压气机中介机匣气动优化设计与分析  

Aerodynamic Optimization Design and Analysis for Compressor Intermediate Duct

作　　者：赵伟光 王英杰 ZHAO Weiguang;WANG Yingjie(AECC HUNAN AVIATION POWERPLANT RESEARCH INSTITUTE,Zhuzhou 412002,Hunan,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《工程与试验》2024年第3期24-26,60,共4页Engineering and Test

摘　　要：结合试验设计、三维数值模拟、自适应遗传算法和神经网络响应面模型,构建了优化设计平台,在此基础上完成了中介机匣轮毂和机匣流道的气动优化,分析了优化结果对中介机匣内部流动和性能的影响。研究结果表明:采用先扩张后收缩的流道面积分布规律有助于降低流动损失,其中面积最大处位于支板最大厚度附近;轮毂流道曲率分布对流动损失具有重要影响,通过流道曲率优化能够实现对壁面压力分布的调控,缓解支板尾缘处的流动分离;相较于原型中介机匣,对轮毂和机匣流道同时优化后总压损失降低27.7%。Based on the experimental design,three-dimensional numerical simulation,adaptive genetic algorithm and neural network response model,an optimization design platform is developed to investigate the flow path design of the compressor intermediate duct.According to optimization results,the internal flow performance of duct is analyzed.The research results indicate that the total pressure loss can be reduced by adopting the duct area distribution law of first expansion and then contraction,in which the area is the largest near the maximum thickness of the strut.The hub curvature distribution has an important effect on the total pressure loss.The pressure distribution can be controlled by optimizing the curvature of hub and the flow separation at the trailing edge of the strut can be alleviated.Compared with the prototype,the total pressure loss is reduced by 27.7%through the optimization of duct hub and shroud.

关 键 词：压气机 中介机匣 气动优化 流动控制 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]