周向畸变条件下压气机非轴对称导叶设计方法研究  

Design Method of Non-Axisymmetric Guide Vane of Compressor under Circumferential Distortion Condition

作　　者：卢绪祥[1] 马玉鹏 杜娟[2] 张敏 巴顿 LU Xu-xiang;MA Yu-peng;DU Juan;ZHANG Min;BA Dun(School of Energy and Power Engineering,Changsha University of Science and Technology,Changsha 410114,China;Advanced Gas Turbine Laboratory,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China)

机构地区：[1]长沙理工大学能源与动力工程学院,湖南长沙410114 [2]中国科学院工程热物理研究所先进燃气轮机实验室,北京100190

出　　处：《推进技术》2022年第12期405-413,共9页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-II-0017-0038)

摘　　要：在侧向蜗壳进气条件下,压气机导叶进口出现畸变区,使导叶总压损失系数增大以及气流角在周向和径向上出现不均匀现象。对此进行导叶非轴对称改型设计,采用实验设计(DOE)方法进行参数寻优,以降低导叶气动损失同时获得更加均匀的出口气流角。改型结果显示:设计工况下气流攻角保持在-2°左右,较原型叶片有较大改善,总压损失系数降低4.9%,出口气流角基本与均匀进气时相同。通过对计算结果的分析,解释了叶型损失降低的机理,对工作在相似环境的叶型设计提出了优化建议。Under the condition of lateral volute flow,distorted region appears at the inlet of compressor guide vane,which increases guide vane total pressure loss coefficient,and makes flow angle circumferential and radial asymmetry.Non-axisymmetric design is used to modify guide vane and design of experiment(DOE)method is used to parameter optimization,in order to reduce the guide vane aerodynamic loss and obtain more uniform outlet flow angle at the same time.The results of modification show that the attack angle is kept around-2°under the design condition.The total pressure loss coefficient is reduced by 4.9%,and the flow outlet angle is basically the same as that under the clean flow condition.Through the analysis of calculated result,the mechanism of blade loss reduction is explained,and some suggestions are put forward to blade design in similar environment.

关 键 词：压气机导叶 非轴对称设计 计算流体力学 总压损失系数 气流角度 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]