首页 | 本学科首页   官方微博 | 高级检索  
     检索      

双激盘理论及其在轴流式弯掠动叶栅气动计算中的应用
引用本文:钟芳源,王建民,蔡娜,李中.双激盘理论及其在轴流式弯掠动叶栅气动计算中的应用[J].航空动力学报,1994,9(4):394-398,444.
作者姓名:钟芳源  王建民  蔡娜  李中
作者单位:上海交通大学
摘    要:轴流式弯掠动叶栅对主气流作用有一个不容忽视的径向分力。为此本文提出“双激盘理论”及相应的一套计算方法,其中包括阻力系数及出口气流角值沿径分布的修正,用来进行低速低负荷轴流式弯掠(即必须计及叶片径向分力影响的)风扇的设计和性能估计。用一个弯掠动叶和一个非弯掠动叶的风扇进行验证性试验,结果表明:计算与实测值吻合甚好。

关 键 词:双激盘理论  弯掠叶片  叶片径向力  轴流动叶
收稿时间:1993/12/1 0:00:00
修稿时间:2/1/1994 12:00:00 AM

APPLICATION OF DIACTUATOR DISC THEORY TO AERODYNAMIC COMPUTATION OF AXIAL-FLOW FAN WITH SKEWED-SWEPT ROTOR BLADES
Zhong Fangyuan,Wang Jianming,Cai Na and Li Zhong.APPLICATION OF DIACTUATOR DISC THEORY TO AERODYNAMIC COMPUTATION OF AXIAL-FLOW FAN WITH SKEWED-SWEPT ROTOR BLADES[J].Journal of Aerospace Power,1994,9(4):394-398,444.
Authors:Zhong Fangyuan  Wang Jianming  Cai Na and Li Zhong
Institution:Dept. of Power Machinery Engineering,Shanghai Jiaotong University,Shanghai 200030;Dept. of Power Machinery Engineering,Shanghai Jiaotong University,Shanghai 200030;Dept. of Power Machinery Engineering,Shanghai Jiaotong University,Shanghai 200030;Dept. of Power Machinery Engineering,Shanghai Jiaotong University,Shanghai 200030
Abstract:In order to spread the advanced technotogy of aeropropfan,skewed swept rotor blades are applied to axial flow fan and compressor.The diactuartor disc theory model is adopted to calculate the main flow of the skewed swept rotor blades in such a manner,as all blades forces affect on the first actuator disc,but the radial forces of blades vanish abruptly on the second actuator disc.Then the radial distribution of the boundary layer thickness (wake thickness) on the outlet surface of the rotor blade is taken as aerodynamic and aeroacoustic characteristic vectors.The effects of the secondary flow,endwall boundary layer,blades rotation and skewed swept regularity (mainly radial forces of blades) are corrected according to plane cascade testing statistical curves.In addition,the results of four calculations demonstrate the effects of the second actuator disc,radial force and corrected outlet flow angle on magnitudes of the calculation results separately.The aerodynamic and acoustic tests show a good agreement of the calculation results with test data.
Keywords:Blades  Blade  forces  Aerodynamic  computations  Diactuator  disc  theory  
本文献已被 CNKI 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号