S弯进气道优化设计及分析 *

推进技术 ›› 2014, Vol. 35 ›› Issue (10): 1317-1324.

S弯进气道优化设计及分析 *

甘文彪^1,2,周　洲¹,许晓平¹,王　睿¹,张　乐¹

西北工业大学无人机特种技术重点实验室，陕西西安 710072; 北京航空航天大学无人驾驶飞行器设计研究所，北京 100191;西北工业大学无人机特种技术重点实验室，陕西西安 710072;西北工业大学无人机特种技术重点实验室，陕西西安 710072;西北工业大学无人机特种技术重点实验室，陕西西安 710072;西北工业大学无人机特种技术重点实验室，陕西西安 710072

发布日期:2021-08-15
作者简介:甘文彪(1985—)，男，博士，讲师，研究领域为计算流体力学与飞行器气动优化设计。
基金资助:
国家装备预研基金(9140A25010312HK0301)；国家自然基金资助项目(11202162)。

S-Duct Inlet Optimal Design and Analysis

Science and Technology on UAV Laboratory，Northwestern Polytechnical University，Xi’an 710072，China; Research Institute of Unmanned Aerial Vehicle，Beihang University，Beijing 100191，China;Science and Technology on UAV Laboratory，Northwestern Polytechnical University，Xi’an 710072，China;Science and Technology on UAV Laboratory，Northwestern Polytechnical University，Xi’an 710072，China;Science and Technology on UAV Laboratory，Northwestern Polytechnical University，Xi’an 710072，China;Science and Technology on UAV Laboratory，Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 为改进隐身飞行器推进系统的气动性能，针对S弯进气道开展了设计和分析。基于数值模拟方法、代理模型和遗传算法构建了一套自动优化方法。在优化设计过程中，结合参数化建模、网格自动生成和改进(SST)湍流模型求解，应用优化方法对飞行器进行了多目标设计，得到了进气道的优化推荐构型。应用尺度自适应模拟(SAS)方法对优化进气道气动性能进行了全面和细致的分析。研究结果表明: SAS方法可以较好地模拟S弯进气道的流动，优化设计能够极大地改进S弯进气道的气动性能；相比原始设计，优化进气道设计点的总压畸变指数降低了16.3%，总压恢复系数提高了1.1%。

关键词: S弯进气道；优化方法；非设计点性能；剪切应力模型；尺度自适应模拟

Abstract: To improve aerodynamic performance of propulsion system for stealth aircraft，S-shaped inlet is designed and analyzed. An automated design optimization method was built，based on computational fluid dynamics (CFD)，surrogate models and genetic algorithm. Combining parameterized solid model，grid auto-generation，modified Menter’s k-ω Shear Stress Transport (SST) turbulent model solver，S-shaped inlet is designed by multi-objective optimization. The optimal recommended configuration is obtained. The aerodynamic performance of optimized inlet is analyzed by Scale Adaptive Simulation (SAS) method on detail and refinement . The results show that SAS method is good at numerical simulation of S-shaped inlet flow. Design optimization can greatly improve the aerodynamic performance of S-shaped inlet. Compared with the original design，the distortion coefficient of optimized inlet is decreased by 16.3% and total pressure recovery factor increased by 1.1% at design point.

Key words: S-duct inlet；Optimization method；Off-design performance；Shear Stress Transport；Scale Adaptive Simulation

甘文彪,周　洲,许晓平,王　睿,张　乐. S弯进气道优化设计及分析 *[J]. 推进技术, 2014, 35(10): 1317-1324.

GAN Wen-biao^1,2,ZHOU Zhou¹,XU Xiao-ping¹,WANG Rui¹,ZHANG Le¹. S-Duct Inlet Optimal Design and Analysis[J]. Journal of Propulsion Technology, 2014, 35(10): 1317-1324.

参考文献

[1] Weske J R. Pressure Loss in Ducts with Compound Elbows[C].USA: NACA Wartime Rept.W-39, National Advisory Committee for Aeronautics Ohio, 1943.
[2] Guo R, Seddon J. An Investigation of Swirl in an S-Duct[J]. The Aeronautical Quarterly, 1982, 33(1):25–58.
[3] Seddon J, Goldsmith E. Intake Aerodynamics [M].London: Collins Professional Books, 1985.
[4] Goldsmith E, Seddon J. Practical Intake Aerodynamic Design [M]. USA: AIAA Education Series, 1993.
[5] Xiao Q, Tsai M H. Computation of Transonic Diffuser Flows by a Lagged k-ω Turbulence Model [J]. Journal of Propulsion and Power, 2003, 19(3): 473-483.
[6] Saha K, Singh S N, Seshadri V. Computational Analysis on Flow Through Transition S-Diffusers: Effect of Inlet Shape [J]. Journal of Aircraft, 2007, 44(1):187-193.
[7] Gerolymos G A, Joly S, Mallet M, et al. Reynolds-Stress Model Flow Prediction in Aircraft-Engine Intake Double-S-Shaped Duct [J]. Journal of Aircraft, 2010, 47(4):1368-1381.
[8] Zhang, W, Knight D, Smith, D. Automated Design of Subsonic Diffuser [J].Journal of Propulsion and Power, 2000, 16(6): 1132-1140.
[9] Lee B J, Kim C. Automated Design Methodology of Turbulent Internal Flow Using Discrete Adjoint Formulation [J].Aerospace Science and Technology, 2007, 11(2):163-173.
[10] Menter F R.Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications [J].AIAA Journal, 1994, 32(8): 1598-1605.
[11] Zhang J M, Wang C F, Lum K Y. Multidisciplinary Design of S-shaped Intake [R]. AIAA 2008-7060.
[12] Aniket A, Jin G L, Doyle, etc al. Automated Design Optimization of a Three-Dimensional Subsonic Diffuser[J]. Journal of Propulsion and Power, 2011, 27(4): 838-846.
[13] Magnus T. Design and Analysis of Compact UAV Ducts[R]. AIAA 2006-2828.
[14] 甘文彪, 周洲, 许晓平, 等. 基于改进SST模型的分离流动数值模拟 [J]. 推进技术, 2013, 34(5):595-602.(GAN Wen-biao, ZHOU Zhou, XU Xiao-ping, et al.Investigation on Improving the Capability of Predicting Separation in Modified SST Turbulence Model [J]. Journal of Propulsion Technology, 2013, 34(5): 595-602.)
[15] Menter, F R, Egorov Y. Formulation of the Scale-Adaptive Simulation (SAS) Model During the DESIDER Project.[J]. Fluid Mechanics and Multidiscipline Design, 2009, 103(1): 1-18.
[16] Jackson I R H. Convergence Properties of Radial Basis Function[J].Constructive Approximation, 1988, 4(1): 243-246.
[17] Krist S L, Biedron R T, Rumsey C L. CFL3D User’s Manual: Ver.5.0[R]. NASA-TM 1998-208444.
[18] Smith R E. Transfinite Interpolation(TFI) Generation Systems [M]. London: CRC Press Inc?, 1999.(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2013-09-26；修订日期:2013-12-09。基金项目:国家装备预研基金(9140A25010312HK0301)；国家自然基金资助项目(11202162)。作者简介:甘文彪(1985—),男,博士,讲师,研究领域为计算流体力学与飞行器气动优化设计。E-mail:ganhope@126.com