基于NSGA-Ⅱ算法的小弯管冲击冷却多目标优化

赵鸿华; 宋双文; 王志凯

doi:10.13224/j.cnki.jasp.20210688

基于NSGA-Ⅱ算法的小弯管冲击冷却多目标优化

doi: 10.13224/j.cnki.jasp.20210688

中国航发湖南动力机械研究所，湖南株洲 412002

详细信息

作者简介:
赵鸿华（1993−），男，工程师，博士生，主要从事航空发动机燃烧室设计的研究

中图分类号: V231.1
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- 文章访问数: 33
- HTML浏览量: 13
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- 被引次数: 0
出版历程
- 收稿日期: 2021-12-01
- 网络出版日期: 2024-01-24

Multi-objective optimization of impingement cooling of concave wall based on NSGA-Ⅱ algorithm

Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
为了获得不同冲击孔径（IA），冲击孔流向间距（IFD）和冲击孔展向间距（ISD）耦合作用对回流燃烧室小弯管冲击冷却特性及结构热应力的影响，开展了数值计算（CFD）及有限元分析（FEA）。选择试验设计（DOE）中的最优拉丁超立方（Opt LHD）采样确定了设计空间中的样本点，构建了高精度径向基神经网络模型，并基于改进非劣类（NSGA-Ⅱ）算法对综合冷却效率，壁温分布不均匀系数以及壁面最大热应力进行了多目标寻优，结果表明：综合冷却效率，壁温分布不均匀系数和壁面最大热应力随流向展向间距比、流向间距孔径比和展向间距孔径比的增大而减小；通过多目标NSGA-Ⅱ算法获得了小弯管冲击冷却结构Pareto前沿的3个目标函数值的范围为壁面最大热应力不大于5 MPa，综合冷却效率不小于0.66，壁温分布不均匀系数不大于0.16；小弯管冲击冷却综合最优结构的组合为：冲击孔径为0.94 mm，冲击孔流向间距为4.04 mm，冲击孔展向间距为5.45 mm。
- 回流燃烧室 /
- 小弯管 /
- 冲击冷却 /
- NSGA-Ⅱ算法 /
- 多目标优化 /
- Pareto前沿
Abstract:
In order to obtain the influences of different impingement aperture (IA), impingement spacing of flow direction of impingement hole (IFD), spacing of span direction of impingement hole (ISD) coupling effect on impingement cooling characteristics and structural thermal stress of concave wall in reverse flow combustor, CFD calculation and FEA analysis were carried out. Opt LHD in DOE was selected to determine the sample points in the design space, and a high-precision RBFNN was constructed. Based on NSGA-Ⅱalgorithm, multi-objective optimization was carried out for comprehensive cooling efficiency, non-uniform coefficient of wall temperature distribution and maximum wall thermal stress. The results showed that comprehensive cooling efficiency, non-uniform coefficient of wall temperature distribution and maximum wall thermal stress decreased with the increase of ratio of IFD to ISD, ratio of IFD to IA and ratio of ISD to IA. Through multi-objective NSGA-Ⅱ algorithm, the value range of the three objective functions of the Pareto front of concave wall impingement cooling structure was obtained, i.e.: maximum wall thermal stress was not greater than 5 MPa, comprehensive cooling efficiency was not less than 0.66, and non-uniform coefficient of wall temperature distribution was not greater than 0.16. According to the combination of the optimal structure of concave wall impingement cooling: IA was equal to 0.94 mm, IFD was equal to 4.04 mm, and ISD was equal to 5.45 mm.
- reverse flow combustor /
- concave wall /
- impingement cooling /
- NSGA-Ⅱ algorithm /
- multi-objective optimization /
- Pareto front

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图 1 小弯管冲击冷却结构参数

Figure 1. Impingement cooling structure parameter of concave wall

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图 2 CFD计算域结构

Figure 2. CFD computational domain structure

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图 3 周期性计算域选取

Figure 3. Periodic computing domain selection

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图 4 网格无关性验证

Figure 4. Grid independence verification

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图 5 不同S/d_i方案η/η_max试验与数值计算结果对比

Figure 5. Comparison of η/η_max experimental results and numerical calculation results for different S/d_i cases

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图 6 不同P/d_i方案η/η_max试验与数值计算结果对比

Figure 6. Comparison of η/η_max experimental results and numerical calculation results for different P/d_i cases

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图 7 小弯管冲击冷却结构气流流动方向

Figure 7. Concave wall impingement cooling structure air flow direction

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图 8 不同结构参数耦合作用对综合冷却效率及结构热应力的影响

Figure 8. Influences of coupling effects of different structural parameters on comprehensive cooling efficiency and structural thermal stress

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图 9 RBF模型误差分析

Figure 9. Error analysis of RBF model

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图 10 Pareto前沿和优化解

Figure 10. Pareto front and optimization solution

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表 1 小弯管冲击冷却计算方案

Table 1. Impingement cooling numerical procedure of concave wall

序号	d_i/mm	S/mm	P/mm	方案	备注
1		5	5		Base
2	1	3.18	7.86	S/P=0.4	相同d_i 不同S/P
3		4.48	5.58	S/P=0.8
4		5.48	4.56	S/P=1.2
5		6.32	3.96	S/P=1.6
6	1.25	5	7.71	S/d_i=4.0	相同S 不同S/d_i
7	0.83		3.52	S/d_i=6.0
8	0.71		2.62	S/d_i=7.0
9	0.63		2.0	S/d_i=8.0
10	1.25	7.71	5	P/d_i=4.0	相同P 不同P/d_i
11	0.83	3.52		P/d_i=6.0
12	0.71	2.62		P/d_i=7.0
13	0.63	2.0		P/d_i=8.0

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表 2 CFD计算边界条件

Table 2. CFD boundary conditions

参数	取值
主流温度T_g/K	473.15
主流进口速度V_g/（m/s）	25
次流温度T_c/K	300
次流进口压力p_tci/Pa	5000

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表 3 DOE方案各结构参数取值范围

Table 3. DOE scheme structure parameter range mm

结构参数	取值范围
冲击孔径d_i	0.6～1.2
流向间距S	2～8
展向间距P	2～8

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表 4 约束变量及其变化范围

Table 4. Constrain variables and their range of variation mm

约束变量	上限	下限
d_i	0.4	2.0
S	2	10
P	2	10

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表 5 优化结果与CFD/FEA结果对比

Table 5. Optimization results are compared with the CFD/FEA results

方法	d_i/mm	S/mm	P/mm	η	δ	σ/MPa
Opt	0.94	4.04	5.45	0.663	0.137	3.902
CFD/FEA	0.94	4.04	5.45	0.657	0.134	4.016
误差率/%				0.91	2.24	−2.84

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