轴对称短舱自然层流优化及转捩敏感性分析

doi:10.7527/S1000-6893.2022.27330

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轴对称短舱自然层流优化及转捩敏感性分析

曹凡, 张美芳, 胡骁, 唐智礼

南京航空航天大学航空学院, 非定常空气动力学与流动控制工业和信息化部重点实验室, 南京 210016

收稿日期:2022-04-27 修回日期:2022-07-04 出版日期:2022-11-15 发布日期:2022-08-17
通讯作者: 唐智礼,E-mail:tangzhili@nuaa.edu.cn E-mail:tangzhili@nuaa.edu.cn
基金资助:
国家自然科学基金（12032011，11772154）；江苏高校优势学科建设工程资助项目（PAPD）

Natural laminar flow optimization and transition sensitivity analysis of axisymmetric nacelle

CAO Fan, ZHANG Meifang, HU Xiao, TANG Zhili

Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2022-04-27 Revised:2022-07-04 Online:2022-11-15 Published:2022-08-17
Supported by:
National Natural Science Foundation of China (12032011,11772154);A Project Funded by the Priority Academia Program Development of Jiangsu Higher Education Institutions (PAPD)

摘要/Abstract

摘要： 大涵道比涡扇发动机短舱摩擦阻力大，高雷诺数下通过自然层流技术（NLF）减小短舱表面摩擦阻力是降低短舱总阻力的一种有效措施。为了提高气动优化效率，发展了一种进化/确定性混合优化算法，并结合六阶形状类别变化函数（CST）参数化方法和γ-Re_θt转捩模型，对高雷诺数几何约束下的轴对称短舱进行自然层流优化设计。为了分析层流范围的变化规律，对设计的轴对称层流短舱开展了局部几何控制参数、流量系数（MFR）和马赫数（Ma）的敏感性研究。结果表明：混合优化算法能够显著提高优化效率，并成功应用于短舱气动外形优化中。在单变量几何参数影响下，短舱外形头部区域对压力分布和层流范围的影响最为显著，是层流设计的重点关注区域。流量系数和马赫数的变化使得层流范围波动较大，设计的短舱在设计点MFR=0.7和Ma=0.85附近，能够保持20%以上范围的层流。

关键词: 自然层流短舱, 转捩预测, 混合优化算法, CST参数化, 敏感性分析

Abstract: The turbofan engine nacelle with a large bypass ratio has large friction drag. At a high Reynolds number, reducing the friction drag on the nacelle surface using the Natural Laminar Flow (NLF) is an effective measure to reduce the total drag of the nacelle. To improve the efficiency of aerodynamic optimization, a hybrid evolutionary/deterministic optimization algorithm is developed, and, combined with a 6th order Class and Shape Transformation (CST) parameterization and a turning model, it is applied to the design of axisymmetric nacelles with NLF and geometric constraints at a high Reynolds number. Sensitivity studies on the local geometry sensitivity, the Mass Flow Ratio (MFR) and the Mach number (Ma) of the designed axisymmetric laminar nacelle are conducted to maintain stable laminar flow performance. The results show that the hybrid optimization algorithm can significantly improve the optimization efficiency and is successfully applied to the nacelle aerodynamic shape optimization. Under the influence of univariate geometric parameters, the head region of the nacelle shape has the most significant effect on the pressure distribution and laminar flow range, which is the key area of concern for laminar flow design. The variation of the flow coefficient and Mach number causes the large fluctuation of the laminar flow range. The designed nacelle can maintain the laminar flow in the range of more than 20% at the design point MFR=0.7 and Ma=0.85.

Key words: natural laminar flow nacelle, transition prediction, hybrid optimization algorithm, CST parameterization, sensitivity analysis

中图分类号:

V221.3

曹凡, 张美芳, 胡骁, 唐智礼. 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): 527330-527330.

CAO Fan, ZHANG Meifang, HU Xiao, TANG Zhili. Natural laminar flow optimization and transition sensitivity analysis of axisymmetric nacelle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 527330-527330.

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轴对称短舱自然层流优化及转捩敏感性分析

Natural laminar flow optimization and transition sensitivity analysis of axisymmetric nacelle

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