计及壁面传热的微型向心涡轮气动设计探讨  

Aerodynamic design of micro radial inflow turbine with wall heat transfer

作　　者：丁超[1] 边磊[1] 邹正平[1] 

机构地区：[1]北京航空航天大学航空发动机气动热力重点实验室,北京100191

出　　处：《北京航空航天大学学报》2014年第7期947-952,共6页Journal of Beijing University of Aeronautics and Astronautics

基　　金：领航创新基金资助项目(YWF-10-01-B03)

摘　　要：毫米级微型向心涡轮传热效应显著区别于常规向心涡轮,发展计及壁面传热效应的微型向心涡轮的气动设计方法对微型燃气轮机的设计具有重要意义.根据微型向心涡轮壁面非绝热的特点,通过理论分析,初步建立了计及固壁传热效应的微型向心涡轮速度三角形的分析模型.在此基础上发展了计及传热效应的微型向心涡轮的气动设计方法.分析得到了考虑传热影响的微型向心涡轮设计规律.利用三维数值模拟手段对模型和设计方法进行了验证.结果初步表明所发展计及壁面传热效应的模型和微型向心涡轮气动设计方法具有较好的可行性.The heat transfer effect is a significant difference between the micro radial inflow turbine and the conventional radial inflow turbine,so it is very important to take the wall heat transfer effect into consideration when designing a micro radial inflow turbine. Based on the feature of non-adiabatic wall in the micro radial inflow turbine,and through theoretical analysis,a velocity diagram analytical model was obtained preliminarily. On that basis,the aerodynamic design method of the micro radial inflow turbine was developed. Then the design rule of the micro radial inflow turbine considering wall heat transfer effect was summarized. Finally a three-dimensional numerical simulation was carried out to verify the obtained model and design method. Results show that the model and design method of the micro radial inflow turbine considering wall heat transfer effect is feasible.

关 键 词：传热 微型 向心涡轮 设计方法 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]