CN116432536B - Limiting optimization method for structural parameters of impact resistance of aero-engine connecting casing - Google Patents
Limiting optimization method for structural parameters of impact resistance of aero-engine connecting casing Download PDFInfo
- Publication number
- CN116432536B CN116432536B CN202310419506.5A CN202310419506A CN116432536B CN 116432536 B CN116432536 B CN 116432536B CN 202310419506 A CN202310419506 A CN 202310419506A CN 116432536 B CN116432536 B CN 116432536B
- Authority
- CN
- China
- Prior art keywords
- casing
- bolt
- energy density
- structural parameters
- bolts
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000005457 optimization Methods 0.000 title claims abstract description 24
- 238000012360 testing method Methods 0.000 claims abstract description 21
- 238000009434 installation Methods 0.000 claims abstract description 19
- 230000004044 response Effects 0.000 claims abstract description 18
- 238000013461 design Methods 0.000 claims abstract description 13
- 239000000463 material Substances 0.000 claims abstract description 13
- 238000011156 evaluation Methods 0.000 claims abstract description 4
- 230000009466 transformation Effects 0.000 claims abstract description 4
- 230000035772 mutation Effects 0.000 claims description 9
- 230000035939 shock Effects 0.000 claims description 5
- 238000004364 calculation method Methods 0.000 claims description 3
- 230000002068 genetic effect Effects 0.000 claims description 3
- 238000012216 screening Methods 0.000 claims description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 229910052759 nickel Inorganic materials 0.000 description 4
- 229910000601 superalloy Inorganic materials 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000013178 mathematical model Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000009747 swallowing Effects 0.000 description 1
Classifications
-
- 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
- G06F30/27—Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
-
- 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
- G06N—COMPUTING ARRANGEMENTS BASED ON SPECIFIC COMPUTATIONAL MODELS
- G06N3/00—Computing arrangements based on biological models
- G06N3/12—Computing arrangements based on biological models using genetic models
- G06N3/126—Evolutionary algorithms, e.g. genetic algorithms or genetic programming
-
- 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
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- Evolutionary Computation (AREA)
- General Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Biophysics (AREA)
- Computer Hardware Design (AREA)
- Life Sciences & Earth Sciences (AREA)
- Artificial Intelligence (AREA)
- Software Systems (AREA)
- Evolutionary Biology (AREA)
- Bioinformatics & Computational Biology (AREA)
- Bioinformatics & Cheminformatics (AREA)
- Mathematical Optimization (AREA)
- Genetics & Genomics (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Computer Vision & Pattern Recognition (AREA)
- Medical Informatics (AREA)
- Physiology (AREA)
- Pure & Applied Mathematics (AREA)
- Biomedical Technology (AREA)
- Computational Linguistics (AREA)
- Data Mining & Analysis (AREA)
- General Health & Medical Sciences (AREA)
- Molecular Biology (AREA)
- Computing Systems (AREA)
- Mathematical Physics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention relates to the technical field of aero-engine case optimization, in particular to a limiting optimization method for structural parameters of impact resistance of an aero-engine connecting case, which comprises the following steps: step S1, determining main structural parameters and a value range of impact resistance of a bolt connection casing installation edge, and performing coding transformation on the main structural parameters and the value range to obtain a test factor horizontal coding table, so as to generate an initial population; s2, determining impact resistance evaluation indexes of a bolt connection structure of a mounting edge of the casing based on the energy density of the bolts; and S3, establishing a three-dimensional geometric model of a bolt connection structure of a casing mounting edge according to the actual size of the aero-engine casing, designing a response surface test scheme by using a Box-Behnken test design method, establishing a finite element model according to the designed scheme, setting material parameters and contact definition, calculating the bolt energy densities of different working conditions, the deformation of the side surface of the casing and the quality of the casing, and establishing a response surface model.
Description
Technical Field
The invention relates to the technical field of aero-engine case optimization, in particular to a limiting optimization method for structural parameters of impact resistance of an aero-engine connecting case.
Background
The rotor system of the aviation turbofan with large bypass ratio is often damaged by factors such as foreign matters sucked into the engine (such as bird swallowing), structural overheating, high cycle fatigue, material defects and the like when the rotor of the aviation turbofan works in a high-temperature, high-pressure and high-rotation-speed limit environment. Each section of casing is connected through the installation limit bolted connection structure, and the intensity of connection structure has decided the security of whole casing, and then influences engine complete machine performance and reliability. The angle and the impact position of the broken blade when flying out are random, and the broken blade impacts the bolt connection structure, so that the installation edge can be broken or the bolt can be broken, and the joint surface of the casing is separated.
Because the bolt connection structure casing with the mounting edge is relatively complex in stress, certain difficulty is brought to the design and analysis of the inclusion. Therefore, the impact resistance of the bolt connection structure at the mounting side of the casing becomes an important point for researching the inclusion property of the casing. At present, few researches on impact resistance problems of bolt connection structures at the mounting side of the case are still carried out at home and abroad, and the optimization design research for improving the impact resistance of the case is lacking. In view of this, we propose a method for limiting optimization of structural parameters of the impact resistance of the connection casing of an aeroengine.
Disclosure of Invention
The invention aims to provide a limiting optimization method for structural parameters of impact resistance of an aeroengine connecting casing, so as to solve the problems in the background art.
In order to achieve the above purpose, the present invention provides the following technical solutions:
the limiting optimization method for the shock resistance structural parameters of the connection casing of the aeroengine comprises the following steps:
step S1, determining main structural parameters and a value range of impact resistance of a bolt connection casing installation edge, and performing coding transformation on the main structural parameters and the value range to obtain a test factor horizontal coding table, so as to generate an initial population;
s2, determining impact resistance evaluation indexes of a bolt connection structure of a mounting edge of the casing based on the energy density of the bolts;
s3, establishing a three-dimensional geometric model of a bolt connection structure of a casing mounting edge according to the actual size of the aero-engine casing, designing a response surface test scheme by using a Box-Behnken test design method, establishing a finite element model according to the designed scheme, setting material parameters and contact definition, calculating the bolt energy densities of different working conditions, the deformation of the side surface of the casing and the quality of the casing, and establishing a response surface model;
and S4, performing operations such as crossing, mutation and the like to generate a new population, and taking the bolt energy density as the fitness of the individual.
S5, judging whether the calculation result meets the limiting conditions by taking the deformation of the side face of the case and the quality of the case as the limiting conditions, if so, directly entering the next step, and if not, setting the energy density value of the bolt to be 100 times, and then carrying out the next step;
s6, establishing a response surface model;
s7, performing operations such as crossing, mutation and the like to generate a new population, and taking the bolt energy density as the fitness of the individual;
s8, judging whether the calculated result meets the limiting condition by taking the deformation of the side face of the case less than 28mm and the mass increment of the case not more than 5% as the limiting condition, if so, directly entering the next step, and if not, setting the energy density value of the bolt to be 100 times, and then carrying out the next step;
and S9, screening the overall according to the energy density of the bolts, and judging whether the output condition is met.
Preferably, the structural parameters of the installation edge of the bolt connection casing to be optimized comprise the height of the installation edge, the thickness of the installation edge, the diameter of the bolts, the number of the bolts and the wall thickness of the casing.
Preferably, the specific method of the step 2 is as follows:
and solving by using nonlinear finite element calculation software to obtain the bolt strain energy of the bolt connection structure of the mounting edge of the casing, and calculating the energy density of the bolt according to the following formula:
d in b For the energy density of the bolts E b The internal energy of the bolt in a stable state after collision is represented by r, the radius of the bolt is represented by r, and the thickness of the mounting edge is represented by t.
Preferably, in the step 3, a finite element model is built according to a designed scheme, different working conditions are calculated, and a response surface model of the bolt energy density, the deformation of the side surface of the casing, the casing quality and each structural parameter is obtained, and the formula is as follows:
lny 1 ＝11.601+1.563t+0.224h-2.184d-1.369n+0.094w-0.040th
-0.030td-0.066tn-0.005tw+0.059hd+0.0547hn+0.009hw
+0.071dn-0.069dw-0.008nw-0.011t 2 -0.020h 2 +0.029d 2
-0.028n 2 +0.0168w 2
y 2 ＝89.85436-4.39726t+0.090110h+0.303555d+0.403034n-17.24801w
+0.015725th+0.060374td+0.055397tn+0.125095tw-0.027795hd
-0.038102hn-0.005749hw-0.019286dn+0.013721dw-0.001217nw
+0.166006t 2 +0.004370h 2 +0.000448d 2 +0.027258n 2 +1.23426w 2
y 3 ＝-0.199211+0.021581t+0.016738h-0.024424d-0.031671n
+1.18877w+0.003925th-0.001475td-0.0009tn-0.003912tw
+1.97015e -18 hd+1.70085e -18 hn-5.15807e -17 hw+0.006659dn
-5.65140e -17 dw+0.000025nw+0.000974t 2 -0.000322h 2
+0.002077d 2 +0.000386n 2 +0.000974w 2 。
preferably, t represents the mounting edgeThickness, h represents mounting side height, d represents bolt diameter, n represents bolt number, w represents casing thickness, y 1 Representing the energy density of the bolt, y 2 Representing the deformation quantity of the side face of the case, y 3 Indicating the casing quality.
Preferably, in the model, the blade material adopts TC4, the casing mounting edge material adopts 45 steel, the bolt material adopts GH4169 nickel-based superalloy, and the nut material adopts GH738 nickel-based superalloy; the blade is arranged to strike at an angle parallel to the joint surface of the mounting edge of the casing, the striking part is the joint of the mounting edge, and an initial speed of 100m/s is applied to the blade. Meanwhile, in order to prevent the cartridge receiver from shifting after being impacted, fixing constraint is needed to be applied to the upper end face and the lower end face of the cartridge receiver, and 10KN of pretightening force is needed to be applied to each bolt.
Preferably, the Box-Behnken test design method is used for designing a response surface test scheme, a finite element model is built according to the designed scheme, and the bolt energy, the case side deformation and the case mass under different working conditions are calculated.
Preferably, in the step S9, if the constraint condition is not satisfied, operations such as crossing and mutation of the genetic algorithm are performed again, and if the constraint condition is satisfied, an optimal parameter value is output, so as to obtain a parameter combination scheme which meets the constraint condition and has the minimum energy density of the bolt.
Compared with the prior art, the invention has the beneficial effects that:
according to the structural parameter limiting optimization method for improving the impact resistance of the aeroengine connecting casing, provided by the invention, the impact of each structural parameter of the casing installation side on the impact resistance of the aeroengine connecting casing is comprehensively considered, the bolt energy density is obtained based on a response surface method, the deformation of the casing side, the quality of the casing and the mathematical model of each structural parameter are obtained, the traditional optimization process is improved by setting limiting conditions, the optimal parameter combination which meets the limiting conditions and has the minimum bolt energy density is obtained, the optimization result is accurate and reliable, and a reference basis can be provided for the optimization design of the impact resistance of the casing installation side bolt connecting structure.
According to the limiting optimization method for the structural parameters of the impact resistance of the aero-engine connecting casing, the thickness of the mounting side, the height of the mounting side, the diameter of bolts, the number of bolts and the thickness of the casing are used as optimization parameters, the deformation of the side face of the casing and the quality of the casing are used as limiting conditions, and the energy density of the bolts is used as an optimization target, so that the optimization design of the impact resistance of the bolt connecting structure of the mounting side of the casing is realized.
Drawings
FIG. 1 is a flow chart of a method for limiting and optimizing structural parameters for improving impact resistance of an aircraft engine bolting casing according to an embodiment of the present invention;
fig. 2 is a schematic diagram of a bolt connection structure according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a three-dimensional geometric model of a bolting configuration according to an embodiment of the invention;
FIG. 4 is a schematic diagram of an initial model bolt energy variation curve provided by an embodiment of the present invention;
FIG. 5 is a schematic diagram of a test factor horizontal coding table of the structural parameters of the mounting edge of the casing according to the present invention;
FIG. 6 shows the design of the test and the test results of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
In the description of this patent, it should be noted that, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "disposed" are to be construed broadly, and may be fixedly connected, disposed, detachably connected, disposed, or integrally connected, disposed, for example. The specific meaning of the terms in this patent will be understood by those of ordinary skill in the art as the case may be.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
Referring to fig. 1-6, the present invention provides a technical solution:
the limiting optimization method for the shock resistance structural parameters of the connection casing of the aeroengine comprises the following steps:
step S1, determining main structural parameters and a value range of impact resistance of a bolt connection casing installation edge, and performing coding transformation on the main structural parameters and the value range to obtain a test factor horizontal coding table, so as to generate an initial population;
s2, determining impact resistance evaluation indexes of a bolt connection structure of a mounting edge of the casing based on the energy density of the bolts;
s3, establishing a three-dimensional geometric model of a bolt connection structure of a casing mounting edge according to the actual size of the aero-engine casing, designing a response surface test scheme by using a Box-Behnken test design method, establishing a finite element model according to the designed scheme, setting material parameters and contact definition, calculating the bolt energy densities of different working conditions, the deformation of the side surface of the casing and the quality of the casing, and establishing a response surface model;
and S4, performing operations such as crossing, mutation and the like to generate a new population, and taking the bolt energy density as the fitness of the individual.
S5, judging whether the calculation result meets the limiting conditions by taking the deformation of the side face of the case and the quality of the case as the limiting conditions, if so, directly entering the next step, and if not, setting the energy density value of the bolt to be 100 times, and then carrying out the next step;
s6, establishing a response surface model;
s7, performing operations such as crossing, mutation and the like to generate a new population, and taking the bolt energy density as the fitness of the individual;
s8, judging whether the calculated result meets the limiting condition by taking the deformation of the side face of the case less than 28mm and the mass increment of the case not more than 5% as the limiting condition, if so, directly entering the next step, and if not, setting the energy density value of the bolt to be 100 times, and then carrying out the next step;
and S9, screening the overall according to the energy density of the bolts, and judging whether the output condition is met.
Further, the structural parameters of the installation edge of the bolt connection casing to be optimized include the height of the installation edge, the thickness of the installation edge, the diameter of the bolts, the number of the bolts and the wall thickness of the casing.
Further, the specific method of the step 2 is as follows:
and solving by using nonlinear finite element calculation software to obtain the bolt strain energy of the bolt connection structure of the mounting edge of the casing, and calculating the energy density of the bolt according to the following formula:
d in b For the energy density of the bolts E b The internal energy of the bolt in a stable state after collision is represented by r, the radius of the bolt is represented by r, and the thickness of the mounting edge is represented by t.
Further, in step 3, a finite element model is built according to a designed scheme, different working conditions are calculated, and a response surface model of the bolt energy density, the deformation of the side face of the casing, the casing quality and structural parameters is obtained, wherein the formula is as follows:
lny 1 ＝11.601+1.563t+0.224h-2.184d-1.369n+0.094w-0.040th
-0.030td-0.066tn-0.005tw+0.059hd+0.0547hn+0.009hw
+0.071dn-0.069dw-0.008nw-0.011t 2 -0.020h 2 +0.029d 2
-0.028n 2 +0.0168w 2
y 2 ＝89.85436-4.39726t+0.090110h+0.303555d+0.403034n-17.24801w
+0.015725th+0.060374td+0.055397tn+0.125095tw-0.027795hd
-0.038102hn-0.005749hw-0.019286dn+0.013721dw-0.001217nw
+0.166006t 2 +0.004370h 2 +0.000448d 2 +0.027258n 2 +1.23426w 2
y 3 ＝-0.199211+0.021581t+0.016738h-0.024424d-0.031671n
+1.18877w+0.003925th-0.001475td-0.0009tn-0.003912tw
+1.97015e -18 hd+1.70085e -18 hn-5.15807e -17 hw+0.006659dn
-5.65140e -17 dw+0.000025nw+0.000974t 2 -0.000322h 2
+0.002077d 2 +0.000386n 2 +0.000974w 2 。
further, wherein t represents the thickness of the mounting side, h represents the height of the mounting side, d represents the diameter of the bolt, n represents the number of bolts, w represents the thickness of the casing, and y 1 Representing the energy density of the bolt, y 2 Representing the deformation quantity of the side face of the case, y 3 Indicating the casing quality.
Further, in the model, the blade material adopts TC4, the casing mounting edge material adopts 45 steel, the bolt material adopts GH4169 nickel-based superalloy, and the nut material adopts GH738 nickel-based superalloy; the blade is arranged to strike at an angle parallel to the joint surface of the mounting edge of the casing, the striking part is the joint of the mounting edge, and an initial speed of 100m/s is applied to the blade. Meanwhile, in order to prevent the cartridge receiver from shifting after being impacted, fixing constraint is needed to be applied to the upper end face and the lower end face of the cartridge receiver, and 10KN of pretightening force is needed to be applied to each bolt.
Further, a Box-Behnken test design method is used for designing a response surface test scheme, a finite element model is built according to the designed scheme, and the bolt energy, the case side deformation and the case quality under different working conditions are calculated.
Further, in step S9, if the constraint condition is not satisfied, operations such as crossing and mutation of the genetic algorithm are performed again, and if the constraint condition is satisfied, an optimal parameter value is output, so as to obtain a parameter combination scheme which meets the constraint condition and has the minimum energy density of the bolt.
In the embodiment, the optimal scheme finally obtained is that the thickness of the installation edge is 8mm, the height of the installation edge is 28mm, the diameter of the bolts is 8mm, the number of the bolts is 9, and the wall thickness of the casing is 5mm. The energy density of the initial model bolt is 1.919J/cm < 2 >, the deformation of the side face of the casing is 23.37mm, the mass of the casing is 6.64kg, the mounting edge structure under the optimal parameter combination is reduced by 84.66% compared with the energy density of the initial model, the deformation of the casing is reduced by 1.50%, and the mass of the mounting edge structure is increased by 4.52%.
When the limiting optimization method for the structural parameters of the impact resistance of the aeroengine connecting casing is used, the influence of each structural parameter of the casing mounting side on the impact resistance of the aeroengine connecting casing is comprehensively considered, the bolt energy density is obtained based on a response surface method, the deformation of the side face of the casing, the quality of the casing and the mathematical model of each structural parameter are obtained, the traditional optimization process is improved by setting limiting conditions, the optimal parameter combination which meets the limiting conditions and has the minimum bolt energy density is obtained, the optimization result is accurate and reliable, and a reference basis can be provided for the optimization design of the impact resistance of the bolt connecting structure of the casing mounting side.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the above-described embodiments, and that the above-described embodiments and descriptions are only preferred embodiments of the present invention, and are not intended to limit the invention, and that various changes and modifications may be made therein without departing from the spirit and scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (3)
1. The limiting optimization method for the shock resistance structural parameters of the connection casing of the aeroengine is characterized by comprising the following steps of:
step S1, determining main structural parameters and a value range of impact resistance of a bolt connection casing installation edge, and performing coding transformation on the main structural parameters and the value range to obtain a test factor horizontal coding table, so as to generate an initial population;
s2, determining impact resistance evaluation indexes of a bolt connection structure of a mounting edge of the casing based on the energy density of the bolts;
s3, establishing a three-dimensional geometric model of a bolt connection structure of a casing mounting edge according to the actual size of the aero-engine casing, designing a response surface test scheme by using a Box-Behnken test design method, establishing a finite element model according to the designed scheme, setting material parameters and contact definition, and calculating the bolt energy densities, the casing side deformation and the casing quality of different working conditions;
s4, performing crossing and mutation operations to generate a new population, and taking the bolt energy density as the fitness of the individual;
s5, judging whether the calculation result meets the limiting conditions by taking the deformation of the side face of the case and the quality of the case as the limiting conditions, if so, directly entering the next step, and if not, setting the energy density value of the bolt to be 100 times, and then carrying out the next step;
s6, establishing a response surface model;
s7, performing crossing and mutation operations to generate a new population, and taking the bolt energy density as the fitness of the individual;
s8, judging whether the calculated result meets the limiting condition by taking the deformation of the side face of the case less than 28mm and the mass increment of the case not more than 5% as the limiting condition, if so, directly entering the next step, and if not, setting the energy density value of the bolt to be 100 times, and then carrying out the next step;
step S9, screening the overall according to the energy density of the bolts, and judging whether the output condition is met or not;
the structural parameters of the installation edge of the bolt connecting casing to be optimized comprise the height of the installation edge, the thickness of the installation edge, the diameter of the bolts, the number of the bolts and the wall thickness of the casing;
the specific method of the step 2 is as follows:
and solving by using nonlinear finite element calculation software to obtain the bolt strain energy of the bolt connection structure of the mounting edge of the casing, and calculating the energy density of the bolt according to the following formula:
D b ＝E b /(2πr 2 t)
d in b For the energy density of the bolts E b The internal energy of the bolt in a stable state after collision is represented by r, the radius of the bolt is represented by r, and the thickness of the mounting edge is represented by t;
in the step 3, a finite element model is established according to a designed scheme, different working conditions are calculated, and a response surface model of the bolt energy density, the deformation of the side surface of the casing, the casing quality and each structural parameter is obtained, wherein the formula is as follows:
lny 1 ＝11.601+1.563t+0.224h-2.184d-1.369n+0.094w-0.040th-0.030td-0.066tn-0.
005tw+0.059hd+0.0547hn+0.009hw+0.071dn-0.069dw-0.008nw-0.011t 2 -0.020h 2 +0.029d 2 -0.028n 2 +0.0168w 2
y 2 ＝89.85436-4.39726t+0.090110h+0.303555d+0.403034n-17.24801w+0.0157
25th+0.060374td+0.055397tn+0.125095tw-0.027795hd-0.038102hn-0.005749hw-0.019286dn+0.013721dw-0.001217nw+0.166006t 2 +0.004370h 2 +0.000448d 2 +0.027258n 2 +1.23426w 2
y 3 ＝
-0.199211+0.021581t+0.016738h-0.024424d-0.031671n+1.18877w+0.003925th-0.001475td-0.0009tn-0.003912tw+1.97015e -18 hd+1.70085e -18 hn-5.15807e -17 hw+0.006659dn-5.65140e -17 dw+0.000025nw+0.000974t 2 -0.000322h 2 +0.002077d 2 +0.000386n 2 +0.000974w 2
the t represents the thickness of the mounting side, h represents the height of the mounting side, d represents the diameter of the bolt, n represents the number of bolts, w represents the thickness of the casing and y 1 Representing the energy density of the bolt, y 2 Representing the deformation quantity of the side face of the case, y 3 Indicating the casing quality.
2. The method for limiting and optimizing the structural parameters of the shock resistance of the connection casing of the aeroengine according to claim 1, wherein the method comprises the following steps: and designing a response surface test scheme by using a Box-Behnken test design method, establishing a finite element model according to the designed scheme, and calculating the bolt energy under different working conditions, the deformation of the side surface of the case and the quality of the case.
3. The method for limiting and optimizing the structural parameters of the shock resistance of the connection casing of the aeroengine according to claim 1, wherein the method comprises the following steps: in the step S9, if not, the crossover and mutation operations of the genetic algorithm are performed again, and if yes, the optimal parameter value is output, so as to obtain a parameter combination scheme which meets the limiting condition and has the minimum energy density of the bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310419506.5A CN116432536B (en) | 2023-04-19 | 2023-04-19 | Limiting optimization method for structural parameters of impact resistance of aero-engine connecting casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310419506.5A CN116432536B (en) | 2023-04-19 | 2023-04-19 | Limiting optimization method for structural parameters of impact resistance of aero-engine connecting casing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116432536A CN116432536A (en) | 2023-07-14 |
| CN116432536B true CN116432536B (en) | 2024-03-08 |
Family
ID=87085056
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310419506.5A Active CN116432536B (en) | 2023-04-19 | 2023-04-19 | Limiting optimization method for structural parameters of impact resistance of aero-engine connecting casing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116432536B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113569448A (en) * | 2021-07-13 | 2021-10-29 | 沈阳航空航天大学 | Response surface method-based strain gauge sensitive grid structure parameter optimization method |
| CN114528637A (en) * | 2022-01-21 | 2022-05-24 | 沈阳航空航天大学 | Method and system for calculating leakage amount of mounting edge of cartridge receiver and storage medium |
| CN115270334A (en) * | 2022-07-29 | 2022-11-01 | 中国航发沈阳发动机研究所 | Bearing case rigidity simulation piece and design method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6085324B2 (en) * | 2015-03-25 | 2017-02-22 | 富士重工業株式会社 | Aircraft structure manufacturing method, aircraft structure design information creation method, aircraft structure design system, and aircraft structure design program |
-
2023
- 2023-04-19 CN CN202310419506.5A patent/CN116432536B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113569448A (en) * | 2021-07-13 | 2021-10-29 | 沈阳航空航天大学 | Response surface method-based strain gauge sensitive grid structure parameter optimization method |
| CN114528637A (en) * | 2022-01-21 | 2022-05-24 | 沈阳航空航天大学 | Method and system for calculating leakage amount of mounting edge of cartridge receiver and storage medium |
| CN115270334A (en) * | 2022-07-29 | 2022-11-01 | 中国航发沈阳发动机研究所 | Bearing case rigidity simulation piece and design method thereof |
Non-Patent Citations (3)
| Title |
|---|
| Robot-assisted ultrasonic impact strengthening strategy for aero-engine blades;Lin Zhu et al.;《Robotics and Computer-Integrated Manufacturing》;20220530;第78卷;全文 * |
| 发动机机匣安装边设计方法研究;刘海月;《CNKI优秀硕士学位论文全文库工程科技Ⅱ辑》(第2期);第1-69页 * |
| 响应面法在机匣螺栓连接结构多目标优化中的应用;艾延廷;武威;陈勇;;机械设计与制造(第12期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116432536A (en) | 2023-07-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109376429B (en) | Concrete dam template safety construction analysis method based on finite element simulation | |
| EP4332825A1 (en) | Integrated cost-reducing optimization design method for support structure of offshore wind turbine | |
| CN110411850B (en) | Method for evaluating service conditions of high-temperature alloy turbine blade | |
| CN113268876B (en) | Marine fan integral coupling fatigue analysis method with additional culture net cage | |
| CN112380794B (en) | Multi-disciplinary parallel cooperation optimization design method for aviation turbine engine blade | |
| CN116432536B (en) | Limiting optimization method for structural parameters of impact resistance of aero-engine connecting casing | |
| CN111709094A (en) | Method for optimizing base structure of anchor and mooring machine | |
| CN115526483A (en) | Rapid evaluation method and system for anti-seismic toughness of shield tunnel structure | |
| CN113609584B (en) | Reliability optimization design method for thrust chamber of reusable rocket engine | |
| CN116541970B (en) | Energy method-based compressor blade vibration reduction optimization design evaluation method | |
| CN111950090A (en) | Anchor chain wheel structure optimization method | |
| CN116432311A (en) | Method for calculating vibration characteristics of annular blisk of uncertain parameter composite material | |
| CN114580094B (en) | Bird strike injury engineering prediction method for rotating state of metal blade | |
| CN114282423B (en) | Fatigue monitoring method and service life prediction method for shore bridge structure | |
| CN112084615A (en) | Lightning risk assessment method for wind driven generator under complex terrain | |
| CN111222269A (en) | CAE-based simulation test method for mechanical impact process of battery pack | |
| CN115270580A (en) | Design method suitable for abrupt change cross section of large-size special-shaped wind tunnel | |
| CN109441287A (en) | A kind of blower fan tower barrel doorframe Parameters design | |
| CN111507606B (en) | Toughness evaluation method for complex energy interconnection system | |
| CN111859561A (en) | Fretting fatigue damage resistance optimization method for turbine joggling structure | |
| Xiong et al. | Integrated fatigue assessment method considering average stress effects of large-scale lattice wind turbine support structures | |
| Oest et al. | Gradient based structural optimization with fatigue constraints of jacket structures for offshore wind turbines | |
| CN110610056A (en) | Vibration checking method for motor cooler | |
| Arora et al. | Response Analysis of Composite Blades of Offshore VAWT Using CFD and FSI for the Indian Ocean | |
| Jiang et al. | Study on lightweight optimization method for the anvil of large-tonnage offshore pile hammers based on anti-fatigue criterion |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |