内置输出轴套肘弯式排气管气动性能优化

丁金涛; 张靖周; 单勇; 张丽娜

doi:10.13224/j.cnki.jasp.20250386

内置输出轴套肘弯式排气管气动性能优化

doi: 10.13224/j.cnki.jasp.20250386

丁金涛^{1, 3,},
张靖周^{1, 2,*, ,},
单勇^{1, 2},
张丽娜³

1.
南京航空航天大学能源与动力学院，南京 210016
2.
教育部进排气系统技术重点实验室，南京 210016
3.
中国航空工业集团公司金城南京机电液压工程研究中心，南京 211106

基金项目: 国家科技重大专项（J2019-Ⅲ-0009-0053）

详细信息

作者简介:
丁金涛（1989-），男，博士生，研究领域为进排气系统设计。E-mail：dingjintao@nuaa.edu.cn

通讯作者:
张靖周（1964-），男，教授，博士，研究领域为传热传质。E-mail: zhangjz@nuaa.edu.cn

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2025-10-14
- 网络出版日期: 2026-10-07

Aerodynamic optimization for elbow-type exhaust duct with a built-in output shaft tube

Ding Jintao^{1, 3
,},
Zhang Jingzhou^{1, 2,*
, ,},
Shan Yong^{1, 2},
Zhang Lina³

1.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Key Laboratory of Inlet and Exhaust system Technology，Ministry of Education，Nanjing 210016，China
3.
Jincheng Nanjing Engineering Institute of Aircraft Systems，Aviation Industry Corporation of China，Limited，Nanjing 211106，China

摘要

摘要:
分析了带输出轴的肘弯式排气管直扩压段扩张角度（α=4°～28°）、弯曲段弯曲角度（β=55°～75°）和下壁面引导线F值（F=0.15～0.75）这三个决定性结构参数对其气动性能的影响；基于响应面模型和多目标遗传算法进行了排气管气动性能优化。结果表明：弯曲排气管内的流动损失主要来源于弯曲管内侧回流、中心套管和支板绕流尾迹涡，排气管中偏转气流和内置构件复杂绕流的耦合流动是其气动损失物理机制。在给定的参数范围内，单一结构参数对排气管总压损失和静压恢复的影响规律均具有很强的非单调变化。相较单因素分析中的特定优选模型（α=16°、β=60°和F=0.6），多目标优化后的排气管具有更大的直扩压段扩张角度（α=18.36°～18.95°）和更小的弯曲段下壁面引导线F值（F=0.39～0.48），弯曲角度基本相当（β=60.2°～65°），排气管的流通能力得到进一步提升。
- 肘弯式排气管 /
- 流动损失 /
- 气动性能 /
- 代理模型 /
- 多目标优化
Abstract:
Numerical simulations were performed for the internal flow inside an elbow-type exhaust duct with a built-in output shaft tube. Given the constrained condition relating to the section contours and locations of inlet and outlet, three geometric parameters were mainly considered to illustrate their individual effect on the aerodynamic performances respectively, including straight diffuser angle (α=4°—28°), bent angle (β=55°—75°) and lower guide line F value (F=0.15—0.75) of the exhaust duct. Furthermore, an optimization and sensitivity analysis was made by using the response surface methodology and multiobjective genetic algorithm. The results showed that the flow losses mainly originated from the recirculating flow near inner-side bent section, the wake vortices behind the central tube and struts. The flow deflection inside the bent duct and the cross flow around built-in components were coupled together to form very complicated flow fields and flow loss mechanisms. Within the present scope, non-monotonous influencing role behaved clearly for each individual geometric effect on the total pressure loss coefficient and the static pressure recovery coefficient. Compared with the specifically preferred situation obtained from single-factor analysis (α=16°, β=60° and F=0.6), the optimized elbow-type exhaust duct had a greater straight diffuser angle (α=18.36°—18.95°) and smaller lower guide line F value (F=0.39—0.48), with nearly consistent bent angle (β=60.2°—65°). It improved the aerodynamic performances effectively.
- elbow-type exhaust duct /
- flow losses /
- aerodynamic performance /
- surrogate model /
- multi-objective optimization

HTML

图 1 动力后输出涡轴发动机排气管

Figure 1. Exhaust ducts of the turboshaft engine with rear-output

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图 2 前输出涡轴发动机进气道内部流动^[22]

Figure 2. Internal flow of the inlet for the turboshaft engine with front-output^[22]

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图 3 排气管结构示意图

Figure 3. Schematic diagram of exhaust duct

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图 4 排气管型面示意图

Figure 4. Schematic diagram of exhaust duct profile

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图 5 计算网格及其无关性测试

Figure 5. Computational meshes and independence test

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图 6 Box-Behnken设计示意图

Figure 6. Schematic diagram of Box-Behnken design

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图 7 基准排气管内部局部流动特征

Figure 7. Local flow features inside baseline exhaust duct

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图 8 典型截面示意图

Figure 8. Schematic diagram of typical sections

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图 9 基准排气管I₀～ I₅截面上的马赫云图

Figure 9. Mach number contours on I₀ — I₅ sections for baseline exhaust duct

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图 10 基准排气管Z₁截面上的流线分布

Figure 10. Streamlines on section Z₁ for baseline exhaust duct

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图 11 基准排气管Z₂截面上的流线分布

Figure 11. Streamlines on section Z₂ for baseline exhaust duct

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图 12 不同扩张角度的排气管型面

Figure 12. Profiles of exhaust duct with different diffuser angles

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图 13 不同扩张角度的排气管局部流场

Figure 13. Local flow fields of exhaust ducts with different diffuser angles

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图 14 直扩压段扩张角度对排气管气动性能的影响

Figure 14. Effects of straight diffuser angle on aerodynamic performance of exhaust ducts

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图 15 不同弯曲角度的排气管型面

Figure 15. Profiles of exhaust duct with different bent angles

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图 16 不同弯曲角度的排气管局部流场

Figure 16. Local flow fields of exhaust ducts with different bent angles

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图 17 弯曲角度对排气管气动性能的影响

Figure 17. Effects of bent angle on aerodynamic performance of exhaust ducts

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图 18 不同下导引线F值的排气管型面

Figure 18. Profiles of exhaust duct with different lower guide line F-values

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图 19 不同导引线F值下的排气管局部流场

Figure 19. Local flow fields of exhaust ducts with different F-values

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图 20 下导引线F值对排气管气动性能的影响

Figure 20. Effects of lower guide line F-value on aerodynamic performance of exhaust ducts

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图 21 CFD计算值和RSM预测值对比

Figure 21. Comparison between CFD calculated values and predicted values of response surface model

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图 22 粒子在设计空间上的分布

Figure 22. Distribution of particles in the design space

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图 23 Pareto最优解

Figure 23. Pareto optimal solution

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图 24 Opt-A排气管的局部流场

Figure 24. Local flow fields of Opt-A exhaust duct

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表 1 基准排气管结构参数

Table 1. Geometric parameters in baseline exhaust duct

参数	数值
D_m/D₀	0.510
L₀/D₀	0.121
α/（°）	4
L_s/D₀	0.164
L_t/D₀	0.95
H_t/D₀	1.05
R₂₁/D₀	0.529
R₂₂/D₀	0.265
R₂₃/D₀	1.058
A₂/A₀	1.3
W₂/H₂	1.65
F	0.6
β/（°）	60

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表 2 排气管设计变量

Table 2. Selected design variables for current exhaust duct

参数	设计范围	取值
扩张角度α/（°）	4～28	4，10，16，22，28
弯曲角度β/（°）	55～75	55，60，65，70，75
下引导线F	0.15～0.75	0.15，0.3，0.45，0.6，0.75

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表 3 总压损失系数和静压恢复系数计算结果

Table 3. Calculation results of total pressure loss coefficient and static pressure recovery coefficient

序号	α/（°）	β/（°）	F	C_tp	C_sp
1	10	60	0.3	0.128	0.359
2	16	65	0.3	0.085	0.403
3	22	60	0.6	0.099	0.421
4	22	60	0.3	0.105	0.396
5	16	55	0.3	0.119	0.416
6	16	60	0.45	0.091	0.432
7	22	65	0.45	0.087	0.418
8	22	55	0.45	0.132	0.392
9	16	65	0.6	0.091	0.398
10	16	60	0.45	0.091	0.432
11	10	55	0.45	0.14	0.378
12	16	60	0.45	0.091	0.432
13	10	65	0.45	0.12	0.312
14	16	60	0.45	0.091	0.432
15	16	60	0.45	0.091	0.432
16	16	55	0.6	0.11	0.41
17	10	60	0.6	0.123	0.318

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表 4 总压损失系数的ANOVA结果

Table 4. ANOVA results for total pressure loss coefficient

变异来源（source）	SS	DOF	MS	F统计值	P值
回归模型整体（model）	0.0051	9	0.0006	131.82	<0.0001
α	0.0010	1	0.0010	229.65	<0.0001
β	0.0017	1	0.0017	411.17	<0.0001
F	0.0000	1	0.0000	6.05	0.0435
αβ	0.0002	1	0.0002	35.33	0.0006
αF	0.0001	1	0.0001	0.17	0.6935
βF	0.0001	1	0.0001	12.61	0.0093
α²	0.0018	1	0.0018	397.52	<0.0001
β²	0.0003	1	0.0003	62.14	<0.0001
F²	0.0000	1	0.0000	4.44	0.0731
残差（residual）	0	7	0
失拟项（lack of fit）	0	3	0
纯误差（pure error）	0	4	0
校正总和（corrected total）	0.0051	16
决定系数R²为0.9941，调整R²为0.9866，预测R²为0.9061

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表 5 静压恢复系数的ANOVA结果

Table 5. ANOVA results for static pressure recovery coefficient

变异来源（source）	SS	DOF	MS	F统计值	P值
回归模型整体（model）	0.0227	9	0.0025	223.34	<0.0001
α	0.0084	1	0.0084	741.97	<0.0001
β	0.0005	1	0.0005	45.06	0.0003
F	0.0001	1	0.0001	7.89	0.0262
αβ	0.0021	1	0.0021	184.94	<0.0001
αF	0.0011	1	0.0011	97.31	<0.0001
βF	0	1	0	0.0221	0.8859
α²	0.0086	1	0.0086	757.98	<0.0001
β²	0.0006	1	0.0006	52.03	0.0002
F²	0.0007	1	0.0007	64.35	<0.0001
残差（residual）	0.0001	7	0
失拟项（lack of fit）	0.0001	3	0
纯误差（pure error）	0	4	0
校正总和（corrected total）	0.0228	16
决定系数R²为0.9965，调整R²为0.9911，预测R² 为0.9445

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表 6 优化的设计参数取值范围

Table 6. Range of optimized design parameters

参数	取值范围
α/（°）	18.36～18.95
β/（°）	60.2～65
F	0.39～0.48

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表 7 优化设计点的气动性能

Table 7. Aerodynamic performance at the optimized design points

模型	参数			$ {C}_{\text{tp}} $		$ {C}_{\text{sp}} $
模型	α/（°）	β/（°）	F	CFD计算值	RSM预测值	CFD计算值	RSM预测值
Ref-1	16	60	0.6	0.095		0.412
Ref-2	4	60	0.6	0.213		0.079
Ref-3	4	60	0.45	0.191		0.165
Opt-A	18.74	62.39	0.473	0.085	0.084	0.442	0.436
Opt-B	18.36	60.25	0.468	0.090	0.089	0.434	0.438

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