基于PARSEC曲线和遗传算法的自然层流短舱的优化设计

耿雪; 俞松林; 李程鸿

doi:10.13224/j.cnki.jasp.20220809

基于PARSEC曲线和遗传算法的自然层流短舱的优化设计

doi: 10.13224/j.cnki.jasp.20220809

中国航发商用航空发动机有限责任公司，上海 200241

详细信息

作者简介:
耿雪（1985-），女，工程师，硕士，主要从事短舱气动设计方向研究

中图分类号: V231.3
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- 文章访问数: 661
- HTML浏览量: 213
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- 被引次数: 0
出版历程
- 收稿日期: 2022-10-23
- 网络出版日期: 2023-04-13

Optimization design of natural laminar flow nacelle based on PARSEC curve and genetic algorithm

Commercial Aircraft Engine Company Limited， Aero Engine Corporation of China，Shanghai 200241，China

摘要

摘要:
为提升短舱外罩层流区域面积以降低阻力，基于PARSEC（parametric section）曲线的型线参数化方法，同时采用遗传算法，以推后短舱外罩转捩位置为优化目标，对短舱特征型线进行优化。同时，研究不同来流马赫数下短舱型面优化结果；对比分析优化前后型面的气动性能与阻力发散特性。结果表明：优化后短舱型面较优化前在设计点阻力降低2.25×10⁻³，但在高来流马赫数的非设计点工况，阻力恶化现象较为严重，导致优化后短舱在较低马赫数即产生阻力发散。
- 自然层流（NFL）短舱 /
- PARSEC曲线 /
- 遗传算法 /
- 转捩 /
- 阻力发散特性
Abstract:
In order to improve the laminar flow area of the nacelle surface to reduce the drag, the parametric method of the profile based on PARSEC (parametric section) curve and genetic algorithm were used to optimize the nacelle, with its goal to push back the transition position of the nacelle. At the same time, the optimization results of nacelle under different Mach numbers were studied; the aerodynamic performance and drag divergence characteristics of the nacelle before and after optimization were compared and analyzed. The results showed that: the drag at the design point of the optimized nacelle was 2.25×10⁻³ lower than original nacelle, but the drag deterioration was more serious at the off design points of high Mach number, which led to the optimized nacelle drag divergence at lower Mach number.
- natural laminar flow (NFL) nacelle /
- PARSEC curve /
- genetic algorithm /
- transition /
- drag divergence characteristics

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图 1 短舱外型面包络成型

Figure 1. Envelop of nacelle profile

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图 2 短舱型线参数化造型方法

Figure 2. Parametric modeling method of nacelle profile

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图 3 短舱计算模型block及网格划分

Figure 3. Block and grid division of nacelle calculation model

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图 4 NFL（1）-0416层流翼型转捩模拟网格划分及计算结果

Figure 4. NFL （1）-0416 simulation grid division and calculation results of laminar airfoil transition

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图 5 层流短舱型面优化设计方法

Figure 5. Optimization design method of laminar flow nacelle profile

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图 6 设计点优化种群分布

Figure 6. Optimized population distribution at design point

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图 7 短舱特征型线优化前后几何对比

Figure 7. Comparison of geometry before and after optimization of nacelle characteristic profile

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图 8 优化前后短舱转捩情况对比

Figure 8. Comparison of nacelle transition before and after optimization

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图 9 优化前后短舱各型线压力分布对比

Figure 9. Comparison of pressure distribution of nacelle profiles before and after optimization

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图 10 不同上型线曲率半径$ {r}_{\mathrm{l}\mathrm{e}\mathrm{u}\mathrm{p}} $的短舱特征型线压力分布及转捩位置情况

Figure 10. Pressure distribution and transition position of nacelle characteristic profile with different curvature radius of upper profile $ {r}_{\mathrm{l}\mathrm{e}\mathrm{u}\mathrm{p}} $

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图 11 不同最大厚度位置曲率半径$ {r}_{\mathrm{x}\mathrm{x}\mathrm{u}\mathrm{p}} $的短舱特征型线压力分布情况

Figure 11. Pressure distribution and transition position of nacelle characteristic profile with different curvature radius of maximum thickness point （$ {r_{{\text{xxup}}}} $）

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图 12 不同最大厚度点轴向坐标$ {X}_{\mathrm{u}\mathrm{p}} $的短舱特征型线压力分布情况

Figure 12. Pressure distribution of nacelle characteristic profile at axial coordinates $ {X}_{\mathrm{u}\mathrm{p}} $ of different maximum thickness points

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图 13 不同最大厚度点径向坐标$ {Y}_{\mathrm{u}\mathrm{p}} $的短舱特征型线压力分布情况

Figure 13. Pressure distribution of nacelle characteristic profile at radial coordinates $ {Y}_{\mathrm{u}\mathrm{p}} $ of different maximum thickness points

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图 14 优化前后短舱阻力发散特性对比

Figure 14. Comparison of drag divergence characteristics of nacelle before and after optimization

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图 15 层流优化短舱在阻力发散前后理想马赫数及转捩情况对比

Figure 15. Comparison of ideal Mach number and transition position of NFL nacelle before and after drag divergence

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图 16 层流优化短舱在不同来流马赫数下表面理想马赫数情况对比

Figure 16. Comparison of ideal Mach number on the laminar flow optimization nacelle at different inflow Mach numbers

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表 1 NFL（1）-0416层流翼型模拟与试验结果对比

Table 1. Comparison between simulation and test results of NFL （1）-0416 laminar airfoil

类别	上表面转捩位置（x_up/C）	下表面转捩位置（x_lo/C）
风洞试验值^[28]	0.35	0.6
Lee等计算结果^[29]	0.348	0.587
本文计算结果	0.362	0.586

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表 2 短舱特征型线优化前后主要型线参数对比

Table 2. Comparison of main profile parameters before and after optimization

优化特征参数	优化前	优化后
$ {r}_{\mathrm{l}\mathrm{e}\mathrm{u}\mathrm{p}} $	34	86
$ {r}_{\mathrm{x}\mathrm{x}\mathrm{u}\mathrm{p}} $	8916	10600
$ {X}_{\mathrm{u}\mathrm{p}} $	890	1002
$ {Y}_{\mathrm{u}\mathrm{p}} $	1800	1867

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参考文献(32)

[1]	袁吉森, 孙爵, 李玲玉, 等. 超声速飞机层流布局设计与评估技术进展[J]. 航空学报, 2022, 43(9): 63-98. YUAN Jisen, SUN Jue, LI Lingyu, et al. Progress of sloersonic aircraft laminar flow layout design and evaluation technology[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(9): 63-98. (in Chinese)
[2]	SHI Y,MADER C A,HE S,et al. National laminar flow airfoil optimization design using a discrete adjoint approach[J]. AIAA Journal,2020,58(1): 4702-4722.
[3]	CARPENTER P W,LUCEY A D. Progress on the use of compliant walls for laminar flow control[J]. Journal of Aircraft,2001,38(3): 504-512. doi: 10.2514/2.2790
[4]	JOSLIN R D. Aircraft laminar flow control[J]. Annual Review of Fluid Mechanics,1998,30: 1-29. doi: 10.1146/annurev.fluid.30.1.1
[5]	朱自强,吴宗成,丁举春. 层流流动控制技术及应用[J]. 航空学报,2011,32(5): 765-784. ZHU Ziqiang,WU Zongcheng,DING Juchun. Laminar flow control technology and application[J]. Acta Aeronautica et Astronautica Sinica,2011,32(5): 765-784. (in Chinese)
[6]	李权, 段卓毅, 张彦军, 等. 民用飞机自然层流机翼研究进展[J]. 航空工程进展, 2013, 4(4): 399-406. LI Quan, DUAN Zhuoyi, ZHANG Yanjun, et al. Progress in research on natural laminar wing for civil aircraft[J]. Advances in Aeronautical Science and Engineering, 2013, 4(4): 399-406. (in Chinese)
[7]	王一雯,兰夏毓,史亚云,等. 考虑吸气影响的层流翼型梯度优化设计研究[J]. 航空学报,2022,43(11): 383-400. WANG Yiwen,LAN Xiayu,SHI Yayun,et al. Optimization design for LFC airfoil based on discrete adjoint method[J]. Acta Aeronautica et Astronautica Sinica,2022,43(11): 383-400. (in Chinese)
[8]	丁玉临,韩忠华,乔建领,等. 超声速民机总体气动布局设计关键技术研究进展[J]. 航空学报,2022,43(9): 20-46. DING Yulin,HAN Zhonghua,QIAO Jianling,et al. Research progress of key technologies for conceptual aerodynamic cofiguration design of sloersonic transport aircraft[J]. Acta Aeronautica et Astronautica Sinica,2022,43(9): 20-46. (in Chinese)
[9]	RIEDEL H,HORSTMANN K H,RONZHEIMER A,et al. Aerodynamic design of a natural laminar flow nacelle and the design validation by flight testing[J]. Aerospace Science and Technology,1998,2(1): 1-12. doi: 10.1016/S0034-1223(98)80001-8
[10]	NICHLOS D A, VUKASINOVIC B, GLEZER A, et al. Fluidic control of nacelle inlet flow in crosswind[R]. AIAA 2020-2955, 2020.
[11]	JOSLIN R D. Overview of laminar flow control[R]. NASA/TP-1998-208705, 1998.
[12]	GREEN J E. Laminar flow control-back to the future[R]. AIAA 2008-3738, 2008.
[13]	ZHANG Y,FANG X,CHEN H,et al. Sloercritical natural laminar flow airfoil optimization for regional aircraft wing design[J]. Aerospace Science and Technology,2015,43: 152-164. doi: 10.1016/j.ast.2015.02.024
[14]	ZHAO T, ZHANG Y F, CHEN H X. Multi-objective aero-dynamic optimization of sloercritical wing with substantial pressure constraints[R]. AIAA 2015-0763, 2015.
[15]	YANGHANS J L. Experimental study on natural laminar flow nacelles[R]. AIAA-84-0034, 1984.
[16]	何雨薇, 刘沛清, 段会申, 等. 超临界翼型吸气层流减阻控制数值研究[J]. 航空动力学报, 2010 25(11): 2444-2449. HE Yuwei, LIU Peiqing, DUAN Huishen, et al. Numerical investigation of the laminar and drag-reduction control by using suction technology on a sloercritical airfoil[J]. Journal of Aerospace Power, 2010, 25(11): 2444-2449. (in Chinese)
[17]	何小龙,白俊强,夏露,等. 基于EFFD方法的自然层流短舱优化设计[J]. 航空动力学报,2014,29(10): 2310-2320. HE Xiaolong,BAI Junqiang,XIA Lu,et al. Natural laminar flow nacelle optimization design base on EFFD method[J]. Journal of Aerospace Power,2014,29(10): 2310-2320. (in Chinese)
[18]	曹凡,胡骁,张美芳,等. 高雷诺数下跨声速自然层流短舱优化设计[J]. 航空动力学报,2021,36(8): 1730-1739. CAO Fan,HU Xiao,ZHANG Meifang,et al. Transonic natural laminar flow nacelle optimization design at high Reynolds number[J]. Journal of Aerospace Power,2021,36(8): 1730-1739. (in Chinese)
[19]	曹凡,张美芳,胡骁,等. 轴对称短舱自然层流优化及转捩敏感性分析[J]. 航空学报,2022,43(11): 401-413. CAO Fan,ZHANG Meifang,HU Xiao,et al. Natural laminar flow optimization and transition sensitivity analysis of axisymmetric nacelle[J]. Acta Aeronautica et Astronaut Sinica,2022,43(11): 401-413. (in Chinese)
[20]	YAO Yuan,MA Dongli,YANG Muqing,et al. Adaptive-surrogate-based robust optimization of transonic natural laminar flow nacelle[J]. Chinese Journal of Aeronautics,2021,34(10): 36-52. doi: 10.1016/j.cja.2021.01.007
[21]	SOBIECZKY H. Parametric airfoils and wings[M]. Wien: Wien Springer, 1999.
[22]	张启鹏. 超临界自然层流翼型优化方法研究[D]. 南京: 南京航空航天大学, 2018. ZHANG Qipeng. Optimization methods for supercritical natural laminar airfoils[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2018. (in Chinese)
[23]	LANGTRY R B. A correlation based transition model using local variables for unstructured parallelized CFD codes[D]. Stuttgart: University Stuttgart, 2006.
[24]	LIN Y,ROBINSON T,EARLY J,et al. Implementation of Menter’s transition model on an isolated natural laminar flow nacelle[J]. AIAA Journal,2011,49(4): 824-835. doi: 10.2514/1.J050890
[25]	LANGTRY R B. A correlation-based transition model using local variables for unstructured parallelized CFD codes[J]. Journal of Turbomachinery,2006,128(3): 424-434.
[26]	RIVERS M B,DITTBERNER A. Experimental Investigation of the NASA Common Research Model[J]. Journal of aircraft,2019,51(4): 1183-1193.
[27]	SPALART P R,RUNNY C L. Effective inflow conditons for turbulence models in aerodynamic calculation[J]. AIAA Journal,2007,45(10): 2544-2553. doi: 10.2514/1.29373
[28]	SOMERS D M. Design and experimental results for a natural laminar flow airfoil for general aviation applications[R]. NASA Technical Paper 1861, 1981.
[29]	LEE J, JAMESON A. Natural laminar flow airfoil and wing design by adjoint method and automatic transition prediction[R]. AIAA-2009- 3514, 2009.
[30]	HOLLAND J H. Adaptation in natural and artificial systems[M]. Ann Arbor, US: University of Michigan Press, 1975.
[31]	赵欢. 基于代理模型的高效气动优化与气动稳健设计方法研究[D]. 西安: 西北工业大学, 2020. ZHAO Huan. Research on surrogate-based efficient aerodynamic optimization and robust aerodynamic design method[D]. Xi’an: Northwestern Poly technical University, 2020. (in Chinese)
[32]	戴嘉. 超临界自然层流翼型鲁棒优化[D]. 南京: 南京航空航天大学, 2020. DAI Jia. Robust optimization of sloercritical natural laminar flow airfoils[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2020. (in Chinese)