低速模拟中叶型最大厚度模化研究  

Research on the Low-speed Similarity Principles for Compressor Stator Airfoils

作　　者：刘宝杰[1,2,3] 张传海 于贤君 安广丰[1,2] LIU Bao-Jie;ZHANG Chuan-Hai;YU Xian-Jun;AN Guang-Feng(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Research Institute of Aero-Engine,Beihang University,Beijing 100191,China;National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,Beijing 100191,China;China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]北京航空航天大学航空发动机研究院,北京100191 [3]航空发动机气动热力国防重点实验室,北京100191 [4]中国空气动力研究与发展中心,绵阳621000

出　　处：《工程热物理学报》2021年第3期586-594,共9页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51806004,No.51790511);国家科技重大专项资助项目(No.2017-H-0001-0013)。

摘　　要：介绍了低速模拟中低速叶型的设计准则,分析说明了叶型喉道宽度与最大厚度、最大厚度位置存在线性关系。建立了最大厚度模型,用以预估低速叶型最大厚度。为了验证最大厚度模型的适用性,进行了一组典型CDA叶型的低速模拟设计。数值计算结果显示,低速模拟叶型的特性和叶表无量纲速度分布较为一致,用以判断最大厚度模型适用性的吸力面峰值速度相对误差仅有0.75%,说明了最大厚度模型的准确性。利用该模型预估最大厚度,可减少低速模拟设计过程的迭代次数。Some design principles in low-speed simulation had been introduced.It was analyzed that there was a linear relationship between blade throat width,maximum thickness-chord ratio and the position of maximum thickness.A maximum thickness model was established to estimate the maximum thickness.In order to verify the applicability of the maximum thickness model,a low-speed airfoil had been performed.The numerical results show that the characteristics of the low-speed airfoil and the non-dimensional velocity distribution are consistent,and the relative error of the peak velocity of the suction surface for judging the applicability of maximum thickness model is only 0.75%,which indicates the accuracy of the model.Using this model to predict the maximum thickness can decrease the number of iterations in low-speed simulation.

关 键 词：低速模拟 最大厚度 模化 

分 类 号：O357.5[理学—流体力学]