade and an adjacent cross-section fillet area; the cross-sectional wall panel area is the area between two cross-sectional fillet areas located on the same cavity.
3. The method for automatically building the finite element model of the H-bar hollow fan blade according to claim 1, wherein in the step 3.3, the specific manner of distributing the grid layer number for the solid segment and the hollow segment of the blade is as follows: the grid layer number of the cross-section solid area along the chord direction is NX1, and the grid layer number along the thickness direction is NY1; the grid layer number of the cross-section wallboard area along the chord direction is NX2, and the grid layer number along the thickness direction is NY2; the grid layer number of the cross-section fillet area along the chord direction is NX3, and the grid layer number along the thickness direction is NY3; and, for each cavity section two-dimensional structure of a solid segment of the blade, ny1=ny2=ny3; for each cavity section two-dimensional structure of the hollow section of the blade, ny1=ny3; the grid layer number NZ1 of the hollow section of the blade along the radial direction; the number of grid layers NZ2 of the solid segments of the blade along the radial direction.
4. The method for automatically building the finite element model of the H-bar hollow fan blade according to claim 1, wherein in the step 3.4:
the concrete mode for establishing the quadrilateral mesh in each cavity section two-dimensional structure of the hollow section of the blade is as follows:
Establishing quadrilateral grids for the solid area of the cross section and the wallboard area of the cross section by a chessboard type dividing method; for the section fillet area, dividing the section fillet area into a leaf basin side fillet area and a leaf back side fillet area by taking a mean camber line L M as a boundary, and establishing a quadrilateral grid on the leaf basin side fillet area and the leaf back side fillet area by adopting a Y-shaped dicing method; combining the quadrilateral grids of the cross section solid area, the cross section wallboard area and the cross section fillet area and sequencing the quadrilateral grids in the sequence from the front edge of the blade to the rear edge of the blade along the chord direction to obtain the quadrilateral grid of each cavity cross section two-dimensional structure of the hollow section of the blade;
the concrete mode for establishing the quadrilateral mesh in each cavity section two-dimensional structure of the solid section of the blade is as follows:
Establishing quadrilateral grids in a chessboard dividing method in a cross section solid area, a cross section wallboard area and a cross section fillet area of each cavity cross section two-dimensional structure of the solid section of the blade, combining the quadrilateral grids in the three areas and sequencing the quadrilateral grids in a sequence from the front edge of the blade to the rear edge of the blade along the chord direction to obtain the quadrilateral grids of each cavity cross section two-dimensional structure of the solid section of the blade.
5. The method for automatically building the finite element model of the H-rib hollow fan blade according to claim 1, wherein in the step 4.1, the specific way of building the three-dimensional model of the transition section is as follows:
The transition section is positioned at the blade root part, three-dimensional filling is carried out between the section S1 and the corresponding section solid area, section wallboard area and section fillet area on the section S3 to form a transition section solid three-dimensional area, a transition section wallboard three-dimensional area and a transition section fillet three-dimensional area, and the transition section solid three-dimensional area, the transition section wallboard three-dimensional area and the transition section fillet three-dimensional area are combined to form a transition section three-dimensional model of the blade root part;
And the transition section positioned at the blade tip part is used for three-dimensionally filling the solid cross section area, the cross section wallboard area and the cross section fillet area which correspond to the cross section S1 'and the cross section S3' to form a solid three-dimensional region of the transition section, a three-dimensional region of the transition section wallboard and a three-dimensional region of the transition section fillet, and combining the solid three-dimensional region of the transition section, the three-dimensional region of the transition section wallboard and the three-dimensional region of the transition section fillet to form the three-dimensional model of the transition section of the blade tip part.
6. The method for automatically building the finite element model of the H-bar hollow fan blade according to claim 3, wherein in the step 4.2, the specific manner of allocating the mesh layer number to the transition section is as follows:
The grid layer number of the transition section solid three-dimensional region along the chord direction is NX1, and the grid layer number along the thickness direction is NY1; the grid layer number of the three-dimensional area of the wall plate of the transition section along the chord direction is NX2, and the grid layer number along the thickness direction is NY4 or NY5, wherein NY4=NY2, NY5=NY1=NY3; the grid layer number of the transition section fillet three-dimensional region along the chord direction is NX3, and the grid layer number along the thickness direction is NY3; the mesh layers of the solid three-dimensional area of the transition section, the three-dimensional area of the wall plate of the transition section and the three-dimensional area of the round corner of the transition section along the radial direction are NZ3, and NZ3=NX3.
7. The method for automatically building the finite element model of the H-bar hollow fan blade according to claim 1, wherein the step 4.3 specifically comprises:
(1) The concrete mode for establishing the hexahedral mesh for the three-dimensional area of the wall plate of the transition section is as follows:
A plurality of layers of transition section wallboard sections extending along the radial direction and the thickness direction of the blade are arranged in the three-dimensional area of the transition section wallboard; dividing the wall plate section of each layer of transition section into a wall plate leaf basin side fillet subregion and a wall plate leaf back side fillet subregion by taking a mean camber line L M as a boundary line, and establishing a quadrilateral grid on the wall plate leaf basin side fillet subregion and the wall plate leaf back side fillet subregion by adopting a Y-type dicing method;
Connecting quadrilateral grids of the sections of every two adjacent layers of transition section wall plates to obtain a hexahedral grid of the three-dimensional area of the blade transition section wall plate;
(2) The concrete mode for establishing the hexahedral mesh for the solid three-dimensional area of the transition section is as follows:
a plurality of layers of solid sections of the transition section extending along the radial direction and the thickness direction of the blade are arranged in the solid three-dimensional area of the transition section;
establishing a quadrilateral grid on the solid section of the transition section by a chessboard type dividing method;
connecting quadrilateral grids with solid sections of every two adjacent layers of transition sections to obtain solid area hexahedral grids of the blade transition sections;
(3) The concrete mode for establishing the hexahedral mesh for the transition section fillet three-dimensional area is as follows:
The three-dimensional area of the transition section fillet is divided into a three-dimensional area of the leaf basin side fillet and a three-dimensional area of the leaf back side fillet by taking a mean camber line L M as a boundary line, and a hexahedral mesh is established in the three-dimensional area of the leaf basin side fillet and the three-dimensional area of the leaf back side fillet.
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| CN108757555B (en) * | 2018-03-28 | 2020-06-05 | 中国航空制造技术研究院 | Hollow blade structure of aircraft engine and design method thereof |
| US11250189B1 (en) * | 2018-04-30 | 2022-02-15 | United States Of America As Represented By The Secretary Of The Air Force | Identifying effects of geometric variations of physical parts |
| CN109409020B (en) * | 2018-12-16 | 2023-04-18 | 中国航发沈阳发动机研究所 | Modeling method of hollow fan blade |
| CN112214849B (en) * | 2020-09-29 | 2022-12-27 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of H-shaped rib hollow fan blade |
| CN112395698B (en) * | 2020-11-02 | 2024-03-29 | 南京航空航天大学 | Hollow blade blank calculation method capable of realizing hollow structural design |
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| CN101751500A (en) * | 2008-12-09 | 2010-06-23 | 利弗莫尔软件技术公司 | Improved entity finite element suitable for large deformation and/or rotation of imitated structure |
| CN103480973A (en) * | 2013-09-22 | 2014-01-01 | 中国东方电气集团有限公司 | Three-stage cold metal transfer welding method for steam turbine hollow static blades |
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