核心机驱动风扇级可变弯度导叶设计方法  

Method of Variable Camber Inlet Guide Vanes Design on Core Driven Fan Stage

作　　者：王前[1] 胡骏[1] 屠宝锋[1] 严伟[1] WANG Qian HU Jun TU Bao-feng YAN Wei(Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power Systems, Nanjing 210016, 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,江苏南京210016

出　　处：《推进技术》2016年第10期1855-1859,共5页Journal of Propulsion Technology

基　　金：南京航空航天大学青年科技创新基金(NS2014021)

摘　　要：为设计出适用于核心机驱动风扇级的可变弯度导叶,在基础叶型设计的基础上,采用数值计算方法详细分析了缝隙形式以及设计点的选取对可变弯度导叶性能的影响。计算结果表明:不同的气流转折角对应着不同的最佳基础叶型;在缝隙设计中采用Coanda型线可以有效提高泄漏流的附壁性能,抑制缝隙后附面层的发展,提高可变弯度导叶性能;可变弯度导叶出口气流角变化范围较大,设计点的选取对可变弯度导叶的性能有显著的影响。In order to design the variable camber inlet guide vanes which are available for the core driven fan stage（CDFS）,the effects of the slotted shapes and design points on the performance of the variable camber inlet guide vanes were studied by the numerical simulation based on the fundamental blade profile design. The analyzed results show that the different flow turning angles are corresponding to the different best fundamental blade profiles and the use of Coanda molded line in the slotted shape design can effectively enhance the wall attachment performance of the leakage flow,suppress the development of the boundary layer behind the slotted position,and improve the overall performance of the variable camber inlet guide vanes. Moreover,the selection of design point has a significant effect on the performance of the variable camber inlet guide vane when the outlet flow angle of variable camber inlet guide vane varies in a wide range.

关 键 词：核心机驱动风扇级 可变弯度导叶 基础叶型 Coanda效应 设计点选取 

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]