某风扇/增压级非设计点性能计算及进气畸变影响分析

赵勇; 胡骏

某风扇/增压级非设计点性能计算及进气畸变影响分析

赵勇,
胡骏

南京航空航天大学能源与动力学院, 南京 210016

基金项目: 国防科研计划资助项目

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- 文章访问数: 1848
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- 被引次数: 0
出版历程
- 收稿日期: 2006-06-12
- 修回日期: 2006-11-21
- 刊出日期: 2007-07-28

Analysis of the influence of inlet flow distortion on the off-design performance of fan/booster

ZHAO Yong,
HU Jun

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

摘要

摘要: 在原流线曲率法程序的基础上, 增加了适用于高速风扇/压气机的双激波损失模型.真实地反映了高速风扇/压气机的实际工作状况, 提高了预测高速风扇/压气机非设计点性能的准确性, 完善了分析进气畸变对风扇/压气机性能及稳定性影响的准三维计算模型.针对一台外涵转子叶尖马赫数大于1.4的大涵道比风扇/增压级, 计算分析了其非设计点性能以及进气畸变的影响.计算结果与试验结果吻合较好, 精度可靠, 可应用于工程实际.
- 航空、航天推进系统 /
- 风扇/增压级 /
- 流线曲率法 /
- 进气畸变 /
- 激盘
Abstract: A dual-shock loss model suitable for high-speed fan/compressor is incorporated into the streamline curvature method to estimate the actual operating condition of high-speed fan/compressor.Moreover,it helps to improve the accuracy of predicting the fan/compressor off-design performance,and further develop the quasi-3D model used to analyze the influence of the inlet flow distortion on the performance and stability of fan/compressor.For a high bypass ratio fan/booster with the Mach number lager than 1.4,the off-design performance and influence of inlet flow distortion is calculated and analyzed.The accurate calculated results,identical to the experimental results,are suitable for engineering applications.
- aerospace propulsion system /
- fan/booster /
- streamline curvature methods /
- inlet flow distortion /
- actuator disk

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参考文献(13)

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