CN116595656A - Regional thin layer unit modeling method for bolt connection structure of mounting edge of casing - Google Patents
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Abstract
A modeling method for a zoned lamellar unit of a bolt connection structure of a mounting edge belongs to the technical field of finite element simulation of aeroengines/gas turbines, and comprises the following steps: step 1: establishing a thin-layer-free casing installation side bolt connection model; step 2: dividing grids, and determining a gridded installation edge model; step 3: setting constraint boundary conditions and load boundary conditions of the installation edge model; step 4: obtaining contact stress distribution of a bonding surface, and obtaining boundary coordinates of different stress areas of the bonding surface; step 5: processing the boundary to obtain a smooth boundary curve; step 6: obtaining a zoned lamellar unit structural model and the like. According to the invention, the thin layer unit modeling is carried out on the installation side bolt connection structure in a zoning way, so that a reliable modeling method is provided for finite element simulation of the installation side bolt connection structure, errors generated when the installation side bolt connection structure of the aero-engine/gas turbine casing is analyzed are reduced, and the simulation analysis precision and efficiency are further improved.
Description
Technical Field
The invention belongs to the technical field of finite element simulation of aero-engine/gas turbine structures, and particularly relates to a split-region thin layer unit modeling method of a bolt connection structure of a casing mounting edge.
Background
The bolt connection structure has the characteristics of simple installation and strong practicability, and is widely applied to connection of aero-engine/gas turbine components. Because of the structural requirement of the mounting edge of the aero-engine/gas turbine casing, the mounting edge is usually required to bear a large load, and it is particularly important to accurately simulate the stress state of the structure. However, the bolt connection structure is complex, so that the integral structure mutation of the aero-engine/gas turbine is easy to cause, and the dynamic characteristics of the aero-engine are influenced. Meanwhile, the bolt connection needs to apply larger pretightening force, so that a plurality of nonlinear factors are generated at the contact part, and a plurality of errors are generated when the rigidity characteristics of the bolt connection are analyzed. Thus, accurate modeling of the bolted connections is the basis for analyzing the stiffness characteristics of the bolted connections. Recent studies have shown that when the bolt preload is sufficiently large or the external excitation amplitude is relatively small, the nonlinear properties of the bolted joint structure can be ignored and linearized. With the development of finite element theory and the improvement of computer storage and computing power, people begin to adopt entity units to carry out high-fidelity modeling on an aeroengine, and neglect the nonlinear characteristics of a bolt connection structure, so that a thin-layer unit method model appears.
The thin layer unit method is to define a layer of virtual material capable of simulating the mechanical characteristics of contact between adjacent contact bodies, to equivalently simulate the actual interface contact stiffness by using the mechanical property parameters of the interface virtual material, and to use a whole thin layer to replace the functions of bolts and pretightening force. Therefore, the thin layer unit method can simulate a bolt connection structure in complex machinery, maintain the structural integrity, more accurately represent the linear rigidity characteristic of the connection part, and the corrected model can be used for subsequent modal analysis and steady state response analysis and can be combined with a physical unit to establish a high-fidelity complete machine model.
However, the method has the defects that firstly, in the finite element modeling process, the thickness of the thin layer unit is selected to determine the accuracy of the simulation result of the thin layer unit, and if the thickness is selected to be too large, the thin layer unit is equivalent to a solid unit and cannot have the simulation effect; too small a thickness results in difficult model calculation, so the thickness selection of the lamellar elements is of great importance. Secondly, because the determination of the material parameters of the thin-layer unit almost all depends on related experimental data, for a complex mechanical structure, due to the limitation of conditions, a lot of experiments are difficult to obtain or cannot obtain proper experimental data at all, and due to the non-uniform distribution of the rigidity of the bolting structure, the common thin-layer unit method cannot accurately simulate the rigidity distribution under different stresses, and the problem of non-uniform axial rigidity distribution of the bolting cannot be considered, so that the result must be corrected through the experimental data. Therefore, there are certain limitations and disadvantages to the application of the thin-layer unit method in the modeling of the complete machine of an aero-engine/gas turbine and in the analysis of the dynamic characteristics.
Disclosure of Invention
Based on the technical problems, the invention provides a split-region thin-layer unit modeling method of a casing installation side bolt connection structure, which is used for modeling the casing installation side bolt connection structure, providing a reliable theoretical model for finite element simulation of the casing installation side bolt connection structure, and is suitable for the problems that when pretightening force is large enough or external excitation amplitude is small, the common thin-layer unit method cannot accurately simulate rigidity distribution under different stresses, and the result is inaccurate.
The invention adopts the following technical scheme:
a modeling method for a split-region thin layer unit of a bolt connection structure of a mounting edge of a casing comprises the following steps:
step 1: according to structural parameters of the mounting edge of the case, a bolt connection model of the mounting edge of the thin-layer-free case is established;
step 2: performing grid division on the thin-layer-free casing installation edge bolting model established in the step 1, and determining a gridded installation edge model;
step 3: setting constraint boundary conditions and load boundary conditions of the installation side model for the model subjected to grid division in the step 2;
step 4: obtaining the contact stress distribution of the joint surface of the mounting edge of the casing through finite element calculation, and obtaining the boundary coordinates of each different stress area of the contact surface;
step 5: processing the boundary by curve fitting to obtain a smooth boundary curve;
step 6: modifying the bolted connection casing model by using a layer unit theory to obtain a regional thin layer unit structure model;
step 7: calculating to obtain the contact stiffness of each regional thin layer unit;
step 8: calculating to obtain the thickness of the thin layer unit;
step 9: calculating to obtain the elastic modulus of the thin layer units in different areas;
step 10: and setting the obtained parameters into the regional thin layer unit structural model to obtain a complete structural model.
Further, the step 1 is specifically to simplify the fan-shaped bolt connecting piece of the original casing installation edge into an L-shaped beam, simplify the twelve-angle bolts and the twelve-angle nuts of the original casing installation edge into cylinders, and establish a simplified model.
Further, in the step 2, a hexahedral grid is specifically selected to divide the thin-layer-free casing installation side bolt connection model established in the step 1 into grids, the geometric body size of the casing installation side and the bolt model is set to be 1mm, meanwhile, grid encryption processing is carried out on the casing installation side contact surface grid, and the unit size of the two contact surfaces is set to be 0.5mm.
Further, the step 3 specifically includes that firstly, the contact surface of the mounting side is set to be in friction contact, the friction coefficient f=0.15, an enhanced lagrangian algorithm is adopted in contact setting, then, bolt pretightening force is set for a bolt structure, finally, one end of a model is set to be fixedly restrained, axial load in the vertical direction is applied to the other end of the model, the load is loaded in two steps, pretightening force is applied in the first step, and the pretightening force is locked in the second step, and meanwhile, the rest load is applied.
Further, the step 5 is specifically usingUGCurve fitting function in software is obtained for step 4And processing the obtained boundary position coordinates, deleting scattered coordinates with larger individual deviation, and further obtaining a smooth boundary curve.
Further, the step 6 is specifically to modify the bolting casing model by applying layer unit theory: the upper and lower connecting pieces are reserved, thin layer units are added, and then the thin layer units are divided by using a zoned layer unit method; the specific dividing method of the thin layer unit comprises the following steps: at the position ofUGAnd (3) carrying out stretching treatment and Boolean operation on the joint surface model of the installation edge of the divided region according to the size of the contact stress in software, and dividing the thin layer unit into different regions to obtain a regional thin layer unit structure model.
Further, the step 7 is specifically by the formulak=0.9933p 0.6736 Calculating the contact stiffness of each area of the thin layer unit, whereinkIs the normal contact stiffness value per unit area,pnormal stress per unit area for the bonding face.
Further, the step 8 specifically includes: by the formulaCalculating the thickness of the thin layer unit, wherein Ratio is a proportionality coefficient, l 1 、l 2 The length and width of the lamellar region are respectively, h is the thickness of the lamellar unit.
Further, the step 9 specifically includes: by the formulaCalculating the elastic modulus of the thin layer units in different areas, whereinE i ’ ，A i ’ ，L i ’ ，K i ’ The elastic modulus, the cross-sectional area, the thickness and the contact stiffness of each part of the structure are respectively.
Further, the step 10 specifically includes: and (3) modifying engineering data in a Workbench, respectively setting the elastic modulus of each thin layer region, uniformly modifying the thickness of the thin layer unit, and setting the obtained parameters into a thin layer unit structure model of a sub-region, thereby obtaining a final bolt connection model of the mounting edge of the thin layer case of the sub-region.
The invention has the advantages and beneficial effects that:
the regional thin layer unit modeling method for the bolt connection structure of the mounting side of the aero-engine/gas turbine casing can accurately simulate the geometric form of the bolt connection structure of the mounting side of the aero-engine/gas turbine casing, can provide an accurate modeling method for the bolt connection structure of the mounting side of the aero-engine casing with different sizes, provides a reliable theoretical model for finite element simulation of the bolt connection structure, and can consider the change of the contact rigidity caused by the integral rigidity and more accurately simulate the rigidity characteristic of the bolt connection structure of the mounting side of the aero-engine/gas turbine casing.
Drawings
FIG. 1 (a) is a diagram of a conventional aircraft engine bolted thin-walled cylindrical casing mounting edge structure;
FIG. 1 (b) is a thin-layer-less casing mounting edge bolting model;
FIG. 2 is a schematic diagram of a thin-layer-free cell model grid;
FIG. 3 is a lamellar less case mounting side model boundary condition;
FIG. 4 is a schematic view of the contact stress distribution of the joint surface of the mounting edge;
FIG. 5 is a schematic diagram of a process of extracting coordinates of each boundary;
FIG. 6 is a graph of curve fitting and smooth curve connection;
FIG. 7 is a schematic view of contact surface stress zoning;
FIG. 8 is a sectional lamina case mounting side bolting pattern.
Description of the embodiments
The invention is further explained below with reference to the drawings and examples.
A modeling method for a split-region thin layer unit of a bolt connection structure of a mounting edge of a casing comprises the following steps:
step 1: according to structural parameters of the mounting edge of the case, a bolt connection model of the mounting edge of the thin-layer-free case is established;
for the convenience of calculation, the structure of the installation edge of the traditional aeroengine bolt connection thin-wall cylinder casing as shown in the figure 1 (a) is simplified into an L-shaped beam, meanwhile, for the purpose of improving calculation efficiency and grid quality, the twelve-angle bolts and the twelve-angle nuts of the original casing installation edge are simplified into cylinders, the chamfering and the spigot of the installation edge are reserved, and a simplified model is established. The specific parameters are set based on a real L-shaped beam model, and the finite element model and the parameter settings are shown in fig. 1 (b): the total length of the thin-layer-free casing installation side bolt connection model casing is 400mm, the outer diameter of the installation side is 68mm, the thickness of the installation side is 2.5mm, the bolt length is 5mm, and the radius of the bolt is 4.5mm. In addition, the selected material is structural steel, and the physical properties of the structural steel are as follows:E=20600MPa，v=0.3，ρ=7.85g/cm 3 。
step 2: performing grid division on the thin-layer-free casing installation edge bolting model established in the step 1, and determining a gridded installation edge model;
the mesh quality is ensured and the convergence speed is improved during mesh division, so that the mesh division method shown in fig. 2 is adopted: the type of the grid is selected to be a hexahedral grid, the accuracy of the finite element result is ensured by a contact surface grid encryption mode, and in addition, the number of grid nodes is reduced as much as possible to reduce the finite element calculation time. Step 2 is specifically to select hexahedral grids to divide grids of the thin-layer-free casing installation side bolt connection model established in step 1, set the geometric body size of the casing installation side and the bolt model to be 1mm, and simultaneously encrypt grids of the casing installation side contact surface and set the unit size of the two contact surfaces to be 0.5mm. Therefore, the convergence rate is improved while the grid quality is ensured.
The specific setting method is that the final obtained grid diagram without thin layer units is shown in fig. 2, and the total number of nodes and the total number of units are 932942 and 214891 respectively.
Step 3: setting constraint boundary conditions and load boundary conditions of the installation edge model;
in order to simulate the working state of the installation edge of a real aero-engine casingThe setting of the boundary conditions of the mounting edge model of the lamellar less casing is shown in figure 3. The method comprises the following steps: the mounting edge contact surface was first set to a friction contact with a coefficient of friction of 0.15 using the enhanced Lagrange algorithm. Then the bolt structures are all arranged in sizeF s =4000NIs used for the bolt pretightening force of the (a). Finally, in order to simulate the real situation, one end of the model is set as fixed constraint, and the other end is applied with axial load and pulling force in the vertical directionF N =5000NThe load is loaded in two steps, the pre-tightening force is applied in the first step, and the pre-tightening force is locked in the second step, and the rest load is applied at the same time.
Step 4: obtaining boundary coordinates of different stress areas of the contact surface by analyzing stress distribution conditions;
and obtaining the contact stress distribution of the joint surface of the mounting edge of the casing through finite element calculation. The specific stress distribution is shown in fig. 4, it can be seen that the contact stress around the bolt hole is far greater than other positions of the joint surface due to the action of the bolt pretightening force, and the contact stress gradually decreases along the radial direction of the bolt hole, and the calculated stress distribution result shows that 6 areas are distributed according to the stress size. And (3) using the Ansys Workbench to solve the self probe function in the system to find boundary points of stress values of each region, and obtaining coordinates of each boundary position. Taking the boundary between the region 4 and the region 5 as an example, the boundary coordinate extraction result is shown in fig. 5.
Step 5: processing the boundary by curve fitting to obtain a smooth boundary curve;
in order to improve the calculation efficiency and obtain the convergence result, a method as shown in FIG. 6 is usedUGAnd the curve fitting function in the software processes the coordinates of each boundary position obtained in the process and deletes scattered coordinates with larger individual deviation, thereby obtaining a smooth boundary curve. A modified interface stress zone diagram as shown in fig. 7 is finally obtained.
Step 6: modifying the bolted connection casing model by using a layer unit theory to obtain a regional thin layer unit structure model;
the bolt connection casing model is modified by the application layer unit theory, and the upper connection and the lower connection are reservedAnd adding thin layer units, and dividing the thin layer units by using a zoned layer unit method. The specific dividing method of the thin layer units comprises the following steps: at the position ofUGThe thin layer unit can be divided into different areas by carrying out stretching treatment and Boolean operation on the installation edge bonding surface model divided into 6 areas according to the size of the contact stress in software, and finally the sectional thin layer unit structure model shown in fig. 8 is obtained.
Step 7: calculating to obtain the contact stiffness of each regional thin layer unit;
by the formulak=0.9933p 0.6736 Calculating the contact stiffness of each area of the thin layer unit, whereinkIs the normal contact stiffness value per unit area,pto combine the face portion unit area normal stresses, the average of all node stresses in each region is used herein as the average stress for calculation. The results of the calculation are shown in table 1.
Table 1 shows the results of calculation of the sheet contact stiffness in each region
Step 8: calculating to obtain the thickness of the thin layer unit;
by the formulaWhere Ratio is the scaling factor, l 1 、l 2 The length and the width of the thin layer area are respectively, and h is the thickness of the thin layer unit; the structural parameters of the lamellar units can be taken in combination with the text>And has the data display: the Ratio is generally 10-100, and the thickness of the thin layer unit can be obtained through calculationhThe value of (2) is in the range of 0.68mm-6.8mm, the thickness of the lamellar unit is selected herehIs 1mm.
Step 9: calculating to obtain the elastic modulus of the thin layer units in different areas;
by the formulaCalculating the elastic modulus of the thin layer units in different areas, whereinE i ’ ，A i ’ ，L i ’ ，K i ’ The elastic modulus, the cross-sectional area, the thickness and the contact stiffness of each part of the structure are respectively. The results of the elastic modulus calculation are shown in table 2.
Table 2 shows the results of calculation of the modulus of elasticity of the thin layer in each region
| Thin layer region | Elastic modulus/GPa | Poisson's ratio |
| 1 | 29.01 | 0.3 |
| 2 | 26.36 | 0.3 |
| 3 | 22.09 | 0.3 |
| 4 | 17.49 | 0.3 |
| 5 | 11.91 | 0.3 |
| 6 | 0.04 | 0.3 |
Step 10: setting the obtained parameters into a regional thin layer unit structure model to obtain a complete structure model;
first atUGSetting the thickness of the thin layer unit in the step 6 to be 1mm in software, then importing a complete UG model into a Workbench, finally modifying engineering data in the Workbench, adding 6 new materials, and assigning two properties of density in physical properties and isotropic elasticity in linear elasticity to the new materials, wherein the density of each material is 7850kg/m 3 The Young's modulus and Poisson's ratio of each material were set according to the data in Table 2. And setting the obtained parameters into the sectional thin layer unit structure model, and obtaining a final sectional thin layer case mounting edge bolting model.
According to the invention, the thin layer unit modeling is carried out on the installation side bolt connection structure in a zoning way, so that a reliable modeling method is provided for finite element simulation of the installation side bolt connection structure, errors generated when the installation side bolt connection structure of the aero-engine/gas turbine casing is analyzed are reduced, and the simulation analysis precision and efficiency are further improved.
While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that alterations, modifications, substitutions and variations may be made in the above embodiments by those skilled in the art within the scope of the invention.
Claims (10)
1. A regional thin layer unit modeling method of a bolt connection structure of a casing installation edge is characterized by comprising the following steps of: the method comprises the following steps:
step 1: according to structural parameters of the mounting edge of the case, a bolt connection model of the mounting edge of the thin-layer-free case is established;
step 2: performing grid division on the thin-layer-free casing installation edge bolting model established in the step 1, and determining a gridded installation edge model;
step 3: setting constraint boundary conditions and load boundary conditions of the installation side model for the model subjected to grid division in the step 2;
step 4: obtaining the contact stress distribution of the joint surface of the mounting edge of the casing through finite element calculation, and obtaining the boundary coordinates of each different stress area of the contact surface;
step 5: processing the boundary by curve fitting to obtain a smooth boundary curve;
step 6: modifying the bolted connection casing model by using a layer unit theory to obtain a regional thin layer unit structure model;
step 7: calculating to obtain the contact stiffness of each regional thin layer unit;
step 8: calculating to obtain the thickness of the thin layer unit;
step 9: calculating to obtain the elastic modulus of the thin layer units in different areas;
step 10: and setting the obtained parameters into the regional thin layer unit structural model to obtain a complete structural model.
2. The method for modeling the split-area lamina unit of the bolt connection structure of the mounting edge of the casing according to claim 1, which is characterized by comprising the following steps: the step 1 is specifically that a fan-shaped bolt connecting piece of an original casing installation edge is simplified into an L-shaped beam, a twelve-angle bolt and a twelve-angle nut of the original casing installation edge are simplified into cylinders, and a simplified model is established.
3. The method for modeling the split-area lamina unit of the bolt connection structure of the mounting edge of the casing according to claim 1, which is characterized by comprising the following steps: step 2 is specifically to select hexahedral grids to divide grids of the thin-layer-free casing installation side bolt connection model established in step 1, set the geometric body size of the casing installation side and the bolt model to be 1mm, and simultaneously encrypt grids of the casing installation side contact surface and set the unit size of the two contact surfaces to be 0.5mm.
4. The method for modeling the split-area lamina unit of the bolt connection structure of the mounting edge of the casing according to claim 1, which is characterized by comprising the following steps: the step 3 is specifically that firstly, the contact surface of the mounting side is set to be in friction contact, the friction coefficient F=0.15, the contact setting adopts an enhanced Lagrange algorithm, then, the bolt pre-tightening force is set for the bolt structure, finally, one end of the model is set to be in fixed constraint, the other end of the model is applied with vertical upward axial load, the load is loaded in two steps, the pre-tightening force is applied in the first step, and the pre-tightening force is locked in the second step, and meanwhile, the rest load is applied.
5. The method for modeling the split-area lamina unit of the bolt connection structure of the mounting edge of the casing according to claim 1, which is characterized by comprising the following steps: said step 5 is specifically the use ofUGAnd (3) processing the coordinates of each boundary position obtained in the step (4) by a curve fitting function in software, deleting scattered coordinates with larger individual deviation, and further obtaining a smooth boundary curve.
6. The method for modeling the split-area lamina unit of the bolt connection structure of the mounting edge of the casing according to claim 1, which is characterized by comprising the following steps: the step 6 is specifically to modify the bolt connection casing model by applying layer unit theory: the upper and lower connecting pieces are reserved, thin layer units are added, and then the thin layer units are divided by using a zoned layer unit method; the specific dividing method of the thin layer unit comprises the following steps: at the position ofUGAnd (3) carrying out stretching treatment and Boolean operation on the joint surface model of the installation edge of the divided region according to the size of the contact stress in software, and dividing the thin layer unit into different regions to obtain a regional thin layer unit structure model.
7. The method for modeling the split-area lamina unit of the bolt connection structure of the mounting edge of the casing according to claim 1, which is characterized by comprising the following steps: the step 7 is specifically realized by a formulak=0.9933p 0.6736 Calculating the contact stiffness of each area of the thin layer unit, whereinkIs the normal contact stiffness value per unit area,pnormal stress per unit area for the bonding face.
8. The method for modeling the split-area lamina unit of the bolt connection structure of the mounting edge of the casing according to claim 1, which is characterized by comprising the following steps: the step 8 specifically comprises the following steps: by the formulaCalculating the thickness of the thin layer unit, wherein Ratio is a proportionality coefficient, l 1 、l 2 The length and width of the lamellar region are respectively, h is the thickness of the lamellar unit.
9. The method for modeling the split-area lamina unit of the bolt connection structure of the mounting edge of the casing according to claim 1, which is characterized by comprising the following steps: the step 9 specifically comprises the following steps: by the formulaCalculating the elastic modulus of the thin layer units in different areas, whereinE i ’ ，A i ’ ，L i ’ ，K i ’ The elastic modulus, the cross-sectional area, the thickness and the contact stiffness of each part of the structure are respectively.
10. The method for modeling the split-area lamina unit of the bolt connection structure of the mounting edge of the casing according to claim 1, which is characterized by comprising the following steps: the step 10 specifically comprises the following steps: and (3) modifying engineering data in a Workbench, respectively setting the elastic modulus of each thin layer region, uniformly modifying the thickness of the thin layer unit, and setting the obtained parameters into a thin layer unit structure model of a sub-region, thereby obtaining a final bolt connection model of the mounting edge of the thin layer case of the sub-region.
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| CN202310269984.2A CN116595656A (en) | 2023-03-20 | 2023-03-20 | Regional thin layer unit modeling method for bolt connection structure of mounting edge of casing |
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| CN202310269984.2A CN116595656A (en) | 2023-03-20 | 2023-03-20 | Regional thin layer unit modeling method for bolt connection structure of mounting edge of casing |
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