轴流压气机转子叶片表面静压分布实验  

Experiment of the static pressure on the rotating blade surface in an axial compressor

作　　者：王庆伟[1] 刘波[1] 薄相峰[1] 项效镕[1] 侯为民[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2011年第5期611-616,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金(50476071)

摘　　要：在低速轴流压气机转子叶片吸力面50%叶高沿轴向埋入5个Kulite动态压力传感器,并采用固定在压气机转轴上一种新型可存储的数据采集器记录数据,对近设计点和2 kr/min转速不同流量工况条件下转子叶片表面静压进行了实验测量,并与CFD数值模拟结果进行了对比。结果表明,除近失速点外,叶片表面静压实验测量值与计算结果吻合较好,说明所采用的的测量方法是成功的,测量结果是可靠的;在近失速工况,实验值与计算结果差值较大,主要是由试验台振动所引起的实验误差和CFD数值计算对近失速点工况流场模拟得不够准确所导致的。Five high response miniature pressure transducers were used on the rotating blade suction surface of an axial compressor at 50% span to measure the static pressure of rotating blade suction surface at design point and different operating conditions at 2kr/min,and the experimental data were compared with the CFD numerically simulated results.In experiment,the data acquisition system was fixed and rotated with the compressor,and directly acquired,magnified,stored the pressure signals.The results show： the blade surface pressure of experimental data has good agreement with simulation results except near stall condition.The experimental data are credible;near stall condition,because of the experiment error and the poor calculations of CFD,the experimental data and simulation results have poor agreement.

关 键 词：轴流压气机 压气机叶片 压力分布 压力测量 压力系数 

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]