CN115081280A - Automatic establishing method of finite element model of H-shaped rib hollow fan blade - Google Patents
Automatic establishing method of finite element model of H-shaped rib hollow fan blade Download PDFInfo
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Abstract
An automatic establishing method of a finite element model of an H-shaped rib hollow fan blade belongs to the technical field of automatic finite element modeling. The automatic establishing 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 appearance data and blade internal characteristic parameters; 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 the hollow section and the solid section of the blade; step 4, establishing 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 section, the transition section, the hollow section, the transition section and the solid section of the blade to obtain the finite element model of the blade. The automatic establishing method of the finite element model of the H-shaped rib hollow fan blade can quickly establish the finite element models of various H-shaped rib structures and hollow blades with similar structures which are directly used for calculation.
Description
Technical Field
The invention relates to the technical field of finite element automatic modeling, in particular to an automatic establishing method of a finite element model of an H-shaped rib hollow fan blade.
Background
At present, fan blade modeling methods with truss core structures have matured. For the fan blade with the coreless structure, the reinforcing ribs are located 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 must be integrated with the blade body, and the shapes of other parts need to be changed along with the bending and twisting free curved surface of the blade body, so that complex calculation derivation and 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 aero-engine is usually to perform modeling through CAD software, then to perform meshing and strength calculation through finite element calculation software, if the strength requirement is not met, parameters are required to be adjusted to perform modeling again, and the steps are repeated so as to meet the strength requirement. Therefore, the structural design of the blade needs to carry out a large amount of repeated modeling work on the model, and if the conventional method is adopted, the model needs to be redrawn from the beginning every time, so that the workload is large.
Therefore, the application provides an automatic establishing method of a 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 a finite element model needs to be repeatedly established for strength calculation and the like in the design of the H-shaped rib hollow fan blade in the prior art, the invention provides an automatic establishing method of the finite element model of the H-shaped rib hollow fan blade, which can quickly establish the finite element models of various H-shaped rib structures and hollow blades with similar structures directly used for calculation, and greatly shortens the modeling and calculating time.
In order to achieve the purpose, the technical scheme of the invention is as follows:
an automatic establishing method of a finite element model of an H-shaped rib hollow fan blade comprises the following steps:
step 1, determining design parameters:
the design parameters comprise solid blade appearance data and blade internal characteristic parameters;
step 2, the blade is segmented along the radial direction:
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;
specifically, the blade is segmented in the radial direction in a specific manner 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 towards the direction of the blade tip 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 towards the blade root by a set distance to obtain a section S3;
taking the sections S3, S1, 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 finite element models 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:
the solid section and the hollow section are both provided with a plurality of layers of cavity sections along the chord direction of the blade;
according to the internal characteristic parameters of the blade, building a two-dimensional structure of each cavity section of the solid section and the hollow section of the blade;
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 wall plate area and a section fillet area along the chord direction;
specifically, the section fillet area is an area formed by a transition fillet and a solid part in a set range outside the transition fillet; the section solid area is an area between the front edge of the blade and an adjacent section fillet area, and an area between the rear edge of the blade and the adjacent section fillet area; the cross-sectional wall panel region is the region between two cross-sectional fillet regions located on the same cavity.
3.3, distributing the number of grid layers for the solid sections and the hollow sections of the blades:
specifically, the specific mode of distributing the number of grid layers for the solid section and the hollow section of the blade is as follows: the number of grid layers of the solid area of the cross section along the chord direction is NX1, and the number of grid layers along the thickness direction is NY 1; the number of grid layers in the chord direction of the section wall plate area is NX2, and the number of grid layers in the thickness direction is NY 2; the number of grid layers in the section fillet area along the chord direction is NX3, and the number of grid layers in the thickness direction is NY 3; and, for each cavity section two-dimensional structure of the blade solid section, NY1 ═ NY2 ═ NY 3; for the two-dimensional structure of each cavity section of the hollow section of the blade, NY1 is NY 3;
the number of grid layers NZ1 of the hollow section of the blade along the radial direction; the number of grid layers NZ2 of the solid sections of the blade in the radial direction;
3.4, establishing finite element models of the hollow section and the solid section of the blade;
establishing quadrilateral grids in the two-dimensional structure of each cavity section of the hollow section and the solid section of the blade;
connecting quadrilateral grids of two-dimensional structures of the sections of the adjacent two layers of cavities to obtain hexahedral grids of the hollow sections and the solid sections of the blades;
sequencing the hexahedral meshes to obtain finite element models of hollow sections and solid sections of the blades;
specifically, the specific way of establishing the quadrilateral grids in the two-dimensional structure of each cavity section of the hollow section of the blade is as follows:
establishing quadrilateral grids for the section solid area and the section wall plate area by a checkerboard type division method;
for the section fillet area, with the mean camber line L M The section is a circular bead areaDividing the square grid into a leaf basin side fillet sub-area and a leaf back side fillet sub-area, and establishing a quadrilateral grid in the leaf basin side fillet sub-area and the leaf back side fillet sub-area by adopting a Y-shaped cutting method;
combining the quadrilateral grids of the section solid area, the section wall plate area and the 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 a quadrilateral grid of a two-dimensional structure of each cavity section of the hollow section of the blade;
specifically, the specific way of establishing the quadrilateral grids in the two-dimensional structure of each cavity section of the solid section of the blade is as follows:
establishing quadrilateral grids in a cross section solid area, a cross section wall plate area and a cross section fillet area of each cavity cross section two-dimensional structure of the solid blade section by a checkerboard type division method, combining the quadrilateral grids of the three areas, 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 blade section;
step 4, establishing a finite element model of the transition section of the blade:
step 4.1, establishing a transition section three-dimensional model, wherein the transition section three-dimensional model comprises a transition section solid three-dimensional area, a transition section wall plate three-dimensional area and a transition section fillet three-dimensional area;
specifically, the specific way of establishing the transition section three-dimensional model is as follows:
the transition section is positioned at the blade root part, the solid filling is carried out between the section S1 and the section solid area, the section wall plate area and the section fillet area which correspond to the section S3 to form a transition section solid three-dimensional area, a transition section wall plate three-dimensional area and a transition section fillet three-dimensional area, and the transition section solid three-dimensional area, the transition section wall plate 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 is positioned at the tip part, the solid area, the section wall plate area and the section fillet area of the section S1 'and the section S3' which correspond to each other are filled in a three-dimensional mode to form a solid three-dimensional area, a three-dimensional area and a three-dimensional area of the transition section wall plate, and a three-dimensional area of the transition section fillet, and the solid three-dimensional area, the three-dimensional area and the three-dimensional area of the transition section fillet are combined to form a three-dimensional transition section model of the tip part;
step 4.2, distributing the number of grid layers for the transition section;
specifically, the specific manner of allocating the number of grid layers to the transition section is as follows:
the number of grid layers of the solid three-dimensional region of the transition section along the chord direction is NX1, and the number of grid layers along the thickness direction is NY 1;
the number of grid layers of the three-dimensional region of the transition section wallboard along the chord direction is NX2, and the number of grid layers along the thickness direction is NY4 or NY5, wherein NY4 is NY2, and NY5 is NY1 is NY 3;
the number of grid layers of the transition section fillet three-dimensional area along the chord direction is NX3, and the number of grid layers along the thickness direction is NY 3;
the number of grid layers in the radial direction 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 is NZ 3;
the number of layers of the distribution grids of the transition section three-dimensional model of the blade root part and the transition section three-dimensional model of the blade tip part is the same;
specifically, NZ3 ═ NX 3.
Step 4.3, respectively establishing hexahedral meshes for a transition section wall plate three-dimensional area, a transition section solid three-dimensional area and a transition section fillet three-dimensional area;
(1) the concrete mode for establishing the hexahedral mesh for the three-dimensional area of the transition section wall plate is as follows:
arranging a plurality of layers of transition section wall plate sections extending along the radial direction and the thickness direction of the blade in a three-dimensional area of the transition section wall plate; by mean camber line L M Dividing the section of each layer of the transition section wall plate into a wall plate leaf basin side fillet sub-area and a wall plate leaf back side fillet sub-area for a boundary, and building a quadrilateral mesh in the wall plate leaf basin side fillet sub-area and the wall plate leaf back side fillet sub-area by adopting a Y-shaped cutting method;
connecting quadrilateral grids of the sections of the wall plates of every two adjacent transition sections to obtain hexahedral grids of the three-dimensional area of the wall plate of the transition section of the blade;
(2) the concrete mode for establishing the hexahedral mesh for the solid three-dimensional area of the transition section is as follows:
arranging a plurality of layers of transition section solid sections extending along the radial direction and the thickness direction of the blade in a transition section solid three-dimensional area;
establishing quadrilateral grids on the solid section of the transition section by a checkerboard type division method;
connecting quadrilateral grids of solid sections of every two adjacent layers of transition sections to obtain hexahedral grids of solid three-dimensional areas of the transition sections of the blades;
(3) the concrete mode for establishing the hexahedral mesh for the transition section fillet solid area is as follows:
by mean camber line L M Dividing the fillet three-dimensional area of the transition section into a leaf basin side fillet three-dimensional area and a leaf back side fillet three-dimensional area for a boundary, and establishing a hexahedral mesh in the leaf basin side fillet three-dimensional area and the leaf back side fillet three-dimensional area;
step 4.4, combining hexahedral meshes 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 meshes 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 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 the finite element model of the blade.
The invention has the beneficial effects that:
1) the automatic establishing method of the H-shaped rib hollow fan blade finite element model realizes the automatic parametric modeling, and the automatic parametric modeling process comprises the following steps: by setting design parameters, the number of grid layers of the solid section and the hollow section of the blade and the number of grid layers NZ3 of the transition section in the radial direction, a finite element model of the H-shaped rib hollow fan blade can be quickly and automatically established, the geometric model of the H-shaped rib hollow fan blade can be well attached to, and the smoothness is good;
2) according to the invention, the density of the blade grids can be flexibly adjusted by giving the number of the grid layers of the solid sections and the hollow sections, and the hexahedral grids are established in a set grid division mode and a set combination sequence, so that the grid subdivision efficiency and precision are ensured, and the method is widely suitable for calculation of hollow blades with various H-shaped rib structures and similar structures;
3) the automatic establishing method of the H-shaped rib hollow fan blade finite element model is applied to design projects, greatly shortens the modeling and calculating time, and achieves good effects.
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 structural diagram of an H-rib hollow fan blade provided by an embodiment of the invention;
FIG. 2 is a schematic diagram of a two-dimensional configuration of a cross-section of a cavity on a solid section and a hollow section provided by an embodiment of the present invention;
FIG. 3 is a schematic illustration of a hollow section cross-sectional grid 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 first schematic diagram of a first transition section grid at a root portion according to an embodiment of the present invention;
FIG. 6 is a second schematic diagram of a transition section grid at a root portion according to an embodiment of the present invention;
FIG. 7 is a partial schematic view of the transition section taken along section A of FIG. 6;
FIG. 8 is a schematic diagram of a method for building a quadrilateral mesh by using a Y-type dicing method according to an embodiment of the present invention;
FIG. 9 is a schematic diagram of a three-dimensional corner area on the side of a leaf basin, which is divided into a plurality of three-dimensional sub-areas according to an embodiment of the present invention;
FIG. 10 is a first schematic diagram of a hexahedral mesh established in a three-dimensional corner area on the side of a leaf basin according to an embodiment of the present invention;
FIG. 11 is a second schematic diagram of the hexahedral mesh established in the fillet solid area on the side of the leaf basin according to the embodiment of the present invention;
FIG. 12 is a schematic grid view of an H-ribbed hollow fan blade provided by an embodiment of the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
In order to solve the problems in the prior art, as shown in fig. 1 to 12, the invention provides an automatic establishing 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 profile data and blade internal characteristic parameters, a solid model of the solid blade is determined from the solid blade profile data;
in the embodiment, the internal characteristic parameters of the blade comprise 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 cross-section skin panel, the width B of the reinforcing ribs, the number N of the reinforcing ribs and the radius of the transition fillet; the blend fillet radii include the blend fillet radius R1 for the leading edge of the cavity, the blend fillet radius R2 between the stiffener and the inner wall surface of the skin, and the blend fillet radius R3 for the trailing edge of the cavity.
Step 2, the blades are segmented along the radial direction:
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;
as shown in fig. 1, the blades are radially segmented in a specific manner:
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, section S2' of the upper boundary of the cavity is offset to one side of the cavity by a blend fillet radius R2;
the section S2 'of the upper boundary of the cavity is offset towards the direction of the blade tip by a set distance to obtain a section S3'; in this embodiment, the section S2' of the upper boundary of the cavity is offset in the direction of the tip by a transition fillet radius R2;
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 is offset to one side of the cavity by a blend fillet radius R2;
the section S2 of the lower boundary of the cavity is offset towards the blade root by a set distance to obtain a section S3; in this embodiment, the section S2 of the lower boundary of the cavity is offset towards the root of the blade by a fillet radius R2;
taking the sections S3, S1, 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'; between section S3 and section S1 and between section S1 'and section S3' are transitions; solid sections 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 the hollow section and the solid section 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 solid section and the hollow section are both provided with a plurality of layers of cavity sections along the chord direction of the blade, and specifically, the plurality of layers of cavity sections are uniformly arranged along the radial direction of the blade to be used as a basis for establishing section grids of the hollow section and the solid section;
according to the internal characteristic parameters of the blade, building a two-dimensional structure of each cavity section of the solid section and the hollow section of the blade; the two-dimensional structure of sections S3, S1, S1 'and S3' is also the two-dimensional structure of the transition segment boundary sections;
in this embodiment, as shown in fig. 2, a two-dimensional structure of each cavity section of the solid section and the hollow section of the blade may be built by a method disclosed in CN112214849, and a cavity section with a structure similar to that of the hollow section is also provided in the solid section, so as to conveniently divide the finite element structure.
In the present embodiment, as shown in fig. 3 and 4, the profile of the two-dimensional structure of each cavity section of the solid and hollow sections of the blade includes a surface curve L on the side of the blade basin 1 Leaf back side surface curve L 2 Fillet transition and camber line L M Central line L of reinforcing rib H Inner wall curve L of side skin of blade basin T1 Inner wall curve L of blade back side skin T2 Inner wall curve L of transition fillet on side skin of blade basin T1 OnTangent point is K T1 The transition fillet is on the inner wall curve L of the blade back side skin T2 Tangent point of (A) is K T2 ；
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 wall plate area and a section fillet area along the chord direction;
the section fillet area is an area formed by a transition fillet and a solid part in a set range outside the transition fillet; the section solid area is an area between the front edge of the blade and the adjacent section fillet area, and an area between the rear edge of the blade and the adjacent section fillet area; the cross-sectional wall panel area is the area between two cross-sectional fillet areas on the same cavity.
In the present 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 、A 12 ) Cross-sectional panel area (A) 31 、A 32 、A 33 、A 34 ) And a cross-sectional fillet area (A) 21 、A 22 、…、A 28 ) (ii) a Each cavity is provided with two transition fillets;
making a tangent point K T1 Curve L to side surface of leaf basin 1 Perpendicular line L Q1 (ii) a Making a tangent point K T2 Curve L to the surface of the blade back side 2 Perpendicular L Q2 (ii) a At the front edge of the cavity, a mean camber line L tangent to the transition fillet and perpendicular to the transition fillet is made M And translating the profile towards the leading edge of the blade by a set distance (preferably, by translating the thickness D of the cross-sectional skin panel) to obtain profile L H0 (ii) a At the rear edge of the cavity, a camber line L tangent to the transition fillet and perpendicular to the transition fillet is made M And translating the profile towards the trailing edge of the blade by a set distance (preferably, by translating the thickness D of the cross-sectional skin panel) to obtain profile L H1 ；
The boundary dividing mode of the solid area of the section is as follows: the boundary of the cross-sectional solid area at the trailing edge of the cavity is: blade trailing edge, profile L H1 And at the trailing edge of the blade and profile L H1 Curve L between 1 And curve L 2 (ii) a The boundary of the cross-sectional solid area at the leading edge of the cavity is: vane leading edge, profile L H0 And at the leading edge of the blade and the profile L H0 Curve L between 1 And curve L 2 (ii) a That is, the section solid region is the region between the leading edge of the blade and the adjacent section fillet region, and the region between the trailing edge of the blade and the adjacent section fillet region;
the section fillet area boundary dividing mode is as follows: the boundary of the cross-sectional fillet area at the cavity trailing edge is: transition fillet and profile L H1 And the molded line L H1 Adjacent perpendicular line L Q1 And the perpendicular line L Q2 At the profile L H1 To adjacent perpendicular line L Q1 Curve L between 1 And located at the profile L H1 To the perpendicular line L Q2 Curve L between 2 (ii) a The boundary of the cross-sectional fillet area at the leading edge of the cavity is: transition fillet and profile L H0 And the molded line L H0 Adjacent perpendicular line L Q1 And the perpendicular line L Q2 At the profile L H0 To adjacent perpendicular line L Q1 Curve L between 1 And located at the profile L H0 To adjacent perpendicular line L Q2 Curve L between 2 (ii) a The boundary of the section fillet area at the reinforcing rib is as follows: central line L of transition fillet and reinforcing rib H And the central line L of the reinforcing rib H Adjacent perpendicular line L Q1 And the perpendicular line L Q2 On the central line L of the reinforcing rib H To adjacent perpendicular line L Q1 Curve L between 1 And is located at the center line L of the reinforcing rib H To adjacent perpendicular line L Q2 Curve L between 2 (ii) a That is, the section fillet area is an area formed by a transition fillet and a solid part in the set range outside the transition fillet;
the boundary dividing method of the section wall plate area is as follows: the boundary of the cross-sectional wall area of the blade bowl side is: two perpendicular lines L located at the same cavity Q1 On two perpendicular lines L Q1 Curve L between 1 And curve L T1 (ii) a The boundary of the cross-sectional wall area of the blade back side is: two perpendicular lines L in the same cavity Q2 On two perpendicular lines L Q2 Curve L between 2 And curve L T2 (ii) a That is, the cross-sectional wall area is located atThe area between two cross-sectional fillet areas on the same cavity.
3.3, distributing the number of grid layers for the solid sections and the hollow sections of the blades:
the specific mode of distributing the number of the grid layers for the solid sections and the hollow sections of the blades is as follows: distributing the number of grid layers along the chord direction and the thickness direction of the blade for the two-dimensional structure of each cavity section of the solid section and the hollow section, wherein the number of grid layers along the chord direction of the solid section area is NX1, and the number of grid layers along the thickness direction is NY 1; the number of grid layers in the chord direction of the section wall plate area is NX2, and the number of grid layers in the thickness direction is NY 2; the number of grid layers in the section fillet area along the chord direction is NX3, and the number of grid layers in the thickness direction is NY 3; and, for each cavity section two-dimensional structure of the blade solid section, NY1 ═ NY2 ═ NY 3; for the two-dimensional structure of each cavity section of the hollow section of the blade, NY1 is NY 3;
the number of grid layers NZ1 of the hollow section of the blade along the radial direction; the number of grid layers NZ2 of the solid sections of the blade in the radial direction;
in practical application, the number of grid layers of each area of the two-dimensional structure of the cavity section is determined to be an appropriate value according to the cavity shape of the blade and the grid density requirement;
3.4, establishing finite element models of the hollow section and the solid section of the blade;
establishing quadrilateral grids in the two-dimensional structure of each cavity section of the hollow section and the solid section of the blade;
connecting quadrilateral grids of two-dimensional structures of the sections of the adjacent two layers of cavities to obtain hexahedral grids of the hollow sections and the solid sections of the blades;
and sequencing the hexahedral meshes to obtain finite element models of the hollow sections and the solid sections of the blades.
In this embodiment, establishing a finite element model of the hollow section of the blade includes:
as shown in fig. 3, a quadrilateral grid is established on each cavity section two-dimensional structure of the hollow section of the blade;
connecting quadrilateral grids of two-dimensional structures of the sections of the adjacent two layers of cavities to obtain hexahedral grids of the hollow section of the blade; specifically, the connection mode is as follows: correspondingly connecting the nodes of the quadrilateral grids with the two-dimensional structures of the sections of the adjacent two layers of cavities to form a hexahedral grid;
sequencing the hexahedral meshes to obtain a finite element model of the hollow section of the blade; specifically, sequencing is carried out according to the sequence from the blade root to the blade tip;
the specific mode for establishing the quadrilateral grids in the two-dimensional structure of each cavity section of the hollow section of the blade is as follows:
for the solid section area and the wall section area, a quadrilateral grid is established by a checkerboard type division method, and in the embodiment, the grids are uniformly distributed along the thickness direction of the blade and the chord direction of the blade;
for the section fillet area, with a mean camber line L M Dividing the section fillet area into a leaf basin side fillet sub-area and a leaf back side fillet sub-area for a boundary, establishing a quadrilateral mesh in the leaf basin side fillet sub-area and the leaf back side fillet sub-area by adopting a Y-shaped cutting method, wherein the mode of establishing the quadrilateral mesh by adopting the Y-shaped cutting method is shown in FIG. 8;
and combining the quadrilateral grids of the section solid area, the section wall plate area and the 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 the two-dimensional structure of each cavity section of the hollow section of the blade.
In this embodiment, establishing a finite element model of the solid section of the blade includes:
as shown in fig. 4, a quadrilateral grid is established on each cavity section two-dimensional structure of the solid section of the blade;
connecting quadrilateral grids of two-dimensional structures of the sections of the adjacent two layers of cavities to obtain hexahedral grids of the solid section of the blade; specifically, the connection mode is as follows: correspondingly connecting the nodes of the quadrilateral grids with the two-dimensional structures of the sections of the adjacent two layers of cavities to form a hexahedral grid;
sequencing the hexahedral meshes to obtain a finite element model of the solid section of the blade; specifically, sequencing is carried out according to the sequence from the blade root to the blade tip;
the specific mode for establishing the quadrilateral grids in the two-dimensional structure of each cavity section of the solid section of the blade is as follows:
establishing quadrilateral meshes in a cross section solid area, a cross section wall plate area and a cross section fillet area of each cavity cross section two-dimensional structure of the solid blade section by a checkerboard type division method, combining the quadrilateral meshes of the three areas (the cross section solid area, the cross section wall plate area and the cross section fillet area) and sequencing the quadrilateral meshes from the front edge of the blade to the rear edge of the blade along the chord direction to obtain the quadrilateral meshes of each cavity cross section two-dimensional structure of the solid blade section; in the embodiment, quadrilateral meshes are established by a checkerboard dividing method and are uniformly distributed along the thickness direction and the chord direction of the blade.
Step 4, establishing a finite element model of the transition section of the blade:
step 4.1, establishing a transition section three-dimensional model, wherein the transition section three-dimensional model comprises a transition section solid three-dimensional area, a transition section wall plate three-dimensional area and a transition section fillet three-dimensional area;
the concrete mode for establishing the transition section three-dimensional model is as follows:
the transition section is positioned at the blade root part, the solid filling is carried out between the section S1 and the section solid area, the section wall plate area and the section fillet area which correspond to the section S3 to form a transition section solid three-dimensional area, a transition section wall plate three-dimensional area and a transition section fillet three-dimensional area, and the transition section solid three-dimensional area, the transition section wall plate 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 (3) filling the solid space among the solid cross section area, the wall section area and the fillet cross section area corresponding to the cross section S1 'and the cross section S3' in the transition section of the blade tip part to form a solid transition section area, a wall plate solid transition section area and a fillet transition section solid transition section area, and combining the solid transition section area, the wall plate solid transition section area and the fillet transition section solid transition section area to form a solid transition section model of the blade tip part.
Specifically, as shown in fig. 5 to 7, in the transition section of the blade root portion, the solid area of the section S1 and the solid area of the section S3 are filled in three-dimensionally to form the solid three-dimensional area D of the transition section of the blade root portion 11 、D 12 (ii) a Erecting a section wall panel region of section S1 and a section wall panel region of section S3Filling the body to form a three-dimensional area D of the transition wall plate of the blade root part 31 、D 32 、D 33 、D 34 (ii) a The space between the section fillet area of the section S1 and the section fillet area of the section S3 is filled to form a transition section fillet space area D of the blade root part 21 、D 22 、D 23 、…、D 28 (ii) a And a transition section solid three-dimensional area, a transition section wallboard three-dimensional area and a transition section fillet three-dimensional area of the blade root part are combined to form a transition section three-dimensional model of the blade root part.
The transition section of the blade tip part is formed by filling a solid section area of the section S1 'and a solid section area of the section S3' in a three-dimensional mode; filling a 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 area of the blade tip part; filling a space between the section fillet area of the section S1 'and the section fillet area of the section S3' to form a transition section fillet area of the blade tip part; the transition section solid three-dimensional area, the transition section wall plate three-dimensional area and the transition section fillet three-dimensional area of the blade tip part are combined to form a transition section three-dimensional model of the blade tip part.
Step 4.2, distributing the number of grid layers for the transition section;
the specific way of distributing the number of grid layers for the transition section is as follows:
the number of grid layers of the solid three-dimensional region of the transition section along the chord direction is NX1, and the number of grid layers along the thickness direction is NY 1;
the number of grid layers of the three-dimensional region of the transition section wallboard along the chord direction is NX2, and the number of grid layers along the thickness direction is NY4 or NY5, wherein NY4 is NY2, and NY5 is NY1 is NY 3;
the number of grid layers of the transition section fillet solid area along the chord direction is NX3, the number of grid layers along the thickness direction is NY3, and NZ3 is NX 3;
the number of grid layers in the radial direction 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 is NZ 3;
the number of layers of the distribution grids of the transition section three-dimensional model of the blade root part and the transition section three-dimensional model of the blade tip part is the same.
Step 4.3, respectively establishing hexahedral meshes for a transition section wall plate three-dimensional area, a transition section solid three-dimensional area and a transition section fillet three-dimensional area;
(1) the concrete mode for establishing the hexahedral mesh for the three-dimensional area of the transition section wall plate is as follows:
a plurality of layers of transition section wall plate sections (such as a section A in fig. 7) extending along the radial direction and the thickness direction of the blade are arranged in the three-dimensional area of the transition section wall plate, in the embodiment, the sections of the transition section wall plates are provided with 1+ NX2 layers, and the sections of the transition section wall plates with 1+ NX2 layers are uniformly arranged along the chord direction of the blade; by mean camber line L M Dividing the section of each layer of the transition section wall plate into a wall plate leaf basin side fillet sub-area and a wall plate leaf back side fillet sub-area for a boundary, establishing a quadrilateral mesh in the wall plate leaf basin side fillet sub-area and the wall plate leaf back side fillet sub-area by adopting a Y-shaped cutting method, and establishing the quadrilateral mesh by adopting the Y-shaped cutting method in a manner shown in FIG. 8;
connecting quadrilateral grids of the sections of the wall plates of every two adjacent transition sections to obtain hexahedral grids of the three-dimensional area of the wall plate of the transition section of the blade; specifically, the connection mode is as follows: correspondingly connecting the nodes of the quadrilateral grids of the sections of the two adjacent layers of transition section wallboards to form a hexahedral grid;
(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 sections of 1+ NX1 layers are uniformly arranged along the chord direction of the blade;
establishing quadrilateral grids on the solid section of the transition section by a checkerboard type division method;
connecting quadrilateral grids of solid sections of every two adjacent layers of transition sections to obtain hexahedral grids of solid three-dimensional areas of the transition sections of the blades; specifically, the connection mode is as follows: correspondingly connecting the nodes of the quadrilateral grids with the solid sections of the two adjacent layers of transition sections to form a hexahedral grid;
(3) the concrete mode for establishing the hexahedral mesh for the transition section fillet solid area is as follows:
by mean camber line L M Dividing the fillet three-dimensional area of the transition section into a leaf basin side fillet three-dimensional area and a leaf back side fillet three-dimensional area for a boundary, and establishing a hexahedral mesh in the leaf basin side fillet three-dimensional area and the leaf back side fillet three-dimensional area;
specifically, the leaf basin side circular angle solid area is divided into a plurality of solid subregions, hexahedral meshes are established in each solid subregion, and then the hexahedral meshes of the plurality of solid subregions are combined to obtain the hexahedral meshes of the leaf basin side circular angle solid area; in this embodiment, as shown in fig. 9, the lobe-basin-side circular-angle solid region is divided into 7 solid sub-regions (Q1, Q2, Q3, Q4, Q5, Q6, and Q7), as shown in fig. 10 and 11, hexahedral meshes are established in each solid sub-region, and then the hexahedral meshes of the 7 solid sub-regions are combined to obtain the hexahedral meshes of the lobe-basin-side circular-angle solid region.
Dividing the leaf back side circular angle stereo region into a plurality of stereo subregions, establishing a hexahedral mesh in each stereo subregion, and combining the hexahedral meshes of the plurality of stereo subregions to obtain the hexahedral mesh of the leaf back side circular angle stereo region; in this embodiment, the leaf back side circular angle solid region is divided into 7 solid subregions, a hexahedral mesh is established in each solid subregion, then the hexahedral meshes of the 7 solid subregions are combined to obtain the hexahedral mesh of the leaf back side circular angle solid region, and the way of establishing the hexahedral mesh in the leaf back side circular angle solid region is the same as that in the leaf basin side circular angle solid region.
And 4.4, combining hexahedral meshes 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 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:
as shown in fig. 12, the finite element models of the solid section, the transition section, the hollow section, the transition section and the solid section of the blade are combined in sequence from the blade root to the blade tip to obtain the finite element model of the blade.
The invention relates to an application process of an automatic establishing method of a finite element model of an H-shaped rib hollow fan blade, which comprises the following steps:
writing a program for automatically establishing a finite element model of the H-shaped rib hollow fan blade in an MATLAB environment, constructing a two-dimensional structure of the section of a cavity of the blade through the processes from step 1 to step 5, dividing different regions, and establishing hexahedral meshes in a set mesh division mode and a set combination sequence;
the shape data of the solid blades of the H-shaped rib hollow fan blade, the internal characteristic parameters of the blades, the number of grid layers of the solid sections and the hollow sections of the blades and the number of grid layers NZ3 of the transition sections in the radial direction are given and input into an established finite element modeling program, so that a finite element model of the H-shaped rib hollow fan blade can be established quickly and automatically, the geometric model of the H-shaped rib hollow fan blade can be well attached to the geometric model of the H-shaped rib hollow fan blade, and the smoothness is good.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. An automatic establishment method of a finite element model of an H-shaped rib hollow fan blade is characterized by comprising the following steps:
step 1, determining design parameters, wherein the design parameters comprise solid blade appearance data and blade internal characteristic parameters;
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 the hollow section and the solid section of the blade;
step 4, establishing 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 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 the finite element model of the blade.
2. The method for automatically building a finite element model of an H-shaped rib hollow fan blade according to claim 1, wherein,
the step 3 comprises the following steps:
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;
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 wall plate area and a section fillet area along the chord direction;
3.3, distributing the grid layer number for the solid section and the hollow section of the blade;
3.4, establishing a finite element model of the hollow section and the solid section of the blade:
establishing quadrilateral grids in the two-dimensional structure of each cavity section of the hollow section and the solid section of the blade; connecting quadrilateral grids of two-dimensional structures of the sections of the adjacent two layers of cavities to obtain hexahedral grids of the hollow sections and the solid sections of the blades; and sequencing the hexahedral meshes to obtain finite element models of the hollow sections and the solid sections of the blades.
3. The method for automatically building a finite element model of an H-shaped rib hollow fan blade according to claim 2, wherein,
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 area, a transition section wall plate three-dimensional area and a transition section fillet three-dimensional area;
step 4.2, distributing the number of grid layers for the transition section;
step 4.3, respectively establishing hexahedral meshes for a transition section wall plate three-dimensional area, a transition section solid three-dimensional area and a transition section fillet three-dimensional area;
and 4.4, combining hexahedral meshes 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 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.
4. The automatic establishing method of the finite element model of the H-shaped rib hollow fan blade as claimed in claim 3, wherein in the step 2, the blade is segmented in the radial direction in a specific way that:
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; a 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 towards the direction of the blade tip 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 towards the blade root by a set distance to obtain a section S3; the sections S3, S1, S1 'and S3' are taken as sectional sections, and 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.
5. The automatic establishing method of the finite element model of the H-shaped rib hollow fan blade as claimed in claim 2, wherein in the step 3.2, the section fillet area is an area formed by a transition fillet and a solid part within a set range outside the transition fillet; the section solid area is an area between the front edge of the blade and an adjacent section fillet area, and an area between the rear edge of the blade and the adjacent section fillet area; the cross-sectional wall panel region is the region between two cross-sectional fillet regions located on the same cavity.
6. The automatic establishing method of the finite element model of the H-shaped rib hollow fan blade as claimed in claim 3, wherein in the step 3.3, the specific manner of distributing the number of the grid layers for the solid section and the hollow section of the blade is as follows: the number of grid layers of the solid area of the cross section along the chord direction is NX1, and the number of grid layers along the thickness direction is NY 1; the number of grid layers in the chord direction of the section wall plate area is NX2, and the number of grid layers in the thickness direction is NY 2; the number of grid layers in the section fillet area along the chord direction is NX3, and the number of grid layers in the thickness direction is NY 3; and, for each cavity section two-dimensional structure of the blade solid section, NY1 ═ NY2 ═ NY 3; for the two-dimensional structure of each cavity section of the hollow section of the blade, NY1 is NY 3; the number of grid layers NZ1 of the hollow section of the blade along the radial direction; the number of layers NZ2 of the grid in the radial direction of the solid blade section.
7. The method for automatically establishing a finite element model of the H-shaped rib hollow fan blade as claimed in claim 2, wherein in the step 3.4:
the specific mode for establishing the quadrilateral grids in the two-dimensional structure of each cavity section of the hollow section of the blade is as follows:
establishing quadrilateral grids for the section solid area and the section wall plate area by a checkerboard type division method; for the section fillet area, with the mean camber line L M Dividing the section fillet area into a leaf basin side fillet sub-area and a leaf back side fillet sub-area for a boundary, and establishing a quadrilateral mesh in the leaf basin side fillet sub-area and the leaf back side fillet sub-area by adopting a Y-shaped cutting method; combining the quadrilateral grids of the section solid area, the section wall plate area and the 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 a quadrilateral grid of a two-dimensional structure of each cavity section of the hollow section of the blade;
the specific mode for establishing the quadrilateral grids in the two-dimensional structure of each cavity section of the solid section of the blade is as follows:
and establishing quadrilateral grids in a cross section solid area, a cross section wall plate area and a cross section fillet area of each cavity cross section two-dimensional structure of the solid blade section by a checkerboard type division method, combining the quadrilateral grids of the three areas, 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 blade section.
8. The automatic establishing method of the finite element model of the H-shaped rib hollow fan blade according to claim 4, wherein in the step 4.1, the concrete mode of establishing the transition section three-dimensional model is as follows:
the transition section is positioned at the blade root part, the solid filling is carried out between the section S1 and the section solid area, the section wall plate area and the section fillet area which correspond to the section S3 to form a transition section solid three-dimensional area, a transition section wall plate three-dimensional area and a transition section fillet three-dimensional area, and the transition section solid three-dimensional area, the transition section wall plate 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 (3) filling the solid space among the solid cross section area, the wall section area and the fillet cross section area corresponding to the cross section S1 'and the cross section S3' in the transition section of the blade tip part to form a solid transition section area, a wall plate solid transition section area and a fillet transition section solid transition section area, and combining the solid transition section area, the wall plate solid transition section area and the fillet transition section solid transition section area to form a solid transition section model of the blade tip part.
9. The automatic establishing method of the finite element model of the H-shaped rib hollow fan blade as claimed in claim 6, wherein in the step 4.2, the specific way of allocating the number of grid layers to the transition section is as follows:
the number of grid layers of the solid three-dimensional region of the transition section along the chord direction is NX1, and the number of grid layers along the thickness direction is NY 1; the number of grid layers of the three-dimensional region of the transition section wallboard along the chord direction is NX2, and the number of grid layers along the thickness direction is NY4 or NY5, wherein NY4 is NY2, and NY5 is NY1 is NY 3; the number of grid layers of the transition section fillet three-dimensional area along the chord direction is NX3, and the number of grid layers along the thickness direction is NY 3; the number of grid layers in the radial direction of the transition section solid three-dimensional area, the transition section wallboard three-dimensional area and the transition section fillet three-dimensional area is NZ3, and NZ3 is NX 3.
10. The automatic establishing method of the finite element model of the H-shaped rib hollow fan blade as claimed in claim 3, wherein the step 4.3 specifically comprises:
(1) the concrete mode for establishing the hexahedral mesh for the three-dimensional area of the transition section wall plate is as follows:
arranging a plurality of layers of transition section wall plate sections extending along the radial direction and the thickness direction of the blade in a three-dimensional area of the transition section wall plate; by mean camber line L M Dividing the wall section of each layer of transition section into wallsThe method comprises the following steps that a plate blade basin side fillet sub-region and a wall plate blade back side fillet sub-region are adopted, and a Y-shaped cutting method is adopted to establish a quadrilateral mesh in the wall plate blade basin side fillet sub-region and the wall plate blade back side fillet sub-region;
connecting quadrilateral grids of the sections of the wall plates of every two adjacent transition sections to obtain hexahedral grids of the three-dimensional area of the wall plate of the transition section of the blade;
(2) the concrete mode for establishing the hexahedral mesh for the solid three-dimensional area of the transition section is as follows:
arranging a plurality of layers of transition section solid sections extending along the radial direction and the thickness direction of the blade in a transition section solid three-dimensional area;
establishing quadrilateral grids on the solid section of the transition section by a checkerboard type division method;
connecting quadrilateral grids of solid sections of every two adjacent layers of transition sections to obtain hexahedral grids of solid three-dimensional areas of the transition sections of the blades;
(3) the concrete mode for establishing the hexahedral mesh for the transition section fillet solid area is as follows:
by mean camber line L M And dividing the fillet three-dimensional area of the transition section into a blade basin side fillet three-dimensional area and a blade back side fillet three-dimensional area for a boundary, and establishing a hexahedral mesh in the blade basin side fillet three-dimensional area and the blade back side fillet three-dimensional area.
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