Shock resistance optimization design method and system for supporting structure of marine gas turbine

Abstract

The invention provides a ship gas turbine supporting structure shock resistance optimization design method and system, and relates to the field of ship mechanical equipment structure optimization design. The method comprises the following steps: S1, establishing a topological optimization mathematical model of a gas turbine support structure in software by using an SIMP material interpolation model in a variable density method; s2, loading the gas turbine support structure based on an equivalent static method; s3, carrying out impact simulation calculation on the optimized gas turbine supporting structure; and S4, comparing results of the support structure before and after optimization. At the initial stage of shock resistance optimization design of a ship gas turbine supporting structure, dynamic response simulation often needs to consume a large amount of calculation time and resources, so that each iteration of structural dynamics analysis is time-consuming, the efficiency is low, and the convergence of a result is difficult to guarantee. Therefore, the optimization design method is efficient and convenient to implement, and the impact resistance of the ship gas turbine supporting structure is improved.

Description

Technical Field

[0001] The present invention belongs to the field of structural optimization design of ship mechanical equipment, and specifically relates to an anti-shock optimization design method and system for a ship's gas turbine support structure. Background Art

[0002] It is crucial to carry out structural anti-shock optimization design on the ship's gas turbine support structure, which can ensure the stable operation of the gas turbine system in the event of sudden maritime situations such as collisions or extreme wave events. The optimization design can not only improve the safety and reliability of the gas turbine and its auxiliary components, but also prevent equipment damage caused by shocks and avoid the occurrence of chain failures. The anti-shock optimization design of the gas turbine support structure is directly related to the safe navigation of the ship, the safety of personnel and the control of operating costs, and is also a key measure to meet the requirements of the harsh maritime operation environment.

[0003] The existing anti-shock optimization methods for ship gas turbine support structures mainly include using finite element analysis for dynamic response simulation, combining topology optimization technology to improve the structural layout, and applying multi-objective optimization algorithms to balance weight and strength requirements. However, dynamic response simulation consumes a large amount of computing time and resources. Especially in the early design stage, the detailed structural dynamics analysis has a long iteration time, low efficiency and difficult convergence of results. Therefore, it is necessary to propose an efficient and easy-to-implement anti-shock optimization design method for ship gas turbine support structures. Summary of the Invention

[0004] The present invention provides an anti-shock optimization design method for a ship's gas turbine support structure, in order to effectively simplify complex dynamic problems into static problems, so as to achieve efficient utilization of materials and reduction of structural weight while ensuring structural strength and stability.

[0005] The present invention provides an anti-shock optimization design system for a ship's gas turbine support structure, which is used to implement an anti-shock optimization design method for a ship's gas turbine support structure.

[0006] The present invention is realized through the following technical solutions:

[0007] An anti-shock optimization design method for a ship's gas turbine support structure, the method comprising the following steps:

[0008] Step S1, establish a topological optimization mathematical model of the gas turbine support structure in the software using the SIMP material interpolation model in the variable density method;

[0009] Step S2, load and optimize the topological optimization mathematical model of the gas turbine support structure in step S1 based on the equivalent static method;

[0010] Step S3, perform shock simulation calculation on the gas turbine support structure after the optimization design in step S2;

[0011] Step S4: Compare the results of the support structure before and after optimization to achieve the anti-shock optimization design of the ship's gas turbine support structure.

[0012] Further, in the SIMP material interpolation model of the variable density method in step S1, it is specifically assumed that the relative density of each material unit takes continuous values between 0 and 1.

[0013] Further, the mathematical expression of the SIMP material interpolation model in step S1 is:

[0014]

[0015] In the formula, E(x i ) is the Young's modulus of material unit i; E min is the Young's modulus of the material when the unit relative density is 0; x i is the unit relative density; P is the penalty coefficient, and E0 is the Young's modulus of the material when the unit relative density is 1.

[0016] The numerical model for the topology optimization of the gas turbine support structure in step S1 is established by TOSCA.

[0017] Further, in the equivalent static force method of step S2, the impact dynamic load is replaced by a static load for the topology optimization design of the gas turbine support structure. Specifically, the equivalent static load that the ship equipment should bear is {N} times the self-weight of the equipment, that is

[0018] F = F 等效静力 = gmN

[0019] In the formula, g is the acceleration due to gravity, m is the mass matrix, and N is the impact design factor.

[0020] Further, loading and optimization are carried out according to the equivalent static force method, and finally a topology optimization model with the minimum compliance of the support structure under stress and volume constraints is obtained:

[0021]

[0022] In the formula, is the topology design variable vector, m is the number of elements in the structure; is the weight coefficient under the l-th load condition; C tol is the combined target compliance; C l is the compliance under the l-th load condition, K is the global stiffness matrix; U l is the displacement vector of the structure in the global coordinate system under the l-th load condition; F l is the l-th load condition; n is the number of load conditions; ρ i and are the initial volume of the i-th physical variable and the No. unit respectively; v (0) is the total volume of the structure during the initial iteration; is the Mises stress value of the j-th section of the i-th unit under the l-th group of load conditions; ρ max and ρ min are the upper and lower limits of the topology design variable respectively, taking V * as the target volume.

[0023] Furthermore, the impact simulation calculation in step S3 is carried out by finite element software.

[0024] Furthermore, the results of step S4 include the gas turbine support structure models before and after optimization, the maximum impact stress received by the gas turbine support structure before and after optimization, and the mass of the gas turbine support structure before and after optimization.

[0025] A ship gas turbine support structure anti-impact optimization design system, the system uses the ship gas turbine support structure anti-impact optimization design method as described above, and the system includes:

[0026] Gas turbine support structure mathematical model establishment module: Use the SIMP material interpolation model in the variable density method to establish the topology optimization mathematical model of the gas turbine support structure in the software;

[0027] Loading and optimization module of the mathematical model: Load and optimize the topology optimization mathematical model of the gas turbine support structure based on the equivalent static force method;

[0028] Impact simulation calculation module: Carry out impact simulation calculation on the optimized gas turbine support structure;

[0029] Result comparison module: Compare the results of the support structure before and after optimization to achieve the anti-impact optimization design of the ship gas turbine support structure.

[0030] A computer device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, it implements the ship gas turbine support structure anti-impact optimization design method as described above.

[0031] A computer-readable storage medium, in which a computer program is stored. When the computer program is executed by a processor, it implements the ship gas turbine support structure anti-impact optimization design method as described above.

[0032] The beneficial effects of the present invention are:

[0033] The present invention can provide a relatively simple way to handle impact loads, and by reasonably selecting the equivalent load, it can reflect the true stress state of the structure.

[0034] The method of the present invention is very useful for those who need to quickly evaluate the response of a structure under impact conditions, especially in the early design stage. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 It is a flowchart of the method of the present invention.

[0036] Figure 2 It is a graph of the design values of the impact factors of the ship equipment of the present invention.

[0037] Figure 3 It is a schematic diagram of the support structure model before and after optimization of the present invention, where (a) is the front view before optimization, (b) is the side view before optimization, (c) is the front view after optimization, and (d) is the side view after optimization.

[0038] Figure 4 It is a schematic diagram of the maximum impact stress of the support before optimization, where (a) is the right front support, (b) is the left front support, (c) is the right rear support, and (d) is the left rear support.

[0039] Figure 5 It is a schematic diagram of the maximum impact stress of the support after optimization of the present invention, where (a) is the right front support, (b) is the left front support, (c) is the right rear support, and (d) is the left rear support. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0040] In the following description, for the purpose of illustration rather than limitation, specific details such as specific system structures, technologies, etc. are set forth in order to provide a thorough understanding of the embodiments of the present application. However, those skilled in the art should clearly understand that the present application can also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to avoid unnecessary details from obscuring the description of the present application.

[0041] It should be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of the described features, wholes, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components, and / or their combinations.

[0042] It should also be understood that the terms used in the specification of the present application are only for the purpose of describing specific embodiments and are not intended to limit the present application. As used in the specification of the present application and the appended claims, unless the context clearly indicates otherwise, the singular forms "a", "an", and "the" are intended to include the plural forms.

[0043] The following is combined with the attached drawings of the specification of the present application Figures 1-5, the technical solutions in the embodiments of the present application are clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present application.

[0044] In the following description, many specific details are set forth in order to fully understand the present application. However, the present application may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the connotation of the present application. Therefore, the present application is not limited by the specific embodiments disclosed below.

[0045] Embodiment 1

[0046] In the initial stage of the anti - impact optimization design of the ship's gas turbine support structure, performing dynamic response simulation often consumes a large amount of computing time and resources. This makes each iteration of the structural dynamics analysis particularly time - consuming, not only inefficient, but also difficult to ensure the convergence of the results. This embodiment provides a method for the anti - impact optimization design of the ship's gas turbine support structure, and the method includes the following steps:

[0047] Step S1: Use the SIMP material interpolation model in the variable density method to establish a topological optimization mathematical model of the gas turbine support structure in the software;

[0048] Step S2: Based on the equivalent static force method, load and optimize the topological optimization mathematical model of the gas turbine support structure in Step S1;

[0049] Step S3: Perform impact simulation calculation on the gas turbine support structure after the optimization design in Step S2;

[0050] Step S4: Compare the results of the support structure before and after optimization to achieve the anti - impact optimization design of the ship's gas turbine support structure.

[0051] This application overcomes the difficulties in the structural optimization of the traditional impact field. By using structural topology optimization with the equivalent static force method, the anti - impact performance of the structure is improved. Traditional anti - impact optimizations are all simple changes in structural thickness, etc., and the optimization effect is not good. The current method has wide applicability, is convenient and rapid for optimization, can achieve rapid iteration of the optimization scheme, and has a good optimization effect.

[0052] Further, the SIMP material interpolation model in the variable density method in Step S1 is specifically that the relative density of each unit of the material is assumed to take continuous values between 0 and 1.

[0053] Further, the mathematical expression of the SIMP material interpolation model in Step S1 is:

[0054]

[0055] Wherein, E(x i ) is the Young's modulus of the material unit i; E min is the Young's modulus of the material when the relative density of the unit is 0; x i is the relative density of the unit; P is the penalty coefficient, and E0 is the Young's modulus of the material when the relative density of the unit is 1;

[0056] The numerical model for topology optimization of the gas turbine support structure in step S1 is established by TOSCA.

[0057] The numerical model for topology optimization of the gas turbine support structure is a well-known formula in the art.

[0058] Furthermore, the equivalent static method in step S2 uses static loads to replace the impact dynamic loads for the topology optimization design of the gas turbine support structure. Specifically, the equivalent static load that the ship equipment should bear is {N} times the self-weight of the equipment, that is

[0059] F = F 等效静力 = gmN

[0060] Wherein, g is the acceleration due to gravity, m is the mass matrix, and N is the impact design factor.

[0061] N is determined according to the design value curve of the impact factor of the ship equipment. Specifically:

[0062] The actual mass of the gas turbine model is 28t. Combining Figure 2 , the equivalent static load is determined as follows:

[0063] (1) Vertical impact load input:

[0064] F 垂向等效静载荷 = 15mg

[0065] (2) Lateral impact load input:

[0066] F 横向等效静载荷 = 9mg

[0067] (3) Longitudinal impact load input:

[0068] F 纵向等效静载荷 = 7mg

[0069] In this specific embodiment, only the topology optimization design of the bracket considering the vertical impact load is considered. The topology optimization design of the brackets for the lateral and longitudinal impact loads can refer to the vertical direction.

[0070] For further limitation on the loading and optimization of the gas turbine support structure based on the equivalent static method, the equivalent static method is to obtain the relationship between element stress and strain by solving the displacement vectors of each node according to the static force equation.

[0071] Furthermore, the static equilibrium equation is:

[0072] Ku = F

[0073] where K is the total stiffness matrix, u is the nodal displacement vector, and F is the equivalent static load.

[0074] The expressions for the obtained stress and strain are:

[0075] ε = Bu

[0076] σ = Dε

[0077] where ε is the element strain, B is the geometric matrix, u is the nodal displacement, σ is the element stress, and D is the elasticity matrix.

[0078] Furthermore, within the TOSCA software, loading and optimization are carried out based on the equivalent static method, and finally a topology optimization model with minimized compliance of the stent structure under stress and volume constraints is obtained:

[0079]

[0080] In the formula, is the topology design variable vector, and m is the number of elements in the structure; is the weight coefficient under the l-th load case; C tol is the combined objective compliance; C l is the compliance under the l-th load case, K is the global stiffness matrix; U l is the displacement vector of the structure in the global coordinate system under the l-th load case; F l is the l-th load case; n is the number of load cases; ρ i and are the initial volume of the i-th physical variable and the i-th element respectively; v (0) is the total volume of the structure at the initial iteration; is the Mises stress value of the j-th cross-section of the i-th element under the l-th load case; ρ max and ρ min are the upper and lower limits of the topology design variable respectively. In the present invention, V * is the target volume.

[0081] Figure 3 is the comparison of the stent structure models before and after optimization.

[0082] Furthermore, the impact simulation calculation in step S3 is carried out by finite element software.

[0083] The impact simulation calculation of the support structure after structural topology optimization design is further limited. The optimized structural model is imported into the finite element software. In this implementation, taking ABAQUS as an example, the imported model is meshed, constraints are established, and loads are applied for impact simulation calculation.

[0084] Furthermore, the results of step S4 include the support structure models of the gas turbine before and after optimization, the maximum impact stresses suffered by the support structures of the gas turbine before and after optimization, and the masses of the support structures of the gas turbine before and after optimization.

[0085] Combined with Figure 4 、 Figure 5 , it is a comparison of the maximum impact stresses suffered by the gas turbine brackets before and after optimization. The impact resistance performance of the bracket structure after topology optimization is improved, and the maximum stress value under impact is greatly reduced. The maximum stress values of the four brackets in the front, rear, left, and right are reduced by at least 16% and at most 34%.

[0086] The mass of the bracket structure after topology optimization is reduced from 54.35 kg before optimization to 39.92 kg, a reduction of 14.43 kg, and the reduction ratio is 26.55%. This shows that topology optimization can reduce the mass of the structure, make full use of the structural materials, remove redundant materials, and save material costs.

[0087] Embodiment 2

[0088] This embodiment provides a ship gas turbine support structure impact resistance optimization design system. The system uses the ship gas turbine support structure impact resistance optimization design method as described in Embodiment 1. The system includes:

[0089] Gas turbine support structure mathematical model establishment module: Use the SIMP material interpolation model in the variable density method to establish the topological optimization mathematical model of the gas turbine support structure in the software;

[0090] Loading and optimization module of the mathematical model: Based on the equivalent static force method, load and optimize the topological optimization mathematical model of the gas turbine support structure;

[0091] Impact simulation calculation module: Perform impact simulation calculation on the gas turbine support structure after optimized design;

[0092] Result comparison module: Compare the results of the support structure before and after optimization to achieve the impact resistance optimization design of the ship gas turbine support structure.

[0093] Specifically, in the gas turbine support structure mathematical model establishment module, the SIMP material interpolation model in the variable density method is specifically that the relative density of each unit of the material is assumed to take continuous values between 0 and 1.

[0094] The mathematical expression of the SIMP material interpolation model of the gas turbine support structure mathematical model establishment module is:

[0095]

[0096] Wherein, E(x i ) is the Young's modulus of the material unit i; E min is the Young's modulus of the material when the relative density of the unit is 0; x i is the relative density of the unit; P is the penalty coefficient, and E0 is the Young's modulus of the material when the relative density of the unit is 1;

[0097] The numerical model of the topology optimization of the gas turbine support structure established by the gas turbine support structure mathematical model establishment module is established by TOSCA.

[0098] For the equivalent static force method of the loading and optimization module of the mathematical model, the impact dynamic load is replaced by the static load for the topology optimization design of the gas turbine support structure. Specifically, the equivalent static load that the ship equipment should bear is {N} times the self-weight of the equipment, that is

[0099] F = F 等效静力 = gmN

[0100] Wherein, g is the acceleration of gravity, m is the mass matrix, and N is the impact design factor.

[0101] N is determined according to the design value curve of the impact factor of the ship equipment. Specifically:

[0102] The actual mass of the gas turbine model is 28t. Combining Figure 2 , the equivalent static load is determined as follows:

[0103] (4) Vertical impact load input:

[0104] F 垂向等效静载荷 = 15mg

[0105] (5) Lateral impact load input:

[0106] F 横向等效静载荷 = 9mg

[0107] (6) Longitudinal impact load input:

[0108] F 纵向等效静载荷 = 7mg

[0109] In this specific embodiment, only the topology optimization design of the support considering the vertical impact load is considered. The topology optimization design of the support for the lateral and longitudinal impact loads can refer to the vertical direction.

[0110] Further limiting the loading and optimization of the gas turbine support structure based on the equivalent static force method, the equivalent static force method is to obtain the relationship between the element stress and strain by solving the displacement vector of each node according to the static force equation.

[0111] Furthermore, the static equilibrium equation is:

[0112] Ku = F

[0113] where K is the global stiffness matrix, u is the nodal displacement vector, and F is the equivalent static load.

[0114] The expressions for the obtained stress and strain are:

[0115] ε = Bu

[0116] σ = Dε

[0117] where ε is the element strain, B is the geometric matrix, u is the nodal displacement, σ is the element stress, and D is the elasticity matrix.

[0118] Furthermore, within the TOSCA software, loading and optimization are carried out according to the equivalent static method, and finally a topology optimization model with minimized compliance of the support structure under stress and volume constraints is obtained:

[0119]

[0120] In the formula, is the topology design variable vector, and m is the number of elements in the structure; is the weight coefficient under the l-th load case; C tol is the combined objective compliance; C l is the compliance under the l-th load case, K is the global stiffness matrix; U l is the displacement vector of the structure in the global coordinate system under the l-th load case; F l is the l-th load case; n is the number of load cases; ρ i and are the initial volumes of the i-th physical variable and the i-th element respectively; v (0) is the total volume of the structure at the initial iteration; is the Mises stress value of the j-th cross-section of the i-th element under the l-th load case; ρ max and ρ min are the upper and lower limits of the topology design variable respectively. In the present invention, V * is the target volume.

[0121] The impact simulation calculation of the impact simulation calculation module is performed by finite element software.

[0122] The support structure after structural topology optimization design is further defined for impact simulation calculation. The optimized structural model is imported into the finite element software. In this implementation, taking ABAQUS as an example, the imported model is meshed to establish constraints, and loads are applied for impact simulation calculation.

[0123] The results of the result comparison module include the gas turbine support structure models before and after optimization, the maximum impact stress on the gas turbine support structure before and after optimization, and the mass of the gas turbine support structure before and after optimization.

[0124] Combined with Figure 4 、 Figure 5 , it is a comparison of the maximum impact stress on the gas turbine bracket before and after optimization. The impact resistance performance of the bracket structure after topology optimization is improved, and the maximum stress value under impact is greatly reduced. The lowest reduction of the maximum stress values of the four brackets in the front, rear, left and right is 16%, and the maximum reduction is 34%.

[0125] The mass of the bracket structure after topology optimization is reduced from 54.35 kg before optimization to 39.92 kg, a reduction of 14.43 kg, and the reduction ratio is 26.55%. It shows that topology optimization can reduce the mass of the structure, make full use of the structural materials, remove redundant materials, and save material costs.

[0126] Embodiment 3

[0127] The embodiment of the present invention provides an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor. Among them, the memory is used to store software programs and modules, and the processor executes various functional applications and data processing by running the software programs and modules stored in the memory. The memory and the processor are connected by a bus. Specifically, when the processor runs the above computer program stored in the memory, any step in Embodiment 1 above is implemented.

[0128] It should be understood that in the embodiment of the present invention, the so-called processor may be a central processing unit (CPU), and the processor may also be other general-purpose processors, digital signal processors (DSPs), application specific integrated circuits (ASICs), off-the-shelf programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc.

[0129] The memory may include a read-only memory, a flash memory, and a random access memory, and provide instructions and data to the processor. A part or all of the memory may also include a non-volatile random access memory.

[0130] As can be seen from the above, the electronic device provided by the embodiment of the present invention can implement the anti-shock optimization design method of the ship engine support structure as described in Embodiment 1 by running a computer program. In the finite element software, a mathematical model for the topology optimization of the engine support structure is established by combining the SIMP material interpolation model in the variable density method principle. Based on the equivalent static force method principle, the impact equivalent static load is calculated, and the static load is applied to the model and submitted to the finite element software for calculation to generate a topology optimization model with the minimum flexibility of the support structure under stress and volume constraints, and the calculation results of the engine support structure before and after optimization are compared.

[0131] It should be understood that if the above integrated module / unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, all or part of the processes in the above method of the embodiment of the present invention can also be completed by a computer program instructing relevant hardware. The above computer program can be stored in a computer-readable storage medium. When the computer program is executed by a processor, the steps of the above various method embodiments can be implemented. Among them, the above computer program includes computer program code, and the above computer program code can be in the form of source code, object code, executable file or some intermediate form, etc. The above computer-readable medium can include: any entity or device capable of carrying the above computer program code, recording medium, USB flash drive, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium, etc. It should be noted that the content included in the above computer-readable storage medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction.

[0132] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0133] Those skilled in the art can clearly understand that, for the convenience and brevity of description, only the above-mentioned division of each functional unit and module is used as an example. In actual applications, the above-mentioned functions can be allocated to different functional units and modules as needed, that is, the internal structure of the above-mentioned device can be divided into different functional units or modules to complete all or part of the functions described above. Each functional unit and module in the embodiment can be integrated into a processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of a software functional unit. In addition, the specific names of each functional unit and module are only for the convenience of mutual distinction and do not limit the protection scope of the present invention. The specific working processes of the units and modules in the above system can refer to the corresponding processes in the foregoing method embodiments and will not be elaborated herein.

[0134] It should be noted that the methods and their detailed examples provided in the above embodiments can be combined with the devices and equipment provided in the embodiments, and reference can be made to each other without further elaboration.

[0135] Those of ordinary skill in the art can realize that the units and algorithm steps of each example described in combination with the embodiments disclosed herein can be implemented by electronic hardware, or by a combination of computer software and electronic hardware. Whether these functions are executed in a hardware or software manner depends on the specific application and design constraints of the technical solution. Professionals can use different methods for each specific application to implement the described functions, but such implementation should not be considered to exceed the scope of the present invention.

[0136] In the embodiments provided by the present invention, it should be understood that the disclosed device / terminal device and method can be implemented in other ways. For example, the device / equipment embodiments described above are only illustrative. For example, the above-mentioned division of modules or units is only a logical function division. In actual implementation, there can be other division methods. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed.

[0137] The above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. And these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention and should all be included in the protection scope of the present invention.

Claims

1. A method for optimizing the impact resistance of a ship engine support structure, characterized in that: The method comprises the following steps: Step S1, using the SIMP material interpolation model in the variable density method to establish a topology optimization mathematical model of the gas turbine support structure in the software; Step S2, loading and optimizing the topology optimization mathematical model of the gas turbine support structure in step S1 based on the equivalent static method; Step S3, performing impact simulation calculation on the engine support structure optimized and designed in step S2; Step S4, comparing the results of the support structure before and after optimization, and realizing the impact-resistant optimization design of the ship engine support structure.

2. The method for optimizing the anti-shock design of a ship engine support structure according to claim 1, characterized in that: The SIMP material interpolation model in the variable density method in step S1 is specifically to assume that the relative density of each unit of the material takes a continuous value between 0 and 1.

3. The method for optimizing the anti-shock design of a ship engine support structure according to claim 2 is characterized in that: The mathematical expression of the SIMP material interpolation model in step S1 is: In the formula, E(x i ) is the Young's modulus of material unit i; E min is the Young's modulus of the material when the unit relative density is 0; x i is the relative density of the unit; P is the penalty coefficient, and E0 is the Young's modulus of the material when the relative density of the unit is 1; In step S1, the numerical model of the topology optimization of the gas turbine support structure is established through TOSCA.

4. The method for optimizing the anti-shock design of a ship engine support structure according to claim 1, characterized in that: The equivalent static method in step S2 uses static load instead of impact dynamic load to perform topological optimization design of the engine support structure. Specifically, the equivalent static load that the ship equipment should bear is {N} times the weight of the equipment itself, that is, F=F 等效静力 =gmN Where g is the acceleration due to gravity, m is the mass matrix, and N is the impact design factor.

5. The method for optimizing the anti-shock design of a ship engine support structure according to claim 4 is characterized in that: Loading and optimization are performed according to the equivalent static method, and finally a topological optimization model with minimal flexibility of the bracket structure under stress and volume constraints is obtained: In the formula, is the vector of topological design variables, m is the number of units in the structure; is the weight coefficient under the first group of load conditions; C tol is the target smoothness of the combination; C l is the flexibility under the first group of load conditions, K is the overall stiffness matrix; U l is the displacement vector of the structure in the global coordinate system under the first group of load conditions; F l is the lth load condition; n is the number of load conditions; ρ i and are the i-th physical variable and the initial volume of the i-th unit respectively; v (0) is the total volume of the structure at the initial iteration; is the Mises stress value of section j of unit i under the lth group of load conditions; ρ max and ρ min are the upper and lower limits of the topological design variables, respectively. V * is the target volume.

6. The method for optimizing the anti-shock design of a ship engine support structure according to claim 1, characterized in that: The impact simulation calculation in step S3 is performed by finite element software.

7. The method for optimizing the anti-shock design of a ship engine support structure according to claim 1, characterized in that: The result of step S4 includes optimizing the front and rear combustion engine support structure models, optimizing the maximum impact stress on the front and rear combustion engine support structures, and optimizing the quality of the front and rear combustion engine support structures.

8. A ship engine support structure impact resistance optimization design system, characterized in that: The system uses the anti-shock optimization design method for a ship engine support structure as claimed in any one of claims 1 to 7, and the system comprises: Mathematical model building module for gas turbine support structure: Use the SIMP material interpolation model in the variable density method to build a topological optimization mathematical model for the gas turbine support structure in the software; Mathematical model loading and optimization module: Load and optimize the topology optimization mathematical model of the gas turbine support structure based on the equivalent static method; Impact simulation calculation module: perform impact simulation calculation on the optimized design of the gas turbine support structure; Result comparison module: Compare the results of the support structure before and after optimization to achieve the impact-resistant optimization design of the ship's gas turbine support structure.

9. A computer device, characterized in that: The method comprises a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, the method according to any one of claims 1 to 7 is implemented.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method according to any one of claims 1 to 7 is implemented.

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