航空科学技术2024，Vol.35Issue(2)：23-30,8.DOI:10.19452/j.issn1007-5453.2024.02.003
动力短舱多点气动优化设计
Multipoint Aerodynamic Design Optimization of Powered-on Nacelle
摘要
Abstract
Design of the nacelle for a transonic engine is highly complicated and always a tradeoff between contradicting design objectives.In this paper,an optimization system for nacelle design is built up to improve the aerodynamic performance of a powered-on engine nacelle at two critical operation conditions.The class shape transformation(CST)method is developed for the parameterization of nacelle contour.The Pareto genetic algorithm(PGA)and the Kriging model are integrated by the loose surrogate management framework.At cruise,the minimization of external peak Mach number is the target function for total drag reduction and improving nacelle external performance.At maximum thrust condition,satisfied air supply should be ensured and the intake peak Mach number around throat is minimized to improve nacelle internal performance.Compared with the reference design,optimized nacelles obtain better performances with respect to both objectives,resulting in a peak Mach number reduction about 5%at cruise and 10%at full thrust condition.The parameter influence analysis indicates that the nacelle leading edge parameters have significant but different impact on nacelle internal and external performance.They should be chosen as the main design variables for integrated optimization design of the nacelle.The Pareto front can provide multiple choices for engineering applications.The results indicate that the optimization design system established in this paper provides an effective tool for the design of powered-on nacelles,and the optimization design results are of practical value.关键词
动力短舱/类别形状函数变换法/Pareto遗传算法/Kriging代理模型/多点优化Key words
powered-on nacelle/CST/PGA/Kriging model/multipoint optimization分类
航空航天引用本文复制引用
顾文婷,马坤,韩杰..动力短舱多点气动优化设计[J].航空科学技术,2024,35(2):23-30,8.基金项目
航空科学基金(2020Z006003001)Aeronautical Science Foundation of China(2020Z006003001) （2020Z006003001）
