多级轴流风扇/压气机非设计点性能计算方法  

Calculation of multistage axial fan/compressor off-design performance

作　　者：赵勇[1] 胡骏[1] 屠宝锋[1] 王志强[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2008年第2期219-224,共6页Journal of Propulsion Technology

摘　　要：为更好反映现代轴流风扇内部流动特征,将适合于高马赫数来流的双激波模型引入基元叶栅法,发展了一种多级轴流风扇、压气机非设计点性能计算方法。该方法通过引入雷诺数修正,考虑了雷诺数对风扇/压气机性能的影响,并使最大静压升系数法可在宽广雷诺数变化范围内预测风扇/压气机稳定边界。该方法灵活、可靠,并经过高压压气机、跨声速风扇及大涵道比风扇/增压级等典型的压气机试验结果验证,既可用于多级轴流风扇/压气机非设计点性能计算,又可发展成为高空低雷诺数条件下高性能风扇/压气机设计和研究的重要工具,有着广泛的工程应用前景。A method to calculate the multistage axial fan/compressor off-design performance was established. It can catch the nature of shock system, and has better accuracy of predicting the loss, owing to a dual-shock loss model suitable for high-speed flow. It＂ is also able to estimate the effects of Reynolds number on the performance of fan/compressor, and the boundary stability of multistage fan/compressor in an extensive range of Reynolds number by means of maximum pressure rise potential. The method is flexible and reliable, validated by test results of three different compressors, such as high-pressure compressor, transonic fan and high bypass ratio fan/booster. Besides predicting the performance of a fan/compressor, it may as a tool of design and researching a fan/compressor in the case of lower Reynolds number. Thus it has an abroad engineering applications foreground.

关 键 词：风扇 压气机 基元叶栅法 双激波模型 边界 雷诺数 

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]