高马赫数、高负荷双级风扇转子叶尖区域激波结构测量  

Measurement of Rotor Tip Shock Wave Structure of a Two Stage Fan with High Mach Number and High Load

作　　者：齐亦农 李承辉[1] 赵刚[1] 

机构地区：[1]沈阳发动机设计研究所,沈阳110015

出　　处：《燃气涡轮试验与研究》2002年第3期33-37,共5页Gas Turbine Experiment and Research

摘　　要：介绍了在高负荷跨声速风扇上采用高频响测试系统进行双级转子尖部激波结构测量的方法。此方法从测试系统的选取、校准、试验与数据处理等各个环节上都保证了激波测量的准确性 ,最后绘制出 n =0 .9、 0 .95、1.0各状态下的激波结构等压线图。对测试结果进行了分析并与气动设计情况进行了对比 ,两者的吻合使叶型优化设计的合理性与测试及数据分析手段的成功应用得到相互印证 ,为改进设计提供了依据。A measurement of rotor tip shock wave structure of a high load transonic fan is introduced with high frequency response instrumentation system. The accuracy of shock wave structure measurement is ensured through the selection, calibration, test and data process of instrumentation system. Shockwave structure contours are finally made at =0.9, 0.95 and 1.0 conditions. The measurements agree well with aerodynamic design from comparison, which indicates rationality of the blade profile optimization design and success in instrumentation and data processing. They provide basis for improvement design

关 键 词：马赫数 负荷 双级风扇 转子 激波 压力测量 

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]