摘要
为提升一体化涡轮过渡段的气动性能,并掌握一体化涡轮过渡段气动优化技术中的关键点,对基于三维CFD与智能算法的一体化涡轮过渡段的气动优化技术开展了研究。结果表明:对优化前过渡段流动特征的分析和认识,是识别主要优化变量、取得较好优化效果的必要前提;过渡段几何参数化的优劣取决于初始模型的构建,初始模型的构建应以对优化前过渡段几何特征的分析为基础;对于原始叶片几何为6个径向截面的过渡段,采用径向3截面相比径向6截面进行参数化拟合,虽然参数化效果稍逊,但能有效减少拟合的参数数目,并消除优化结果叶片几何沿径向的扭曲。只对流道、只对叶片、同时对流道与叶片进行优化的过渡段,其总压损失降低效果分别达到0.49%、0.56%、1.12%。
In order to improve the aerodynamic performance of a certain integrated inter-turbine duct(IITD),and to master the key points in the IITD optimization techniques,a research on the IITD optimi⁃zation techniques based on three-dimensional CFD and intelligent algorithm was carried out.The research shows that the analysis and understanding of the original IITD flow features is a prerequisite to recognize the main optimization variables and to achieve optimization.The quality of IITD geometric parameterization is determined by the construction of the initial model,which is based on the analysis to the original IITD geometric features.As for the original IITD with 6-radial-sections,compared to 6-radial-section paramet⁃ric model,the 3-radial-section-parametric model achieves a slightly inferior fitting result.However,it can reduce the parameter counts needed to fit and remove the radial distortion in the optimization resultant blades.The three optimization schemes that were respectively only optimize flow passage,only optimize blades,and optimize both passage and blades,can respectively result in a total pressure loss reduction to 0.49%,0.56%,1.12%.
作者
杨杰
宋友富
熊清勇
杨伟平
YANG Jie;SONG You-fu;XIONG Qing-yong;YANG Wei-ping(Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Hunan Key Laboratory of Turbomachinery on Medium and Small Aero-Engine,Zhuzhou 412002,China)
出处
《燃气涡轮试验与研究》
北大核心
2020年第6期1-8,共8页
Gas Turbine Experiment and Research
关键词
航空发动机
涡轮
一体化过渡段
气动优化
CFD
智能算法
aero-engine
turbine
integrated inter-turbine duct
aerodynamic optimization
CFD
intelligent algorithm
