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某跨音风扇转子全三维设计与数值模拟
引用本文:丁建国,胡骏.某跨音风扇转子全三维设计与数值模拟[J].工程热物理学报,2006,27(Z1):157-160.
作者姓名:丁建国  胡骏
作者单位:南京航空航天大学能源与动力学院,江苏,南京,210016
摘    要:本文采用与三维流场分析程序相匹配的任意叶轮机通用叶片造型程序,进行某单级高通流、跨音、宽弦长风扇转子设计。在设计过程中,通过调整转子进口流量、出口总压、叶片最大相对厚度和前后缘厚度等参数沿径向的分布,弯度和最大弯度位置沿弦向的分布,从设计上减弱了叶片上部的激波强度、降低了激波及其关联的损失,克服了该转子叶尖高相对马赫数和低损失、高效率的矛盾。最终获得满足气动性能和结构强度的风扇转子.

关 键 词:航空  航天推进系统  跨音  风扇转子  全三维设计  数值模拟
文章编号:0253-231X(2006)Suppl.1-0157-04
修稿时间:2006年2月23日

FULL THREE-DIMENSION DESIGN AND NUMERICAL SIMULATION OF A TRANSONIC ROTOR
DING Jian-Guo,HU Jun.FULL THREE-DIMENSION DESIGN AND NUMERICAL SIMULATION OF A TRANSONIC ROTOR[J].Journal of Engineering Thermophysics,2006,27(Z1):157-160.
Authors:DING Jian-Guo  HU Jun
Abstract:The paper employ arbitrary airfoils blade design procedure of turbomachinery to design a high through-flow,transonic and wide-chord rotor fan.In the process of design,by adjust radial distribution of these parameters such as inlet mass flux of rotor,outlet total pressure,max relative thickness and thickness of leading and treading of blade and so on,adjust camber and max thickness as a fraction of chord,so weaken shock intension of blade tip,debase the loss of shock,overcome the conflict of the high relative mach number and low loss,high efficiency,finally obtain the rotor fan of satisfying the requirement of performance and structural,stress intensity.
Keywords:aerospace propulsion system  transonic  rotor fan  full three-dimension design  numerical simulation
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