某掠形跨声风扇设计与数值模拟

丁建国; 胡骏

某掠形跨声风扇设计与数值模拟

丁建国,
胡骏

南京航空航天大学能源与动力学院, 南京 210016

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- 被引次数: 0
出版历程
- 收稿日期: 2005-12-19
- 修回日期: 2006-03-20
- 刊出日期: 2007-01-28

Design and numerical simulation of a transonic swept fan DING Jian2guo,H U Jun

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 采用与计入三维激波结构轴对称流设计程序相匹配的任意中弧线叶片造型程序, 进行某单级跨声、小展弦比、具有小前掠和后掠的内外涵风扇设计.在设计过程中, 通过调整风扇转子压比、叶型最大相对厚度和前后缘厚度等参数沿展向的分布, 以及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, 克服了该风扇转子高相对马赫数与低损失、高效率的矛盾, 内外涵数值模拟结果表明, 该风扇具有宽广的高效率区和高喘振裕度.
- 航空、航天推进系统 /
- 跨声 /
- 掠形风扇 /
- 设计 /
- 数值模拟
Abstract: The paper employs arbitrary airfoil blade design procedures of turbomachinery to design a transonic wide-chord fan with forward-swept and back-swept blades.In the process of designing,the radial distributions of parameters(such as total pressure ratio,maximum relative thickness and thickness of leading and trailing edges of blade and so on,camber and maximum thickness as a fraction of chord) are adjusted,so that shock intension of blade tip is weakened,the loss of shock is debased,the conflict of high relative Mach number with low loss and high efficiency is overcome.Numerical simulation of core and bypass indicates that,the fan has a higher efficiency over a wider range and better stall margin.
- aerospace propulsion system /
- transonic /
- swept fan /
- design /
- numerical simulation

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参考文献(6)

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