^{1, 2}Nanjing University of Aeronautics and Astronautics, Nanjing, China
^{3}Wuxi Orient Software Technology Co., Ltd, Wuxi, China
^{2}Corresponding author
Vibroengineering PROCEDIA, Vol. 20, 2018, p. 289294.
https://doi.org/10.21595/vp.2018.20292
Received 7 October 2018; accepted 10 October 2018; published 19 October 2018
JVE Conferences
With the development of science and technology, traditional design methods can no longer meet the needs of modern design and production development. Parametric and optimal design has become one of the most popular application technologies in CAD. Parametric and optimal design was studied based on VB.net language for secondary development of AutoCAD and MATLAB language for secondary development of ANSYS Apdl for disc of aeroengine. The structural parameterization technology was used to realize the rapid forming, and genetic algorithm retains elite was used to optimal design. The optimal design was carried out by using the developed software in this paper, and the optimal results shown that the disc weight was reduced by 34.48 %, the reduction effect of weight was obvious.
Keywords: parameterization, disc design, genetic algorithm, structural optimization.
1. Introduction
With the development of science and technology, traditional design methods have been unable to meet the needs of modern design and production development. Parametric design and structural optimization design techniques have been emerged and developed. The disc of aeroengine was composed of the rim, the spoke and the hub, these were all axisymmetric structures typically, and they could be designed rapidly with parametric design and structural optimization design technology [13].
Many researchers have done excellent work in this area. Yuwang Song and others from Beihang University conducted research on parametric design techniques for turbine blades, the threedimensional solid model of the blade could be quickly established using the wellwritten modules. Jichun Zhang and others from Beihang University applied the characteristicbased parametric technology to the rapid design of the Vtype engine [4]; Kaiyuan Zheng and others at Nanjing University of Aeronautics and Astronautics conducted parameterization design technique for compressors, turbines and combustion chamber of a certain type of engine, and they have developed their work into software at the end [5]; Yongxian Luan from Nanjing University of Aeronautics and Astronautics combined the parameter design and finite element calculation technology for boltless baffles and developed it into software [6]; Yingchun Bai and Jiping Zhong used the shell and body unit to establish the finite element model of the boom. The optimal distribution path of the material was obtained through the topology optimization of the parts, and the optimal model of the boom was established [7]. The parameterization and genetic algorithm optimization technology were combined in this study, and the parametric rapid prototyping technology was applied to the structural optimization program, which greatly improved the design efficiency of the disc of aeroengine.
2. Structural parameterization of disc
2.1. The process of structural parameterization
The graphic files of AutoCAD could be read through the Active X control in VB.net. Typical axisymmetric parts of aeroengines is researched by developing AutoCAD twice with the help of VB’s powerful functions in the paper. Firstly, the basic structure contour could be completed using a twodimensional graphic designed by AutoCAD; then, detailed design of 3D solid cutting and merging would be performed by boolean operations; lastly, the structural weight could be obtained based on material property parameters. The process of the structural parameterization of disc was shown as Fig. 1.
Fig. 1. The process of the structural parameterization of disc
Fig. 2. The diagram of the parameter used in design
2.2. The parameters used in structural parameterization of disc
The structural parameters of disc were shown in Fig. 2. Table 1 showed all parameters used in parametric design.
Table 1. The details of parameters used in design
Parameter

Description of parameter

Parameter

Description of parameter

Fore(Post)_r_H

Front (Back) radius of the outer edge

W_DS

The thickness in the inner radius of the disk

Fore(Post)_r_R

Front (Back) radius of the edge of the plate and the disk

N

Number of holes

Fore(Post)_r_D

Front (Back) radius of the middle of the disk

Rr

Radius of the hole

Fore(Post)_r_S

Front (Back) radius of the reinforced part of the middle part of the disk

Dr

Distance from the center of the hole to the axis of symmetry

Fore(Post)_r_I

Front radius of the inner ring of the disk

SN

Number of gutters

W_R

The thickness of the rim

SDr

Distance from the center of the gutter to the axis of symmetry

W_DR

The thickness of the joint part of rim and spoke

Aglx(y)z

The angle between the gutter and the Z axis in the X(Y)Z plane

W_D

The thickness in the middle radius of the disc

Height

The height of Blade

2.3. The quick design of engine disc
The VB.net program consists of four modules: FanPan used for the disc design module, Holeclass for the hole design module, SunCaoClass for the gutter design module, and BladeClass for the rotor blade design. Among them, Holeclass, SunCaoClass and BladeClass were submodules of FanPan and the drawing results were shown in Fig. 3.
Fig. 3. The structure designed by parametric software
a) Blade
b) Disc
3. Structural optimization of disc
3.1. The process of optimization
The parameterized model of the disc was used for optimization, and the optimized part was jointly completed by MATLAB and APDL language. The function of MATLAB language was to use parametric structural model, generated optimized command stream, to call ANSYS and controlled it to read optimized command stream file; APDL was used to read command stream file and control optimization and obtain optimized structural model. The optimal design flow was shown in Fig. 4.
As in optimal program in MATLAB, firstly, it created the initial population, set the generation counter and calculated the objective function value of the initial population, then the program started the process of iteration, assigned the fitness value, selected the population, got on reorganization, mutation and calculated the target value. The program also set the performance tracking of genetic algorithm.
Fig. 4. The process of structural optimization
3.2. The analysis model used in optimization
The weight and strength of the disc were considered at the same time in optimal design, which means it belongs to a multiobjectives optimization problem.
The optimized mathematical model expression was expressed as:
where the $U$ denoted the strength and $WT$ represent the weight of the disc; $f\left(x\right)$ is objective function; ${g}_{i}\left(x\right)$ is inequality constraints including stress and strain constraints; ${x}_{i}^{\left(l\right)}$ express the minimum while the ${x}_{i}^{\left(u\right)}$ denoted the maximum of the $i$th variable; ${w}_{1}$ and ${w}_{2}$ are the weighting coefficients of the two target ($U$ and $WT$).
Before weighting, each target needs to be regularized to eliminate the difference in the order of magnitude. It is usually taken as ${w}_{1}+{w}_{2}=1$, and ${w}_{1}>0$, ${w}_{2}>0$.
It is found that the unreasonable regularization method would strengthen or weaken a certain target inadvertently in practice, which leads to the weighting coefficient cannot accurately reflect the importance of the target, and finally the optimal result will be deviated from expectations. A better regularization method should convert both the weight and strength target values into dimensionless values in the range of 01 using the Eq. (3):
where ${\alpha}_{1}$ and ${\alpha}_{2}$ were the maximum values of the two targets of strength and weight, while ${\beta}_{1}$ and ${\beta}_{2}$ were the minimum values in the entire optimized region; the strength and the weight minimum are taken based on the strength limit and the given safety margin; the weight and the strength maximum are obtained at the geometric constraint boundary conditions, $\stackrel{}{U}$ and $\overline{WT}$ denoted regularized target, then the Eq. (1) should be written as:
3.3. The range of variables used in design
It can be seen that there were 14 design parameters of the disc according to Fig. 2. In order to optimize the disc model and improve computational efficiency, the through holes, the gutters and the blade roots are not considered here. Aerodynamic performance was ensured by simplifying the blade root and gutter structure. The geometry at the rim cannot be used as a design variable because of the optimization of the hoe and the gutter needed to consider the contact problem, it needs to be optimized separately. In order to reduce the number of design variables and improve the efficiency of optimization, it was considered that the spoke and hub of the disc are mirrorsymmetrical structures. Finally, there were five design variables of the disc optimization, which were the radius of the middle portion of the disk (RD), the radius of the reinforcing portion of the middle portion of the disk (RS), the radius of the inner ring of the disk (RI), the thickness of the intermediate radius of the disk (WD), and the thickness of the inner radius of the disk (WDS). The optimization of the disc is based on the size of the established disc model initially and the design variable range changed with the running of the program, scope files of variables could be generated by software with the changing of the model. The program for quick design of engine disc could generate disc model according to the changed parameter in time. The following relationships should be satisfied for the five design variables:
(1) The initial value of the radius of the inner ring of the disk < RD < The initial value of the radius of the joint portion edge between the plate and disk;
(2) The initial value of the radius of the inner ring of the disk < RS < The initial value of the radius of the joint portion edge between the plate and disk;
(3) The initial value of the radius of the inner ring of the disk < RI < The initial value of the radius of the joint portion edge between the plate and disk;
(4) 2 mm < WD < Initial thickness of the inner radius of the disk;
(5) 2 mm < WDS < Initial thickness of the inner radius of the disk.
Among them, ‘2 mm’ is the lower limit of the thickness in this research, which can be modified according to the actual engineering conditions.
3.4. Constraint conditions of optimization
The following were optimal constraints:
(1) Stress constraints:
where ${\sigma}_{\mathrm{m}\mathrm{a}\mathrm{x}}$ represented the maximum stress calculated for the disc; $\left[\sigma \right]$ is the allowable stress of the disc.
(2) Geometric boundary constraints:
3.5. The results of optimization
The generations of optimization was set as 150, The initial values of the parameters of the disc model was listed in Table 2. The range of the design variables was determined according to the initial values and geometric constraints of the model. Material parameters and applied load parameters were required during optimization. Material parameters included material density, elastic modulus, Poisson's ratio, maximum allowed stress, and load parameters included the distance between blade’s centroid and the center of disc, the speed of disc and the generations of optimization. The mass of blades was converted into a centrifugal force and loaded on the rim when the strength calculation was ran, and the axial and circumferential displacement constraints were added to the rim of the front surface of the disc center. The material parameters and applied loads were shown in Table 3 and Table 4.
Table 2. Initial value of the parameter
Parameter name

Initial value of the parameter (mm)

Parameter name

Initial value of the parameter (mm)

Fore_r_H

120

Post_r_S

40

Post_r_H

125

Fore_r_I

25

Fore_r_R

105

Post_r_I

25

Post_r_R

105

W_R

34

Fore_r_D

50

W_DR

10

Post_r_D

50

W_D

38

Fore_r_S

40

W_DS

50

Table 3. Material performance parameters
Material name

Material density

Elastic modulus

Poisson’s ratio

Allowable stress

1Cr11Ni2W2MoV

7800 kg/m^{3}

1.96e11

0.3

450 MPa

Table 4. Load parameter
Number of blades

Weight of single blade

The distance from the center of
the blade to the center of the disc

Disc speed

26

0.5 kg

150 mm

1000 rad/s

Table 5. The results of structural optimization
The value of parameter (mm)

The generations
of convergence

Objective value
function (Kg)


RI

RS

RD

WD

WDS


81.389

89.212

93.308

2.003

33.611

52

5.75

The optimal results were shown in Table 5 and Fig. 5. It could be seen that the target value was converged around 50 generations from the target curve of optimization, and the weight of the disc was reduced from 8.7 kg to 5.75 kg while the strength met the allowable conditions. The weight of disc reduction was nearly 3 kg accounting for 34.48 % of the original weight.
Fig. 5. The target curve of optimization
4. Conclusions
The parametric design method and structural optimization technology of aeroengine component structure were studied in this paper. Following were the conclusions:
1) The parametric design software for aeroengine disc was designed using VB.net language to develop AutoCAD.
2) The program of structural optimization was designed based on the MATLAB language to call the ANSYS Apdl statement.
3) The weight of the disc was reduced by 34.48 % after optimizing while the strength met the allowable conditions. It can be seen that the weight reduction effect was very considerable.
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