CN115438427A - Resin-based composite material hollow fan blade material-structure integrated design method - Google Patents
Resin-based composite material hollow fan blade material-structure integrated design method Download PDFInfo
- Publication number
- CN115438427A CN115438427A CN202211079821.XA CN202211079821A CN115438427A CN 115438427 A CN115438427 A CN 115438427A CN 202211079821 A CN202211079821 A CN 202211079821A CN 115438427 A CN115438427 A CN 115438427A
- Authority
- CN
- China
- Prior art keywords
- blade
- hollow fan
- strength
- hollow
- height
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/04—Constraint-based CAD
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/26—Composites
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Evolutionary Computation (AREA)
- Computer Hardware Design (AREA)
- General Engineering & Computer Science (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a sheet material-structure integrated design method of a hollow fan made of a resin-based composite material, and in the method, a parameterized modeling method of the hollow fan sheet is provided; automatically updating the layering parameters and the structure size parameters through a mesh division strategy of a finite element model, and completing the high-efficiency mechanical property analysis of the hollow fan blade structure; obtaining key variables and a main effect diagram by carrying out parameter sensitivity analysis on the strength and the modulus of the composite material; obtaining the selection range of the strength and the modulus by combining the main effect diagram, and selecting a plurality of materials from the material database according to the selection range; based on a multi-island genetic algorithm and a Chua-Wu failure criterion, the modal performance, the strength performance and the rigidity performance of the hollow fan blade are taken as optimization constraints, and the total volume of the hollow fan blade is optimally designed to achieve the purpose of weight reduction.
Description
Technical Field
The invention belongs to the technical field of aerospace engines, and particularly relates to a blade material-structure integrated design method for a resin-based composite hollow fan.
Background
The fan blade is one of the most important structural components of the civil large-bypass-ratio turbofan engine, in order to meet the increasing requirements of low oil consumption and high thrust-weight ratio, the advanced civil turbofan engine is developing towards the direction that the bypass ratio is larger and the structural mechanical property is more stable, and the resin-based composite material fan blade is applied to the civil large-bypass-ratio turbofan engine due to the characteristics of light weight and good vibration reduction performance, and has important significance in light weight design of the fan blade.
The optimization design of the fan blade made of the resin-based composite material mainly comprises the following three aspects: selecting the type of materials, optimizing the layering structure of the blade and optimizing the size of the hollow structure of the blade. The traditional optimization design method fails to consider the hollow structure of the composite material fan blade, the selection of optimization variables is single and mainly takes a layering angle, the optimization target mainly takes strength or resonance margin as the optimization target, the optimization design is rarely carried out on the quality of the blade, the maximum utilization of materials cannot be realized, and the improvement of the integral thrust-weight ratio of an engine is not facilitated.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a material-structure integrated design method for a hollow fan blade made of a resin-based composite material, which adopts a high-efficiency automatic modeling method and a Chua-Wu failure criterion for the hollow fan blade, and optimizes the quality of the hollow fan blade by taking modal performance, strength performance and rigidity performance of the hollow fan blade as optimization constraints based on a multi-island genetic algorithm. The influences of composite material parameters, the layering angle and the size of the hollow foam structure on the performance of the fan blade can be considered, and the quality of the fan blade is further reduced.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a resin matrix composite hollow fan blade material-structure integrated design method comprises the following steps:
step 1: introducing blade configuration curve data points by using three-dimensional modeling software, generating a curve by using splines, constructing a curved surface by using a curve group, realizing modeling of the solid fan blade by using sewing, and then introducing a reference surface and an offset to realize parametric modeling of a geometric model of the hollow fan blade;
and 2, step: running simulation software, importing the hollow fan blades and the PMI (polymethacrylimide) foam sandwich entity model established in the step 1, performing operations of geometric model processing, automatic grid division, layer attribute endowment, load and boundary condition application, and starting structural mechanical property analysis and calculation to obtain Chua-Wu strength factor distribution, blade elongation, modal frequency of each order and generate a command script; the ply attribute assignment includes a ply angle selection;
and step 3: and (3) realizing integration of an automatic updating module of the parameterized geometric model by utilizing multidisciplinary design software: extracting key parameters of the hollow fan blades in the key parameter control file as design variables, completing the integration of the command script in the step 2, reading the key parameters in the design variables by the command script, completing the updating of self programs, completing the automatic partitioning of the hollow fan blades in the finite element analysis software by using the command script, and realizing the transmission of the parameters in the three-dimensional modeling software model, the command script and the finite element model;
and 4, step 4: analyzing the parameter sensitivity of the material strength and modulus of the composite material on the parameter transmission method established in the step 3 to obtain a key variable and a main effect diagram; obtaining the selection range of the strength and the modulus by combining the main effect diagram, and selecting a plurality of materials from a material database according to the selection range;
and 5: on the basis of the variable variation range obtained in the steps 1 to 4, the geometric parameters (offset and height of a reference surface defined in a hollow cavity) of the hollow fan blade in the step 1, the ply angle in the finite element model in the step 2 and the composite material key material parameters (modulus and Poisson ratio) determined in the step 3 are taken as design variables, the Chua-Wu strength factor, the blade elongation and the modal frequency are taken as optimization constraints, the blade quality function is taken as an optimization target to establish an optimization model, and the ply angle and the hollow structure size of the hollow fan blade are optimally designed by adopting a multi-island genetic algorithm.
Further, in step 1, the parametric modeling of the geometric model specifically includes: defining five reference planes from the blade tip to the bottom height of the cavity as M 0 -M 4 The height intervals between the five sections are respectively H 1 -H 4 (ii) a Offsetting the blade profile within each section by an amount G 1 -G 5 Thereby forming five closed curves L 0 -L 4 The five closed curves are stitched together to complete the modeling.
Further, the processing and range constraint criteria of the geometric model parametric modeling are as follows: the processing and range constraint criterion of the geometric model parametric modeling is as follows: h is to be 2 -H 4 Is constrained by a parameter E, H 1 Is constrained by a parameter H; the value range of H is 7% -17% of the height of the blade body, the value of H is smaller than 7% of the height of the blade body, so that the plane is close to the curved surface of the blade tip, a contour curve cannot be generated, the value of H is larger than 17% of the height of the blade body, and M is enabled to be larger than 1 Curved surface and M 2 The curved surfaces are overlapped; the E value is less than 9% of the height of the blade body, so that the contour curve cannot be sewn into an entity, and the E value greater than 25% of the height of the blade body exceeds the range of the height of the blade body;
the area enclosed by each section curve of the hollow cavity is kept basically consistent so as to form a regular foam filling cavity; mixing L with 4 Curve offset G 4 Set as parameters G, L 0 -L 3 The offset is sequentially decreased to be 0.9G, 0.85G, 0.82G and 0.76G respectively, and the value range of G is limited to be 11-19% of the width of the cross-section blade.
Further, in step 2, the automatic mesh division specifically includes: firstly, dividing a hollow area and a solid area of the blade into an M4 plane; and then, dividing the smooth region in the middle of the blade from the profiled regions with blade edge configurations on two sides, determining that all points required by a dividing plane are structural midpoints, and acquiring and inputting the points into a command script in three-dimensional modeling software.
Further, in the step 2, the constraint criteria for selecting the ply angle specifically include: (1) a layering balance symmetry principle: the layering sequence is symmetrical about the middle plane, the layering angles are kept balanced, and the number of layers at 45 degrees is kept the same as that at +45 degrees; (2) according to the ply orientation principle under the load condition: the 0-degree layer has stronger capability of bearing uniaxial tensile load; the 90-degree paving layer has stronger capacity of bearing shearing load; the +/-45-degree paving layer has stronger capability of bearing torsional load; selecting a layering mode according to the actual loading condition; (3) layering sequence principle: the interlaminar stress is reduced by adopting a staggered laying mode, the strength performance is improved, and 0-degree laying layers are not laid on the upper surface and the lower surface of the component.
Further, the key variables in step 4 include: transverse tensile strength Y T Longitudinal modulus of elasticity E 1 And transverse modulus of elasticity E 2 And obtaining the selection range of the key variable through the main effect graph: transverse tensile strength Y T >40MPa, modulus of elasticity in the longitudinal direction E 1 >160GPa and transverse elastic modulus E 2 <9000Mpa。
Further, in step 5, the limit of the optimization constraint is determined by the following method: the Chua-Wu strength factor is greater than or equal to 1, represents that the composite material structure is damaged and does not meet the strength requirement; if the number is less than 1, the composite material structure does not lose efficacy and meets the strength requirement; the safety coefficient of the composite material is not lower than 1.5, namely the Chua-Wu strength factor is less than 0.66; the ratio of the maximum deformation to the height of the blade body is less than 1 percent; the blade has a margin of resonance of at least 10%.
Compared with the prior art, the invention has the advantages that:
in the aspect of geometric modeling, compared with the traditional geometric modeling of the composite material fan blade, the geometric modeling of the hollow foam cavity of the composite material fan blade is added, the geometric parameterization strategy of the hollow blade structure is provided by combining the existing foam sandwich process, the three-dimensional modeling of the hollow cavity can be standardized, and the existing parameters are reasonably simplified to improve the optimization design efficiency; in the aspect of simulation modeling, compared with the traditional automatic meshing, the finite element modeling partitioning strategy is provided aiming at the calculation requirement of a composite material layering structure, the automatic meshing of hollow fan blades with different structures can be realized while the meshing quality and the layering direction are ensured, the automatic updating of a finite element model is realized, and the optimization efficiency is improved; in the aspect of optimization criteria, compared with the situation that the traditional fan blade is single in optimization variable and the optimization target is lack of attention to the quality of the blade, a novel optimization material-structure integrated design method is provided, and the quality of the hollow fan blade is optimized by taking the modal performance, the strength performance and the rigidity performance of the hollow fan blade as optimization constraints. The influences of composite material parameters, a layering angle and the size of the hollow foam structure on the performance of the fan blade can be considered, and the quality of the fan blade is further reduced.
Drawings
FIG. 1 is a flow chart of a resin matrix composite hollow fan blade material-structure integrated design method of the present invention;
FIG. 2 is a schematic view of the inner cavity of the hollow foam in a substantially planar manner and its positional parameters;
FIG. 3 is an offset schematic view of the cross-sectional configuration of the hollow foam chamber;
FIG. 4 is a hollow fan blade zoning result;
FIG. 5 is a hollow fan blade meshing result.
Detailed Description
The technical scheme of the blade material-structure integrated design method of the resin-based composite material hollow fan is further explained below with reference to the accompanying drawings.
As shown in fig. 1, the method for designing a blade material-structure integration of a resin-based composite hollow fan of the present invention mainly comprises: the method comprises the following specific implementation steps of geometric parametric modeling of the composite hollow blade, selection of materials and material ranges, finite element analysis of modal performance, strength performance and rigidity performance of the composite hollow blade, and optimization of a blade layering structure and a hollow structure size, wherein the specific implementation steps are as follows:
step 1: and (3) realizing the parametric modeling of the geometric models of the fan blades and the hollow foam inner cavity by utilizing three-dimensional modeling software UG. Defining five reference planes from the blade tip to the bottom height of the hollow inner cavity as M 0 -M 4 The height intervals between the five sections are respectively H 1 -H 4 As in fig. 2. By means of the biasing function in UG, the blade profile is biased in each section, the biasing result being shown in fig. 3, the amount of which is G respectively 1 -G 5 Thereby forming a closed curve L 0 -L 4 And sewing the five curves to complete the modeling of the hollow foam inner cavity.
And (3) standardizing three-dimensional modeling of the hollow inner cavity by adopting a parameterization strategy: will H 2 -H 4 Is constrained by a parameter E, H 1 Is constrained by a parameter H; wherein the value range of H is 7-17% of the height of the blade body, the value of H is less than 7% of the height of the blade body, so that the plane is close to the curved surface of the blade tip, a contour curve can not be generated, the value of H is more than 17% of the height of the blade body, so that M is enabled to be M 1 Curved surface and M 2 Superposing the curved surfaces; the E value is less than 9% of the height of the blade body, so that the contour curve can not be stitched into an entity, the E value is more than 25% of the height of the blade body, and the value range of H is determined to be 40<H<90,E has a value in the range of 50<E<The units of 140, E and H are determined according to the actual blade length and width.
In order to facilitate PMI foam sandwich filling and bonding, the area enclosed by each section curve of the hollow cavity is kept basically consistent so as to form a regular foam filling cavity. Meanwhile, the sectional area of each section of the blade profile of the fan blade is in an increasing relationship, and the closer to the section of the blade tip, the larger the sectional area of the blade profile is, so that L is equal to L 4 Curve offset G 5 Set as parameters G, L 0 -L 3 Is reduced by a fixed proportional relation of a parameter G, where N is set 3 The offset of the cross section is 0.9G 2 The offset of the cross section is 0.85G 1 The offset of the cross section is 0.82G, N 0 The offset of the cross section was 0.76G. In order to ensure that the skin thickness is not too small and the contour curve of the blade tip section can keep a larger area, the value range of G is limited to the sectional blade11% to 19% of the width, i.e. 3.7<G<6.5。
Adopting a parameterization strategy, and combining 9 independent parameters (H) of the hollow inner cavity 1 ～H 4 、G 1 ～G 5 ) The modeling method is simplified into 3 independent parameters (H, E and G), the parametric modeling efficiency and the optimized design efficiency are greatly improved, and the molding of the hollow inner cavity is normalized through the mutual correlation among the parameters, so that the processing requirements are met;
step 2: and (3) running ABAQUS simulation software, importing the hollow fan blades and the PMI foam sandwich solid model established in the step (1), and then carrying out operations such as geometric model processing, grid division, layer attribute endowing, load and boundary condition application and the like to carry out structural mechanical property analysis and calculation. In order to facilitate the automatic calculation of parameter transmission of subsequent steps, automatic grid division needs to be realized, and the realization of automatic grid division needs to reasonably partition a complex blade structure, and the specific partitioning strategy is as follows: the method comprises the steps of controlling the partition of a blade by a Python command script of ABAQUS, firstly, dividing a hollow area and a solid area of the blade into M planes 4 A plane; and then, dividing the smooth region in the middle of the blade from the profiled regions on the blade edges at two sides, determining that the points required by the dividing plane are structural midpoints, and acquiring and inputting the points into a Python command script in UG software. After the partitioning strategy is adopted, the hollow fan blades with different structures and sizes can realize automatic hexahedral mesh division in ABAQUS, and the efficiency of finite element modeling is greatly improved. The partitioning results are shown in fig. 4, and the meshing results under this partitioning strategy are shown in fig. 5.
In ply attribute assignment, excessive ply lay-up directions can cause inconvenience to the production, processing and storage of prepregs. In engineering, the ply lay directions are typically only 4, i.e. 0 degrees, ± 45 degrees and 90 degrees. In the field of aviation, the layering sequence design of the composite material should meet the following principles: (1) a layering balance symmetry principle: the sequence of plies is symmetrical about the mid-plane, the ply angles are kept uniform, -the number of plies at 45 degrees should be kept the same as +45 degrees (2) according to the ply orientation principle under load: the 0-degree layering has stronger capability of bearing uniaxial tensile load; the 90-degree paving layer has stronger capacity of bearing shearing load; 45 degrees plus or minusThe layer bearing torsion load capacity is strong; selecting a layering mode according to the actual loading condition; (3) layering sequence principle: by adopting the staggered laying mode, the interlaminar stress can be reduced, the strength performance is improved, and the impact resistance of the 0-degree laying layer is poor, so that the 0-degree laying layer is not laid on the upper surface and the lower surface of the component. According to the technical scheme that the thickness of a skin of a hollow part of the blade is 3mm, the average thickness of the solid part of the blade is about 10mm, the thickness of a single-layer prepreg of an EH918-HF40C resin-based composite material is 0.187mm, the number of layers of the skin part of the blade is set to 16, and the initial layer laying angles are [ -45,0, 90,0 ] by combining the layer laying design principle and adopting a symmetrical layer laying mode] s . The number of layers of the solid part of the blade is set to be 48 layers, and the layer angle is set to be [ -45,0, 90,0 [ -45] 3s I.e. the lay-up of the skin section is repeated 3 times. The layering mode can ensure that the layering modes of the upper surface and the lower surface of the blade are consistent, so that the layering of the solid part and the covering is continuous, and the processing defects are reduced. For parts where the blade root exceeds 48 layers of prepreg thickness, continue to press to [ -45,0, 90,0 [ -45,0] s The laying mode is repeated from the surface to the center, and the laying continuity of the prepreg during processing is ensured. For the parameterization required for optimization, according to the ply design principle, considering symmetry, only setting the ply angle of one side of the symmetry plane from outside to inside as a group parameter group [ x ] every 8 plies 1 ,x 2 ,…,x 8 ]The parameter set satisfies the constraint x1 ≠ 0, and the laying is repeated for 3 times for 24 layers of the solid part;
and 3, step 3: the integration of the parameterized geometric model automatic updating module is realized by using a Simcode module in multidisciplinary design software ISIGHT: extracting an offset G and a reference surface height H of a hollow structure in a key parameter control file as design variables, finishing the integration of a Python command script in the step 2 by using a Data exchange module, reading key parameters in the design variables by using the Python command script, finishing the updating of a self program, finishing the automatic partitioning of the hollow fan blades in finite element analysis software ABAQUS by using the Python command script, and realizing the transmission of the parameters in a UG model, the Python command script and the finite element model;
and 4, step 4: parameter passing established in step 3In the method, sensitivity analysis is carried out on material parameters of the composite material, key variables and a main effect diagram thereof are obtained, and the key variables are selected through a Pareto diagram of the sensitivity analysis: transverse tensile strength Y T Longitudinal modulus of elasticity E 1 And transverse modulus of elasticity E 2 Obtaining the selection range of the key variable through the main effect graph: transverse tensile strength Y T >40MPa, modulus of elasticity in the longitudinal direction E 1 >160GPa and transverse modulus of elasticity E 2 <9000MPa. Selecting a number of materials from a material database that meet the key variable selection, here M40J/5182;
and 5: on the basis of the geometric variables and the variation ranges obtained in the step 1, the ply angle variables and the variation ranges obtained in the step 2 and the material variables and the variation ranges obtained in the step 4, material parameters, ply angles and hollow structure sizes of the blades are taken as design variables, chua-Wu strength factors, blade elongation and modal frequency are taken as optimization constraints, and blade quality functions are taken as optimization targets to establish an optimization model.
In the selection of optimization constraints, the safety coefficient is selected to be 2.7, and the constraint Chua-Wu factor does not exceed 0.364; the critical rotating speed of the blade is obtained by drawing a Campbell diagram of the blade and utilizing a graphical method, the resonance margin of the hollow fan blade is determined, according to the requirements in the structural design criteria of aviation turbojet and turbofan engines, the resonance margin of the blade is at least 10%, the actual design usually takes 20% of the resonance margin as the design standard, and the natural frequencies of the first order and the sixth order are close to a rotating speed line in the example and need to be restricted; the maximum deformation of the blade can not exceed 1 percent of the height ratio of the blade body.
In summary, it translates into the formulation of the optimization problem:
wherein x is 1 ～x 8 Is the angle of the layering; x is the number of 9 ～x 11 The dimensional parameters of the hollow structure are shown; w (x) is a mass function of the hollow fan blade and is expressed by the total volume of the blade; g (x) is a sixth order natural frequency function(ii) a f (x) is a first order natural frequency function; TW (x) is a strength performance function of the hollow fan blade and is expressed by a Chua-Wu strength factor; u (x) is a hollow fan blade stiffness performance function expressed in terms of maximum deflection values.
In the aspect of strength performance, the Chua-Wu strength factor is a dimensionless quantity, is more than or equal to 1 and represents that the composite material structure is damaged and does not meet the strength requirement; if the content is less than 1, the composite material structure does not lose efficacy and meets the strength requirement. In practical engineering application, partial margin needs to be reserved, and safety factors are introduced to judge whether the structure meets design requirements or not. The safety coefficient of the composite material is generally required to be not lower than 1.5, namely the Chua-Wu strength factor is less than 0.66, and the required value of the safety coefficient is larger and generally more than 2 in consideration of special requirements such as environmental corrosion and the like.
In the aspect of rigidity performance, the clearance between the blade control tip and the casing needs to be strictly controlled, pneumatic efficiency is reduced when the clearance is too large, collision and abrasion faults occur when the clearance is too small, and the ratio of the maximum deformation to the height of the blade body is generally required to be less than 1%.
In the aspect of modal performance, the natural frequency of the blade needs to be ensured according to the working rotating speed principle, resonance is avoided, the resonance margin of the blade is at least 10% according to the requirements in the structural design criteria of aviation turbojet and turbofan engines, and the actual design usually takes 20% of the resonance margin as the design standard. And obtaining the frequency order needing to be restrained according to the Campbell diagram of the blade, and restraining according to the 20% resonance margin.
The method is characterized in that M40J/5182 is used as a blade material, WH75 commonly used in the domestic composite hollow fan blade process is used as a foam sandwich material, and a multi-island genetic algorithm is adopted to optimally design the layering angle and the hollow structure size of the hollow fan blade. The population number in the multi-island genetic algorithm is set to be 20, the island size is set to be 5, the total evolution algebra is set to be 20, and the cross probability is set to be 0.9. The optimization process takes 33h56min after 2000 cycles in total. And (3) selecting an optimization result by referring to the layer design rule in the step (2), so as to obtain an optimal solution meeting the process constraint.
The above examples are provided for the purpose of describing the present invention only and are not intended to limit the scope of the present invention. The scope of the invention is defined by the appended claims. Various equivalent substitutions and modifications can be made without departing from the spirit and principles of the invention, and are intended to be included within the scope of the invention.
Claims (7)
1. A method for designing a resin-based composite hollow fan blade material-structure integration is characterized by comprising the following steps:
step 1: introducing blade configuration curve data points by using three-dimensional modeling software, generating a curve by using splines, constructing a curved surface by using a curve group, realizing modeling of the solid fan blade by using sewing, and then introducing a reference surface and an offset to realize parametric modeling of a geometric model of the hollow fan blade;
step 2: operating simulation software, importing the hollow fan blades and the polymethacrylimide foam sandwich entity model established in the step 1, performing geometric model processing, automatic grid division, layer attribute endowment, load and boundary condition application, starting structural mechanical property analysis and calculation to obtain Chua-Wu strength factor distribution, blade elongation, modal frequency of each order and generating a command script; the ply attribute assignment includes ply angle selection;
and step 3: and (3) realizing integration of an automatic updating module of the parameterized geometric model by utilizing multidisciplinary design software: extracting key parameters of the hollow fan blades in the key parameter control file as design variables to complete the integration of the command script in the step 2, wherein the command script reads the key parameters in the design variables to complete the updating of the self program, and the command script is utilized to complete the automatic partitioning of the hollow fan blades in the finite element analysis software so as to realize the transmission of the parameters in the three-dimensional modeling software model, the command script and the finite element model;
and 4, step 4: analyzing the parameter sensitivity of the material strength and modulus of the composite material on the parameter transmission method established in the step 3 to obtain a key variable and a main effect diagram; obtaining a selection range of the strength and the modulus by combining the main effect diagram, and selecting a plurality of materials from a material database according to the selection range;
and 5: on the basis of the variable variation range obtained in the steps 1-4, the geometric parameters of the hollow fan blade in the step 1, the ply angle in the finite element model in the step 2 and the key parameters of the composite material determined in the step 3 are taken as design variables, the Chua-Wu strength factor, the blade elongation and the modal frequency are taken as optimization constraints, the blade quality function is taken as an optimization target to establish an optimization model, and the ply angle of the hollow fan blade and the size of the hollow structure are optimally designed by adopting a multi-island genetic algorithm.
2. The method for integrally designing the blade material-structure of the resin-based composite hollow fan according to claim 1, wherein: in step 1, the geometric model parametric modeling specifically includes: defining five reference planes from the blade tip to the bottom height of the cavity as M 0 -M 4 The height intervals between the five sections are respectively H 1 -H 4 (ii) a The blade profile is offset in each section by G 1 -G 5 Thereby forming five closed curves L 0 -L 4 Five closed curves were stitched to complete the modeling.
3. The integrated design method for the blade material-structure of the resin matrix composite hollow fan according to claim 2, characterized in that: the processing and range constraint criterion of the geometric model parametric modeling is as follows: h is to be 2 -H 4 Is constrained by a parameter E, H 1 Is constrained by a parameter H; the value range of H is 7% -17% of the height of the blade body, the value of H is smaller than 7% of the height of the blade body, so that the plane is close to the curved surface of the blade tip, a contour curve cannot be generated, the value of H is larger than 17% of the height of the blade body, and M is enabled to be larger than 1 Curved surface and M 2 The curved surfaces are overlapped; the E value is less than 9% of the height of the blade body, so that the contour curve cannot be sewn into an entity, and the E value greater than 25% of the height of the blade body exceeds the range of the height of the blade body;
the area enclosed by each section curve of the hollow cavity is kept basically consistent so as toForming a regular foam-filled cavity; mixing L with 4 Curve offset G 5 Set as parameters G, L 0 -L 3 The offset is sequentially decreased to be 0.9G, 0.85G, 0.82G and 0.76G respectively, and the value range of G is limited to be 11-19% of the width of the cross-section blade.
4. The method for integrally designing the blade material-structure of the resin-based composite hollow fan according to claim 3, wherein: in the step 2, the automatic mesh division specifically includes: firstly, dividing a hollow area and a solid area of the blade into an M4 plane; and then, dividing the smooth region in the middle of the blade from the profiled regions with blade edge configurations on two sides, determining that all points required by a dividing plane are structural midpoints, and acquiring and inputting the points into a command script in three-dimensional modeling software.
5. The method for integrally designing the blade material-structure of the resin-based composite hollow fan according to claim 4, wherein the method comprises the following steps: in the step 2, the constraint criteria for selecting the ply angle specifically include: (1) a layering balance symmetry principle: the layering sequence is symmetrical about the middle plane, the layering angles are kept balanced, and the number of layers at 45 degrees is kept the same as that at +45 degrees; (2) according to the ply orientation principle under the load condition: the 0-degree layering has stronger capability of bearing uniaxial tensile load; the 90-degree paving layer has stronger capacity of bearing shearing load; the plus or minus 45-degree layering has stronger capability of bearing torsional load; selecting a layering mode according to the actual loading condition; (3) layering sequence principle: the interlaminar stress is reduced by adopting a staggered laying mode, the strength performance is improved, and 0-degree laying layers are not laid on the upper surface and the lower surface of the component.
6. The integrated design method of the resin matrix composite hollow fan blade material-structure as claimed in claim 5, wherein: the key variables in step 4 include: transverse tensile strength Y T Longitudinal modulus of elasticity E 1 And transverse modulus of elasticity E 2 And obtaining the selection range of the key variable through the main effect graph: transverse tensile strength Y T >40MPa, modulus of elasticity in the longitudinal direction E 1 >160GPa and transverse elastic modulus E 2 <9000Mpa。
7. The method for integrally designing the blade material-structure of the resin-based composite hollow fan according to claim 6, wherein: in step 5, the limit of the optimization constraint is determined by the following method: the Chua-Wu strength factor is greater than or equal to 1, represents that the composite material structure is damaged and does not meet the strength requirement; if the number is less than 1, the composite material structure does not lose efficacy and meets the strength requirement; the safety coefficient of the composite material is not lower than 1.5, namely the Chua-Wu strength factor is less than 0.66; the ratio of the maximum deformation to the height of the blade body is less than 1 percent; the blade has a margin of resonance of at least 10%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211079821.XA CN115438427A (en) | 2022-09-05 | 2022-09-05 | Resin-based composite material hollow fan blade material-structure integrated design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211079821.XA CN115438427A (en) | 2022-09-05 | 2022-09-05 | Resin-based composite material hollow fan blade material-structure integrated design method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115438427A true CN115438427A (en) | 2022-12-06 |
Family
ID=84246579
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211079821.XA Pending CN115438427A (en) | 2022-09-05 | 2022-09-05 | Resin-based composite material hollow fan blade material-structure integrated design method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115438427A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116522420A (en) * | 2023-06-25 | 2023-08-01 | 山东石油化工学院 | Mechanical property simulation design method and system for curved surface column type composite material |
-
2022
- 2022-09-05 CN CN202211079821.XA patent/CN115438427A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116522420A (en) * | 2023-06-25 | 2023-08-01 | 山东石油化工学院 | Mechanical property simulation design method and system for curved surface column type composite material |
| CN116522420B (en) * | 2023-06-25 | 2023-08-29 | 山东石油化工学院 | Mechanical property simulation design method and system for curved surface column type composite material |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107103138A (en) | A kind of laser peening variation rigidity light weight method | |
| Peeters et al. | Effect of steering limit constraints on the performance of variable stiffness laminates | |
| CN110083900B (en) | Rapid collaborative optimization method for hybrid fiber composite material plate shell structure | |
| CN103366070B (en) | A kind of composite material beam method for designing that can be used for helicopter and Fixed Wing AirVehicle | |
| CN115438427A (en) | Resin-based composite material hollow fan blade material-structure integrated design method | |
| CN105447269A (en) | Non-structural mass trimming method for airplane in steady overload state | |
| Goerke et al. | Aerodynamic and mechanical optimization of CF/PEEK blades of a counter rotating fan | |
| CN110866353B (en) | Aircraft composite material structure optimization method based on strain neighborhood | |
| Lozano et al. | A design algorithm to model fibre paths for manufacturing of structurally optimised composite laminates | |
| CN112507587A (en) | Variable-stiffness composite material structure optimization design method oriented to compression stability | |
| CN103678763A (en) | Method for aeroelastic tailoring of composite wing and genetic/sensitivity-based hybrid optimization method of composite wing | |
| CN112100880A (en) | Optimized design method for ceramic matrix composite material laying prefabricated body | |
| Muramatsu et al. | Distributed-parametric optimization approach for free-orientation of laminated shell structures with anisotropic materials | |
| Moors et al. | Weight trades in the design of a composite wing box: effect of various design choices | |
| Vasilopoulos et al. | CAD-based aerodynamic optimization of a compressor stator using conventional and adjoint-driven approaches | |
| CN111859483B (en) | Lightweight design method for armor type thin-wall structure | |
| Tian et al. | Buckling optimization of curvilinear fiber-reinforced composite structures using a parametric level set method | |
| CN110826284B (en) | Modeling and analyzing method for composite material laminated board of interweaved and laminated mixed laying layers | |
| CN115680784B (en) | Modeling and calculating method for laminated structure resin-based composite material blade | |
| Baranovski et al. | STRUCTURALLY OPTIMIZED POLYMER COMPOSITE WING DESIGN. PART 2: TOW-STEERED COMPOSITE | |
| CN108595724A (en) | Composite material revolving meber design method | |
| CN113987689A (en) | Composite material grid reinforced pressure frame comprehensive optimization design method based on shape modification | |
| CN117436344B (en) | Wind turbine blade structure optimization design method based on parameterization description | |
| Zhao et al. | Multiobjective Optimization of Composite Flying-wings with SpaRibs and Multiple Control Surfaces | |
| Bahia Monteiro et al. | Bi-level Multidisciplinary Design Optimization of a Wing Considering Maneuver Load Alleviation and Flutter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |