附加涵道风扇系统低稠度叶尖涡轮气动设计研究  

Aerodynamic Design of a Low Solidity Tip-turbine with an Additional Tip-driving Fan System

作　　者：王远庆 夏晨 张衍 向鑫 WANG Yuanqing;XIA Chen;ZHANG Yan;XIANG Xin(College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing 210016, China;Aerospace System Engineering Shanghai, Shanghai 201109, China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏省航空动力系统重点实验室,南京210016 [2]上海宇航系统工程研究所,上海201109

出　　处：《重庆理工大学学报（自然科学）》2018年第11期76-85,共10页Journal of Chongqing University of Technology：Natural Science

基　　金：航空推进技术验证计划项目(APTD-0302-01)

摘　　要：针对一种可以极大提高涵道比的新型气驱附加涵道风扇结构开展研究,采用数值模拟手段分析其核心部件叶尖涡轮的能量损失构成和流动特征,初步探究了中弧线的设计规律,为后续发展这种结构奠定理论基础。研究发现:该叶尖涡轮在低稠度下主要能量损失的是叶型损失,占到总损失的70%,其损失量是常规稠度下叶型损失的5倍;叶背处产生的大面积分离涡是其叶型损失的主要来源,载荷前移时,吼道位置随着稠度降低渐渐推出流道是其主要流动特征。基于这一特点,将中弧线最大挠度位置前移能有效地提高叶尖涡轮的效率和能量提取率。Aiming at the structure of a novel additional tip-driving fan system which can greatly improve the bypass ratio,using numerical simulation analyzes the loss structure and flow characteristics of the tip-turbine which is its core components.Besides,the design rules of the camber line are preliminarily studied,which laid the theoretical foundation for the further development of high bypassratio propulsion.It is found that the main loss of this tip-turbine under low solidity is profile loss,accounting for70%of the total loss,and its loss is5times of the profile loss under the normal consistency.The large area separation vortex generated on the suction surface is the main source of the profile loss,the load advancement,and the position of the throat gradually introduced into the leading edge with the decrease of the solidity are the main flow characteristics.Based on this feature,advancing the maximum deflection position of the camber line can effectively improve the tip turbine efficiency and energy extraction rate.

关 键 词：附加涵道风扇 叶尖涡轮 低稠度 低展弦比 流动特征 叶型设计 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]