摘要
以平面叶栅为试验研究对象,研究了叶片槽道气流旋涡与噪声声压级的关系。在此结果的基础上,以某发动机高压压气机零级静子叶片组成扇形试验件,在不同进口气流速度和攻角下,进行了叶片发声试验研究。得出了不同进口气流速度和攻角下,叶片出口气动噪声频谱及声压级的变化规律,认为分离区内强烈的气流脉动是其噪声产生的根源,且产生的较高能量的宽频噪声或宽频激振源会对构件产生声疲劳破坏,应引起足够重视并进行深入研究。
Taking the compressor cascade as the testing research object, the relationship between the air-flow vortex of blade channels and the level of noise was investigated. On the basis of investigation results, zero-stage vanes of an aero-engine HPC were formed to sector test specimen and research on sound was carried out with different inlet airflow velocity and angle of attack. The vane outlet aerodynamic noise fre-quency spectrum and the level of noise varying with the inlet airflow velocity and angle of attack were ac-quired. It was recognized that strong airflow impulse in the separation zone was the cause of noise, at the same time the broadband noise or shock excitation source produced by airflow impulse would do acoustic fa-tigue to the construction parts that should arouse attention and deep research.
出处
《燃气涡轮试验与研究》
北大核心
2013年第4期1-7,共7页
Gas Turbine Experiment and Research
关键词
航空发动机
压气机
叶片发声机理
激振
气动声学试验
宽频噪声
aero-engine
compressor
blade sound mechanism
shock excitation
aero-acoustics experiment
broadband noise
